GARMIN SOFTWARE ENHANCEMENT UPDATES (V. 58) ICA Supplement

TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

MODEL NO: 700

SUPPLEMENT NO: ICA-700-42-00001 SUPPLEMENT DATE: 9/21/2020

REVISIONS

ICA-700-42-00001 Rev: - Date: Sep 21/2020 ICA Summary Pages 1-10 Manuals Affected Description Title Introduction List of Revisions page 1 Introduction Revision Summary/Highlights Model 700 Electrical Wiring pages 1 and Interconnect System (EWIS) 2 Manual Revision 3 20-70-05 pages EWIS Identification - Maintenance Practices NOTE: 201-215 Refer to the Model 700 20-75-05 pages Electrical Connectors - Maintenance Practices Electrical Wiring Interconnect 201-286 System Manual Revision 3 and above. 24-60-00 pages Electrical Load Analysis - Description and Operation 1-45 28-00-05 pages Critical Design Configuration Control Limitations 1-7 (CDCCL) - Description and Operation • Added revision 3 of the Electrical Wiring Interconnect System (EWIS) Manual. • Refer to the Revision Summary/Highlights Document in the Model 700 Electrical Wiring Interconnect System (EWIS) Manual Revision 3 for detailed changes made in support of the Garmin Software Enhancement Updates (V. 58)

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22-10-00 pages Garmin Automatic Flight Control System (AFCS) - 1-4 Description and Operation 22-10-00 pages Garmin Automatic Flight Control System (AFCS) - 501-505 Adjustment/Test 22-10-25 pages Control Wheel Steering Switch - Removal/Installation 401-404 22-30-00 pages Autothrottle System - Description and Operation 1-4 22-30-00 pages Autothrottle System - Troubleshooting 101-103 23-50-00 pages Digital Audio System - Description and Operation 1-6 23-50-00 pages Digital Audio System - Troubleshooting 101-102 Model 700 Maintenance 23-50-00 pages Digital Audio System - Adjustment/Test Manual 501-506 23-50-55 pages Observer Seat Audio Panel - Removal/Installation 401-402 27-11-00 pages Control Wheel Assembly - Description and Operation 1 and 2 27-11-05 pages Control Wheel - Removal/Installation 401-403 28-00-00 pages Fuel - Troubleshooting 101-122 28-40-00 pages Fuel Indicating System - Description and Operation 1-6 29-00-00 pages Hydraulic Power - Troubleshooting 101-120 29-10-00 pages Main Hydraulic System - Description and Operation 1-12 • These ATA's contain the Instructions for Continued Airworthiness for the addition of the Control Wheel Switch, Observer Seat Audio Panel and CAS messages related to the Garmin G5000 System software updates. Model 700 Maintenance 34-21-00 pages Honeywell Intertial Reference System - Description and Manual 1-3 Operation 34-21-00 pages Honeywell Intertial Reference System - Adjustment/Test NOTE: 501-503 The instructions related to the Honeywell Inertial Reference 34-21-05 pages Honeywell Intertial Reference Unit (IRU) - System were released in the 401-403 Removal/Installation original issue of the Model 700 Maintenance Manual, these 34-21-10 pages Honeywell IM-950 Configuration Module - instructions are now applicable 401-403 Removal/Installation with the Garmin Software 34-40-00 pages Garmin Traffic Collision Avoidance System (TCAS II)- Enhancement Updates (V. 58). 1-5 Description and Operation

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• These ATA's contain the Instructions for Continued Airworthiness for the Honeywell Inertial Reference System and components and Garmin G5000 System software updates. 42-00-00 page 1 Integrated Modular Avionics - General 42-10-00 pages Garmin G5000 Integrated Avionics System Software - 1-4 Description and Operation 42-10-00 page Garmin G5000 Integrated Avionics System Software - 501 Adjustment/Test 42-11-00 pages Garmin G5000 Integrated Avionics System Software Model 700 Maintenance 101-109 (Version 58) - Troubleshooting Manual 42-11-00 pages Garmin G5000 Integrated Avionics System Software 501-549 (Version 58) - Adjustment/Test 42-11-01 pages Garmin G5000 Integrated Avionics System LRU Software 501-569 (Version 58) - Adjustment/Test 42-20-00 pages Garmin G5000 Integrated Avionics System - Description 1-8 and Operation • These ATAs contain the Instructions for Continued Airworthiness for the Garmin Software Enhancement Updates (V. 58) Appendix A: Illustrated Parts Refer to Appendix A, Table 1. Catalog 22-30-01 Throttle Quadrant Figure 02 pages 1-7 23-15-01, Broadband Swift Figure 01 pages 1-4, Figure 02 pages 1-4, Figure 03 pages 1-4 23-16-01 Broadband - ATG Figure 02 pages 1-7 and Figure 03 pages 1-7 Appendix B: Model 700 Wiring 23-50-01 Dual Audio and Voice Figure 02 pages 1-22 Diagram Manual 23-70-01 Cockpit Voice Recorder Figure 02 pages 1-6 27-70-01 Control Lock Figure 01 pages 1-4 and Figure 02 pages 1-4 29-10-01 Hydraulic System Figure 01 pages 1-18 and Figure 03 pages 1-15 52-00-01 External Doors Figure 03 pages 1-17 • These ATAs contain the wiring and wiring parts changes necessary for Garmin Software (Version 58) updates.

1. Export Compliance A. This publication contains technical data and is subject to U.S. export regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991

2. Revision Bars A. Revision bars in this ICA supplement identify new ICAs and/or changes to the current ICAs in the released maintenance manual.

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• New ICAs that are not in the current maintenance manual will have a revision bar from top to bottom along the left margin. • ICAs that are in the current maintenance manual and have information added, deleted or revised will have a revision bar(s) in the left margin adjacent to the added, deleted or revised information. • New or changed illustrations will have a change bar for the entire length of the page.

3. Page Numbering A. The page number system for ICA included in this supplement have three-element numbers that are separated by dashes. The three-element number is found at the bottom right corner of the page, left of the page number. The date is found below the page number.

B. When the chapter/system element number is followed with zeros in the section/subsystem and subject/unit element number (28-00-00), the information is applicable to the entire system. C. When the section/subsystem element number is followed with zeros in the subject/unit element number (28-21-00), the information is applicable to the subsystems in the system. D. The subject/unit element number is used to identify information applicable to units in the subsystems. The subject/unit element number continues in sequence from the number -01- with the number of subsystem units in which maintenance information is necessary. E. All system/subsystem/unit (chapter/section/subject) maintenance data is separated into specified types of information: Description and Operation, Troubleshooting, Maintenance Practices, etc. Blocks of page numbers that are in sequence are used to identify the type of information: (1) Description and Operation or Troubleshooting information may not be included if the procedure is easy. When subtopics are short, they may be put together into the Maintenance Practices section. Maintenance Practices can have a mix of subtopics that includes information to service, remove, install, adjust, test, clean, paint or do approved repairs. (2) Longer procedures that are not as easy to do may be included in a specified section. Page 1 through 99 - Description and Operation Page 101 through 199 - Troubleshooting Page 201 through 299 - Maintenance Practices Page 301 through 399 - Servicing Page 401 through 499 - Removal/Installation Page 501 through 599 - Adjustment/Test Page 601 through 699 - Inspection/Check Page 701 through 799 - Cleaning/Painting Page 801 through 899 - Approved Repairs F. A typical page number:

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G. Illustrations use the same figure numbers as the page block in which they appear. For example, Figure 202 would be the second figure in a Maintenance Practices section.

4. Supplement Revisions A. Revisions to this supplement may be accomplished if changes to this supplement are required after release of the original issue and prior to incorporation into the manuals listed in the REVISIONS table. B. All revisions to this supplement will have changes identified in detail in the revision block(s) above. C. All pages in this ICA supplement will have the same date and are valid as of the date shown.

5. ICA Incorporation into Applicable Manuals

NOTE: Most ICA supplements will be incorporated in the next available revision to the manuals listed above and should be used in conjunction with those manuals until the next available revision is released. A. The ICA Supplement List located in the Introduction section of each manual listed in the REVISIONS table will indicate the incorporation status as of the release date of the published revision. B. The manual revision level of the supplement incorporation will be listed in the "Manual Incorporation Status" column in the ICA Supplement List, when those ICAs associated with that manual have been incorporated. After ICAs are incorporated, the manual that they are incorporated in must now be used for those ICAs instead of the supplement. • Based on revision cycle times for the affected manuals, MM ICAs, WDM ICAs, etc. in this supplement may be incorporated in the manuals at different times. • There will not be a revision to this supplement to indicate incorporation in the manuals. Users are required to check the ICA Supplement List for each manual affected to determine incorporation status. C. This supplement will be completely superseded by the manuals listed in the REVISIONS table when it has been incorporated in all of the manuals.

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INTRODUCTION

1. Purpose A. The purpose of this Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the GARMIN SOFTWARE ENHANCEMENT UPDATES (V. 58) on the Cessna Model 700 until this information gets incorporated into the next revision to the manuals listed in the "REVISIONS" section of this supplement. B. This ICA supplement is designed to satisfy the requirements of 14 CFR 25.1529. "Instructions for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 700 Maintenance Manual and will be incorporated in the next revision to the manual. C. When this information is incorporated in the next revision to the manuals listed in the "REVISIONS" section, those manuals shall take precedence over this supplemental document. Refer to the "ICA Supplement List" in the "Introduction" section of the respective manual for the status of all applicable ICA Supplements. D. Revisions to this supplement may occur if there is a change to any of the ICAs in this supplement prior to incorporation into all of the affected manuals.

NOTE: This document must be placed with the aircraft operator's Technical Library CD-ROM or Model 700 Maintenance Manual and incorporated into the operator's scheduled maintenance program.

2. Effectivity A. These Instructions for Continued Airworthiness (ICA) are effective for the following aircraft model and serialization.

Model Beginning Effectivity Ending Effectivity 700 -0033 and On

3. Complete ICA Documents A. The following document(s) and/or manuals, in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the GARMIN SOFTWARE ENHANCEMENT UPDATES (V. 58) on the Cessna Model 700. All items must be available to the operator at initial delivery.

CAUTION: Make sure to use the most current revision to any document and/or manual listed below.

(1) Model 700 Airworthiness Limitations Manual (ALM) (2) Model 700 Electrical Wiring Interconnect System (EWIS) Manual

NOTE: This design change complies with the approved EWIS program.

(3) Model 700 Maintenance Manual (4) Model 700 Wiring Diagram Manual (5) Model 700 Illustrated Parts Catalog (6) Cessna Citation Standard Practices Manual (7) Garmin G5000 Integrated Avionics System Line Maintenance Manual - Cessna Citation Longitude 700, Part Number: 190-02403-00

4. System Components A. Refer to Appendix A: Illustrated Parts Catalog Table

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B. Refer to Appendix B: Wiring Diagram Manual

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LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Revision 3 and above, Model 700 Electrical Wiring Interconnect System (EWIS) Manual A. Introduction (1) Refer to List of Revisions and Revision Summary/Highlights B. Chapter 20, Standard Practices - Airframe (1) Refer to 20-70-05, EWIS Identification - Maintenance Practices (2) Refer to 20-75-05, Electrical Connectors - Maintenance Practices C. Chapter 24, Electrical Power (1) Refer to 24-60-00, Electrical Load Analysis - Description and Operation D. Chapter 28, Fuel (1) Refer to 28-00-05, Critical Design Configuration Control Limitations (CDCCL) - Description and Operation

2. Model 700 Maintenance Manual A. Chapter 22, Auto Flight (1) Refer to 22-10-00, Garmin Automatic Flight Control System (AFCS) - Description and Operation (2) Refer to 22-10-00, Garmin Automatic Flight Control System (AFCS) - Adjustment/Test (3) Refer to 22-10-25, Control Wheel Steering Switch - Removal/Installation (4) Refer to 22-30-00, Autothrottle System - Description and Operation (5) Refer to 22-30-00, Autothrottle System - Troubleshooting B. Chapter 23, Communications (1) Refer to 23-50-00, Digital Audio System - Description and Operation (2) Refer to 23-50-00, Digital Audio System - Troubleshooting (3) Refer to 23-50-00, Digital Audio System - Adjustment/Test (4) Refer to 23-50-55, Observer Seat Audio Panel - Removal/Installation C. Chapter 27, Flight Controls (1) Refer to 27-11-00, Control Wheel Assembly - Description and Operation (2) Refer to 27-11-05, Control Wheel - Removal/Installation D. Chapter 28, Fuel (1) Refer to 28-00-00, Fuel - Troubleshooting (2) Refer to 28-40-00, Fuel Indicating System - Description and Operation E. Chapter 29, Hydraulic Power (1) Refer to 29-00-00, Hydraulic Power - Troubleshooting (2) Refer to 29-10-00, Main Hydraulic System - Description and Operation F. Chapter 34, Navigation (1) Refer to 34-21-00, Honeywell Inertial Reference System - Description and Operation (2) Refer to 34-21-00, Honeywell Inertial Reference System - Adjustment/Test (3) Refer to 34-21-05, Honeywell Inertial Reference Unit (IRU) - Removal/Installation (4) Refer to 34-21-10, Honeywell IM-950 Configuration Module - Removal/Installation

NOTE: These instructions were released in the original issue of the Model 700 Maintenance Manual, these instructions are now applicable to the Honeywell Inertial Reference System with the Garmin Software Enhancement Updates (V. 58).

(5) Refer to 34-40-00, Garmin Traffic Collision Avoidance System (TCAS II) - Description and Operation G. Chapter 42, Integrated Modular Avionics - General (1) Refer to 42-00-00, Integrated Modular Avionics - General

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(2) Refer to 42-10-00, Garmin G5000 Integrated Avionics System Software - Description and Operation (3) Refer to 42-10-00, Garmin G5000 Integrated Avionics System Software - Adjustment/Test (4) Refer to 42-11-00, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting (5) Refer to 42-11-00, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test (6) Refer to 42-11-01, Garmin G5000 Integrated Avionics System LRU Software (Version 58) - Adjustment/Test (7) Refer to 42-20-00, Garmin G5000 Integrated Avionics System - Description and Operation

3. Appendix B, Model 700 Wiring Diagram Manual Supplement A. Model 700 Wiring Diagram Manual Supplement, Pages 001 thru 0032. (1) Refer to Appendix B, ATA 22-33-01 Throttle Quadrant, Figure 02 pages 1-7. (2) Refer to Appendix B, ATA 23-15-01 Broadband Swift, Figure 01 pages 1-4, Figure 02 pages 1-4, and Figure 03 pages 1-4 (3) Refer to Appendix B, ATA 23-16-01 Broadband - ATG, Figure 02 pages 1- 7and Figure 03 pages 1-7. (4) Refer to Appendix B, ATA 23-50-01 Dual Audio and Voice, Figure 02 pages 1-22. (5) Refer to Appendix B, ATA 23-70-01 Cockpit Voice Recorder, Figure 02 pages 1-6. (6) Refer to Appendix B, ATA 27-70-01: Control Lock, Figure 01 pages 1-4 and Figure 02 pages 1-4. (7) Refer to Appendix B, ATA 29-10-01 Hydraulic System, Figure 01 pages 1-18 and Figure 03 pages 1-15. (8) Refer to Appendix B, ATA 52-00-01 External Doors, Figure 03 pages 1-17.

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INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

1. Continuous Inspection Program A. This ICA Supplement does affect the current inspection program.

2. Airworthiness Limitations A. Cessna Aircraft Company Model 700 Airworthiness Limitations Manual contains the system and airframe limitations for the Model 700.

NOTE: The Airworthiness Limitations section is FAA-approved and specifies maintenance required under Section 43.16 and 91.403 of Title 14 Code of Federal Regulations, unless an alternative program has been FAA approved.

(1) There are new airworthiness limitations associated with this equipment and/or installation. Refer to the most current revision of the Cessna Model 700 Airworthiness Limitations Manual.

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GARMIN AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and operation of the Garmin automatic flight control system (AFCS). The line replaceable units (LRU's) in the Garmin AFCS are the roll servo cable, Garmin GSA 9000 autopilot roll servo actuator, Garmin GSM 9100 autopilot roll servo gearbox, pitch servo cable, Garmin GSM 9100 autopilot pitch servo gearbox, Garmin GSA 9000 autopilot pitch servo actuator, Garmin GMC 7200 AFCS mode controller, MASTER DISCONNECT switch, and control wheel steering (CWS) switch (airplanes -0033 and On). B. Refer to Figure 1 for a general view of the Garmin AFCS.

2. Description A. Roll Servo Cable (1) There is one roll servo cable installed below the cockpit floorboard access panel approximately at FS 160.683 in the airplane. It attaches to the Garmin GSM 9100 autopilot roll servo gearbox and to the aileron forward sector. B. Garmin GSA 9000 Autopilot Roll Servo Actuator (1) There is one Garmin GSA 9000 autopilot roll servo actuator installed below the cockpit floorboard access panel approximately at FS 160.683 and LBL 8.525 in the airplane. It attaches to the Garmin GSM 9100 autopilot roll servo gearbox with bolts and washers. An electrical connector connects to the roll servo actuator. (2) The roll servo actuator is an electrical clutch without a mechanical slip clutch that controls the roll axis of the airplane. If the roll servo actuator is not operational, the autopilot system disengages and the flight crew is alerted. C. Garmin GSM 9100 Autopilot Roll Servo Gearbox (1) There is one Garmin GSM 9100 autopilot roll servo gearbox installed below the cockpit floorboard access panel approximately at FS 160.683 and LBL 8.525 in the airplane. It attaches to the aileron autopilot servo bracket assembly and to the Garmin GSA 9000 autopilot roll servo actuator with bolts and washers. A roll servo cable attaches to the roll servo gearbox. (2) The roll servo gearbox gives correct gearing and torque control to the roll servo actuator. It is a fully mechanical unit. D. Pitch Servo Cable (1) There are two pitch servo cables (top and bottom) installed below the cockpit floorboard access panel approximately at FS 169.59 in the airplane. They attach to the Garmin GSM 9100 autopilot pitch servo gearbox and to the elevator cockpit sector. E. Garmin GSM 9100 Autopilot Pitch Servo Gearbox (1) There is one Garmin GSM 9100 autopilot pitch servo gearbox installed below the cockpit floorboard access panel approximately at FS 169.59 and LBL 8.56 in the airplane. Itattaches to the elevator autopilot servo bracket assembly and to the Garmin GSA 9000 autopilot pitch servo actuator with bolts and washers. Two pitch servo cables (top and bottom) attach to the pitch servo gearbox. (2) The pitch servo gearbox gives correct gearing and torque control to the pitch servo actuator. It is a fully mechanical unit. F. Garmin GSA 9000 Autopilot Pitch Servo Actuator (1) There is one Garmin GSA 9000 autopilot pitch servo actuator installed below the cockpit floorboard access panel approximately at FS 169.59 and LBL 8.56 in the airplane. Itattaches to the Garmin GSM 9100 autopilot pitch servo gearbox with bolts and washers. An electrical connector connects to the pitch servo actuator. (2) The pitch servo actuator is an electrical clutch without a mechanical slip clutch that controls the pitch axis of the airplane. If the pitch servo actuator is not operational, the autopilot system disengages and the flight crew is alerted. (3) The pitch servo actuator functions as the stick pusher in the angle-of-attack (AOA) system. For more data on the stick pusher function and the AOA system, refer to Chapter 34, Angle-of-Atack (AOA) System - Description and Operation.

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Garmin Automatic Flight Control System (AFCS) Figure 1 (Sheet 1)

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Garmin Automatic Flight Control System (AFCS) Figure 1 (Sheet 2)

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G. Garmin GMC 7200 AFCS Mode Controller (1) There is one Garmin GMC 7200 AFCS mode controller installed on top of the instrument panel approximately at FS 116.33 in the airplane. It attaches to the instrument panel with pawl latches. An electrical connector connects to the AFCS mode controller. (2) The AFCS mode controller is a single channel controller that controls the functions of the flight director (FD), the autopilot, and the auto-throttle systems. It sends flight crew commands to the Garmin integrated avionics (GIA) 64E unit. It shows the selected mode and the coupled FD as a status light on the AFCS mode controller panel. H. MASTER DISCONNECT Switch (1) There are two MASTER DISCONNECT switches (one pilot and one copilot) installed on the outboard control wheel cap in the airplane. It attaches to the control wheel cap with a setscrew. Electrical wires connect to the MASTER DISCONNECT switch. I. Control Wheel Steering (CWS) Switch (Airplanes -0033 and On) (1) There are two CWS switches (one pilot and one copilot) installed on the outboard control wheel cap in the airplane. It attaches to the control wheel cap with a lock washer and a nut. Electrical wires connect to the CWS switch.

3. Operation A. Garmin Automatic Flight Control System (AFCS) (1) The autopilot system is a three-axis fail passive system for pitch, roll, and the yaw that interfaces with the autothrottle system and the GIA unit. It is available to the flight crew from the takeoff to the landing. The flight crew can use the autopilot system with or without the autothrottle engagement. The GIA units calculate the mode logic, the FD, and the auto trim values. The mode select buttons are on the AFCS mode controller panel. (2) The primary flight displays (PFD's) show the FD commands and the mode annunciations. The left center of the PFD shows the roll modes and the right side of the PFD shows the pitch modes. The bottom edge of the AFCS annunciation field of each PFD shows the armed modes in white and you can see the active modes in green above the armed modes. (3) The roll and the pitch servo actuators receive the sensor data and the FD commands from the GIA unit. With this data, the roll and the pitch servo actuators calculate and command the control surface movement to let the airplane follow the FD commands. (4) The MASTER DISCONNECT switch lets the flight crew disconnect the autopilot, primary pitch trim system, roll trim, rudder trim, and nose wheel steering system when necessary during the airplane's operation. (5) For airplanes -0033 and On, when the flight crew pushes the CWS switch, the system removes the servo power and gives the crew temporary control of the airplane even when the autopilot system continues to stay engaged. When the flight crew releases the CWS switch, the autopilot system starts to control the airplane. (6) The backup yaw damper system is controlled by the GIA's and the roll servo actuator. It is only active in the event of a rudder failure and gives side-slip compensation (basic yaw damping functionality through the alierons). (7) When the flight crew pushes the FD button on the AFCS mode controller panel, itsetsthe selected FD to the default vertical (Pitch Hold) and lateral (Roll Hold) modes. When the flight crew pushes the FD button again, it disconnects the FD and removes the command bars on the PFD. When the flight crew engages the autopilot, the PFD shows the FD and the FD buttonon the AFCS mode controller panel goes off. (8) The manual electric pitch trim is available to the flight crew at all times. The autopilot system disengages, when the flight crew operates the manual trim switch on the control wheel.

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GARMIN AUTOMATIC FLIGHT CONTROL SYSTEM (AFCS) - ADJUSTMENT/TEST

1. General A. This section gives the adjustment and tests necessary for the Garmin automatic flight control system (AFCS). For a general description of the Garmin automatic flight control system, refer to Chapter 22, Garmin Automatic Flight Control System (AFCS) - Description and Operation.

2. Garmin Automatic Flight Control System (AFCS) Operational Check A. Tools and Equipment

CAUTION: Do the rigging of the flight control surfaces correctly. If the flight control surfaces are not correctly rigged, damage to the equipment can occur.

(1) Make sure that the preliminary rigging on all the flight control surfaces is done. (2) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. C. Do the Garmin Automatic Flight Control System (AFCS) Operational Check. (1) Do the Garmin Automated Preflight Test as follows: (a) After you connect to electrical power, the AFCS system performs power-up self-tests to make sure that the RAM, ROM, input/output interfaces, and wrap around operate correctly. (b) After the power-up tests are complete, the AFCS performs a series of tests to make sure that AFCS installation and operation of system monitoring functions operate correctly. (c) At the end of the successful preflight test, you will hear an AUTOPILOT aural sound onthe speaker. (d) If the preflight test is unsatisfactory, an AP FAIL CAS message shows on the primary flight display (PFD). (e) When the PFT message goes off, the system is ready for usual operation. (2) Do the Autopilot Circuit Breaker Assurance Check as follows: (a) Make sure that PITCH SERVO and PITCH SERVO AUX circuit breakers on the left circuit breaker panel are engaged. (b) Disengage the PITCH SERVO circuit breaker on the left circuit breaker panel. 1 Make sure that a white AP FAIL crew alerting system (CAS) message does not display on the PFD. 2 Make sure that you can continue to engage the autopilot while you push the AP button on the GMC 7200 mode controller. 3 Engage the PITCH SERVO circuit breaker on the left circuit breaker panel. (c) Disengage the PITCH SERVO AUX circuit breaker on the left circuit breaker panel. 1 Make sure that a white AP FAIL CAS message does not display on the PFD. 2 Make sure that the autopilot stays engaged. 3 If the autopilot is not engaged, push the AP button on the GMC 7200 mode controller. a Make sure that the autopilot engages. (d) Disengage the PITCH SERVO circuit breaker on the left circuit breaker panel. 1 Make sure that a white AP FAIL CAS message shows on the PFD. 2 Make sure that the autopilot disengages.

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3 Make sure that you cannot engage the autopilot while you push the AP button on the GMC 7200 mode controller. 4 Engage the PITCH SERVO and PITCH SERVO AUX circuit breaker on the left circuit breaker panel. 5 After one minute, make sure that the white AP FAIL CAS message does not show. (e) Disengage the ROLL SERVO circuit breaker on the left circuit breaker panel. 1 Make sure that a white AP FAIL CAS message shows. 2 Make sure that you cannot engage the autopilot while you push the AP button on the GMC 7200 mode controller. 3 Engage the ROLL SERVO circuit breaker on the left circuit breaker panel. 4 Make sure that after one minute, the white AP FAIL CAS message does not show. (f) Disengage the AFCS CTRL circuit breaker on the left circuit breaker panel. 1 Make sure that a white AP FAIL CAS message shows. 2 Make sure that the panel lights on the GMC 7200 mode controller do not show. 3 Engage the AFCS CTRL circuit breaker on the left circuit breaker panel. 4 Make sure that after one minute, the white AP FAIL CAS message does not show. 5 Make sure that the panel lights on the GMC 7200 mode controller show. (g) Remove power from left mission/main buses as follows: 1 Set the L ELEC switch from NORM to the EMER position. 2 Make sure that none of the circuit breakers in Table 501 disengage.

Table 501. Circuit Breakers

Circuit Breaker Location AFCS CTRL (HC001) Left Circuit Breaker Panel PITCH SERVO (HC028) Left Circuit Breaker Panel PITCH SERVO AUX (HF064) Left Circuit Breaker Panel ROLL SERVO (HC029) Left Circuit Breaker Panel (h) Supply power to the left mission/main buses as follows: 1 Set the L ELEC switch from EMER to the NORM position. (i) Remove power from right mission/main buses as follows: 1 Set the R ELEC switch from NORM to the EMER position. 2 Make sure that none of the circuit breakers in Table 501 disengage. (j) Supply power to the right mission/main buses as follows: 1 Set the R ELEC switch from EMER to the NORM position. (3) Do the Flight Director Operation Functional Check as follows: (a) On the GMC 7200 mode controller, push the CPL button as necessary to make the arrow point to the left on the PFD. (b) Push the TO/GA button on the left throttle lever. 1 Make sure that the flight director (FD) command bars show at approximately 10 degrees nose up. (c) Push the FD button on the right side of the GMC 7200 mode controller. 1 Make sure that the FD command bars are removed from the copilot's PFD. (d) For airplanes -0033 and On, do as follows: 1 Push and hold the CWS switch on the pilot's control wheel. 2 Make sure that the FD mode boxes show CWS. 3 Release the CWS switch. 4 Push the FD button on the right side of the GMC 7200 mode controller. 5 Make sure that the FD command bars are removed from the copilot's PFD. (e) Push the CPL button on the guidance panel to change the arrow point to the right on the PFD. (f) Do the flight director operation functional check for the opposite side. (4) Do the Autopilot Operation Functional Check as follows:

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WARNING: Make sure that the personnel and equipment are away from the flight control surfaces before you engage the autopilot ormove the flight control surfaces. If the personnel and equipment are not away from the flight control surfaces, injury to personnel and damage to the aircraft and equipment will occur.

(a) After two minutes with electrical power on, make sure that the AP FAIL, FORCE SENSOR L-R and AP STAB TRIM INOP crew alerting system (CAS) messages do not show. (b) Push the CPL button on the GMC 7200 AFCS mode controller as necessary to point the arrow to the left. (c) Push the HDG button on the GMC 7200 AFCS mode controller to engage the heading mode. (d) Push the HDG knob on the GMC 7200 AFCS mode controller to sync the heading bug to the current course. (e) Do not let the autopilot move the flight control surfaces to the stops during the steps that follow:

NOTE: It is recommended that you read to the end of this procedure before you continue.

1 Use the pitch wheel and the heading knobs as necessary to keep the control column in the center position. 2 Push the MASTER DISCONNECT switch on the control wheel if you think the autopilot will move the flight control surface to the stops. a The autopilot will disengage. (f) Move the control columns to the center position. (g) Push the AP button on the GMC 7200 mode controller to engage the autopilot. 1 Make sure that the green AP annunciation shows on the pilot's and the copilot's primary flight display (PFD). (h) Do a check of the pitch axis as follows: 1 Turn the pitch wheel on the GMC 7200 mode controller to the nose UP direction. a Make sure that the control columns move aft. b Let the control columns move aft to approximately half travel. 2 Turn the pitch wheel on the GMC 7200 mode controller to the nose DN direction. a Make sure that the control columns move forward towards the center position. b If necessary, turn the pitch wheel on the GMC 7200 mode controller to keep the control wheel in the center position. c Make sure that the autopilot does not disconnect. (i) Do a check of the roll axis as follows: 1 Push the HDG button on the GMC 7200 mode controller. 2 Turn the HDG knob on the GMC 7200 mode controller to the right. a Make sure that the control wheel moves to the right. b Let the control wheel move to the right to approximately half travel. 3 Turn the HDG knob on the GMC 7200 mode controller to the left. a Make sure that the control wheel moves to the left towards the center position. b If necessary, turn the HDG knob on the GMC 7200 mode controller to keep the control wheel in the center position. c Make sure that the autopilot does not disconnect. (j) Do a check of the MASTER DISCONNECT switch as follows: 1 Push the MASTER DISCONNECT switch on the pilot's control wheel. a Make sure that the autopilot disconnects. 2 Push the MASTER DISCONNECT switch on the pilot's control wheel to stop the disconnect aural sound. 3 Push the AP button on the GMC 7200 mode controller to engage the autopilot again. 4 Push the MASTER DISCONNECT switch on the copilot's control wheel. a Make sure that the autopilot disconnects.

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5 Push the MASTER DISCONNECT switch on the copilot's control wheel to stop the disconnect aural sound. 6 Push the AP button on the GMC 7200 mode controller to engage the autopilot again. (k) On the MFD GTC systems test page do as follows: 1 Start the Stall Warn autotest. 2 The stick pusher starts to operate. 3 Push the MASTER DISCONNECT switch on the pilot's control wheel to stop the stick pusher. a Make sure that the amber STICK PUSHER FAIL CAS message shows on the PFD. 4 Engage L RAT HEAT, L AOA CASE HEAT, and L AOA VANE HEAT circuit breakers on the left circuit breaker panel, R RAT HEAT, R AOA CASE HEAT, and R AOA VANE HEAT circuit breakers on the right circuit breaker panel. a Make sure that the amber STICK PUSHER FAIL CAS message does not show on the PFD. 5 Push the AP button on the GMC 7200 mode controller to engage the autopilot again. (l) Do a check of the secondary trim as follows: 1 Push the SECONDARY TRIM ON/OFF switch on the pedestal to the ON position. a Make sure that the autopilot disconnects. 2 Push the SECONDARY TRIM ON/OFF switch on the pedestal to the OFF position. 3 Push the MASTER DISCONNECT switch on the pilot's control wheel to stop the disconnect aural sound. 4 Push the AP button on the GMC 7200 mode controller to engage the autopilot again. (m) Do a check of the manual trim as follows: 1 Push and hold the two halves of the trim switch on the pilot's control wheel to the UP position. a Make sure that the autopilot disconnects. b Release the two halves of the trim switch. c Push the MASTER DISCONNECT switch on the pilot's control wheel to stop the disconnect aural sound. d Push the AP button on the GMC 7200 mode controller to engage the autopilot again. 2 Push and hold the two halves of the trim switch on the copilot's control wheel to the UP position. a Make sure that the autopilot disconnects. b Release the two halves of the trim switch. c Push the MASTER DISCONNECT switch on the copilot's control wheel to stop the disconnect aural sound. d Push the AP button on the GMC 7200 mode controller to engage the autopilot again. (n) Do a force override check as follows: 1 Set the control columns near the neutral position. 2 Engage the autopilot. 3 Hold the pilot's control wheel and pull the control column to simulate a pitch up force. 4 Make sure that the autopilot disconnects. 5 Push the MASTER DISCONNECT switch on the pilot's control wheel to stop the disconnect aural sound. 6 Engage the autopilot again. 7 Hold the pilot’s control wheel and push the control column to simulate a pitch down force. 8 Make sure that the autopilot disconnects. 9 Push the MASTER DISCONNECT switch on the pilot's control wheel to stop the disconnect aural sound. 10 Push the AP button on the GMC 7200 mode controller to engage the autopilot again. 11 Hold the copilot's control wheel and pull the control column to simulate a pitch up force. 12 Make sure that the autopilot disconnects.

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13 Push the MASTER DISCONNECT switch on the copilot's control wheel to stop the disconnect aural sound. 14 Engage the autopilot again. 15 Hold the copilot’s control wheel and push the control column to simulate a pitch down force. 16 Make sure that the autopilot disconnects. 17 Push the MASTER DISCONNECT switch on the copilot's control wheel to stop the disconnect aural sound. 18 Push the AP button on the GMC 7200 mode controller to engage the autopilot again. (o) For Airplanes -0033 and On, do a check of the CWS switch as follows: 1 Push and hold the CWS switch on the pilot's control wheel. a Make sure that the autopilot servos disengage as shown by free control column movement. b Move the control column back to the center position and release the CWS switch. c Make sure that the autopilot servos engage again. 2 Push and hold the CWS switch on the copilot's control wheel. a Make sure that the autopilot servos disengage as shown by free control column movement. b Move the control column back to the center position and release the CWS switch. c Make sure that the autopilot servos engage again. (p) Do a check of the trim interface as follows: 1 Push and hold forward on the control wheel. a After a period of time, the trim will start to move to release the load. b Make sure that the trim moves in the nose UP direction. 2 Release the control wheel. a Make sure that the trim stops. (q) Push the MASTER DISCONNECT switch to disconnect the autopilot. D. Put the Airplane Back to its Initial Condition. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

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CONTROL WHEEL STEERING SWITCH - REMOVAL/INSTALLATION (Airplanes -0033 and On)

1. General A. This section gives the removal and installation procedures for the control wheel steering (CWS) switch (SXM303). For a general description of the CWS switch, refer to Chapter 22, Garmin Automatic Flight Control System (AFCS) - Description and Operation.

2. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 22, Auto Flight - General. For the supplier publication part number and manufacturer data, refer to the introduction - Supplier Publication List. A. Tools and Equipment • None. B. Special Consumables • Tags. C. Reference Material • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 25, Control Wheel Pad - Removal/Installation • Citation Standard Practices Manual, Chapter 20, Wiring and Resistors - Maintenance Practices • Citation Standard Practices Manual, Chapter 20, Soldering - Maintenance Practices.

3. Setup A. Prepare the Airplane for the Control Wheel Steering (CWS) Switch Removal. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Disengage the circuit breakers given in Table 401.

Table 401. Circuit Breakers

Circuit Breaker Name Circuit Breaker Location AFCS CTRL Left Circuit Breaker Panel

PITCH SERVO Left Circuit Breaker Panel ROLL SERVO Left Circuit Breaker Panel (3) Remove the control wheel pad from the applicable control wheel. Refer to Chapter 25, Control Wheel Pad - Removal/Installation.

4. Control Wheel Steering (CWS) Switch Removal A. Remove the CWS Switch (Refer to Figure 401).

NOTE: The removal of the left and the right CWS switches is typical.

(1) Disconnect the electrical connectors (PXM028 and PXM030) from the electrical connectors (JXM028 and JXM030). (2) Remove the screws that attach the control wheel cap to the control wheel. (3) Carefully remove the control wheel cap from the control wheel. (4) Identify and tag the electrical wires on the CWS switch (SXM303). Refer to the Citation Standard Practices Manual, Chapter 20, Wiring and Resistors - Maintenance Practices. (5) Disconnect the electrical wires from the CWS switch. Refer to the Citation Standard Practices Manual, Chapter 20, Soldering - Maintenance Practices. (6) Remove the nut and the lock washer that attach the CWS switch to the control wheel cap.

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Control Wheel Steering (CWS) Switch Installation Figure 401 (Sheet 1)

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(7) Remove the CWS switch from the control wheel cap. (8) Remove the CWS switch from the airplane.

5. Control Wheel Steering (CWS) Switch Installation A. Install the CWS Switch (Refer to Figure 401).

NOTE: The installation of the left and the right CWS switches is typical.

(1) Put the CWS switch (SXM303) in its position in the control wheel cap. (a) Install the lock washer and the nut. (2) Solder the electrical wires to the CWS switch. Refer to the Citation Standard Practices Manual, Chapter 20, Soldering - Maintenance Practices. (3) Remove the tags from the electrical wires on the CWS switch. (4) Put the control wheel cap with the CWS switch in its position on the control wheel. (a) Install the screws. (5) Connect the electrical connectors (PXM028 and PXM030) to the electrical connectors (JXM028 and JXM030).

6. Control Wheel Steering (CWS) Switch Post-Maintenance Checks A. Do the CWS Switch Post-Maintenance Checks. (1) Engage the circuit breakers shown in Table 401. (2) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

WARNING: Make sure that personnel and equipment are away from the flight control surfaces before you engage the autopilot ormove the flight control surfaces. If you do not do this, injury to personnel or damage to the equipment can occur.

NOTE: Make sure that you wait for a minimum of two minutes after the airplane powers on, before you do the CWS switch operational check.

(3) Do the CWS switch operational check as follows: (a) Make sure that the white AP FAIL, white AP FORCE SENSOR L-R, and amber AP STAB TRIM INOP crew alerting system (CAS) messages do not show on the primary flight display (PFD) in the cockpit. (b) Push the CPL button on the Garmin GMC 7200 automatic flight control system (AFCS) mode controller panel in the cockpit as necessary to point the arrow to the left. (c) Push the HDG button to engage the heading mode. (d) Push the HDG knob to sync the heading bug to the current course. (e) Do not let the autopilot move the flight control surfaces to the stops during the steps that follow. 1 Push the MASTER DISCONNECT switch on the control wheel if you think that the autopilot will move the flight control surface to the stops.

NOTE: When you push the MASTER DISCONNECT switch, the autopilot will disengage.

(f) Move the control columns to the center position. (g) Push the AP button on the Garmin GMC 7200 AFCS mode controller panel to engage the autopilot. 1 Make sure that the green AP annunciation shows on the pilot's and the copilot's PFD's. (h) Push and hold the CWS switch on the pilot's control wheel. 1 Make sure that the autopilot servos disengage as shown by the free movement of the control column.

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(i) Move the control column back to the center position and release the CWS switch. 1 Make sure that the autopilot servos engage again. (j) Push and hold the CWS switch on the copilot's control wheel. 1 Make sure that the autopilot servos disengage as shown by the free movement of the control column. (k) Move the control column back to the center position and release the CWS switch. 1 Make sure that the autopilot servos engage again. (4) Push the AP button on the Garmin GMC 7200 AFCS mode controller panel to disengage the autopilot.

7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Install the control wheel pad. Refer to Chapter 25, Control Wheel Pad - Removal/Installation.

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AUTOTHROTTLE SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and the operation of the autothrottle system. The only line replaceable unit (LRU) in the autothrottle system is the autothrottle. B. Refer to Figure 1 for a general view of the autothrottle system.

2. Description A. Autothrottle (1) There is one autothrottle installed on the airplane. The autothrottle is installed in the cockpit at the center of the pedestal at approximately RBL 2.78 and FS 128.38. It is attached to the pedestal, autothrottle LED panel, and electrical connectors.

3. Operation A. Autothrottle System (1) The autothrottle system moves the throttle levers automatically to give automatic engine thrust control to decrease the pilot's workload. The autothrottle system can operate during any phase of flight from takeoff to landing. You can operate the autothrottle system with or withoutthe Garmin Autopilot System. Push the A/T button on one of the two throttle levers to engage the autothrottle system. The A/T DISC buttons on the throttle levers will disengage the autothrottle system. The autothrottle system control loop operates in the thrust mode or the speed mode. In the speed mode, the reference speed is compared to the actual speed supplied by the air data system. In the thrust mode, the N1 thrust target from the full-authority digital engine-control (FADEC) is compared to the actual N1. Then, it adjusts the throttles to reduce the error. (2) Before takeoff, the pilots push the A/T button to arm the autothrottle system but the throttle levers will not move until the pilot manually moves the throttles levers more than the preset throttle lever angle (TLA). This is to make sure that the airplane is in the takeoff configuration. The autothrottle system will then engage the hold mode and remove the electrical power from the throttle lever servos until the airplane goes more than 400 feet (121.9 m) above ground level (AGL). After 400 feet (121.9 m) AGL, the autothrottle system will disengage the hold mode and continue takeoff thrust until the landing gear and the flaps are up and a vertical mode is set. Then, the autothrottle system will control the throttle levers. (3) The autothrottle system controls the thrust during the climb, cruise, descent, approach, and landing phases of flight as related to the flight guidance mode selected. You can set theflight guidance mode with the mode selector on the autopilot mode controller to the FMS or the MAN position. In the FMS position, the autothrottle system uses the speed values from the flight management system (FMS) to control the throttle levers. In the MAN position, the autothrottle system uses the manual speed target to control the autothrottle. (a) Airplanes with G5000 System Software Version 58 and higher, in addition to the above, the autothrottle system can function during takeoff. Arming of the autothrottle occurs when the crew presses the AT Engage switch and it is annunciated to the crew as a white ‘TO’ that appears in the flight mode annunciator. Engagement of the autothrottle will occur after the crew manually advances throttle levers to takeoff thrust while the autothrottle is armed. The autothrottle will engage directly into Hold mode, which is indicated as a green ‘Hold’ in the flight mode annunciator. While in Hold mode, the GIAs continue to withhold the enable discrete power from the throttle quadrant servos to ensure that no automatic

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Autothrottle System Figure 1 (Sheet 1)

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throttle movement can occur during takeoff. After takeoff, the autothrottle will stay in Hold mode until the aircraft exceeds 400ft above field elevation at which point it will reenable the throttle quadrant servos and resume normal operation.

NOTE: This update to the autothrottle system relies upon wiring changes to make sure both GIAs output the same signal through a relay. This relay will only pass power through to the throttle quadrant if both GIA signals are present. For additional information on the wiring changes, refer to the Model 700 Wiring Diagram Manual, Chapter 22, Throttle Quadrant. For additional electrical load distribution information, refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 24, Electrical Load Analysis - Description and Operation.

(4) During the approach phase, the radar altimeter is used to start the retard mode at approximately 50 feet (15.2 m) AGL. The retard mode moves the throttle levers to the IDLE position for landing. If the radar altimeter becomes out-of-range or does not operate, an amber AT RETARD FAIL crew alerting system (CAS) message will show and the retard mode will not operate. Approximately five seconds after landing, the autothrottle system becomes disengaged. During the approach if a pilot pushes the TO/GA button on one of the throttle levers, the autothrottle system will move the throttle levers to the TO position and a green TO will show on the left side of the flight mode annunciations (FMA). (5) The autothrottle system has a fine TLA trim command function to prevent frequent small throttle lever adjustments during operation. This lets the autothrottle system ignore TLA changes of 2 degrees or less. (6) The autothrottle system also supplies speed protection automatically for low speeds and high speeds. It is not necessary to engage the autothrottle system for the speed protection mode to operate. For high-speed protection, the throttle levers are decreased and the autopilot system makes changes to the pitch. The high-speed protection operates at VMO +5 knots indicated airspeed (KIAS), MMO +0.015M, V FE +5 KIAS, and VLE/VLO +5 KIAS. For low-speed protection, the throttle levers are increased as you approach a high angle-of-attack before the stall warning. The low-speed protection operates as related to the normalized angle-of-attack. (7) The autothrottle system emergency descent mode will automatically operate if the cabin altitude becomes too high. The autopilot system and the autothrottle system will engage the FLC mode for a descent at VMO/MMO -5 KIAS down to 15,000 feet (4572 m). (8) The autothrottle system gives engine indicating system (EIS) data, CAS messages, and flight mode annunciations. (a) The EIS shows the thrust mode indication, N1 T bug, and N1 V bug. The thrust mode indication is a textual indication to show the value of the N1 V bug. The N1 T bug indication shows the current TLA as an N1 value with the current altitude, airspeed, and temperature. The N1 V bug indication shows a reference or limit value to help to set the throttle position. The N1 V bug is always at or above the N1 T bug. The different colors of the N1 V bug are shown as follows: • Amber shows the FADEC in control. • Green shows when the thrust mode indication is TO and the N1 V bug is 0.5% or less from the N1 pointer. • Magenta shows when the autothrottle is engaged. • Cyan shows when the N1 V bug is 3% or less from the N1 T bug. • White shows during all other conditions. (b) The amber AT RETARD FAIL CAS message shows when the retard mode is not available. The red AT HOLD FAIL CAS message shows when the throttle levers do not increase to the TO position or when the hold mode disengages before 400 feet (121.9 m) AGL during takeoff. The white or the amber AT FAIL CAS message shows for autothrottle system failures. (c) The FMA is at the top of the left and the right primary flight displays (PFD's) above the attitude indicator. The FMA shows armed and active modes for the autopilot system and the autothrottle system. The armed modes are shown in white and the active modes are shown in green.

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B. Envelope Speed Protection (ESP), Airplanes with G5000 System Software Version 58 and higher. (1) The ESP function consists of both Underspeed Protection (USP) and Overspeed Protection (OSP) modes and is available when the autothrottle is NOT engaged. (a) The USP mode activation is indicated as a green ‘MIN SPD’ mode. USP mode provides protection against aircraft underspeed conditions. This mode uses angle of attack information to determine when the aircraft is approaching a stall condition and activates prior to stick shaker activation. The USP mode is also inhibited during the landing phase to prevent nuisance activations during high crew workload situations. (b) The OSP mode activation is indicated as a green ‘MAX SPD’ mode in the FMA. OSP mode provides protection against aircraft overspeed conditions. This mode uses airspeed information to determine when the aircraft is approaching an overspeed condition and activates prior to the primary overspeed warning alerts. The crew will be alerted when the ESP function has engaged through an amber AT AUTO ON PFD alert, an ‘AIRSPEED’ aural annunciation, and a green mode indication shown in the FMA to inform the crew of which mode has activated. (2) As the aircraft approaches either an overspeed or underspeed condition, the autothrottle will automatically engage, correct the condition by adjusting the throttle levers, then automatically disconnect once the condition no longer exists. (3) The automatic disengagement is annunciated to the crew as a normal autothrottle disconnect: a single ‘AUTOTHROTTLE’ aural annunciation will sound and the ‘AT’ status in the Flight Mode Annunciator (FMA) will flash inverse amber for 5 seconds.

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AUTOTHROTTLE SYSTEM - TROUBLESHOOTING

1. General A. This section gives the troubleshooting for the autothrottle system. For a general description of the autothrottle system, refer to Chapter 22, Autothrottle System - Description and Operation.

2. Autothrottle System Troubleshooting A. Tools and Equipment

(1) Tools and Equipment • Multimeter. (2) Special Consumables • None. (3) Reference Material • Chapter 22, Autothrottle System - Adjustment/Test • Chapter 22, Autothrottle - Removal/Installation • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 42, Garmin G5000 Integrated Avionics System Software - Adjustment/Test • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, EWIS Repair and Replacement - Maintenance Practices • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Wire Harness Installation - Maintenance Practices. B. Prepare the Airplane for the Autothrottle System Troubleshooting. (1) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. C. Do the Autothrottle System Troubleshooting.

NOTE: The autothrottle system initiates a preflight check (PFT) at system power on. This PFT checks latent wiring faults that would prevent the GIAs from being able to control the state of the enable function.

NOTE: The autothrottle system initiates a modified preflight check (PFT) with G5000 system software version 58 and higher, at system power on. This PFT checks latent wiring faults and GIA enable discrete signals by activating the enable signal from each GIA that would prevent the GIAs from being able to control the state of the enable function.

(1) Make sure that the circuit breaker given in Table 101 is engaged.

Table 101. Circuit Breakers

Circuit Breaker Name Circuit Breaker Location AUTO THROTTLE Left Circuit Breaker Panel (2) Do the Autothrottle Operational Check. Refer to Chapter 22, Autothrottle System - Adjustment/ Test. (3) If the problem continues, examine the electrical wiring and components as follows: Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Wire Harness Installation - Maintenance Practices. (a) Do a visual check of the electrical connectors and airplane electrical connectors for bent pins and pushed back pins. 1 If necessary, repair the damage. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, EWIS Repair and Replacement - Maintenance Practices

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(b) Make sure that electrical power and ground signals are present. (c) Make sure that data bus lines are correctly terminated and secure.

CAUTION: Do not touch bus wiring to each other or to shield grounds. Damage to equipment or circuits can result.

(d) Use a multimeter to do a continuity check of the bus wires.

NOTE: Check the high-speed data bus (HSDB) and the ARINC 429 bus wiring.

1 Make sure that there is continuity only from each wires' related pin end to end and to no other wires, airplanes grounds, or shields. (e) Do a visual check of the wiring components and make sure that all applicable strapping is correct and any necessary G5000 system strapping is correct. (f) Do a visual check of the wiring bundles for damage. 1 If necessary, repair or replace the wiring bundles. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, EWIS Repair and Replacement - Maintenance Practices. (g) Do a check of the applicable system wiring for continuity, ground faults, or other unserviceable conditions. 1 If necessary, repair or replace the wiring bundles. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, EWIS Repair and Replacement - Maintenance Practices. (4) If a Garmin line replaceable unit (LRU) was replaced with a new unit or interchanged with another unit, make sure that the correct software and configuration was loaded. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Adjustment/Test. (5) Make sure that the hardware configuration/avionics status is correct as follows: (a) On the pilot's right Garmin GTC 575 Touchscreen Control Unit, do as follows: 1 Select Home. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status.

NOTE: The Avionics Status screen will show the status of the LRU's on the airplane. Use Up and Down to scroll through the list of LRU's.

(b) Make sure that every unit in the LRU Info tab has a green check mark in the status column to show that it is operational.

NOTE: If the status shows an amber X for a LRU, a problem is possible with the LRU's data bus or its 28V/GND connections.

NOTE: The serial numbers are not reported for the equipment that follows: COM1, COM2, NAV1, NAV2, and WX500.

NOTE: If a Serial Number or a Version Number is dashed, a problem is possible with the LRU's data bus or the software load.

(6) Replace the Autothrottle. Refer to Chapter 22, Autothrottle - Removal/Installation.

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D. Autothrottle Envelope Speed Protection (ESP), Airplanes with G5000 system software version 58 and higher. (1) Autothrottle Overspeed Protection (OSP) fails to operate correctly:

NOTE: OSP function is indicated when an overspeed condition occurs, as a green ‘MAX SPD’ mode in the FMA.

(a) Do the autothrottle system troubleshooting. Refer to this document, Autothrottle System - Troubleshooting. (2) Autothrottle Underspeed Protection (USP) fails to operate correctly:

NOTE: USP function is indicated when an underspeed condition occurs, as a green ‘MIN SPD’ mode in the FMA.

(a) Do the autothrottle system troubleshooting. Refer to this document, Autothrottle System - Troubleshooting. E. Autothrottle fails to operate correctly during takeoff, Airplanes with G5000 system software version 58 and higher.

NOTE: AT function during takeoff is indicated during takeoff under 400ft, as a green ‘HOLD’ mode in the FMA.

(1) Do the autothrottle system troubleshooting. Refer to this document, Autothrottle System - Troubleshooting. F. Put the Airplane Back to its Initial Condition. (1) Disconnect the external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

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DIGITAL AUDIO SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and operation of the digital audio system. The line replaceable units (LRU's) in the digital audio system are the Garmin GMA 36B Audio Processor, hand microphone jack, tailcone maintenance interphone jack, microphone/interphone push to talk (PTT) switch, nose wheel well maintenance interphone jack, microphone jack panel assembly, headset interphone jack, powered headset jack, audio line in jack (stereo), crew oxygen mask microphone jack, and optional observer seat audio panel. B. Refer to Figure 1 for a general view of the digital audio system.

2. Description A. Garmin GMA 36B Audio Processor (1) The two Garmin GMA 36B Audio Processors receive and interpret all audio signals from communication and navigation radios and supply audio to the cockpit speakers or the crew's headsets. The audio processors communicate directly with the Garmin GIA 64E Integrated Avionics Unit and the Garmin GTC 575 Touchscreen Control Unit. The touchscreen control units are used for the display and control of its settings (COM, NAV, volume, frequency, marker, etc.). The audio processors use digital audio technology which allow for the mix of audio from different sources. (2) The audio processors provide numerous analog input/output interface options. The interface options include COM radios, NAV radios, prioritized and mixed aural alerting, and entertainment audio. The audio processors also supply marker beacon functionality. The marker beacon antenna is installed on the forward fuselage fairing at BL 0.00 and aft of FS 225.50. For more data on the marker beacon system, refer to Chapter 34, Landing and Taxi Navigational Aids - Description and Operation. (3) The audio processors are connected by a digital audio link. If there is a primary digital audio link failure, the backup RS-232 is an analog fail-safe line. The audio processor communicates to the touchscreen control units with the high speed data bus (HSDB). (4) The audio processors are installed behind the instrument panel in the cockpit, behind the Garmin GDU 1450W Flight Displays. B. Hand Microphone Jack (1) There are two hand microphone jacks that connect hand microphones to the digital audio system. (2) The hand microphone jacks are installed on the pilot and copilot control columns. C. Tailcone Maintenance Interphone Jack (1) The tailcone maintenance interphone jack lets maintenance personnel communicate between the cockpit and the tailcone. The tailcone maintenance interphone jack has two connections: (a) The MIC connection is used to connect a standard aviation headset microphone to the audio system. This lets the ground crew talk to the flight crew. (b) The AUDIO connection is used to connect a standard aviation headset to the audio system. This lets the ground crew hear the flight crew. (2) The tailcone maintenance interphone jack is installed in the tailcone below the air cycle refrigeration pack (ACRP) at approximately FS 608.40. D. Microphone/Interphone Push To Talk (PTT) Switch (1) There are four PTT switches found in the cockpit. They can be used by the pilot and the copilot to communicate on the different radio systems, the passenger address (PA) system, and with each other. (2) Two PTT switches are installed in the pilot and the copilot's control wheels, and two are installed in the left and the right cockpit side consoles. (a) The control wheel PTT switches have three positions - a momentary position that is held for PTT, an off (neutral) position, and a latched position that holds the microphone on until the switch is unlatched. (b) The side console PTT switches have two positions - a momentary position that is held for PTT, and an off (neutral) position.

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Digital Audio System Figure 1 (Sheet 1)

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Digital Audio System Figure 1 (Sheet 2)

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Digital Audio System Figure 1 (Sheet 3)

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E. Nose Wheel Well Maintenance Interphone Jack (1) The nose wheel well maintenance interphone jack lets maintenance personnel communicate between the cockpit and the nose wheel well. The nose wheel well maintenance interphone jack has two connections: (a) The MIC connection is used to connect a standard aviation headset microphone to the audio system. This lets the ground crew talk to the flight crew. (b) The AUDIO connection is used to connect a standard aviation headset to the audio system. This lets the ground crew hear the flight crew. (2) The nose wheel well maintenance interphone jack is installed on nose wheel well access panel 213AZ at approximately FS 44.35. F. Microphone Jack Panel Assembly (1) There are two microphone jack panel assemblies, one for the pilot and the other for the copilot. Each microphone jack panel assembly contains a headset interphone jack, powered headset jack, and an audio line in jack (stereo). (2) The microphone jack panel assemblies are installed in the left and the right cockpit side consoles at approximately FS 160.56 and WL 128.26. G. Headset Interphone Jack (1) The headset interphone jack lets maintenance personnel communicate between the cockpit and the nose wheel well. The headset interphone jack has two connections: (a) The MIC connection is used to connect a standard aviation headset microphone to the audio system. This lets the flight crew talk to the ground crew. (b) The PHONE connection is used to connect a standard aviation headset to the audio system. This lets the flight crew hear the ground crew. (2) There is a headset interphone jack installed on the left and the right microphone jack panel assemblies. H. Powered Headset Jack (1) The powered headset jack is used to connect aviation headsets which require airplane power to operate. (2) There is a powered headset jack installed on the left and the right microphone jack panel assemblies. I. Audio Line In Jack (Stereo) (1) The audio line in jack (stereo) is used to connect a source of audio which can be heard through the flight compartment and passenger compartment headsets and speakers. (2) There is an audio line in jack (stereo) installed on the left and the right microphone jack panel assemblies. J. Crew Oxygen Mask Microphone Jack (1) The two crew oxygen mask microphone jacks connect the crew oxygen masks to the digital audio system. For more data on the crew oxygen masks, refer to Chapter 35, Crew Oxygen System - Description and Operation. (2) The crew oxygen mask microphone jacks are installed on the bottom of the left and the right crew oxygen mask stowage boxes between FS 132.00 and FS 147.50. K. Observer Seat Audio Panel (1) The optional observer seat audio panel is installed in the left forward closet. The audio panel has HEADSET and MIC plug-ins, a MIC button, and VOLUME buttons. When you push the MIC button, a green light will come on. (2) The audio panel interfaces with the pilot's Garmin GMA 36B Audio Processor and connects to the secondary crew headset audio out and the secondary crew MIC In.

3. Operation A. Garmin GMA 36B Audio Processor (1) The Garmin GMA 36B Audio Processors receive and interpret all voice audio signals and interfaces to audio signal sources and destinations such as the Garmin GTC 575 Touchscreen Control Units, Garmin GIA 64E Integrated Avionics Units, Collins ADF-4000 Automatic Direction

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Finder (ADF) Receiver, Collins DME-4000 Distance Measuring Equipment (DME) Receiver, Garmin GDL 59 Data Link, Honeywell KHF-1050 HF Communication System, Garmin GDR-66 VHF Data Link Radio, cockpit voice recorder (CVR), and the marker beacon antenna. (2) The Garmin GMA 36B Audio Processor has four modes of operation. The system runs in normal mode for regular flight activity. Other modes are provided for specific tasks like maintenance, system updates and operation during a failure condition. The modes of operation are described below: (a) The Normal mode is used during regular flight activity. (b) The Configuration mode is only used for configuration updates. It is used toeditand validate the configuration items for the audio processor. (c) The Boot Block mode is used to do system software uploads. The system automatically enters this mode when the Garmin SD card is used to update the software for the audio processor. (d) The Failsafe mode is used until the system has a successful power on self test (POST). After the POST, the audio processor switches to normal mode. B. Cockpit Audio System (1) There are two speakers to the cockpit audio, one for the pilot and one for the copilot. The pilot's speaker is connected to audio processor #1 and the copilot's speaker is connected to audio processor #2. A cockpit speaker mute function is integrated in the GTC's that lets the crew to deselect the cockpit speaker audio. There is a MIKE SEL switch/light on the left and right switch panel that are used to select the crew’s headset mic or crew oxygen mask mic. The COM1/COM2 TUNE switch/lights interface directly with the primary VHF radios and the GMA 36 Audio Processors (one switch per radio). The COM1/COM2 TUNE switch/lights operate as a dedicated frequency tuner. For more data on the MIKE SEL switch/lights and the COM1/ COM2 TUNE switch/lights, refer to Chapter 23, VHF Communication System - Description and Operation. C. Passenger Address (PA) System (1) The Garmin GTC 575 Touchscreen Control Units allow the pilots to select the PA system. On the GTC Audio & Radios screen, select PA and make sure that the green indicator comes on below it. A PTT switch must be pushed and held for the crew to give PA messages. The audio processors provide the output to drive the speakers. (2) The PA amplifier (or optional PA/Stereo amplifier) digitally amplifies audio with integrated digital signal processing (DSP). The optional 40 watt, 8 channel stereo amplifier uses entertainment speakers and functions also as an integrated PA module. For more data on the PA amplifier or optional PA/Stereo amplifier, refer to the Model 700 Interior Maintenance Manual and Illustrated Parts Catalog. D. Maintenance Audio System (1) The maintenance audio system is based on voice operated exchange (VOX) operated mics. No crew/cockpit action is required when a mic is plugged into the nose wheel maintenance interphone jack or the tailcone maintenance interphone jack . Audio control is accessed through the GTC's when you select Intercom. This brings up the Intercom screen that lets the crew adjust the maintenance audio system. When the maintenance audio is available, the flight crew can talk to the ground crew at the nose and tail of the airplane. The maintenance audio system is only available for ground operations and is not able to transmit on any of the communication radios. To close the Intercom screen, select Intercom again or Back on the GTC. E. Observer Seat Audio Panel (1) To operate the optional observer seat audio panel, it is necessary to select the Intercom button from one of the four Garmin GTC 575 Touchscreen Control Units. You can connect the audio panel intercom to the pilot and/or the copilot. You can control the audio panel volume with the Intercom volume slide on the GTC's. Fine volume tuning can be done with the VOLUME buttons on the audio panel. (2) Radio selections that are available to the flight crew are also available at the audio panel with volume control for all selections. The radio selections are on the Observer Audio tab on the GTC's.

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DIGITAL AUDIO SYSTEM - TROUBLESHOOTING

1. General A. This section gives the troubleshooting procedures for the digital audio system and the optional observer seat audio panel. For a general description of the digital audio system, Chapter 23, Digital Audio System - Description and Operation.

2. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 23, Communications - General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List. A. Tools and Equipment • Digital Multimeter • Site Master Analyzer S331L (or equivalent). B. Special Consumables • None. C. Reference Material • Chapter 42, Garmin G5000 Integrated Avionics System Software - Adjustment/Test • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Wire Harness Installation - Maintenance Practices • Model 700 Interior Maintenance Manual and Illustrated Parts Catalog.

3. Digital Audio System Troubleshooting A. Do the Digital Audio System Troubleshooting as follows: (1) If a Garmin line replaceable unit (LRU) was replaced with a new unit or interchanged with another unit, make sure that the correct software and configuration was loaded. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Adjustment/Test. (2) Make sure that the wiring is correct. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Wire Harness Installation - Maintenance Practices. (a) Use a Site Master Analyzer S331L (or equivalent) to make sure that the coaxial cable losses are correct. (3) Crew Alerting System (CAS) Message Troubleshooting (a) GMA FAIL 1-2 (Amber) 1 Make sure that the electrical connectors are correctly connected to the malfunctioning unit.

NOTE: This message is displayed for loss of the function of the GMA. It is displayed for complete loss of function, major loss of audio processing hardware, loss of aural warning, or any other failure needing indication to make fault trees work. The GMA will go to the "fail safe" mode which connects the headphones to that side's COM only.

(b) DATA BUS FAIL (Amber) 1 Make sure that the electrical connectors are correctly connected to the malfunctioning unit.

NOTE: This message is displayed for a loss of a databus connecting two Garmin LRU's and is used to address unknown failures. This message is not displayed for a total loss of data from an applicable LRU. It is displayed in the case of communication is lost over a particular link, but the LRU's at both ends of the link are still in communication with other LRU's.

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4. Observer Seat Audio Panel Troubleshooting

NOTE: The observer seat audio panel is optional. A. Do the Observer Seat Audio Panel Troubleshooting. (1) If there is no electrical power at the observer seat audio panel, do as follows: (a) Use a digital multimeter and make sure that there is 28 VDC at electrical connector (PC2157) pin contact 11. Refer to the Model 700 Interior Maintenance Manual and Illustrated Parts Catalog. (2) If necessary, repair or replace the electrical wiring. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Wire Harness Installation - Maintenance Practices.

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DIGITAL AUDIO SYSTEM - ADJUSTMENT/TEST

1. General A. This section gives the adjustments and tests necessary for the digital audio system and the optional observer seat audio panel. For a general description of the digital audio system, refer to Chapter 23, Digital Audio System - Description and Operation.

2. Digital Audio System Operational Check A. Tools and Equipment

(1) Tools and Equipment • Aviation Headset (Airplane-Powered, Single Plug) • Aviation Headset (Standard, Dual Plug) • Music Playing Device. (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 42, Garmin G5000 Integrated Avionics System Software - Adjustment/Test. B. Prepare the Airplane for the Digital Audio System Operational Check. (1) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Make sure that the L BATT and R BATT switch/lights are selected to the ON position. (3) If a Garmin GMA 36B Audio Processor was replaced with a new unit or interchanged with another unit, make sure that the correct software and configuration was loaded. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Adjustment/Test. (4) Make sure that the hardware configuration/avionics status is correct as follows: (a) On the pilot's right Garmin GTC 575 Touchscreen Control Unit, do as follows: 1 Select Home. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status.

NOTE: The Avionics Status screen will show the status of the line replaceable units (LRU's) on the airplane. Use Up and Down to scroll through the list of LRU's.

(b) Make sure that every unit in the LRU Info tab has a green check mark in the status column to show that it is operational.

NOTE: If the status shows an amber X for a LRU, a problem is possible with the LRU's data bus or its 28V/GND connections.

NOTE: The serial numbers are not reported for the equipment that follows: COM1, COM2, NAV1, NAV2, and WX500.

NOTE: If a Serial Number or a Version Number is dashed, a problem is possible with the LRU's data bus or the software load.

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C. Do the GMA Power and Circuit Breaker Test. (1) Disengage the AUDIO 1 AUX circuit breaker on the left circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that GMA 1 has a green check mark in the box.. (2) Disengage the AUDIO 1 circuit breaker on the left circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that GMA 1 has an amber X in the box. (b) Make sure that a GMA 1 CAS message shows. (3) Engage the AUDIO 1 AUX circuit breaker on the left circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that GMA 1 has a green check mark in the box. (b) Make sure that the GMA 1 CAS message does not show. (4) Engage the AUDIO 1 circuit breaker on the left circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that there is no change in the GMA 1 status. (5) Disengage the AUDIO 2 AUX circuit breaker on the right circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that GMA 2 has a green check mark in the box.. (6) Disengage the AUDIO 2 circuit breaker on the right circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that GMA 2 has an amber X in the box. (b) Make sure that a GMA 2 CAS message shows. (7) Engage the AUDIO 2 AUX circuit breaker on the right circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that GMA 2 has a green check mark in the box. (b) Make sure that the GMA 2 CAS message does not show. (8) Engage the AUDIO 2 circuit breaker on the right circuit breaker panel. (a) On the pilot's right GTC Avionics Status screen, make sure that there is no change in the GMA 2 status. D. Do the GMA 1 and GMA 2 EMER Power Check.

NOTE: Two aviation headsets with separate microphone and headphone plugs and two airplane-powered aviation headsets with a single plug are necessary to do this check.

(1) Connect the aviation headsets (standard, dual plug) to the pilot's and the copilot's headset interphone jacks (JXM513 microphone, JXM514 phone). (2) Make sure that the EXT PWR switch/light is set to the ON position. (3) Select the L BATT switch/light and the R BATT switch/light to the OFF position. (4) Select the L ELEC switch/light and the R ELEC switch/light to the EMER position. (5) Tune COM1 to a frequency that has continuous audio, such as air traffic control (ATC) or aerodrome flight information service (AFIS). (a) Make sure that you hear COM1 in the pilot's headset. (b) Make sure that you hear COM1 in the copilot's headset. (6) Disconnect the aviation headsets (standard, dual plug) from the pilot's and the copilot's headset interphone jacks (JXM513 microphone, JXM514 phone). (7) Connect the aviation headsets (airplane-powered, single plug) to the pilot's and the copilot's powered headset jacks (JXM500). (a) Make sure that you hear COM1 in the pilot's headset. (b) Make sure that you hear COM1 in the copilot's headset. (8) Disconnect the aviation headsets (airplane-powered, single plug) from the pilot's and the copilot's powered headset jacks (JXM500). (9) Select the L ELEC switch/light and the R ELEC switch/light to the NORM position. (10) Select the L BATT switch/light and the R BATT switch/light to the ON position.

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E. Do the Intercom Isolation Operational Check.

NOTE: Two aviation headsets with separate microphone and headphone plugs are necessary to do this check.

(1) Connect the aviation headsets (standard, dual plug) to the pilot's and the copilot's headset interphone jacks (JXM513 microphone, JXM514 phone). (2) Speak into the pilot's headset microphone and make sure that your voice is heard in the copilot's headset. (3) Speak into the copilot's headset microphone and make sure that your voice is heard in the pilot's headset. F. Do the Nose Wheel Well Maintenance Interphone Jack Operational Check.

NOTE: Two people and two aviation headsets with separate microphone and headphone plugs are necessary to do this check. One tester will need to be in the cockpit and the other tester will need to be at the nose wheel well.

(1) If necessary, connect an aviation headset (standard, dual plug) to the pilot's headset interphone jack (JXM513 microphone, JXM514 phone). (2) Connect an aviation headset (standard, dual plug) to the tailcone maintenance interphone jack (JT511 microphone, JT512 audio). (3) Speak into the tailcone maintenance headset microphone and make sure that your voice is heard in the pilot's headset. (4) Speak into the pilot's headset microphone and make sure that your voice is heard in the tailcone maintenance headset. H. Do the Headset and Oxygen Mask (MIC SEL) Switch/Light Operational Check. (1) For the pilot's MIC SEL switch/light and oxygen mask, do as follows: (a) Select the pilot's MIC SEL switch/light to the MASK position to set the oxygen mask as the active microphone. (b) Set the push to talk (PTT) switch on the pilot's control wheel to the latched, MIC ON position (outboard). (c) Speak into the pilot's oxygen mask and make sure that your voice is heard on the overhead speakers. (d) Set the PTT switch on the pilot's control wheel to the off position. (e) Select the pilot's MIC SEL switch/light to the HEADSET position. (2) For the copilot's MIC SEL switch/light and oxygen mask, do as follows: (a) Select the copilot's MIC SEL switch/light to the MASK position to set the oxygen mask as the active microphone. (b) Set the PTT switch on the copilot's control wheel to the latched, MIC ON position (inboard). (c) Speak into the copilot's oxygen mask and make sure that your voice is heard on the overhead speakers. (d) Set the PTT switch on the copilot's control wheel to the off position. (e) Select the copilot's MIC SEL switch/light to the HEADSET position.

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(3) For the optional observer/jump seat MIC SEL switch/light and oxygen mask, do as follows: (a) Select the pilot's MIC SEL switch/light to the MASK position. (b) Select the observer/jump seat MIC SEL switch/light to the MASK position. (c) Set the push to talk (PTT) switch on the pilot's control wheel to the latched, MIC ON position (outboard). (d) At the observer seat audio panel, set the MIC switch to the On position. 1 Make sure that the green MIC switch light comes on. (e) Speak into the observer/jump seat oxygen mask and make sure that your voice is heard on the overhead speakers. (f) At the observer seat audio panel, set the MIC switch to the Off position. 1 Make sure that the green MIC switch light goes off. (g) Speak into the observer/jump seat oxygen mask and make sure that your voice is not heard on the overhead speakers. (h) Set the PTT switch on the pilot's control wheel to the off position. (i) Select the pilot's MIC SEL switch/light to the HEADSET position. (j) Select the observer/jump seat MIC SEL switch/light to the HEADSET position. I. Do the Passenger Address System Operational Check.

NOTE: Two aviation headsets with separate microphone and headphone plugs are necessary to do this check.

(1) Connect the aviation headsets (standard, dual plug) to the pilot's and the copilot's headset interphone jacks (JXM513 microphone, JXM514 phone). (2) On the pilot's right GTC, do as follows to turn on the passenger address system: (a) Select Home. (b) Select Audio & Radios. (c) Select PA. 1 Make sure that the green indicator below PA comes on. (3) Push the PTT switch on the pilot's side console. (4) Speak into the pilot's headset microphone. (a) Make sure that your voice is heard on the cabin overhead speakers. (5) Push the PTT switch on the copilot's side console. (6) Speak into the copilot's headset microphone. (a) Make sure that your voice is heard on the cabin overhead speakers. (7) On the pilot's right GTC Audio & Radios screen, select PA. (a) Make sure that the green indicator below PA goes off. J. Do the Audio Line In Jack (Stereo) Operational Check.

NOTE: Two aviation headsets with separate microphone and headphone plugs and two airplane-powered aviation headsets with a single plug are necessary to do this check.

(1) Connect the aviation headsets (standard, dual plug) to the pilot's and the copilot's headset interphone jacks (JXM513 microphone, JXM514 phone). (2) Connect a music playing device to the pilot's audio line in jack (stereo) (JXM512). (3) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select Audio & Radios. (c) Select L AUDIO IN. 1 Make sure that the green indicator below L AUDIO IN comes on. (4) Play an audio selection from the music playing device. (5) Adjust the volume to the necessary level. (6) Make sure that you hear the audio selection on the pilot's headset. (7) Disconnect the music playing device from the pilot's audio line in jack (stereo). (8) Connect the music playing device to the copilot's audio line in jack (stereo) (JXM512). (9) On the pilot's right GTC Audio & Radios screen, do as follows: (a) Select L AUDIO IN. 1 Make sure that the green indicator below L AUDIO IN goes off.

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(b) Select R AUDIO IN. 1 Make sure that the green indicator below R AUDIO IN comes on. (10) Play an audio selection from the music playing device. (11) Adjust the volume to the necessary level. (12) Make sure that you hear the audio selection on the copilot's headset. (13) Disconnect the music playing device from the copilot's audio line in jack (stereo). (14) On the pilot's right GTC Audio & Radios screen, do as follows: (a) Select R AUDIO IN. 1 Make sure that the green indicator below R AUDIO IN goes off. (15) Disconnect the aviation headsets (standard, dual plug) from the pilot's and the copilot's headset interphone jacks (JXM513 microphone, JXM514 phone). (16) Connect the aviation headsets (airplane-powered, single plug) to the pilot's and the copilot's powered headset jacks (JXM500). (17) Repeat the Audio Line In Jack (Stereo) Operational Check with the aviation headsets (airplane- powered, single plug). K. Do the Powered Headset Jack Operational Check.

NOTE: Two airplane-powered aviation headsets with a single plug is necessary to do this check.

(1) Connect the aviation headsets (airplane-powered, single plug) to the pilot's and copilot's powered headset jacks (JXM500). (2) Speak into the pilot's headset microphone and make sure that your voice is heard in the copilot's headset. (3) Speak into the copilot's headset microphone and make sure that your voice is heard in the pilot's headset. L. Put the Airplane Back to its Initial Condition. (1) Remove all aviation headsets from the airplane. (2) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

3. Observer Seat Audio Panel Operational Check

NOTE: The observer seat audio panel is optional. A. Tools and Equipment

(1) Tools and Equipment • Aviation Headset (Airplane-Powered, Single Plug) • Aviation Headset (Standard, Dual Plug). (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices. B. Prepare the Airplane for the Observer Seat Audio Panel Operational Check. (1) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. C. Do the Observer Seat Audio Panel Lighting Check. (1) Turn the PANEL light switch on the overhead light switch panel fully clockwise. (a) Make sure that the observer seat audio panel MIC switch is fully bright. (2) Turn the PANEL light switch on the overhead light switch panel fully counterclockwise. (a) Make sure that the observer seat audio panel MIC switch is fully dim. (3) Turn the PANEL light switch on the overhead light switch panel to adjust the lighting as necessary.

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D. Do the Observer Seat Audio System Check.

NOTE: Three aviation headsets with separate microphone and headphone plugs are necessary to do this check.

(1) Connect the aviation headsets to the pilot's, copilot's, and observer seat headset jacks. (2) On the pilot's right Garmin GTC 575 Touchscreen Control Unit, do as follows: (a) Select Home. (b) Select Intercom. (c) Select the green arrow between the Pilot and the Observer. 1 Make sure that the green arrow is active between the Pilot and the Observer. (3) On the copilot's left Garmin GTC 575 Touchscreen Control Unit, do as follows: (a) Select Home. (b) Select Intercom. (c) Select the green arrow between the Copilot and the Observer. 1 Make sure that the green arrow is active between the Copilot and the Observer. (4) Speak into the pilot's headset microphone while you listen on the observer's headset. (a) Make sure that you can hear the pilot's voice in the observer's headset. (5) Speak into the copilot's headset microphone while you listen on the observer's headset. (a) Make sure that you can hear the copilot's voice in the observer's headset. (6) Speak into the observer's headset microphone while you listen on the pilot's headset. (a) Make sure that you can hear the observer's voice in the pilot's headset. (7) Speak into the observer's headset microphone while you listen on the copilot's headset. (a) Make sure that you can hear the observer's voice in the copilot's headset. E. Do the Observer Seat Oxygen Mask Check. (1) Select the pilot's MIC SEL switch/light to the MASK position. (2) Select the observer/jump seat MIC SEL switch/light to the MASK position. (3) Set the push to talk (PTT) switch on the pilot's control wheel to the latched, MIC ON position (outboard). (4) At the observer seat audio panel, set the MIC switch to the On position. (a) Make sure that the green MIC switch light comes on. (5) Speak into the observer/jump seat oxygen mask and make sure that your voice is heard on the overhead speakers. (6) At the observer seat audio panel, set the MIC switch to the Off position. (a) Make sure that the green MIC switch light goes off. (7) Speak into the observer/jump seat oxygen mask and make sure that your voice is not heard on the overhead speakers. (8) Set the PTT switch on the pilot's control wheel to the off position. (9) Select the pilot's MIC SEL switch/light to the HEADSET position. (10) Select the observer/jump seat MIC SEL switch/light to the HEADSET position. F. Put the Airplane Back to its Initial Condition. (1) Remove all aviation headsets from the airplane. (2) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

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OBSERVER SEAT AUDIO PANEL - REMOVAL/INSTALLATION

1. General A. This section gives the removal and installation procedures for the optional observer seat audio panel. For a general description of the observer seat audio panel, refer to Chapter 23, Digital Audio System - Description and Operation.

2. Tools and Equipment

3. Setup A. Prepare the Airplane for the Observer Seat Audio Panel Removal. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Disengage the circuit breaker given in Table 401.

Table 401. Circuit Breakers

Circuit Breaker Name Circuit Breaker Location AUDIO 1 AUX Left Circuit Breaker Panel (3) Open the left forward jump seat closet to get access to the observer seat audio panel. (4) Remove the adjustable shelf to get access to the observer seat audio panel. (5) Remove the goggle panel to get access to the observer seat audio panel. (6) Remove the access panel on the back (outboard) of the left forward jump seat closet to get access to the observer seat audio panel.

4. Observer Seat Audio Panel Removal A. Remove the Observer Seat Audio Panel. (1) Disconnect the electrical connector (PC2157) from the observer seat audio panel. (2) Remove the screws that attach the observer seat audio panel to the switch bracket. (3) Remove the observer seat audio panel.

5. Observer Seat Audio Panel Installation A. Install the Observer Seat Audio Panel. (1) Put the observer seat audio panel in its position at the switch bracket. (a) Install the screws. (2) Connect the electrical connector (PC2157) to the observer seat audio panel.

6. Observer Seat Audio Panel Post-Maintenance Checks A. Do the Observer Seat Audio Panel Post-Maintenance Checks. (1) Engage the circuit breaker given in Table 401. (2) Do the Observer Seat Audio Panel Operational Check. Refer to Chapter 23, Digital Audio System - Adjustment/Test.

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7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Install the access panel on the back (outboard) of the left forward jump seat closet. (2) Install the goggle panel. (3) Install the adjustable shelf. (4) Close the left forward jump seat closet.

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CONTROL WHEEL ASSEMBLY - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and the operation of the control wheel assembly. The line replaceable units (LRU's) in the control wheel assembly are the control wheel and the control wheel force sensor. B. Refer to Figure 1 for a general view of the control wheel assembly.

2. Description A. Control Wheel (1) The pilot's and the copilot's control wheel assemblies are installed on the control column assemblies and the wheel adapters. The control wheel switches, control wheel caps, and face pads (with clip assembly) are installed on the control wheel. The control wheel assembly controls the movement of the ailerons and the roll spoilers. (2) There are four control wheel switches installed on the pilot's and the copilot's control wheel assemblies. The switches are the pitch trim switch, microphone/interphone push to talk (PTT) switch, transponder identification switch (XPDR IDNT), MASTER DISCONNECT switch, and control wheel steering switch (CWS) (airplanes -0033 and On). The MASTER DISCONNECT, pitch trim, and microphone/interphone switches are installed on the outboard part of the control wheel assembly. The XPDR IDNT switch is installed on the inboard part of the control wheel assembly. (a) For a general description of the pitch trim switch, refer to Chapter 27, Horizontal Stabilizer Control System - Description and Operation. (b) For a general description of the microphone/interphone PTT switch, refer to Chapter 23, Digital Audio System - Description and Operation. (c) For a general description of the XPDR IDNT switch, refer to Chapter 34, Garmin GTX 3000 Transponder System - Description and Operation. (d) For a general description of the MASTER DISCONNECT switch and the CWS switch (airplanes -0033 and On), refer to Chapter 22, Garmin Automatic Flight Control System (AFCS) - Description and Operation. B. Control Wheel Force Sensor (1) The left and the right control wheel force sensors are installed between the control wheel and the control columns. The control wheel force sensors are attached to the control column and the sector hub with screws. The sensors monitor the force applied to the control column and the control wheel. The sensors also supply control wheel force data to the avionics for use by the optional flight data recorder and the automatic flight control system (AFCS).

3. Operation A. Control Wheel Assembly (1) When you turn the control wheels to the left (counterclockwise), the right aileron, which will turn down, and the left aileron, which will turn up, will cause left roll of the airplane. When you turn the control wheels to the right (clockwise), the opposite occurs. For a general description of the aileron control system, refer to Chapter 27, Aileron Control System - Description and Operation. For a general description of the spoiler control system, refer to Chapter 27, Spoiler/Speed Brake Control System - Description and Operation.

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Control Wheel Assembly Figure 1 (Sheet 1)

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CONTROL WHEEL - REMOVAL/INSTALLATION

1. General A. This section gives the removal and installation procedures for the control wheel. For a general description of the control wheel, refer to Chapter 27, Control Wheel - Description and Operation.

2. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 27, Flight Controls - General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List. A. Tools and Equipment • None. B. Special Consumables • None. C. Reference Material • Chapter 22, MASTER DISCONNECT Switch - Removal/Installation • Chapter 22, Control Wheel Steering Switch - Removal/Installation • Chapter 23, VHF Communication System - Adjustment/Test • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 25, Flight Crew Seat - Removal and Installation • Chapter 27, Horizontal Stabilizer Trim Control System - Adjustment/Test • Chapter 34, Garmin GTX 3000 Transponder System - Inspection/Check • Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices • Model 700 Interior Maintenance Manual and Illustrated Parts Catalog.

3. Setup A. Prepare the Airplane for the Control Wheel Removal. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) If necessary, remove the pilot's or the copilot's flight crew seats to get access to the applicable control wheel. Refer to Chapter 25, Flight Crew Seat - Removal and Installation. (3) Remove the control wheel pad from the applicable control wheel. Refer to the Model 700 Interior Maintenance Manual and Illustrated Parts Catalog. (4) Disengage the circuit breakers given in Table 401.

Table 401. Circuit Breakers

Circuit Breaker Name Circuit Breaker Location AFCS CTRL Left Circuit Breaker Panel AUDIO 1 Left Circuit Breaker Panel RUDDER TRIM Left Circuit Breaker Panel XPDR 1 Left Circuit Breaker Panel AUDIO 2 Right Circuit Breaker Panel XPDR 2 Right Circuit Breaker Panel HZ162 PRI STAB TRIM PWR A Left DC Power J-Box HZ012 PRI/SEC STAB TRIM PWR B Right Emergency J-Box

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4. Control Wheel Removal A. Remove the Control Wheel (Refer to Figure 401).

NOTE: The removal of the left and the right control wheels is typical.

(1) Disconnect the electrical connector (PXM028) from the electrical connector (JXM028). (2) Disconnect the electrical connector (PXM029) from the electrical connector (JXM029). (3) Disconnect the electrical connector (PXM030) from the electrical connector (JXM030). (4) Remove and discard the safety wire from the bolts on the control wheel. (5) Remove the bolts and the washers that attach the control wheel to the wheel adapter on the control column assembly. (6) Remove the control wheel from the airplane.

5. Control Wheel Installation A. Install the Control Wheel (Refer to Figure 401).

NOTE: The installation of the left and the right control wheels is typical.

(1) Put the control wheel in its position on the wheel adapter on the control column assembly. (a) Install the washers and the bolts. (2) Safety the bolts with the safety wire. Refer to the Citation Standard Practices Manual, Chapter 20, Safetying - Maintenance Practices. (3) Connect the electrical connector (PXM028) to the electrical connector (JXM028). (4) Connect the electrical connector (PXM029) to the electrical connector (JXM029). (5) Connect the electrical connector (PXM030) to the electrical connector (JXM030).

6. Control Wheel Post-Maintenance Checks A. Do the Control Wheel Post-Maintenance Checks. (1) Engage the circuit breakers given in Table 401. (2) For the pitch trim switch, do the Primary Trim Operational Check. Refer to Chapter 27, Horizontal Stabilizer Trim Control System - Adjustment/Test. (3) For the microphone/interphone push to talk (PTT) switch, do the GIA COM 1 and COM 2 Audio Transmission and Antenna Operational Check. Refer to Chapter 23, VHF Communication System - Adjustment/Test. (4) For the XPDR IDNT switch, do the XPDR IDNT Switch Operational Check. Refer to Chapter 34, Garmin GTX 3000 Transponder System - Inspection/Check. (5) For the MASTER DISCONNECT switch, do the MASTER DISCONNECT Switch Post- Maintenance Checks. Refer to Chapter 22, MASTER DISCONNECT Switch - Removal/ Installation. (6) For airplanes -0033 and On and the CWS switch, do the CWS Switch Post-Maintenance Checks. Refer to Chapter 22, Control Wheel Steering Switch - Removal/Installation.

7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Install the control wheel pad on the control wheel. Refer to the Model 700 Interior Maintenance Manual and Illustrated Parts Catalog. (2) If necessary, install the pilot's or the copilot's flight crew seats. Chapter 25, Flight Crew Seat- Removal and Installation.

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Control Wheel Installation Figure 401 (Sheet 1)

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FUEL - TROUBLESHOOTING

1. General A. This section also lists all central maintenance computer (CMC) event driven fault messages that are related to the fuel system as well as descriptions and related data to help in troubleshooting. For more data on the Central Diagnostic Maintenance System, refer to Chapter 45, CMC Viewer - Description and Operation.

2. Use of CMC Event Driven Fault Message for Troubleshooting A. General Overview of Information. (1) A brief description of how the troubleshooting data is structured and presented is as follows: (a) The CMC Alert ID number is a unique identifier given to each CMC event driven fault message. 1 Event Driven Fault Message is the text identifier associated with the specified CMC Alert ID number. a Serial Effectivity is the applicable serial range for that specified CMC Alert ID number. b Type and Color gives the type of CMC event driven fault message and the color of the text as follows: advisory (white), caution (amber), warning (red), non-CAS initiated (blue). c Maintenance Inhibit is applicable to most of the CMC event driven fault messages to prevent fault logging unless specified conditions are met. To Inhibit Logging During Ground Operations, refer to Chapter 45, CMC Logs Folder Management and Transmit - Maintenance Practices. • "None" means that fault recording is active while airplane power is on • "Standard" inhibit prevents fault recording unless at least one engine is running and the parking brake is released. d Indicated Cause is a summary of the CMC event driven fault message and gives a probable cause. e Additional Description gives the logic and the conditions that contribute to the CMC event driven fault message. f Troubleshooting (as available) gives more detailed system data to help in troubleshooting. B. General Notes on Troubleshooting. (1) It is important for the technician to think about all potential contributing factors to a CMC event driven fault message. These potential contributing factors can include: • Electrical faults that can include opens, shorts, high impedance, and ground and shielding issues • Electrical connector faults that can include pushed back pins or FOD contamination • LRU or sensor rigging • Sensor faults that give a false positive or false negative signal • Transient environmental conditions (condensation or temperature). (2) For more data on electrical wiring, refer to the Model 700 Wiring Diagram Manual. (3) For more data on troubleshooting, refer to the Garmin G5000 Integrated Avionics System Line Maintenance Manual. Refer to the Introduction - Supplier Publication List.

3. Event Driven Fault Messages A. CMC Alert ID 1100. (1) Event Driven Fault Message: FUEL INLET COLD L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: Standard. (d) Indicated Cause. 1 LH FADEC indicates the Fuel Temp is out of range. (e) Additional Description. 1 This fault is triggered when the LH FADEC senses the Fuel Temp is out of range.

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B. CMC Alert ID 1101. (1) Event Driven Fault Message: FUEL INLET COLD R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: Standard. (d) Indicated Cause. 1 RH FADEC indicates the Fuel Temp is out of range. (e) Additional Description. 1 This fault is triggered when the RH FADEC senses the Fuel Temp is out of range. C. CMC Alert ID 1102. (1) Event Driven Fault Message: FUEL LEVEL LOW L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: Standard. (d) Indicated Cause. 1 FLCU indicates LH Fuel Level is low. (e) Additional Description. 1 This fault is triggered when the Fuel Level Control Unit (FLCU) input to GEA3 indicates the LH Fuel Level has been low for more than 90 seconds. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a left low fuel level signal from the FLCU (UY003) through pin 81PT408. D. CMC Alert ID 1103. (1) Event Driven Fault Message: FUEL LEVEL LOW T. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: Standard. (d) Indicated Cause. 1 FLCU indicates RH Fuel Level is low. (e) Additional Description. 1 This fault is triggered when the Fuel Level Control Unit (FLCU) input to GEA3 indicates the RH Fuel Level has been low for more than 90 seconds. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a right low fuel level signal from the FLCU (UY003) through pin 26PT408. E. CMC Alert ID 1104. (1) Event Driven Fault Message: FUEL PRESS LOW L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH FADEC indicates Low Fuel Pressure. (e) Additional Description. 1 This fault is triggered when FADEC MCID 101 is active on either CH A or CH B. Refer to the Detail Parameters for individual Channel Fault status. Refer to the Honeywell Engine Maintenance Manual for further direction on this fault. (f) Troubleshooting. 1 The left Fuel Control PCB (FUEL CONTROL, DC power J-Box) (NZ116) receives a low fuel pressure signal from the left FADEC Interface PCB (FADEC INT, DC power J-Box) (NZ104) through pin 54JZ116. F. CMC Alert ID 1105. (1) Event Driven Fault Message: FUEL PRESS LOW R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None.

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(d) Indicated Cause. 1 RH FADEC indicates Low Fuel Pressure. (e) Additional Description. 1 This fault is triggered when FADEC MCID 101 is active on either CH A or CH B. Refer to the Detail Parameters for individual Channel Fault status. Refer to the Honeywell Engine Maintenance Manual for further direction on this fault. (f) Troubleshooting. 1 The right Fuel Control PCB (FUEL CONTROL, DC power J-Box) (NZ116) receives a low fuel pressure signal from the right FADEC Interface PCB (FADEC INT, DC power J-Box) (NZ204) through pin 54JZ216. G. CMC Alert ID 1120. (1) Event Driven Fault Message: FUEL QTY FAIL L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH Fuel Qty data invalid or stale. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Total Fuel Qty data on Label 201 is stale or invalid on both channels. 2 On Airplanes with Garmin G5000 Software Version 58 and higher, this fault is also triggered when CH 1 and CH 2 Left Wing Fuel Qty data on Label 201 miscompares by 100 pounds or more for 5 seconds. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO). H. CMC Alert ID 1121. (1) Event Driven Fault Message: FUEL QTY FAIL R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH Fuel Qty data invalid or stale. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Total Fuel Qty data on Label 203 is stale or invalid on both channels. 2 On Airplanes with Garmin G5000 Software Version 58 and higher, this fault is also triggered when CH 1 and CH 2 Right Wing Fuel Qty data on Label 203 miscompares by 100 pounds or more for 5 seconds. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD3 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). I. CMC Alert ID 1122. (1) Event Driven Fault Message: FUEL QTY FAULT 1. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH FQGC Label 276 Invalid. (e) Additional Description. 1 This fault is triggered when LH Fuel Qty data Label 276 is stale or invalid.

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(f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO). J. CMC Alert ID 1123. (1) Event Driven Fault Message: FUEL QTY FAULT 2. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH FQGC Label 276 Invalid. (e) Additional Description. 1 This fault is triggered when RH Fuel Qty data Label 276 is stale or invalid. (f) Troubleshooting. 1 The FQGC supplies ARINC 429 data to GSD3 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). K. CMC Alert ID 1124. (1) Event Driven Fault Message: FUEL FW S/O FAIL L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH FW S/O Valve indicates both Open and Closed. (e) Additional Description. 1 This fault is triggered when the LH Fuel Firewall Shutoff Valve Open and Closed inputs to GSD2 indicate the valve is both Open and Closed at the same time. (f) Troubleshooting. 1 The GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) receives a 28v / Open signal through pins 42PT413 (OPEN) and 60PT413 (CLOSED). L. CMC Alert ID 1125. (1) Event Driven Fault Message: FUEL FW S/O FAIL R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH FW S/O Valve indicates both Open and Closed. (e) Additional Description. 1 This fault is triggered when the RH Fuel Firewall Shutoff Valve Open and Closed inputs to GSD3 and GEA3 indicate the valve is both Open and Closed at the same time. (f) Troubleshooting. 1 The GSD3 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT402) receives a 28v / Open signal through pin 60PT414 (OPEN) and the GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a 28V / Open signal through pin 48PT410 (CLOSED). M. CMC Alert ID 1126. (1) Event Driven Fault Message: FUEL FW S/O FAIL L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH FW S/O Valve indicates neither Open or Closed.

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(e) Additional Description. 1 This fault is triggered when the LH Fuel Firewall Shutoff Valve Open and Closed inputs to GSD2 indicate the valve is not Open or Closed. (f) Troubleshooting. 1 The GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) receives a 28v / Open signal through pins 42PT413 (OPEN) and 60PT413 (CLOSED). N. CMC Alert ID 1127. (1) Event Driven Fault Message: FUEL FW S/O FAIL R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH FW S/O Valve indicates neither Open or Closed. (e) Additional Description. 1 This fault is triggered when the RH Fuel Firewall Shutoff Valve Open and Closed inputs to GSD3 and GEA3 indicate the valve is not Open or Closed. (f) Troubleshooting. 1 The GSD3 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT402) receives a 28v / Open signal through pin 60PT414 (OPEN) and the GEA3 receives a 28v / Open signal through pin 48PT410 (CLOSED). O. CMC Alert ID 1128. (1) Event Driven Fault Message: FUEL FW S/O FAIL L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH FW S/O Valve not closed with Fire SW pressed. (e) Additional Description. 1 This fault is triggered when the LH Fuel Firewall Shutoff Valve Open and Closed inputs to GSD2 indicate the valve was open when the LH Fire switch was pressed. (f) Troubleshooting. 1 The GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) receives a 28v / Open signal through pins 42PT413 (OPEN) and 60PT413 (CLOSED). P. CMC Alert ID 1129. (1) Event Driven Fault Message: FUEL FW S/O FAIL R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH FW S/O Valve not closed with Fire SW pressed. (e) Additional Description. 1 This fault is triggered when the LH Fuel Firewall Shutoff Valve Open and Closed inputs to GSD3 and GEA3 indicate the valve was open when the RH Fire switch was pressed. (f) Troubleshooting. 1 The GSD3 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT402) receives a 28v/Open signal through pin 60PT414 (OPEN) and the GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a 28v / Open signal through pin 48PT410 (CLOSED). Q. CMC Alert ID 1130. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None.

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(d) Indicated Cause. 1 LH SPR valve Closed with Gravity XFlow selected. (e) Additional Description. 1 This fault is triggered when the LH Single Point Refuel (SPR) Shutoff valve Open input to GEA2 is NOT active and the Closed input to GEA2 is active, and Gravity Crossflow was selected. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a Gnd / Open input from the left SPR (single-point refueling / defueling shutoff valve) (VL003) through pin 97PT407 (OPEN). The GEA2 receives a Gnd / Open input from the left SPR through pin 111PT407 (CLOSED). R. CMC Alert ID 1131. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH SPR valve not open with Gravity XFlow selected. (e) Additional Description. 1 This fault is triggered when the LH Single Point Refuel (SPR) Shutoff valve Open input to GEA3 is NOT active and the Closed input to GEA 3 is active, and Gravity Crossflow was selected. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open input from the right SPR (single-point refueling / defueling shutoff valve) (VR002) through pin 110PT408 (OPEN). The GEA3 receives a Gnd / Open input from the right SPR through pin 111PT408 (CLOSED). S. CMC Alert ID 1132. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH SPR valve not closed. (e) Additional Description. 1 This fault is triggered when the LH Single Point Refuel (SPR) Shutoff valve Closed input to GEA2 indicates the valve was not Closed when Gravity Crossflow was NOT selected. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a Gnd / Open input from the left SPR (single-point refueling / defueling shutoff valve) (VL003) through pin 97PT407 (OPEN). The GEA2 receives a Gnd / Open input from the left SPR through pin 111PT407 (CLOSED). T. CMC Alert ID 1133. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH SPR valve not closed. (e) Additional Description. 1 This fault is triggered when the RH Single Point Refuel (SPR) Shutoff valve Closed input to GEA3 indicates the valve was not Closed when Gravity Crossflow was NOT selected.

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(f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open input from the right SPR (single-point refueling / defueling shutoff valve) (VR002) through pin 110PT408 (OPEN). The GEA3 receives a Gnd / Open input from the right SPR through pin 111PT408 (CLOSED). U. CMC Alert ID 1134. (1) Event Driven Fault Message: FUEL GRV XFLOW ON. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH and RH SPR valves not closed. (e) Additional Description. 1 This fault is triggered when the LH and RH Single Point Refuel (SPR) Shutoff valve Closed inputs to GEA2 and GEA3 indicate the valves were not Closed when Gravity Crossflow was NOT selected. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a Gnd / Open input from the left SPR (single-point refueling / defueling shutoff valve) (VL003) through pin 111PT407 (CLOSED). The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open input from the right SPR (single-point refueling / defueling shutoff valve) (VR002) through pin 111PT408 (CLOSED). V. CMC Alert ID 1135. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH SPR valve not open or closed. (e) Additional Description. 1 This fault is triggered when the LH Single Point Refuel (SPR) Shutoff valve Open and closed inputs to GEA2 indicate the valve was NOT open or closed when Gravity Xflow was selected. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a Gnd / Open input from the left SPR (single-point refueling / defueling shutoff valve) (VL003) through pin 97PT407 (OPEN). The GEA2 receives a Gnd / Open input from the left SPR through pin 111PT407 (CLOSED). W. CMC Alert ID 1136. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH SPR valve not open or closed. (e) Additional Description. 1 This fault is triggered when the RH Single Point Refuel (SPR) Shutoff valve Open and Closed inputs to GEA3 indicate the valve was NOT open or closed when Gravity Xflow was selected. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open input from the right SPR (single-point refueling / defueling shutoff valve) (VR002) through pin 110PT408 (OPEN). The GEA3 receives a Gnd / Open input from the right SPR through pin 111PT408 (CLOSED).

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X. CMC Alert ID 1137. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH SPR valve indicates both open and closed. (e) Additional Description. 1 This fault is triggered when the LH Single Point Refuel (SPR) Shutoff valve Open and closed inputs to GEA2 both active at the same time when Gravity Xflow was selected. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a Gnd / Open input from the left SPR (single-point refueling / defueling shutoff valve) (VL003) through pin 97PT407 (OPEN). The GEA2 receives a Gnd / Open input from the left SPR through pin 111PT407 (CLOSED). Y. CMC Alert ID 1138. (1) Event Driven Fault Message: FUEL GRV XFLOW FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH SPR indicates both open and closed. (e) Additional Description. 1 This fault is triggered when the RH Single Point Refuel (SPR) Shutoff valve Open and closed inputs to GEA3 both active at the same time when Gravity Xflow was selected. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open input from the right SPR (single-point refueling / defueling shutoff valve) (VR002) through pin 110PT408 (OPEN). The GEA3 receives a Gnd / Open input from the right SPR through pin 111PT408 (CLOSED). Z. CMC Alert ID 1140. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Outer Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Outer Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AA. CMC Alert ID 1141. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Outer Probe 2 Faulted.

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(e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Outer Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AB. CMC Alert ID 1142. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Mid Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Mid Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AC. CMC Alert ID 1143. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Mid Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Mid Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AD. CMC Alert ID 1144. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Inner Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Inner Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted.

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(f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AE. CMC Alert ID 1145. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Inner Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Inner Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AF. CMC Alert ID 1146. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Inner Probe 3 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Inner Probe 3 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AG. CMC Alert ID 1147. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Comp Probe Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the Left Wing Comp Probe indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO).

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AH. CMC Alert ID 1148. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Outer Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Outer Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AI. CMC Alert ID 1149. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Outer Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Outer Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AJ. CMC Alert ID 1150. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Mid Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Mid Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AK. CMC Alert ID 1151. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None.

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(d) Indicated Cause. 1 FQGC indicates Right Wing Mid Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Mid Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AL. CMC Alert ID 1152. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Inner Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Inner Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AM. CMC Alert ID 1153. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Inner Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Inner Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AN. CMC Alert ID 1154. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Inner Probe 3 Faulted.

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(e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Inner Probe 3 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AO. CMC Alert ID 1155. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Comp Probe Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the Right Wing Comp Probe indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AP. CMC Alert ID 1156. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Center Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Center Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AQ. CMC Alert ID 1157. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Center Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Center Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted.

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(f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AR. CMC Alert ID 1158. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Center Probe 3 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Center Probe 3 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AS. CMC Alert ID 1159. (1) Event Driven Fault Message: Fuel System Fault.. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Center Probe 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Center Probe 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AT. CMC Alert ID 1160. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Center Probe 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Center Probe 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO).

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AU. CMC Alert ID 1161. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Center Probe 3 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Center Probe 3 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AV. CMC Alert ID 1162. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Tank Harness 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Tank Harness 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AW. CMC Alert ID 1163. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Left Wing Tank Harness 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Tank Harness 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AX. CMC Alert ID 1164. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None.

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(d) Indicated Cause. 1 FQGC indicates Left Wing Tank Harness 3 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Tank Harness 3 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AY. CMC Alert ID 1165. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Tank Harness 1 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Tank Harness 1 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). AZ. CMC Alert ID 1166. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Tank Harness 2 Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Right Wing Tank Harness 2 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BA. CMC Alert ID 1167. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Right Wing Tank Harness 3 Faulted.

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(e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when Left Wing Tank Harness 3 indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BB. CMC Alert ID 1170. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates RH Fuel Temp Sensor Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the RH Fuel Temp Sensor indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BC. CMC Alert ID 1171. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates LH Low Level Sensor Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the LH Low Level Sensor indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BD. CMC Alert ID 1172. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates RH Low Level Sensor Faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the RH Low Level Sensor indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted.

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(f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BE. CMC Alert ID 1173. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates Refuel/Defuel function faulted. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the Refuel/Defuel function indicates faulted on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BF. CMC Alert ID 1174. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates LH Channel is failed. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the LH Channel failure status is active on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BG. CMC Alert ID 1175. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates RH Channel is failed. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the RH Channel failure status is active on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO).

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BH. CMC Alert ID 1179. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates GSD2 data bus input is failed. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the Avionics Data bus input from GSD2 indicates failed on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. BI. CMC Alert ID 1180. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates GSD3 data bus input is failed. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the Avionics Data bus input from GSD3 indicates failed on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. BJ. CMC Alert ID 1181. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates LH Power input is failed. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the LH Power Input indicates failed on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted. (f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BK. CMC Alert ID 1182. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FQGC indicates RH Power input is failed. (e) Additional Description. 1 The Fuel Quantity Gauging Computer (FQGC) provides redundant data on L and R channels. This fault is triggered when the RH Power Input indicates failed on either channel. This fault can contribute to FUEL QTY DEGRADE, FAIL, FAULT, and Maintenance messages being posted.

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(f) Troubleshooting. 1 The FQGC (UY004) supplies ARINC 429 data to GSD2 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT401) through pins 43PT411 (HI) and 44PT411 (LO) and to GSD3 (Garmin GSD 41HE Harsh Environment DCU) (UT402) through pins 43PT412 (HI) and 44PT412 (LO). BL. CMC Alert ID 1183. (1) Event Driven Fault Message: Fuel System Fault. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Non-Cas Initiated (Blue). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 FLCU LH Fuel Tank Temp Data out of range. (e) Additional Description. 1 This fault is triggered when GSD3 senses the LH Fuel Tank Temp data on Label 300 from the Fuel Level Control Unit (FLCU) is out of range or invalid. (f) Troubleshooting. 1 The GSD3 (Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU)) (UT402) receives ARINC 429 data from the FLCU (UY003) through pins 46PT414 (HI) and 47PT414 (LO). BM. CMC Alert ID 1200. (1) Event Driven Fault Message: FUEL TRANSFER FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Both Fuel Boost Pumps indicate ON. (e) Additional Description. 1 This fault is triggered when Fuel Transfer is selected in either direction and the LH and RH Boost Pump inputs to GEA2 and GEA3 indicate both pumps are running. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a 28V signal through pin 73PT405 and ground is on pin 74PT405. The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a 28V signal through pin 75PT406 and ground is on pin 76PT406. BN. CMC Alert ID 1201. (1) Event Driven Fault Message: FUEL TRANSFER FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Fuel Boost Pumps not running. (e) Additional Description. 1 This fault is triggered when Fuel Transfer is selected in either direction and the LH and RH Boost Pump inputs to GEA2 and GEA3 indicate neither pump is running. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a 28V signal through pin 73PT405 and ground is on pin 74PT405. The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a 28V signal through pin 75PT406 and ground is on pin 76PT406. BO. CMC Alert ID 1202. (1) Event Driven Fault Message: FUEL TRANSFER FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Fuel Transfer Valve not open.

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(e) Additional Description. 1 This fault is triggered when Fuel Transfer is selected in either direction and the Fuel Transfer Valve Position input to GEA3 indicates the valve is NOT open. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open signal from the Fuel Transfer Valve (transfer valve) (VY001) through pin 119PT408. BP. CMC Alert ID 1203. (1) Event Driven Fault Message: FUEL TRANSFER FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Fuel Transfer Valve open with no Transfer CMD. (e) Additional Description. 1 This fault is triggered when Fuel Transfer is NOT selected in either direction and the Fuel Transfer Valve Position input to GEA3 indicates the valve is open. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a Gnd / Open signal from the Fuel Transfer Valve (transfer valve) (VY001) through pin 119PT408. BQ. CMC Alert ID 1204. (1) Event Driven Fault Message: FUEL TRANSFER FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 LH Boost pump ON with Left Tank Xfer Selected. (e) Additional Description. 1 This fault is triggered when Left Tank Fuel Transfer is selected and GEA2 senses the LH Boost pump is running. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a 28V signal through pin 73PT405 and ground is on pin 74PT405. BR. CMC Alert ID 1205. (1) Event Driven Fault Message: FUEL TRANSFER FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 RH Boost pump ON with Right Tank Xfer Selected. (e) Additional Description. 1 This fault is triggered when Left Tank Fuel Transfer is selected and GEA2 senses the LH Boost pump is running. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a 28V signal through pin 75PT406 and ground is on pin 76PT406. BS. CMC Alert ID 1206. (1) Event Driven Fault Message: FUEL BST PUMP FAIL L. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Low fuel press switch indicates low with pump ON.

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(e) Additional Description. 1 This fault is triggered when the LH Low Fuel Pressure switch on the boost pump outlet line indicates pressure is low and the pump should be running. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a ground from the left boost pump low fuel pressure switch (SY005) pin 12PT407 when pressure is OK. BT. CMC Alert ID 1207. (1) Event Driven Fault Message: FUEL BST PUMP FAIL R. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Low fuel press switch indicates low with pump ON. (e) Additional Description. 1 This fault is triggered when the RH Low Fuel Pressure switch on the boost pump outlet line indicates pressure is low and the pump should be running. (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a ground from the right boost pump low fuel pressure switch (SY006) pin 12PT408 when pressure is OK.

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FUEL INDICATING SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a description and the operation of the fuel indicating system. The line replaceable units (LRU's) in the fuel indicating system are the fuel probe, fluid quantity gauging computer (FQGC), fuel level control unit (FLCU), fuel sensing unit, fuel temperature sensor, fuel pressure switch, recirculation pump pressure switch, and thermometer (airplanes -0001 thru -0042). B. Refer to Figure 1 for a general view of the fuel indicating system.

2. Description A. Fuel Probe (1) There are eleven fuel probes installed in the left and the right wing fuel tanks, from FS 362.68 to FS 419.81 and CWS 67.26 to CWS 365.73. The fuel probes are a capacitance-type probe. The fuel probe installed adjacent to the fuel hopper tank acts as the fuel density compensator. The probes interface with the fluid quantity gauging computer (FQGC). B. Fluid Quantity Gauging Computer (FQGC) (1) The FQGC is installed on the aft side of the fairing frame at FS 310.50, adjacent to the fuel level control unit (FLCU). It monitors signals from the fuel probes and the right fuel temperature sensor. The FQGC sends signals to the Garmin G5000 system. C. Fuel Level Control Unit (FLCU) (1) There are two FLCU's installed on the airplane. The FLCU #1 is installed on the aft side of the fairing frame at FS 310.50, adjacent to the FQGC. The FLCU #2 is installed on the forward side of the fairing frame at FS 310.50. The FLCU #1 monitors signals from the fuel low-level #1 sensing units, fuel high-level sensing units, and left fuel temperature sensor. The FLCU #1 sends low level status and left fuel temperature data to the Garmin G5000 system for display. The FLCU #2 monitors signals from the low-level #2 fuel sensing units. D. Fuel Sensing Unit (1) There are three fuel sensing units installed in each wing fuel tank. The inboard fuel sensing units are installed on the inboard side of RIB 1 at WS 32.74. The outboard fuel sensing unit is installed on the outboard side of RIB 16 at CWS 388.74. (2) The inboard low-level #1 fuel sensing units sense a low-level fuel condition. When the wing fuel quantity is 600 pounds, +10 or -10 pounds, the amber FUEL LEVEL LOW L-R crew alerting system (CAS) message will come on. (3) The inboard low-level #2 fuel sensing units open the scavenge valves in the scavenge supply tubes at the same low fuel level as the inboard low-level #1 fuel sensing units. (4) The outboard fuel sensing unit senses a high-level condition and supplies a signal to the FLCU #1 when the wing is full of fuel. E. Fuel Temperature Sensor (1) For airplanes -0001 thru -0042, there is one fuel temperature sensor installed in each wing, on the inboard side of the rib at CWS 67.26. The left sensor sends signals to the FLCU #1. The right sensor sends signals to the FQGC. (2) For airplanes -0043 and On, there is one fuel temperature sensor installed in the left wing and two in the right wing. The left sensor and the right aft sensor are installed on the inboard side of the rib at CWS 67.26. The right forward sensor is installed adjacent to the right aft fuel temperature sensor. The left sensor sends signals to the FLCU #1. The right aft sensor sends signals to the FQGC. The right forward sensor sends signals to the FLCU #2. F. Fuel Pressure Switch (1) The left and the right fuel pressure switches are installed on the aft side of the aft spar, outboard of BL 0.00. The pressure switch has one pressure sensing port and an electrical connector.

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Fuel Indicating System Figure 1 (Sheet 1)

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Fuel Indicating System Figure 1 (Sheet 2)

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Fuel Indicating System Figure 1 (Sheet 3)

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G. Recirculation Pump Pressure Switch (1) The left and the right recirculation pump pressure switches are installed on the aft side of the aft spar, outboard of BL 0.00. The pressure switch has one pressure sensing port and an electrical connector. The pressure switch is connected to a fuel supply line and it monitors the fuel supply pressure. H. Thermometer (Airplanes -0001 thru -0042) (1) The left and the right thermometers show the fuel temperature in the wing and have face plates with a temperature range of -50 to 60°C. The thermometer face plates are installed on the aft side of the aft spar. (2) The left and the right thermometers are installed in the aft spar, outboard of BL 0.00, and in the main landing gear wheel well area.

3. Operation A. Fuel Quantity Indicating System (1) The fuel indication system supplies crew alerts, warnings, and system data for the fuel system. The fuel quantity gauging system includes capacitance-type fuel probes installed in each wing bay for precision. A fuel density compensator probe is installed external of the fuel hopper tank. Fuel probe signal conditioning is supplied by the FQGC. Fuel quantity data is sent to the Garmin G5000 system for display in the cockpit. (a) On airplanes with Garmin G5000 System Software Version 58 and higher, the FUEL QTY FAIL L-R message will be displayed if CH 1 and CH 2 signals miscompare by more than 100 pounds for over 5 seconds. For additional information, refer to Fuel - Troubleshooting. B. Fuel Temperature Indicating System (1) For airplanes -0001 thru -0042, the left wing fuel temperature sensor supplies the measured fuel temperature to the FLCU #1. The right wing fuel temperature sensor supplies the measured fuel temperature to the FQGC. The inboard fuel sensing unit will signal the FLCU when the wing fuel level has decreased to 600 pounds, +10 or -10 pounds. (2) For airplanes -0043 and On, the left wing fuel temperature sensor supplies the measured fuel temperature to the FLCU #1. The right wing aft fuel temperature sensor supplies the measured fuel temperature to the FQGC. The right wing forward fuel temperature sensor supplies the measured fuel temperature to the FLCU #2. The inboard fuel sensing unit will signal the FLCU when the wing fuel level has decreased to 600 pounds, +10 or -10 pounds. (3) On airplanes with Garmin G5000 System Software Version 58 and higher, the Amber FUEL TANK COLD L-R CAS message is enabled. This message is displayed when the fuel tank temperature sensors indicate the fuel temperature is at or below -34.6 degrees F (-37 degrees C). (4) On airplanes with Garmin G5000 System Software Version 58 and higher, the Amber FUEL TEMP MISCOMPARE CAS message is enabled. This message is displayed when the fuel tank temperature sensors indicate there is more than 9 degrees F (5 degrees C) difference in the fuel temperatures between the left and right fuel systems. C. Fuel Pressure Indicating System (1) The fuel pressure switch will operate when the fuel pressure decreases to 4.65 psi (32.06 kPa). When fuel pressure decreases to 4.65 psi (32.06 kPa), the fuel pressure switch closes and sends a signal to the related Garmin GEA 7100 Engine/Airframe Interface Unit. The switch is used as an input for the FUEL RECIRC and the FUEL SCAV CAS messages. When the fuel pressure increases to 6.4 psi (44.13 kPa), the fuel pressure switch will not operate. D. Fuel Scavenge System (1) The scavenge system operates only at low fuel levels after the inboard low-level #2 fuel sensing units open the scavenge valves in the scavenge supply tubes. The FLCU #2 interfaces with the low-level #2 fuel sensing units.

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(2) On airplanes with Garmin G5000 System Software Version 58 and higher, the fuel system self test will monitor the scavenge pressure switch and the scavenge valve position to make sure the system can open the scavenge valves when required. This will also check to make sure the pressure switch is functioning and that the Garmin G5000 system can monitor the pressure switch. (a) The self test will fail If the check indicates the boost pump is ON and the Fuel Pressure or Scavenge Pressure is low. (b) The self test will pass if both left and right Fuel Level Low sensors indicate low and both left and right Scavenge Valves indicate open during the test.

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HYDRAULIC POWER - TROUBLESHOOTING

1. General A. This section gives the troubleshooting procedures for the hydraulic power. The troubleshooting procedures for the hydraulic power include the main hydraulic system, auxiliary hydraulic system, and hydraulic indicating system. For a general description of the hydraulic power, refer to Chapter 29, Main Hydraulic System - Description and Operation, Chapter 29, Auxiliary Hydraulic System - Description and Operation, and Chapter 29, Hydraulic Indicating System - Description and Operation. B. This section lists all central maintenance computer (CMC) event driven fault messages that are related to hydraulic power as well as descriptions and related data to help in troubleshooting. For more data on the Central Diagnostic Maintenance System, refer to Chapter 45, CMC Viewer - Description and Operation.

2. Hydraulic System Troubleshooting A. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 29, Hydraulic Power - General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List.

(1) Tools and Equipment • None. (2) Special Consumables • None. (3) Reference Material • Chapter 6, Dimensions and Areas - Description and Operation • Chapter 12, Hydraulic Reservoir - Servicing • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 29, Main Hydraulic System - Adjustment/Test • Chapter 29, Engine-Driven Hydraulic Pump - Removal/Installation • Chapter 29, Engine-Driven Hydraulic Pump Discharge Filter Element - Removal/ Installation • Chapter 29, Engine-Driven Hydraulic Pump Case Drain Filter Element - Removal/ Installation • Chapter 29, Hydraulic System Return Filter Element - Removal/Installation • Chapter 29, Hydraulic Shutoff Valve - Removal/Installation • Chapter 29, Power Transfer and Conversion Unit (PTCU) - Removal/Installation • Chapter 29, Landing Gear Return Filter Element - Removal/Installation • Model 700 Wiring Diagram Manual. B. Prepare the Airplane for the Hydraulic System Troubleshooting. (1) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Open the hydraulic service door to get access to the hydraulic reservoir service panel. Refer to Chapter 6, Dimensions and Areas - Description and Operation. C. The Hydraulic System Does Not Operate. (1) Examine the hydraulic fluid level on the hydraulic reservoir volume indicator. (a) If necessary, do the Hydraulic Reservoir Servicing. Refer to Chapter 12, Hydraulic Reservoir - Servicing. (2) Examine the position of the hydraulic shutoff valves (VY011 left, VY012 right). Refer to Chapter 29, Hydraulic Shutoff Valve - Removal/Installation for access. (a) If the hydraulic shutoff valve is not fully open, do as follows: 1 Examine for unserviceable electrical wiring and repair or replace as necessary. Refer to the Model 700 Wiring Diagram Manual. 2 If necessary, replace the hydraulic shutoff valve. Refer to Chapter 29, Hydraulic Shutoff Valve - Removal/Installation.

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(b) If the hydraulic shutoff valve is closed, do as follows: 1 Make sure that the ENG FIRE switch/light is not engaged. 2 Make sure that the applicable HYDRAULICS PUMP switch is not in the SHUTOFF or the MIN position. 3 Make sure that the L HYD FW SOV and the R HYD FW SOV circuit breakers on the left and the right circuit breaker panels are engaged. 4 Examine for unserviceable electrical wiring and repair or replace as necessary. Refer to the Model 700 Wiring Diagram Manual. (3) Examine the main hydraulic system filters for contamination. Refer to Chapter 29, Engine- Driven Hydraulic Pump Discharge Filter Element - Removal/Installation, Chapter 29, Engine- Driven Hydraulic Pump Case Drain Filter Element - Removal/Installation, Chapter 29, Hydraulic System Return Filter Element - Removal/Installation, and Chapter 29, Landing Gear Return Filter Element - Removal/Installation. (a) If you find metal particles in a filter element, do as follows: 1 Replace all filter elements. Refer to Chapter 29, Engine-Driven Hydraulic Pump Discharge Filter Element - Removal/Installation, Chapter 29, Engine-Driven Hydraulic Pump Case Drain Filter Element - Removal/Installation, Chapter 29, Hydraulic System Return Filter Element - Removal/Installation, and Chapter 29, Landing Gear Return Filter Element - Removal/Installation. 2 If you find metal particles in the engine-driven hydraulic pump case drain filter element, replace the worn engine-driven hydraulic pump. Refer to Chapter 29, Engine-Driven Hydraulic Pump - Removal/Installation. 3 If you find metal particles in the engine-driven hydraulic pump discharge filter element but not in the engine-driven hydraulic pump case drain filter element, replace the worn power transfer and conversion unit (PTCU). Refer to Chapter 29, Power Transfer and Conversion Unit (PTCU) - Removal/Installation. 4 Flush the hydraulic system with clean fluid. (4) Do the Engine-Driven Hydraulic Pump Operational Check. Refer to Chapter 29, Main Hydraulic System - Adjustment/Test. (a) If necessary, replace the engine-driven hydraulic pump. Refer to Chapter 29, Engine- Driven Hydraulic Pump - Removal/Installation. (5) Examine the control valve for the applicable hydraulic system. (a) If necessary, replace the applicable control valve. D. Put the Airplane Back to its Initial Condition. (1) Close the hydraulic service door. Refer to Chapter 6, Dimensions and Areas - Description and Operation. (2) Disconnect the external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

3. Use of CMC Event Driven Fault Messages for Troubleshooting A. General Overview of Information. (1) A brief description of how the troubleshooting data is structured and presented is as follows: (a) The CMC Alert ID number is a unique identifier given to each CMC event driven fault message. 1 Event Driven Fault Message is the text identifier associated with the specified CMC Alert ID number. a Serial Effectivity is the applicable serial range for that specified CMC Alert ID number. b Type and Color gives the type of CMC event driven fault message and the color of the text as follows: advisory (white), caution (amber), warning (red), non-CAS initiated (blue). c Maintenance Inhibit is applicable to most of the CMC event driven fault messages to prevent fault logging unless specified conditions are met. To Inhibit Logging During Ground Operations, refer to Chapter 45, CMC Logs Folder Management and Transmit - Maintenance Practices. • "None" means that fault recording is active while airplane power is on

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• "Standard" inhibit prevents fault recording unless at least one engine is running and the parking brake is released. d Indicated Cause is a summary of the CMC event driven fault message and gives a probable cause. e Additional Description gives the logic and the conditions that contribute to the CMC event driven fault message. f Troubleshooting (as available) gives more detailed system data to help in troubleshooting. B. General Notes on Troubleshooting. (1) It is important for the technician to think about all potential contributing factors to a CMC event driven fault message. These potential contributing factors can include: • Electrical faults that can include opens, shorts, high impedance, and ground and shielding issues • Electrical connector faults that can include pushed back pins or FOD contamination • LRU or sensor rigging • Sensor faults that give a false positive or false negative signal • Transient environmental conditions (condensation or temperature). (2) For more data on electrical wiring, refer to the Model 700 Wiring Diagram Manual. (3) For more data on troubleshooting, refer to the Garmin G5000 Integrated Avionics System Line Maintenance Manual. Refer to the Introduction - Supplier Publication List.

4. Event Driven Fault Messages A. CMC Alert ID 1250. (1) Event Driven Fault Message: HYD O'PRESS A. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 System A pressure greater than 3350 PSI. (e) Additional Description. 1 This fault is triggered when System A Hydraulic PCB senses a pressure greater than 3350 PSI from the System A Hydraulic Manifold Pressure Transducer. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a pressure signal from the pressure transducer on the system A hydraulic manifold (hydraulic system filter manifold) (UY012) through pins 12JZ115 (TS PRSS XDUCER (-)) and 13JZ115 (TS PRSS XDUCER (+)). B. CMC Alert ID 1251. (1) Event Driven Fault Message: HYD O'PRESS B. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 System B pressure greater than 3350 PSI. (e) Additional Description. 1 This fault is triggered when System B Hydraulic PCB senses a pressure greater than 3350 PSI from the System B Hydraulic Manifold Pressure Transducer. (f) Troubleshooting. 1 The System B Hydraulic PCB (DC power J-Box) (NZ215) receives a pressure signal from the pressure transducer on the system B hydraulic manifold (hydraulic system filter manifold) (UY014) through pins 12JZ215 (TS PRSS XDUCER (-)) and 13JZ215 (TS PRSS XDUCER (+)). C. CMC Alert ID 1252. (1) Event Driven Fault Message: HYD PRESS LOW A. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber).

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(c) Maintenance Inhibit: None. (d) Indicated Cause. 1 System A pressure less than 2000 PSI. (e) Additional Description. 1 This fault is triggered when System A Hydraulic PCB senses a pressure less than 2000 PSI from the System A Hydraulic Manifold Pressure Transducer. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a pressure signal from the pressure transducer on the system A hydraulic manifold (hydraulic system filter manifold) (UY012) through pins 12JZ115 (TS PRSS XDUCER (-)) and 13JZ115 (TS PRSS XDUCER (+)). D. CMC Alert ID 1253. (1) Event Driven Fault Message: HYD PRESS LOW B. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 System B pressure less than 2000 PSI. (e) Additional Description. 1 This fault is triggered when System B Hydraulic PCB senses a pressure less than 2000 PSI from the System B Hydraulic Manifold Pressure Transducer. (f) Troubleshooting. 1 The System B Hydraulic PCB (DC power J-Box) (NZ215) receives a pressure signal from the pressure transducer on the system B hydraulic manifold (hydraulic system filter manifold) (UY014) through pins 12JZ215 (TS PRSS XDUCER (-)) and 13JZ215 (TS PRSS XDUCER (+)). E. CMC Alert ID 1254. (1) Event Driven Fault Message: HYD PUMP FAIL A. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys A Manifold Press Switch indicates low pressure. (e) Additional Description. 1 This fault is triggered when System A Hydraulic Manifold Pressure Switch input to the Sys A Hyd PCB indicates the Pump is not producing hydraulic pressure. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a signal from the pressure switch on the system A hydraulic manifold (hydraulic system filter manifold) (UY012) through pin 10JZ115. F. CMC Alert ID 1255. (1) Event Driven Fault Message: HYD PUMP FAIL B. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys B Manifold Press Switch indicates low pressure. (e) Additional Description. 1 This fault is triggered when System B Hydraulic Manifold Pressure Switch input to the Sys B Hyd PCB indicates the Pump is not producing hydraulic pressure. (f) Troubleshooting. 1 The System B Hydraulic PCB (DC power J-Box) (NZ215) receives a signal from the pressure switch on the system B hydraulic manifold (hydraulic system filter manifold) (UY014) through pin 10JZ215.

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G. CMC Alert ID 1256. (1) Event Driven Fault Message: HYD VOLUME LOW A. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys A Volume less than 100 cubic Inches. (e) Additional Description. 1 This fault is triggered when the System A Reservoir Volume Pot input to the Sys A PCB indicates Volume is less than 100 cubic inches. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a signal from the system A reservoir volume pot (LY002) through pins 35JZ115 (RES VOL HI), 7JZ115 (RES VOL WIPER), 8JZ115 (RES VOL LO), and 36JZ115 (RES VOL LO).

NOTE: Airplanes with G5000 System Software version up to 37, the hydraulic reservoir volume indicators for System A is powered via the left main bus.

NOTE: Airplanes with G5000 System Software version 58 and higher, the hydraulic reservoir volume indicators for System A is powered via the left emergency bus.

NOTE: This change in power distribution increases the functionality of the roll spoiler system. For additional electrical load distribution information, refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 24, Electrical Load Analysis - Description and Operation. H. CMC Alert ID 1257. (1) Event Driven Fault Message: HYD VOLUME LOW B. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys B Volume less than 100 cubic Inches. (e) Additional Description. 1 This fault is triggered when the System B Reservoir Volume Pot input to the Sys B PCB indicates Volume is less than 100 cubic inches. (f) Troubleshooting. 1 The System B Hydraulic PCB (DC power J-Box) (NZ215) receives a signal from the system B reservoir volume pot (LY004) through pins 35JZ215 (RES VOL HI), 7JZ215 (RES VOL WIPER), 8JZ215 (RES VOL LO), and 36JZ215 (RES VOL LO).

NOTE: Airplanes with G5000 System Software version up to 37, the hydraulic reservoir volume indicators for System B is powered via the right main bus.

NOTE: Airplanes with G5000 System Software version 58 and higher, the hydraulic reservoir volume indicators for System B is powered via the right emergency bus.

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(c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys A temp greater than 107°C. (e) Additional Description. 1 This fault is triggered when the System A Hyd Temp Mon RTD input to GEA2 is greater than 107°C (224.6°F). (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a temperature signal from the system A hyd temp mon RTD (hydraulic temperature transducer) (TY014) through pins 10PT407 (A HYD TEMPLO) and 9PT407 (A HYD TEMP HI). J. CMC Alert ID 1259. (1) Event Driven Fault Message: HYD O'TEMP B. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys B temp greater than 107°C. (e) Additional Description. 1 This fault is triggered when the System B Hyd Temp Mon RTD input to GEA3 is greater than 107°C (224.6°F). (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a temperature signal from the system B hyd temp mon RTD (hydraulic temperature transducer) (TY016) through pins 10PT410 (B HYD TEMP LO) and 9PT410 (B HYD TEMP HI). K. CMC Alert ID 1260. (1) Event Driven Fault Message: HYD O'TEMP A. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Warning (Red). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys A temp greater than 135°C. (e) Additional Description. 1 This fault is triggered when the System A Hyd Temp Mon RTD input to GEA2 is greater than 135°C (275°F). (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a temperature signal from the system A hyd temp mon RTD (hydraulic temperature transducer) (TY014) through pins 10PT407 (A HYD TEMPLO) and 9PT407 (A HYD TEMP HI). L. CMC Alert ID 1261. (1) Event Driven Fault Message: HYD O'TEMP B. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Warning (Red). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Sys B temp greater than 135°C. (e) Additional Description. 1 This fault is triggered when the System B Hyd Temp Mon RTD input to GEA3 is greater than 135°C (275°F). (f) Troubleshooting. 1 The GEA3 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT404) receives a temperature signal from the system B hyd Temp mon RTD (hydraulic temperature transducer) (TY016) through pins 10PT410 (LO) and 9PT410 (HI).

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M. CMC Alert ID 1270. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 GSD1 not receiving valid data from PTCU Controller. (e) Additional Description. 1 This fault is triggered when GSD1 indicates Label 270 from the PTCU controller is Invalid or Stale. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). N. CMC Alert ID 1271. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU senses Hyd Pressure output is low. (e) Additional Description. 1 This fault is triggered when either of the system A or B pressure input to the PTCU controller indicate system pressure is low. (f) Troubleshooting. 1 The PTCU controller (UY009) receives pressure reference through pins CPY059 (PSI_A_REF), DPY059 (PSI_A_REF), RPY059 (PSI_B_REF), and PPY059 (PSI_B_REF). O. CMC Alert ID 1272. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Over Voltage Detected. (e) Additional Description. 1 This fault is triggered when the PTCU controller senses the voltage output is greater than xxvdc. The fault will latch until power is cycled. (f) Troubleshooting. 1 The PTCU controller (UY009) senses voltage through pins TPY059 (FOR_CUR_SNS-) and SPY059 (FOR_CUR_SNS+). P. CMC Alert ID 1273. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Over Current Detected. (e) Additional Description. 1 This fault is triggered when the PTCU controller senses the current limit threshold has been exceeded. The current limit thresholds change with Over Temp conditions and also drive the GEN LOAD HYD message active. (f) Troubleshooting. 1 The PTCU controller (UY009) senses voltage through pins TPY059 (FOR_CUR_SNS-) and SPY059 (FOR_CUR_SNS+).

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Q. CMC Alert ID 1274. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Temp greater than 90°C. (e) Additional Description. 1 This fault is triggered when the PTCU controller senses the temperature is greater than 90°C (194°F). (f) Troubleshooting. 1 The PTCU controller (UY009) supplies a ground through pin LPY059 when active. R. CMC Alert ID 1275. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Vicor A failed. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Vicor A is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). S. CMC Alert ID 1276. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Vicor B failed. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Vicor B is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). T. CMC Alert ID 1277. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Logic Voltage out of range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the motor current is less than 88 amps during the resolver rigging process. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). U. CMC Alert ID 1278. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber).

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(c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Field Connection Open. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Field Connection is open. (f) Troubleshooting. 1 The PTCU controller (UY009) uses Power Ground as a reference. V. CMC Alert ID 1279. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Over Voltage Monitor failed. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Over Voltage Monitor is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). W. CMC Alert ID 1280. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Clutch A Open. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch A is Open. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). X. CMC Alert ID 1281. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Clutch B Open. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch B is Open. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). Y. CMC Alert ID 1282. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Clutch A Driver Fail.

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(e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch A Driver is Failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). Z. CMC Alert ID 1283. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Clutch B Driver Fail. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch B Driver is Failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AA. CMC Alert ID 1284. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU System A pressure out of range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the signal being received from the System A Hydraulic Manifold Pressure Sensor is invalid. (f) Troubleshooting. 1 The PTCU controller (UY009) receives pressure reference through pins CPY059 (PSI_A_REF), DPY059 (PSI_A_REF), RPY059 (PSI_B_REF), and PPY059 (PSI_B_REF). AB. CMC Alert ID 1285. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU System B pressure out of range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the signal being received from the System B Hydraulic Manifold Pressure Sensor is invalid. (f) Troubleshooting. 1 The PTCU controller (UY009) receives pressure reference through pins CPY059 (PSI_A_REF), DPY059 (PSI_A_REF), RPY059 (PSI_B_REF), and PPY059 (PSI_B_REF). AC. CMC Alert ID 1286. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Resolver Failed. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the resolver is failed.

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(f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AD. CMC Alert ID 1287. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Motor RTD A Out of Range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Motor RTD A Out of Range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AE. CMC Alert ID 1288. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Controller RTD A Out of Range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates RTD A Out of Range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AF. CMC Alert ID 1289. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Controller RTD A Out of Range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates RTD A Out of Range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AG. CMC Alert ID 1290. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Controller RTD B Out of Range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates RTD B Out of Range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)).

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AH. CMC Alert ID 1291. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Vicor A Voltage Fail. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Vicor A Voltage Failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AI. CMC Alert ID 1292. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Vicor B Voltage Fail. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Vicor B Voltage Failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AJ. CMC Alert ID 1293. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Air Valve Connection Open. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Air Valve Connection is Open. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AK. CMC Alert ID 1294. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU FET Fail Phase A HI. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates FET Phase A HI is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AL. CMC Alert ID 1295. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On.

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(b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU FET Fail Phase A Lo. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates FET Phase A Lo is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AM. CMC Alert ID 1296. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU FET Fail Phase B HI. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates FET Phase B HI is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AN. CMC Alert ID 1297. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU FET Fail Phase B Lo. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates FET Phase B Lo is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AO. CMC Alert ID 1298. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU FET Fail Phase C HI. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates FET Phase C HI is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AP. CMC Alert ID 1299. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU FET Fail Phase C Lo.

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(e) Additional Description. 1 This fault is triggered when the PTCU controller indicates FET Phase C Lo is failed. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AQ. CMC Alert ID 1300. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Advisory (White). (c) Maintenance Inhibit: Standard. (d) Indicated Cause. 1 PTCU O'Temp in Aux Mode. (e) Additional Description. 1 This fault is triggered when the PTCU Generator is operating in either Aux Mode A or B and an Overtemp condition required it to shut off. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AR. CMC Alert ID 1301. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU motor current. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the motor current is less than 88 amps during the resolver rigging process. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AS. CMC Alert ID 1302. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Motor current. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the motor current is less than 5 amps during the resolver rigging process, or less than 1 amp while operating in Gen mode. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AT. CMC Alert ID 1303. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Internal fault with PTCU Hi side Field Driver.

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(e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the internal IC Drive for the Hi Side Field is faulted. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AU. CMC Alert ID 1304. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Internal fault with PTCU Lo side Field Driver. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the internal IC Drive for the Lo Side Field is faulted. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AV. CMC Alert ID 1305. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Generator RPM. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates generator RPM is less than the 2500 RPM threshold needed to generate voltage. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AW. CMC Alert ID 1306. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Clutch slipping in PTCU mode. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch slippage because the motor RPM was greater than 5000 RPM for 20 seconds when operating in PTCU mode. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AX. CMC Alert ID 1307. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None.

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(d) Indicated Cause. 1 PTCU Clutch A not locked. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch A is not locked because motor RPM was less than 50 at completion of the Wiggle task. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AY. CMC Alert ID 1308. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Clutch B not locked. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Clutch B is not locked because motor RPM was less than 50 at completion of the Wiggle task. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). AZ. CMC Alert ID 1309. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU 28 volt Bus Current fault. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Bus current is out of range or there is a mismatch between the Bus current and Aircraft current shunt indication. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BA. CMC Alert ID 1310. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Phase A current sensor out of range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Phase A current sensor is out range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BB. CMC Alert ID 1311. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber).

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(c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Phase B current sensor out of range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Phase B current sensor is out range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BC. CMC Alert ID 1312. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Phase C current sensor out of range. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Phase C current sensor is out range. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BD. CMC Alert ID 1313. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Aircraft Current shunt fault. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Aircraft Shunt current is out of range or there is a mismatch between the Aircraft current and the 28 volt Bus current shunt indication. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BE. CMC Alert ID 1314. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Bus relay not closed when commanded. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Bus Relay is not closed when commanded. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BF. CMC Alert ID 1315. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On.

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(b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Internal PWM signal Emer Stop fault. (e) Additional Description. 1 This fault is triggered when the PTCU controller stops all PWM output to control the motor because of an internal system fault. This fault may be caused by generator over voltage, over temp, or power supply faults. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BG. CMC Alert ID 1316. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Bus Current >500 amps. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Bus Current is greater than 500 amps. This fault is latched until power is cycled. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BH. CMC Alert ID 1317. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Bus voltage >50. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates the Bus Voltage is greater than 50 volts. This fault is latched until power is cycled. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BI. CMC Alert ID 1318. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU resover rigging failed. (e) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BJ. CMC Alert ID 1319. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None.

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(d) Indicated Cause. 1 PTCU Rotor Overtemp. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates a Rotor Overtemp. This fault is latched until power is cycled. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BK. CMC Alert ID 1320. (1) Event Driven Fault Message: PTCU FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 PTCU Internal Bus Relay Driver Fault. (e) Additional Description. 1 This fault is triggered when the PTCU controller indicates Bus Relay Driver should be commanding the Relay open, but the monitored driver output is not active. (f) Troubleshooting. 1 The GSD1 (Garmin GSD 41 Data Concentrator Unit (DCU)) (UI410) receives ARINC 429 data from the PTCU controller (UY009) through pins 62PI411 (PTCU CTRL (A429 IN HI)) and 63PI411 (PTCU CTRL (A429 IN LO)). BL. CMC Alert ID 1390. (1) Event Driven Fault Message: RUDDER STBY O'TEMP. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Rudder Standby Fluid Over Temp. (e) Additional Description. 1 This fault is triggered when the Rudder Standby System Fluid Temperature Switch input GIA1 indicates over temp. (f) Troubleshooting. 1 The GIA1 (Garmin GIA 64E Integrated Avionics Unit) (UI301) receives a Gnd / Open input signal through pin 42PI305. Open shows an overheated condition. BM. CMC Alert ID 1391. (1) Event Driven Fault Message: RUDDER STBY O'TEMP. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Rudder Standby Motor Over Temp. (e) Additional Description. 1 This fault is triggered when the Rudder Standby System Motor Temperature Switch input GEA2 indicates over temp. (f) Troubleshooting. 1 The GEA2 (Garmin GEA 7100 Engine/Airframe Interface Unit) (UT403) receives a Gnd / Open input signal through pin 4PT407. Open shows an overheated condition. BN. CMC Alert ID 1392. (1) Event Driven Fault Message: RUDDER STBY FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Rudder Standby Reservoir Level Low.

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(e) Additional Description. 1 This fault is triggered when the Rudder Standby System Reservoir Level Switch input to the Sys A Hyd PCB indicates the level is low. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a Gnd / Open input signal through pin 56JZ115. Open shows a low level condition. BO. CMC Alert ID 1393. (1) Event Driven Fault Message: RUDDER STBY FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Rudder Standby Pressure Low. (e) Additional Description. 1 This fault is triggered when the Rudder Standby System Pressure Switch input to the Sys A Hyd PCB indicates pressure is low. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a Gnd / Open input signal through pin 50JZ115. Open shows a low pressure condition. BP. CMC Alert ID 1394. (1) Event Driven Fault Message: RUDDER STBY FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Rudder Standby Selector Valve failed OFF. (e) Additional Description. 1 This fault is triggered when the Rudder Standby System Selector Valve Position Switch input to the Sys A Hyd PCB indicates the valve is failed in the OFF position. (f) Troubleshooting. 1 The System A Hydraulic PCB (DC power J-Box) (NZ115) receives a Gnd / Open input signal through pin 51JZ115. Open shows an off condition. BQ. CMC Alert ID 1395. (1) Event Driven Fault Message: RUDDER STBY FAIL. (a) Serial Effectivity: Airplanes -0001 and On. (b) Type and Color: Caution (Amber). (c) Maintenance Inhibit: None. (d) Indicated Cause. 1 Rudder Standby Selector Valve failed ON. (e) Additional Description. 1 This fault is triggered when the Rudder Standby System Selector Valve Position Switch input to the Sys A Hyd PCB indicates the valve is failed in the ON position.

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MAIN HYDRAULIC SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a description and the operation of the main hydraulic system. (1) For Airplanes -0001 thru -0016 and -0018 thru -0021, the line replaceable units (LRU's) in the main hydraulic system are the left engine hydraulic hose, right engine hydraulic hose, engine-driven hydraulic pump, engine-driven hydraulic pump discharge filter element, engine-driven hydraulic pump case drain filter element, HYDRAULICS PUMP switch, tailcone shroud, empennage shroud, hydraulic system accumulator, hydraulic fluid heat exchanger, hydraulic reservoir volume indicator, hydraulic reservoir, hydraulic reservoir relief cable, hydraulic reservoir ecology bottle, hydraulic reservoir servicing coupling, hydraulic reservoir servicing check valve, hydraulic system filter manifold, hydraulic system return filter element, hydraulic shutoff valve, hydraulic priority valve, hydraulic reservoir return check valve, hydraulic return check valve, power transfer unit (PTU), PTCU rotary switch, PTCU ventilation valve, landing gear return filter assembly, and landing gear return filter element. (2) For Airplanes -0017 and -0022 and On, the line replaceable units (LRU's) in the main hydraulic system are the left engine hydraulic hose, right engine hydraulic hose, engine-driven hydraulic pump, engine-driven hydraulic pump discharge filter element, engine-driven hydraulic pump case drain filter element, HYDRAULICS PUMP switch, tailcone shroud, empennage shroud, hydraulic system accumulator, hydraulic fluid heat exchanger, hydraulic reservoir volume indicator, hydraulic reservoir, hydraulic reservoir relief cable, hydraulic reservoir ecology bottle, hydraulic reservoir servicing coupling, hydraulic reservoir servicing check valve, hydraulic system filter manifold, hydraulic system return filter element, hydraulic shutoff valve, hydraulic priority valve, hydraulic reservoir return check valve, hydraulic return check valve, power transfer and conversion unit (PTCU), breather desiccator, PTCU rotary switch, PTCU ventilation valve, landing gear return filter assembly, and landing gear return filter element. (3) For the left engine hydraulic hose and the right engine hydraulic hose, refer to the GKN Aircraft Maintenance Manual (AMM) for the Engine Nacelle. B. Refer to Figure 1 for a general view of the main hydraulic system.

2. Description A. Engine-Driven Hydraulic Pump (1) There is a System A and a System B engine-driven hydraulic pump installed on the airplane. The engine-driven hydraulic pumps are installed on the bottom of the left and the right engines. They are attached to the forward side of the accessory gearbox to a quick attach detach (QAD) mount and hydraulic hoses. (2) The engine-driven hydraulic pump is a variable-displacement, pressure-compensated, axial piston type hydraulic pump that can supply 3000 psi, +50 or -50 psi and 19.6 gallons-per-minute at 6000 revolutions-per-minute to the related system. It has an integral pressure pulsation damper on the pressure discharge of the pump. It has a spherical fitting used to damp any pressure fluctuations. B. Engine-Driven Hydraulic Pump Discharge Filter Element (1) There is a System A and a System B engine-driven hydraulic pump discharge filter element installed on the airplane. The engine-driven hydraulic pump discharge filter elements are installed on the right side of the aft fairing. They are attached to the filter bowl and the hydraulic system filter manifold. (2) The engine-driven hydraulic pump discharge filter element is a non-cleanable, 5 micron filter that removes contamination from the hydraulic fluid of the engine-driven hydraulic pump discharge. The filter has a minimum dirt retaining capacity of 5.2 grams. C. Engine-Driven Hydraulic Pump Case Drain Filter Element (1) There is a System A and a System B engine-driven hydraulic pump case drain filter element installed on the airplane. The engine-driven hydraulic pump case drain filter elements are installed on the right side of the aft fairing. They are attached to the filter bowl and the hydraulic system filter manifold.

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Main Hydraulic System Figure 1 (Sheet 1)

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Main Hydraulic System Figure 1 (Sheet 2)

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Main Hydraulic System Figure 1 (Sheet 3)

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Main Hydraulic System Figure 1 (Sheet 4)

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(2) The engine-driven hydraulic pump case drain filter element is a non-cleanable, 5 micron filter that removes contamination from the hydraulic fluid of the engine-driven hydraulic pump case drain. The filter has a minimum dirt retaining capacity of 1.6 grams. D. HYDRAULICS PUMP Switch (1) There is a System A and a System B HYDRAULICS PUMP switch installed on the airplane. The HYDRAULICS PUMP switches are installed on the right side of the center pedestal. They are attached to the right forward pedestal switch panel and electrical wires. (2) The HYDRAULICS PUMP switch is a three-position toggle switch with NORM, MIN, and SHUTOFF positions. E. Tailcone Shroud (1) There are three left and three right tailcone shrouds installed on the airplane. The tailcone shrouds are installed on the left and the right side of the tailcone. They are attached to the shroud base assemblies. (2) The tailcone shrouds give protection to the hydraulic tubes in the tailcone. They also help to contain hydraulic fluid leakage. F. Empennage Shroud (1) There are two empennage shrouds (top and bottom) installed on the airplane. The empennage shrouds are installed on the aft side of the vertical stabilizer. They are attached to the base plate assemblies. (2) The empennage shrouds give protection to the hydraulic tubes in the empennage. They also help to contain hydraulic fluid leakage. G. Hydraulic System Accumulator (1) There is a System A and a System B hydraulic system accumulator installed on the airplane. The hydraulic system accumulator is installed on the left and the right side of the aft fairing. They are attached to the bracket and hydraulic tube. (2) The hydraulic system accumulator is made of 15-5PH stainless steel with AM-350 stainless steel bellows. It is pre-charged with 11.26 cubic inches of Helium. H. Hydraulic Fluid Heat Exchanger (1) There is a System A and a System B hydraulic fluid heat exchanger installed on the airplane. The hydraulic fluid heat exchangers are installed on the left and the right side of the centerfuel tank. They are attached to the brackets and hydraulic tubes. (2) The hydraulic fluid heat exchanger transfers heat from the hydraulic fluid to the fuel inthewing fuel tank. I. Hydraulic Reservoir Volume Indicator (1) There is a System A and a System B hydraulic reservoir volume indicator installed on the airplane. The hydraulic reservoir volume indicators are installed on the hydraulic service panel. They are attached to the hydraulic service panel and electrical connector. (2) Airplanes with G5000 System Software version up to 37, the hydraulic reservoir volume indicators for System A and System B are powered via the left and right main bus, respectively. (3) Airplanes with G5000 System Software version 58 and higher, the hydraulic reservoir volume indicators for System A and System B are powered via the left and right emergency bus, respectively.

(4) The hydraulic reservoir volume indicators are installed on the hydraulic service panel. They are attached to the hydraulic service panel and electrical connector. (5) The hydraulic reservoir volume indicator is an electric gage that shows between 0 and 700 CUBIC INCHES.

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J. Hydraulic Reservoir (1) There is a System A and a System B hydraulic reservoir installed on the airplane. The hydraulic reservoirs are installed on the right side of the aft fairing. They are attached to the brackets, hydraulic tubes, hydraulic reservoir relief cable, electrical connector, and wiring splices. (2) The hydraulic reservoir is a 3000 psi, bootstrap, reservoir with 700 cubic inches capacity. K. Hydraulic Reservoir Relief Cable (1) There is a System A and a System B hydraulic reservoir relief cable installed on the airplane. The hydraulic reservoir relief cables are installed on the left and the right side of the aft fairing. They are attached to the hydraulic service panel, hydraulic reservoir, and aft fairing structure. (2) The hydraulic reservoir relief cable is a push/pull control rod with a brass guide tube. L. Hydraulic Reservoir Ecology Bottle (1) There is a System A and a System B hydraulic reservoir ecology bottle installed on the airplane. The hydraulic reservoir ecology bottles are installed on the right side of the aft fairing. They are attached to the adapter. (2) The hydraulic reservoir ecology bottle is a translucent, low-density, polyethylene container that can hold 0.25 ounce (7.4 ml). M. Hydraulic Reservoir Servicing Coupling (1) There are two System A (pressure and return) and two System B (pressure and return) hydraulic reservoir servicing couplings installed on the airplane. The hydraulic reservoir servicing couplings are installed on the hydraulic service panel. They are attached to the hydraulic service panel and the hydraulic tube. (2) The hydraulic reservoir servicing coupling is a self-sealing, quick-disconnect, bulkhead coupling. N. Hydraulic Reservoir Servicing Check Valve (1) There is a System A and a System B hydraulic reservoir servicing check valve installed on the airplane. The hydraulic reservoir servicing check valves are installed on the hydraulic service panel. They are attached to the hydraulic service panel and the hydraulic tube. (2) The hydraulic reservoir servicing check valve is used with the hand pump servicing. O. Hydraulic System Filter Manifold (1) There is a System A and a System B hydraulic system filter manifold installed on the airplane. The hydraulic reservoir system manifolds are installed on the right side of the aft fairing. They are attached to the brackets, hydraulic tubes, and electrical connectors. (2) The hydraulic system filter manifold includes the engine-driven hydraulic pump discharge filter element, engine-driven hydraulic pump case drain filter element, hydraulic system return filter element, bypass valve, pressure transducer, temperature transducer, and pressure switch. P. Hydraulic System Return Filter Element (1) There is a System A and a System B hydraulic system return filter element installed on the airplane. The hydraulic system return filter elements are installed on the right side oftheaft fairing. They are attached to the filter bowl and the hydraulic system filter manifold. (2) The hydraulic system return filter element is a non-cleanable, 5 micron filter that removes contamination from the hydraulic reservoir return fluid. The filter has a minimum dirt retaining capacity of 7.4 grams. Q. Hydraulic Shutoff Valve (1) There is a System A and a System B hydraulic shutoff valve installed on the airplane. The hydraulic shutoff valves are installed on the left and the right side of the aft fairing. They are attached to the bracket, hydraulic tubes, and electrical connector. (2) The hydraulic shutoff valve is a 28 VDC, motor-operated shutoff valve. R. Hydraulic Priority Valve (1) There is one hydraulic priority valve installed on the airplane. The hydraulic priority valve is installed on the left side of the aft fairing. It is attached to the bracket and the hydraulic tubes. (2) The hydraulic priority valve rated flow is 8.4 gallons-per-minute at 2450 psi maximum fullflow pressure.

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S. Hydraulic Reservoir Return Check Valve (1) There is one System A and three System B hydraulic reservoir return check valves installed on the airplane. The hydraulic reservoir return check valves are installed on the left and the right side of the fairing, forward of the main landing gear wheel well. They are attached to the hydraulic tubes. (2) The hydraulic reservoir return check valve rated flow is 3.5 gallons-per-minute at 15 psi maximum differential pressure. T. Hydraulic Return Check Valve (1) There is a System A and a System B hydraulic return check valve installed on the airplane. The hydraulic return check valves are installed on the left and the right side of the tailcone below the tailcone shroud. They are attached to the hydraulic tubes. (2) The hydraulic return check valve rated flow is 6.0 gallons-per-minute at 15 psi maximum differential pressure. U. Power Transfer Unit (PTU) (Airplanes -0001 thru -0016 and -0018 thru -0021) (1) There is one PTU installed on the airplane. The PTU is installed on the left side of the aft fairing. It is attached to the brackets, hydraulic tubes, drain tubes, cooling tube, electrical connectors, and electrical terminals. (2) The PTU includes the motor/generator assembly and two motor-controlled hydraulic pumps. V. Power Transfer and Conversion Unit (PTCU) (Airplanes -0017 and -0022 and On) (1) There is one PTCU installed on the airplane. The PTCU is installed on the left side of the aft fairing. It is attached to the brackets, hydraulic tubes, drain tubes, cooling tube, breather desiccators, electrical connectors, and electrical terminals. (2) The PTCU includes the motor/generator assembly and two motor-controlled hydraulic pumps. W. Breather Desiccator (Airplanes -0017 and -0022 and On) (1) There are two breather desiccators installed on the airplane. The breather desiccators are installed on the left side of the aft fairing. They are attached to the desiccant tube assemblies on the PTCU. (2) The breather desiccator includes 4 Angstrom molecular sieve desiccant with a color-changing humidity indicator that changes from blue to pink when it is necessary for replacement. It has an inlet and an outlet valve with cracking pressure of 1.0 psi, +0.25 or -0.25 psi (6.8 kPa, +1.7 or -1.7 kPa). The breather desiccators help prevent moisture in the PTCU. X. PTCU Rotary Switch (1) There is one PTCU rotary switch installed on the airplane. The PTCU rotary switch is installed on the right side of the center pedestal. It is attached to the right forward pedestal switch panel and electrical wires. (2) For Airplanes -0001 thru -0016 and -0018 thru -0021, the PTCU rotary switch is a single-pole, single-deck switch with OFF, SPARE, NORM, SPARE, and ON positions. (3) For Airplanes -0017 and -0022 and On, the PTCU rotary switch is a single-pole, single-deck switch with OFF, AUX A, NORM, AUX B, and HYD GEN positions. Y. PTCU Ventilation Valve (1) There is one PTCU ventilation valve installed on the airplane. The PTCU ventilation valve is installed on the left side of the aft fairing. It is attached to the PTCU duct, PTCU vent supports, and wiring splices. (2) The PTCU ventilation valve is a normally-closed, electrothermally-powered open valve. Z. Landing Gear Return Filter Assembly (1) There is one landing gear return filter assembly installed on the airplane. The landing gear return filter assembly is installed on the left side of the aft fairing. It is attached to the bracketsandthe hydraulic tubes. (2) The landing gear return filter assembly rated flow capacity is 10.5 gallons-per-minute. AA. Landing Gear Return Filter Element (1) There is one landing gear return filter element installed on the airplane. The landing gear return filter element is installed on the left side of the aft fairing. It is attached to the landing gearreturn filter assembly.

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(2) The landing gear return filter element is a bypass-able, non-cleanable, 5 micron filter that removes contamination from the landing gear return fluid. It does not have a differential pressure indicator (DPI).

3. Operation A. Main Hydraulic System (1) The main hydraulic system includes two independent hydraulic systems (System A and System B) that operate at 3000 psi (20,684 kPa). System A receives mechanical power from the left engine and System B receives mechanical power from the right engine. The two hydraulic systems supply hydraulic power to the inboard, middle, and outboard spoilers, landing gear, main landing gear brakes, thrust reversers, rudder, and nosewheel steering. The main hydraulic system operates with MIL-PRF-87257 hydraulic fluid and synthetic rubber (Nitrile) standard size O-rings. The normal operating fluid temperature range for the main hydraulic system is -40to 225°F (-40 to 107°C). The designed ambient temperature range for the system is -65 to 130°F (-53 to 54°C). The hydraulic fluid on the pressure side of the system operates at 3000 psi (20,684 kPa) through stainless steel and titanium tubing. Stainless steel tubing is used only in the main landing gear wheel wells where they are exposed to tire burst and in the engine pylons where they go through the firewall. The hydraulic fluid on the return side of the system operates at50psi (344 kPa) through titanium tubing, aluminum tubing, and stainless steel tubing in the wheel well and the engine pylons. The minimum system flow rates in the two systems at the engine-driven hydraulic pump discharge ports is 1.65 gallons-per-minute, +0.16 or -0.16 gallons-per-minute (6.24 liters, +0.61 or -0.61 liters) during normal operation. (2) The engine-driven hydraulic pumps can operate with the inlet line closed during some emergencies. The engine-driven hydraulic pump has three engine hydraulic hoses connected to it. The suction hose supplies pressurized hydraulic fluid to the engine-driven hydraulic pump at a nominal pressure of 50 psi (406 kPa) and can be closed with the hydraulic shutoff valve. The pressure hose supplies 3000 psi (20,684 kPa) hydraulic fluid to the hydraulic system filter manifold. The case drain hose returns normal internal pump leaks to the hydraulic system filter manifold after being cooled by the a plate-fin hydraulic fluid heat exchanger inthewing fuel tank. The case drain hose operates at a nominal pressure of 125 psi (861 kPa). The engine-driven hydraulic pump uses an internal depressurization valve to depressurize the pump when commanded by the hydraulic control printed circuit board (PCB). The depressurization valve is an electrically-controlled, three-port, solenoid valve, which, when energized open by a depressurize signal from the full authority digital engine control (FADEC), lets pressurized pump discharge fluid to bypass the compensator and act directly on the pump's stroking piston. This causes the pump to move to a minimum output condition. Depressurizing the hydraulic pump lets the engine windmill with less airflow during an air restart. A shaft seal drain lineis connected to the accessory gearbox aft of the hydraulic pump and collects any hydraulic pump shaft seal leakage and sends it to the engine drain mast that drains overboard. (3) For Airplanes -0001 thru -0016 and -0018 thru -0021, a power transfer unit (PTU) puts together the functions of two separate components. First, it operates as a bi-directional hydraulic power transfer unit to supply hydraulic power between System A and System B to retract the landing gear during a single-engine takeoff and to operate the antiskid brake system during a rejected takeoff. (4) For Airplanes -0017 and -0022 and On, a power transfer and conversion unit (PTCU) operates as a bi-directional hydraulic power transfer unit to supply hydraulic power between System A and System B to retract the landing gear during a single-engine takeoff and to operate the antiskid brake system during a rejected takeoff. Second, it operates as an electric motor-driven hydraulic pump that can operate System A or System B sequentially to supply hydraulic power to set the parking brake, and supply bootstrap pressure to the hydraulic reservoir during engine start since they are installed below the hydraulic pumps, and for supplying hydraulic power for ground maintenance if an external hydraulic power unit is not available. Third, it operates as an emergency electrical generator that is operated by System A or System B if the two engine-driven DC generators become unserviceable. (5) There are nine different no-maintenance helium-charged accumulators to support different functions if there is a hydraulic fluid leak or pressure decrease. For System A, there is a hydraulic system accumulator, inboard parking brake accumulator, outboard spoiler accumulator, and left

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and right inboard spoiler accumulators. For System B, there is a hydraulic system accumulator, middle spoiler accumulator, nosewheel steering accumulator, and outboard parking brake accumulator. (a) The System A and the System B hydraulic system accumulators in the aft fuselage fairing absorb sudden changes in hydraulic pressure from the operation of the system components. (6) The hydraulic system includes thirteen manifolds. There are two hydraulic system filter manifolds in the aft fairing, a landing gear control manifold in the aft fairing, four hydraulic spoiler accumulator manifolds, four roll spoiler manifolds, and two ground spoiler manifolds. (a) The System A and the System B hydraulic systems have a hydraulic system filter manifold. The hydraulic system filter manifold distributes the hydraulic fluid to the different partsof the hydraulic system and gives a location for the attachment of the filters and sensors. The hydraulic system filter manifold allows the removal of the filter elements without disconnecting fittings, removing the filter manifold, or losing hydraulic fluid. Noneofthe filter assemblies contain a differential pressure indicator (DPI). (b) The System A and the System B hydraulic system filter manifolds have a pressure switch that supplies a signal for the amber HYD PUMP FAIL A-B crew alerting system (CAS) message when the related engine-driven hydraulic pump pressure decreases below 2200 psi (15,168 kPa). The system pressure switches send this signal to the hydraulic control PCB's. The pressure switch is reset when the hydraulic pressure increases to more than 2700 psi (18,616 kPa). (c) The System A and the System B hydraulic system filter manifolds include a platinum, dual- element, resistance temperature detector (RTD). The output of the first element is sent to the hydraulic control PCB. The output of the second element supplies a signal to open and close the heat exchanger bypass valve inside the filter manifold. The temperature transducer monitors the temperature of the hydraulic fluid returning to the manifold from the case drain heat exchanger after it has passed through the case drain filter. (d) The System A and the System B hydraulic system filter manifolds have a temperature- compensated pressure transducer that measures the absolute pressure of the hydraulic fluid and sends this signal to the hydraulic control PCB and directly to thePTU.The pressure transducers receive electrical power from the emergency power J-Box. The sensor measures pressure in 100 psi (689 kPa) increments and has a full-scale reading of 4000 psi (27,579 kPa). If the pressure indicated by this sensor drops to less than 2200 psi (15,168 kPa), the amber HYD PRESS LOW A-B CAS message will come on. If it increases above 3300 psi, then the amber HYD O'PRESS A-B CAS message will come on. (7) There are six dual-acting actuators in the wing. For System A, there are two inboard roll spoiler actuators and two outboard roll spoiler actuators. For System B, there are two middle ground spoiler actuators. Hydraulic power is supplied or removed from the actuators with pilot input and limit switches. Each hydraulic system has its own spoiler isolation valve to be used if there is a hydraulic fluid leak or pressure decrease. (8) The hydraulic reservoir is a bootstrap pressurized reservoir with an area ratio of approximately 60:1. When the system is operating at 3000 psi (20,684 kPa), the bootstrap pressure is approximately 50 psi (344 kPa). The bootstrap pressure gives a constant head pressure for the hydraulic pump and the PTU inlets to prevent cavitation. The hydraulic reservoir helps with changes in system fluid volume that occurs with changes in system pressure and temperature. It also compensates for actuator movement and accumulator charge and discharge, both of which will return/draw fluid to/from the hydraulic reservoir. The hydraulic reservoir is protected from too much internal pressure by a relief valve that is discharged overboard. The relief valve can discharge maximum inlet flow to the reservoir while it keeps maximum permitted pressure. The relief valve can be manually opened to bleed air from the hydraulic reservoir by pulling the hydraulic reservoir relief cable knob on the hydraulic service panel in the left aft fairing. The hydraulic reservoir includes a linear potentiometer that converts reservoir piston position to the fluid volume it contains. The volume signal is sent to both the hydraulic control PCBandto the hydraulic reservoir volume indicator. The hydraulic reservoir also contains a marked visual sight glass. Two sight doors on the right fairing give access to these sight glasses. A reservoir relief valve on the hydraulic reservoir protects against overfilling during the hydraulic reservoir servicing. The reservoir relief valve will automatically open when the volume in the hydraulic

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reservoir increases to more than 120 psi (827 kPa). The reservoir relief valve can also be manually operated to bleed air out of the hydraulic reservoir during ground maintenance. The manual operation of the reservoir relief valve occurs by pulling the bleed knob in the hydraulic service panel for the related hydraulic reservoir. The knob is attached to a cable, that attaches to the reservoir relief valve. Hydraulic fluid from the relief valve is routed first to an ecology bottle, then out of an unheated drain below the hydraulic reservoirs. The ecology bottles are installed at tees in the hydraulic reservoir overboard vent tubes in the aft fairing. The ecology bottles are accessible through a latched fuselage fairing panel below the bottles. (9) The airplane has an electrically-controlled and monitored, hydraulically-actuated, retractable, tricycle landing gear system. Each landing gear is operated by its related hydraulic-locking landing gear actuator. Hydraulic power to the locking landing gear actuators is supplied by hydraulic System B. The hydraulically-operated main landing gear inboard doors cover the main landing gear wheel wells when the landing gear is retracted or extended. Each main landing gear has a main landing gear emergency extend actuator to help the free fall extension. The main landing gear emergency extend actuators are operated by hydraulic System A. (10) The thrust reverser assemblies are hydraulically-activated. The left thrust reverser assembly is operated by System A and it has its own isolation valve. The right thrust reverser assembly is operated by System B and also has its own isolation valve. (11) The System B hydraulic system has a hydraulic priority valve that gives pressure priority primarily to the rudder and roll spoilers. It is a relief valve installed in the hydraulic supply line that goes to the landing gear. During normal landing gear operation (at high-flow demand), the system pressure decreases. To keep the hydraulically-controlled rudder and spoiler flight controls in operation during the landing gear operation cycle, the hydraulic priority valve closes at 2400 psi (16,547 kPa) to prevent the landing gear from decreasing the system pressure too low to affect flight control performance. (12) The airplane has electrically-controlled and hydraulically-actuated main landing gear brake assemblies. Pilot inputs from the toe brakes on the rudder pedals are electrically transmitted to the brake control valves to modulate the hydraulic pressure to the main landing gear brakes in proportion to the pilot input. Each brake control valve includes two servo valves to modulate the brake fluid pressure. The inboard main landing gear brakes are operated by SystemA and the outboard main landing gear brakes are operated by System B. There is also a parking brake valve that is mechanically connected with a cable to the emergency/parking brake handle assembly. The emergency/parking brake handle assembly lets the pilots modulate the emergency brake pressure. The emergency/parking brake handle assembly also lets the pilots fully apply the parking brake pressure. (13) The nosewheel steering is operated with hydraulic power to turn the nose wheels as related to the pilot's input. (14) Ground servicing of the hydraulic system is done through the hydraulic service panel on the left aft fairing. A set of hydraulic reservoir servicing couplings (PRESSURE and RETURN) connect to System A and a set of hydraulic reservoir servicing couplings (PRESSURE and RETURN) connect to System B. The hydraulic reservoir can be serviced with the external hydraulic power unit through the hydraulic reservoir servicing couplings or with a hand pump through the hydraulic reservoir servicing check valves (MANUAL FILL PORT) on the hydraulic service panel. Hydraulic reservoir volume indicators are also installed on the hydraulic service panel for System A and System B. (15) The HYDRAULICS PUMP switches (System A and System B) installed in the center pedestal have NORM, MIN, and SHUTOFF positions to control the operation of the engine-driven hydraulic pumps. (a) In the NORM (normal operation) position, the engine-driven hydraulic pump operates at normal pressure and flow and the hydraulic shutoff valve is open and the engine-driven hydraulic pump depressurization valve is closed. In the event of an in-flight restart, the FADEC will supply a signal to the hydraulic control PCB to automatically open the engine- driven hydraulic pump depressurization valve which decreases the torque necessary to restart the engine. In the event of an engine fire, the engine fire switch is pressed, which causes the hydraulic firewall shutoff valve to close, stopping fluid from flowing to theengine- driven hydraulic pump. If this occurs, the engine-driven hydraulic pump depressurization valve will not open.

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(b) If the amber HYD O'TEMP A-B CAS message comes on, per the Model 700 Approved Airplane Flight Manual, the flight crew will set the related HYDRAULICS PUMP switch to the MIN position. This will send a signal to the FADEC that commands the engine-driven hydraulic pump depressurization valve to open which will depressurize the engine-driven hydraulic pump. In the MIN (minimum operation) position, the engine-driven hydraulic pump operates at a pressure and flow that is less than normal operation pressure andthe hydraulic shutoff valve is open. (c) If the red HYD O'TEMP A-B CAS message comes on, per the Model 700 Approved Airplane Flight Manual, the flight crew will set the related HYDRAULICS PUMP switch to the SHUTOFF position. In the SHUTOFF position, the engine-driven hydraulic pump depressurization valve stays open, the engine-driven hydraulic pump does not operate, and the hydraulic shutoff valve is closed. During normal operations, the motor-operated hydraulic shutoff valves stay open. If the related ENGINE FIRE switch/light is pushed, electrical power is sent to the valve to close it and stop the flow of hydraulic fluid tothe engine-driven hydraulic pump. The valve is monitored for open or closed position and will send a signal to the engine indicating and crew alerting system (EICAS) system. The hydraulic shutoff valve has an external indicator that shows the valve position. (16) The emergency/parking brake handle assembly, when pulled, operates the parking brake valve in the aft fairing. Then, the parking brake valve sends hydraulic pressure from the inboard and outboard parking brake accumulators to the brake shuttle valves in the main landing gear wheel well. When the emergency/parking brake handle assembly is stowed, the system is in normal brake operation. (17) For Airplanes -0001 thru -0016 and -0018 thru -0021, the PTCU rotary switch installed in the center pedestal has OFF, SPARE, NORM, SPARE, and ON positions. • In the OFF position, the PTU does not operate. • In the SPARE positions, the PTU operates the same as in the NORM position. • In the NORM (normal operation) position, the PTU defaults to PTCU standby mode. • In the ON position, the PTU defaults to PTU mode (opens PTCU shutoff valves independent of the system pressure or volume). (18) For Airplanes -0017 and -0022 and On, the PTCU rotary switch installed in the center pedestal has OFF, AUX A, NORM, AUX B, and HYD GEN positions. • In the OFF position, the PTCU is switched to the OFF mode and the PTCU reverts to standby mode. • In the AUX A position, the PTCU supplies auxiliary hydraulic pressure at 2750 psi, +100 or -100 psi to System A. The auxiliary pump will run for a few minutes before the PTCU rotor reaches its over-temperature limit and shuts down. • In the NORM (normal operation) position, the PTCU supplies hydraulic pressure to the parking brake and primes the engine-driven hydraulic pumps during engine starts. It defaults to the PTCU standby mode. During flight, the PTCU is in the PTU mode. Ifthere is a loss of a hydraulic system power, it will transfer power from the operating hydraulic system to the non-operating hydraulic system. • In the AUX B position, the PTCU supplies auxiliary hydraulic pressure at 2750 psi, +100 or -100 psi to System B. The auxiliary pump will run for a few minutes before the PTCU rotor reaches its over-temperature limit and shuts down. • In the HYD GEN position, the PTCU operates as an electric generator using hydraulic pressure from System A or System B. (19) The landing gear handle module installed in the right switch panel has GEAR UP and GEAR DOWN positions. In the GEAR UP position, the landing gear retracts to the up and locked position. In the GEAR DOWN position, the landing gear extends to the down and locked position. (20) The emergency gear release handle assembly, when pulled, releases the nose and the main landing gear from the nose and the main landing gear uplocks. The nose landing gear will free- fall to the down and locked position with the help of air drag. The main landing gear emergency extend actuators help move the left and the right main landing gear to the down and locked position. When the emergency gear release handle assembly is stowed, hydraulic pressure is not supplied to the main landing gear emergency extend actuators.

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HONEYWELL INERTIAL REFERENCE SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and the operation of the optional Honeywell Inertial Reference System. The line replaceable units (LRU's) in the Honeywell Inertial Reference System are the Honeywell Inertial Reference Unit (IRU) and the Honeywell IM-950 Configuration Module. B. The alterative to the Honeywell Inertial Reference System is the LITEF LCR-100/100N Navigation System. For a general description of the LITEF LCR-100/100N Navigation System, refer to Chapter 34, LITEF LCR-100/100N Navigation System - Description and Operation. C. Refer to Figure 1 for a general view of the Honeywell Inertial Reference System.

2. Description A. Honeywell Inertial Reference Unit (IRU) (1) The IRU is a solid-state strap-down all attitude inertial sensor that generates angular rate and linear acceleration about the body axes of the aircraft and digitally processes this data to get three axis angle, rate acceleration and navigation data. It contains three force rebalance accelerometers and three laser gyros to measure inertial motion. (2) The left and the right IRU's are installed in the nose avionics bay. The left unit is installed at FS 69.27, LBL 8.55, and WL 107.56 and the right unit is installed at FS 69.27, RBL 8.55, and WL 107.56. B. Honeywell IM-950 Configuration Module (1) The configuration module contains an EEPROM chip that stores unique aircraft alignment and configuration parameters. The only function of the configuration module is to supply thecontents of the memory to the IRU when it is powered on. (2) The left and the right configuration modules are installed in the nose avionics bay on brackets forward of each IRU.

3. Operation A. Honeywell Inertial Reference System (1) The Honeywell Inertial Reference System gives 3-axis angle, rate, and acceleration data and also gives navigation data to the Garmin G5000 Integrated Avionics System. The IRU senses the Earth's rotation during the gyro-compass alignment process, augmented by GPS reference coordinates provided during initialization, to determine the true north heading reference and airplane position. The inertial reference system applies a magnetic declination value from a lookup table stored in internal memory to the sensed true heading value to determine magnetic heading. (2) The inertial reference system is able to calculate and output inertial position, velocities, heading, attitude, and related parameters such as magnetic variation (based on computer position), earth rate (depending on latitude), angular rate, and body acceleration. The inertial reference system uses rotational data from the laser gyros and/or acceleration data from the accelerometers to calculated attutude and heading at power up and present position, velocity, heading, wind, and attitude data while in flight. (3) The IRU typically gives the attitude and heading data referenced to magnetic north to the Garmin GIA 64E Integrated Avionics Unit through high speed ARINC 429 data buses. The inertial reference system heading reference can be manually steered to a new heading at flight crew discretion with the Garmin GTC 575 Touchscreen Control Units. Select FREE DG Mode on the GTC, then use the HDG SET button to input a new desired heading reference. For more data on the GIA's and GTC's, refer to Chapter 42, Garmin G5000 Integrated Avionics System - Description and Operation. (4) The configuration module allows the IRU to be replaced without a compass swing ortrayre- alignment. Once it is programmed with the menu driven PC tool, the configuration module remains with the tray. (5) The IRU receives power in the configurations that follow: (a) When the BATT switch is ON and the MAIN switch is OFF, both IRU's receive power from the on-side EMER bus.

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Honeywell Inertial Reference System Figure 1 (Sheet 1)

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(b) When the MAIN switch is ON and ELEC is in the NORM position, each unit is powered by the respective on-side Main power bus. (c) When the ELEC switch is in the EMER position, power is removed from the ATT/HDG AUX circuit breaker but continues to be provided from the on-side main aircraft battery through the primary ATT/HDG circuit breaker.

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HONEYWELL INERTIAL REFERENCE SYSTEM - ADJUSTMENT/TEST

1. General A. This section gives the adjustments and tests necessary for the optional Honeywell Inertial Reference System. For a general description of the Honeywell Inertial Reference System, refer to Chapter 34, Honeywell Inertial Reference System - Description and Operation.

2. Honeywell Inertial Reference System Operational Check A. Tools and Equipment

(1) Tools and Equipment • None. (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices. B. Prepare the Airplane for the Honeywell Inertial Reference System Operational Check. (1) If necessary, move the airplane to a position where it can receive correct global positioning system (GPS) signals. (2) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. C. Do the Honeywell Inertial Reference System Operational Check. (1) Make sure that the pitch and the roll angles shown on the left and the right primary flight displays (PFD's) agree after approximately 30 seconds.

NOTE: It takes approximately 30 seconds after you apply electrical power to the system to get the correct attitude and heading data.

(2) Make sure that the Garmin G5000 integrated avionics system is receiving GPS signals. (3) Make sure that the inertial reference unit (IRU) has completed alignment and any associated system messages have been cleared after approximately 10 minutes. D. Put the Airplane Back to its Initial Condition. (1) Disconnect the external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

3. Honeywell Inertial Reference System Alignment A. Tools and Equipment

(1) Tools and Equipment • Ethernet cable • IRS Test Box • IRU PC Tray Alignment Software • Laptop. (2) Special Consumables • None. (3) Reference Material • Chapter 7, Lifting - Maintenance Practices

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• Chapter 8, Leveling - Maintenance Practices • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 32, Landing Gear - Maintenance Practices • Laseref VI Configuration Index. B. Prepare the Airplane for the Honeywell Inertial Reference System Alignment. (1) If necessary, move the airplane to a position where it can receive correct global positioning system (GPS) signals. (2) Connect the nose gear and the main gear simulator test boxes. Refer to Chapter 32, Landing Gear - Maintenance Practices. (a) Set the simulators to the ON GROUND position. (3) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (4) Put the airplane on jacks. Refer to Chapter 7, Lifting - Maintenance Practices. (5) Level the airplane. Refer to Chapter 8, Leveling - Maintenance Practices. C. Do the Honeywell Inertial Reference System Alignment. (1) Connect the IRS test box to the IRU as follows: (a) Disconnect the electrical connector (PN321 left, PN322 right) from the IRU. (b) Connect the IRS test box electrical connectors to the IRU and the electrical connector. (c) Connect a laptop to the IRS test box with a non-crossover type Ethernet cable. (2) Start the tray alignment software on the laptop. (a) Make sure that applicable configuration index file is listed at the top of the Alignment Main Menu. (b) Select Manual Alignment. (c) On the Manual Tray Alignment window, select Nose Plunge. (d) Set the Measured Pitch and the Measured Roll to 0 degrees. (e) Enter 40 for the A/C Type. (f) Enter the airplane's serial number for A/C SN. (g) Select Start Manual Alignment. (3) Set the S1 switch on the IRS test box to the OPEN position. (a) Wait 4 seconds. (b) Set the S1 switch to the CLOSED position. (c) On the Instruction Panel window, select IRU/AHRS #1 or IRU/AHRS #2 as applicable. (d) Make sure that all listed tasks have been completed. (e) Select CHECK ALL. (f) Select Done.

NOTE: A pop-up will appear to allow the user to monitor the alignment data and remaining time. The Communications Status field on the Main Panel displays status messages during the alignment.

NOTE: The IRU/AHRS Status light on the manual tray alignment menu will display amber during alignment.

(4) After approximately 13 minutes, a new Instructions Panel will appear. (a) Adjust the nose jack until the airplane nose is 1.0 +0.1 or -0.1 degrees below level. Refer to Chapter 8, Leveling - Maintenance Practices. (b) Make sure that all listed tasks have been completed. (c) Select CHECK ALL (d) Select Done. (5) After approximately 3 minutes, a new Instructions Panel will appear. (a) Adjust the nose jack until the airplane nose is 1.0 +0.1 or -0.1 degrees above level. Refer to Chapter 8, Leveling - Maintenance Practices. (b) Make sure that all listed tasks have been completed. (c) Select CHECK ALL (d) Select Done. (6) After approximately 3 minutes until a new Instructions Panel will appear. (a) Go back the airplane to level. Refer to Chapter 8, Leveling - Maintenance Practices.

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(b) Set the S1 switch on the IRS test box to the OPEN position. (c) Wait 4 seconds. (d) Set the S1 switch to the CLOSED position. (e) Make sure that all listed tasks have been completed. (f) Select CHECK ALL (g) Select Done. (7) After approximately 3 minutes, the Configuration Index Validation window will appear. (a) Make sure that the APM CRC values listed are correct. Refer to the Laseref VI Configuration Index. (b) Select OK. (8) Set the S1 switch on the IRS test box to the OPEN position. (a) Make sure that all listed tasks have been completed. (b) Select CHECK ALL (c) Select Done.

NOTE: When the alignment is completed, the IRU/AHRS Status light on the manual tray alignment menu will display green.

(9) Disconnect the IRS test box from the IRU. (10) Do the Honeywell Inertial Reference System Attitude Verification as follows: (a) Make sure that the pitch and the roll angles shown on the left and the right primary flight displays (PFD's) agree after approximately 30 seconds.

NOTE: It takes approximately 30 seconds after you apply electrical power to the system to get the correct attitude and heading data.

(b) Make sure that the airplane is level. Refer to Chapter 8, Leveling - Maintenance Practices. (c) Make sure that airplane level matches the IRU navigator +0.3 or -0.3 degree. (d) Record the pitch and the roll values. (e) Adjust the nose jack until the airplane nose is 1.0 degree below level. Refer to Chapter 8, Leveling - Maintenance Practices. (f) Record the new pitch and the new roll values. (g) Make sure that the difference between the two IRU's is not greater that 0.2 degrees. (11) Make sure that the Garmin G5000 integrated avionics system is receiving GPS signals. (12) Make sure that the inertial reference unit (IRU) has completed alignment and any associated system messages have been cleared after approximately 10 minutes. D. Put the Airplane Back to its Initial Condition. (1) Disconnect the external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Remove all test equipment from the airplane.

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HONEYWELL INERTIAL REFERENCE UNIT (IRU) - REMOVAL/INSTALLATION

1. General A. This section gives the removal and installation procedures for the optional Honeywell Inertial Reference Unit (IRU) (UN321 left, UN322 right). For a general description of the IRU, refer to Chapter 34, Honeywell Inertial Reference System - Description and Operation.

2. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 34, Navigation - General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List. A. Tools and Equipment • None. B. Special Consumables • None. C. Reference Material • Chapter 6, Dimensions and Areas - Description and Operation • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 34, Honeywell Inertial Reference System - Adjustment/Test • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices • Citation Standard Practices Manual, Chapter 20, Torque Value - Maintenance Practices.

3. Setup A. Prepare the Airplane for the Honeywell Inertial Reference Unit (IRU) Removal. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Disengage the circuit breakers given in Table 401.

Table 401. Circuit Breakers

Component Circuit Breaker Name Circuit Breaker Location Left IRU L ATT/HDG Left Circuit Breaker Panel L ATT/HDG AUX Left Circuit Breaker Panel Right IRU R ATT/HDG Right Circuit Breaker Panel R ATT/HDG AUX Right Circuit Breaker Panel (3) Open the left and the right nose access doors to get access to the left and the right IRU (UN321 left, UN322 right). Refer to Chapter 6, Dimensions and Areas - Description and Operation.

4. Honeywell Inertial Reference Unit (IRU) Removal A. Remove the Honeywell Inertial Reference Unit (IRU) (Refer to Figure 401).

NOTE: The removal of the left and the right IRU's is typical.

(1) Disconnect the electrical connector (PN321 left, PN322 right) from the IRU (UN321 left, UN322 right). (2) Loosen the captive screws that attaches the IRU to the mounting tray. (3) Remove the IRU from the mounting tray.

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Honeywell Inertial Reference Unit (IRU) Installation Figure 401 (Sheet 1)

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5. Honeywell Inertial Reference Unit (IRU) Installation A. Install the Honeywell Inertial Reference Unit (IRU) (Refer to Figure 401).

NOTE: The installation of the left and the right IRU's is typical.

(1) Put the IRU (UN321 left, UN322 right) in its position on the mounting tray. (a) Make sure that you correctly install the IRU in the guide pins. (2) Tighten the captive screws that attach the IRU to the mounting tray. (a) Torque the captive screws to 28.0 inch-pounds, +1.5 or -1.5 inch-pounds (3.16 N-m, +0.17 or -0.17 N-m). Refer to the Citation Standard Practices Manual, Chapter 20, Torque Value - Maintenance Practices. (3) Connect the electrical connector (PN321 left, PN322 right) to the IRU.

6. Honeywell Inertial Reference Unit (IRU) Installation Post-Maintenance Checks A. Do the Honeywell Inertial Reference Unit (IRU) Post-Maintenance Checks. (1) Do an electrical bond check (Type I) from the mounting tray to the airplane structure. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices. (2) Engage the circuit breakers given in Table 401. (3) If the hybrid navigator has been replaced or had the position changed, do the Honeywell Inertial Reference System Alignment. Refer to Chapter 34, Honeywell Inertial Reference System - Adjustment/Test. (4) If the hybrid navigator has not been replaced or had the position changed, do the Honeywell Inertial Reference System Operational Check. Refer to Chapter 34, Honeywell Inertial Reference System - Adjustment/Test.

7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Close the left and the right nose access doors. Refer to Chapter 6, Dimensions and Areas - Description and Operation.

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HONEYWELL IM-950 CONFIGURATION MODULE - REMOVAL/INSTALLATION

1. General A. This section gives the removal and installation procedures for the optional Honeywell IM-950 Configuration Module (UN323 left, UN324 right). For a general description of the configuration module, refer to Chapter 34, Honeywell Inertial Reference System - Description and Operation.

2. Tools and Equipment

3. Setup A. Prepare the Airplane for the Honeywell IM-950 Configuration Module Removal. (1) Disconnect external electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (2) Disengage the circuit breakers given in Table 401.

Table 401. Circuit Breakers

Component Circuit Breaker Name Circuit Breaker Location Left Configuration Module L ATT/HDG Left Circuit Breaker Panel L ATT/HDG AUX Left Circuit Breaker Panel Right Configuration Module R ATT/HDG Right Circuit Breaker Panel R ATT/HDG AUX Right Circuit Breaker Panel (3) Open the left or the right nose access door to get access to the configuration module (UN323 left, UN324 right). Refer to Chapter 6, Dimensions and Areas - Description and Operation.

4. Honeywell IM-950 Configuration Module Removal A. Remove the Honeywell IM-950 Configuration Module (Refer to Figure 401).

NOTE: The removal of the left and the right configuration modules is typical.

(1) Loosen the captive screws that attach the electrical connector (PN323 left, PN324 right) to the configuration module (UN323 left, UN324 right). (a) Disconnect the electrical connector from the configuration module. (2) Remove the screws that attach the configuration module to the bracket. (3) Remove the configuration module from the airplane.

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Honeywell IM-950 Configuration Module Installation Figure 401 (Sheet 1)

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5. Honeywell IM-950 Configuration Module Installation A. Install the Honeywell IM-950 Configuration Module (Refer to Figure 401).

NOTE: The installation of the left and the right configuration modules is typical.

(1) Put the configuration module (UN323 left, UN324 right) in its position at the bracket. (2) Install the screws that attach the configuration module to the bracket. (3) Connect the electrical connector (PN323 left, PN324 right) to the configuration module. (a) Tighten the captive screws that attach the electrical connector to the configuration module.

6. Honeywell IM-950 Configuration Module Post-Maintenance Checks A. Do the Honeywell IM-950 Configuration Module Post-Maintenance Checks. (1) Engage the circuit breakers given in Table 401. (2) Do the Honeywell Inertial Reference System Alignment. Refer to Chapter 34, Honeywell Inertial Reference System - Adjustment/Test.

7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Close the left or the right nose access door. Refer to Chapter 6, Dimensions and Areas - Description and Operation.

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GARMIN TRAFFIC COLLISION AVOIDANCE SYSTEM (TCAS II) - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and the operation of the Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) The line replaceable units (LRU's) in the TCAS II are the Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Upper Antenna, Garmin GTS 8000Traffic Collision Avoidance System (TCAS II) Lower Antenna, and Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Processor. B. Refer to Figure 1 for a general view of the Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II).

2. Description A. Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Upper Antenna (1) There is one TCAS II upper antenna installed on the top of the fuselage. It is installed on the fuselage skin above the cabin door, at approximately FS 221.8 and BL 0.00. The antenna has four coaxial connectors that are connected through an antenna adapter. (2) The TCAS II upper antenna is used to derive the bearing of a intruder aircraft. This antenna only transmits directional interrogations to reduces the potential for interference on the 1090 MHz band. B. Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Lower Antenna (1) There is one TCAS II lower antenna installed on the lower fuselage fairing. It is installed aft of the cabin door at approximately FS 249.66 and BL 0.00. The antenna has four coaxial connectors that are connected through an antenna adapter. (2) The TCAS II lower antenna is a directional antenna that transmits omnidirectional interrogations to intruding aircraft. This antenna will see any targets that are not visible to the TCAS II upper antenna. C. Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Processor (1) There is one TCAS II processor installed in the right cockpit side console. It is installed on a support tray between FS 147.30 and 169.63 at approximately WL 103.00. The processor has three electrical connectors and eight coaxial connectors on the front of the processor. (2) The TCAS II processor uses data received from the TCAS II antennas to monitor and compute intruder aircraft threat potential based on range, bearing, vertical speed and altitude. (3) The TCAS II processor uses data received from the TCAS II antennas to monitor and compute intruder aircraft threat potential based on intruder range, relative altitude (if the intruder responder reports altitude), relative bearing, and vertical speed. The intruder position, altitude, altitude trend (climbing/descending at greater than 500 feet/minute), and threat potential are shown on the flight displays.

3. Operation A. Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) (1) The TCAS II does traffic surveillance and advisory functions with airborne avionics systems without ground station inputs or support. The system uses the transponders to monitor the surrounding area by listening for Mode-S squitter or Mode C messages from nearby aircraft transponders. (2) When a squitter message is received (on 1090 MHz), TCAS II interrogates the intruder aircraft's Mode S transponder (on 1030 MHz). The intruder's transponder replies to the TCAS II interrogation. The interrogation/reply sequence continues until the aircraft is out of TCAS II surveillance range. (3) There are four different intruder symbols. Each symbol represents a specific threat potential and is shown on the multifunction display (MFD) through an Ethernet High Speed Data Bus (HSDB). (a) The first symbol is a hollow white diamond shape that represents the lowest threat andis referred to as "other" traffic. (b) The second symbol is a solid white diamond which indicates "proximity" traffic. (c) The third symbol is represented with a solid yellow circle that is associated with an advisory function called a Traffic Advisory "TA".

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Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Figure 1 (Sheet 1)

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(d) The fourth symbol is a solid red square that is associated with an advisory function call a Resolution Advisory "RA". (4) The Garmin GTC 575 Touchscreen Control Unit are the primary interface for the TCAS II. The pilot can select the desired operating mode, altitude range, altitude display, and active transponder and code when TCAS II is selected on the MFD or primary flight display (PFD). (5) The pilot has the option to select five different TCAS II operational modes. The modes areauto, traffic advisories (TA) only, altitude reporting, ON, and standby. The modes operate as follows: (a) In auto mode, TCAS II switches between Traffic Advisories/Resolution Advisories (TA/RA) and TA only, depending on the airplane altitude above ground. The system will automatically switch to TA/RA when the aircraft's altitude is at least 1000 feet (305 m) above ground level (AGL). The transponder will automatically operate in Mode S ground mode (it transmits acquisition squitter and only replies to discretely addressed Mode S interrogations, such as from airport surface detection equipment) while on the ground, and transition to altitude reporting mode (it replies to Mode A, C, and S interrogations) when airborne. (b) In TA only mode, TCAS II only gives TA and does not give any advisories to resolve the potential conflict. (c) In altitude reporting mode, TCAS II operation is inhibited, but the transponder will generate Mode A, C, and S replies. (d) In ON mode, TCAS II operation is inhibited, but the transponder will generate Mode A and S replies. (e) In Standby mode, the TCAS II does not transmit any data to other aircraft as the TCAS II and transponder are inhibited. (6) The pilots have the option to select four altitude ranges. The four modes are Unrestricted, Above, Normal, and Below. Each mode restricts amount of traffic shown to the crew. These modes allow the pilot to reduce the amount of shown targets. The modes will show non-threat and proximity traffic as follows: (a) For unrestricted mode, traffic 9,900 feet (3,018 m) above and below the aircraft isshown. (b) For above mode, traffic 9,900 feet (3,018 m) above and 2,700 feet (823 m) belowthe aircraft is shown. (c) For normal mode, traffic 2,700 feet (823 m) above and below the aircraft isshown. (d) For below mode, traffic 2,700 feet (823 m) above and ,900 feet (3,018 m) below the aircraft is shown. (7) The pilots can show the altitude as either relative or absolute to their position. (a) Relative mode shows the intruder’s aircraft with respect to the TCAS II. It will include a plus (+) sign if the target is above or a minus (-) sign if the target is below. (b) Absolute mode provides the altitude of traffic in the area. Each selection shows a three digit number to the crew that represents hundreds of feet. For example, if +021 shows in the relative altitude display mode, the target aircraft is 2,100 feet above the aircraft. B. Vertical Situation Display (VSD), Airplanes with G5000 System software version 58 and higher. (1) The Vertical Situation Display (VSD) is a Navigation Map inset window that displays a vertical profile referenced to the current aircraft track or the flight plan. (2) The VSD provides an optional vertical cross section of the aircraft flight plan on a multi-function window on the MFD to enhance situational awareness. The VSD does not provide caution or warning information or crew alerts that require acknowledgment. (3) The VSD is enabled/disabled by the crew via either center GTC’s Home screen by selecting Map>Map Selection>Map Settings> Inset Window and pressing the VERT Situation Display button. (4) Common display elements to all modes include horizontal scale, vertical scale, own-ship symbol, terrain, point obstacles, wire obstacles, wind vectors. The horizontal scale indicates twice the full-scale range of the map. The VSD horizontal scale range is equal to the Navigation Map indicated range. The vertical scale indicates barometric altitude, and the range is linked to the horizontal scale range such that the ratio of vertical range to horizontal range is constant until both the minimum and maximum display limits have been met. The own-ship symbol is displayed on the left side of the VSD, adjacent to the vertical scale. The vertical position is set based on the phase of flight, climb or aircraft on ground, cruise, and descent. The VSD swath determines

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what terrain and obstacles to display on the VSD. Terrain and obstacles are positioned vertically relative to the own-ship symbol based on the GPS altitude difference from the aircraft. Terrain coloring is based on the terrain layer option chosen in the Map Settings. (5) Wind vectors are shown as barbed arrows to indicate along-track component of the wind at each labeled altitude along the center of the swath. Wind speeds are displayed in 5-knot increments. (6) The preselected altitude vane is indicated at the top left of the VSD. The vertical track vector is a solid cyan line extending from the nose of the own-ship symbol that indicates the current climb or descent gradient. (7) Modes for the VSD include Track Mode (TRK), Flight Plan Mode (FPL), and Auto Mode with Track displayed (AUTO TRK), and Auto mode with Flight Plan (AUTO FPL) displayed. The mode indication is a text string at the top left of the VSD. (a) In Track Mode, the swath is centered on and aligned with the current aircraft track. The VSD horizontal scale range is equal to the Navigation Map indicated range. In addition, only the common display elements are shown. When the Track mode boundary setting is on and the VSD is in Track mode, a VSD path box is shown on the Navigation Map to indicate the plan view extent of the swath. (b) In Flight Plan mode, the swath is centered on and aligned with the flight plan. The VSD horizontal scale range is the lower of twice the Navigation Map indicated range or the lowest range increment that displays all of the remaining flight plan. The boundary display onthe Navigation Map is not available in Flight Plan mode. Flight plan waypoints are indicated by grey vertical dashed lines with the identifier label at the top of the line. The identifier label color is magenta for the active waypoint and white for inactive waypoints. To reduce clutter, along track waypoint labels differ from the labels shown on the GTC flight plan page in that each label contains only the offset distance and sign, not the waypoint identifier. (c) When Auto mode is selected, the VSD automatically selects Flight Plan mode when the aircraft is within the flight plan swath and Track mode when the aircraft is outside the flight plan swath. VSD settings are selected from the Vertical Situation Display Settings popup, accessed on the Inset Window tab from the MAP Settings GTC page. (8) The Mode setting can be Auto, Track, or Flight Plan. The Track boundary control allows toggling the track mode boundary shown on the map when in Track mode and includes a setting for the maximum indicated map range at which boundary is shown. The Winds selection toggles display of wind barbs. Climb and descend Icons are shown in magenta to the right of the own-ship symbol when the active leg’s flight plan line is above or below the altitude shown ontheVSD. If a future leg’s flight plan line will be above the highest altitude shown on the VSD duringthe climb phase, a white icon will be displayed to the right of the last leg visible on the VSD. (9) Discontinuities in the flight plan, (e.g. between a manual sequence waypoint and the following waypoint or prior to a vectors to final approach that has not been activated where the intercept path is not shown on the Navigation map) are shown on the VSD by a gap between the waypoints on either end of the discontinuity where terrain, obstacles, and the flight plan line are removed. The length of the gap is equal to the straight-line distance between the waypoints on either end of the discontinuity. (10) Holding patterns are capable of being depicted on the VSD with hold circuits including entry points and waypoints. In the Climb phase, the flight plan line indicates the highest altitude the aircraft can climb on each leg without exceeding a future AT, AT OR BELOW, Or Between altitude constraints. In the Cruise phase the flight plan is shown at cruise altitude when the aircraft is within 240 feet of the cruise altitude. During the Descent phase the vertical path matches VNAV guidance for each leg where the VPATH is supported. The Approach phase VNAV vertical path is displayed between the end of the baro VNAV path and the MAP. (11) Status messages are displayed on the VSD to indicate reasons for not displaying VSD information. Each message is displayed in white text in the center of the VSD inside a white-bordered text box. Refer to Table 1, VSD Display Messages.

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Table 1. VSD Display Messages

Display Message Condition VSD is loading data due to a range change, full/half Loading switch, or first being selected for display Flight Plan mode is selected and there is not a flight Flight Plan Not Available plan loaded with at least one leg All of the following are true:

Flight Plan mode unavailable because aircraft off Flight Plan mode is selected course and active leg over 200NM The active leg is greater than 200 nautical miles The aircraft is outside the swath Flight Plan mode is selected and the aircraft's Aircraft Beyond Active Leg position, as projected on the flight plan, is past the end of the active leg. At least one of the following is true: Valid terrain database not available GPS MSL altitude not available VSD Not Available Current barometric altitude not available GPS position not available Map range setting is less than 1 nautical mile Flight plan preview is selected VSD Data Old. Deselect and Reselect VSD VSD data has failed to update for 2 seconds or more

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INTEGRATED MODULAR AVIONICS - GENERAL

1. Scope A. This chapter gives all applicable maintenance procedures necessary for the integrated modular avionics system. This section gives a list of the systems included in this chapter and a tool and equipment list for the chapter.

2. Description A. This chapter is divided into sections to help maintenance personnel find data. The systems that follow are included in this chapter: • Garmin G5000 Integrated Avionics System Software • Garmin G5000 Integrated Avionics System.

3. Tools and Equipment A. Table 1 gives a list of the tools and equipment that are used to complete some of the maintenance procedures in this chapter.

NOTE: You can use equivalent tools or equipment.

Table 1. Tools and Equipment

Name Number Manufacturer Use Cessna G5000 Default 8203142-X (NOTE 1) Textron Aviation To export and import Pilot Profile SD Card Citation Marketing the pilot profiles to the Division multifunction display P.O. Box 7706 (MFD). Wichita, KS 67277 Cessna Longitude CMC 8204541-X (NOTE 1) Textron Aviation To operate the CMC Viewer SD Card Viewer program from the top SD card slot of the MFD. Microfiber Cloth Commercially Available To clean the screen of the Garmin GTC 575 Touchscreen Control Unit. Multimeter Commercially Available To check for electrical continuity in electrical connectors. PC Laptop Computer Commercially Available To load the G5000 Software Version 58. Protective Cover Commercially Available To protect components. Soft Cotton Cloth Commercially Available To clean the screen of the Garmin GTC 575 Touchscreen Control Unit. Software Loader SD Card 010-00474-50 Textron Aviation To load the G5000 Software Version 58.

NOTE 1: The part numbers for the Cessna G5000 Default Pilot Profile SD Card and the Cessna Longitude CMC Viewer SD Card are shown as "-X" because the part numbers are related to what software version is installed on the SD card. Different software versions will have different part numbers.

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GARMIN G5000 INTEGRATED AVIONICS SYSTEM SOFTWARE - DESCRIPTION AND OPERATION

1. General A. This section gives a description and the operation of the Garmin G5000 Integrated Avionics System Software. B. The Garmin G5000 Integrated Avionics System Software connects the various line replaceable units (LRU's) in the Garmin G5000 Integrated Avionics System to each other and shows avionics data to the flight crew. It can be updated to add additional features and give different functionality topartsof the G5000 system without the need to replace any avionics LRU's.

2. Description A. SD Cards (1) Each Garmin GDU 1450W Flight Display has two SD card slots in the top right section of the GDU that are used for different functions: (a) The top SD card slot is used to upload software and configuration files, upload and download flight plans, log fixed content data, and save data that was logged intheGDU. To upload software and configuration files, the card must be removed after the upload is completed. To log fixed content data, the SD card can stay in the top slotofthe multifunction display (MFD). In flight, only the MFD can have an SD card installed inthe top slot. (b) The bottom SD card slot is not used. (2) SD cards are used for several purposes with the G5000 system software. The types of SD cards are as follows: (a) Software Loader SD Card 1 The conformed software is installed onto the airplane with an SD card supplied by Garmin. This SD card is labeled and loaded with the related conformed software. (b) Garmin Database SD Card 1 The Garmin database SD card contains files for all the databases except for the navigation database. After the databases are loaded in the bottom SD card slot of the MFD, the Garmin database SD card does not need to stay in the bottom SD card slot of the MFD during normal operation. The Garmin database SD card is included with the airplane delivery. The database files are available on a subscription basis from FlyGarmin.com or Jeppesen and can be loaded onto a Garmin database SD card from any computer that has an SD card reader. (c) Option Loader SD Card 1 There are many different option loader SD cards for different optional systems that can be installed on the airplane. The option loader SD cards let you activate a specific option for a specific airplane. Once it is loaded on a specific airplane, it cannotbeused on any other airplane. The SD card will be labeled and loaded with the respective software. (d) Cessna Longitude CMC Config SD Card 1 The CMC configuration files are installed onto the airplane with a labeled SDcard. The CMC diagnostic configuration must be loaded to the MFD after the initial load of the base system software, after the MFD is replaced, and after any base configuration load to the system software. Failure to do this will stop all CMCprocess and log operations. For more data about how to update the CMC configuration files, refer to Chapter 45, Update CMC Configuration/CMC Viewer Version - Maintenance Practices. (e) Cessna Longitude CMC Viewer SD Card 1 The CMC viewer SD card does not load software or configuration files onto the airplane. Instead, it is loaded with the files that are necessary to use the CMC viewer. The CMC viewer SD card must be put into the top SD card slot of the MFD to use the CMC viewer. The CMC viewer SD card is kept in the MFD during normal operation and is typically only removed when a different SD card needs to be installed for a maintenance procedure. For more data about the CMC viewer, refer to Chapter 45, CMC Viewer - Description and Operation.

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(f) Pilot Profile SD Card 1 The pilot profile files are installed onto the airplane with a labeled SD card. Thepilot profile must be reloaded after the MFD is replaced. B. Databases (1) Databases are used in the G5000 system to give updates for avionics data that changes more frequently than software. There are several databases used by the G5000 system that are kept in the internal memory of each GDU. (2) Many of the databases have expiration dates and need to be updated regularly. The latest versions of the databases that are on the Garmin Database SD Card can be downloaded from FlyGarmin.com and Jeppesen. The ChartView database must be downloaded from Jeppesen. (3) The databases that are used in the G5000 system are as follows: (a) Checklist 1 The checklist database is optionally installed and is made and customized by the user. (b) Basemap 1 The basemap gives ground-based references such as roads and bodies of water. The basemap does not have a scheduled update cycle and as such does not have an expiration date. (c) Terrain 1 The terrain and airport terrain databases are required to be in the G5000 system for functions such as synthetic vision system (SVS), terrain awareness and warning system (TAWS), and TERRAIN-SVS. The standard terrain database gives ground elevation with a 4.9 arc-sec resolution. The airport terrain gives additional resolution near most airports with a resolution of 4.9 arc-sec. A higher resolution terrain database is used with SVS that gives continuous 4.9 arc-sec resolution. The terrain and airport databases do not have an expiration date. (d) Obstacle 1 The obstacle database gives identification of known obstacles greater than 200 feet above ground level (AGL). This database is also used with TAWS and TERRAIN- SVS. Obstacle data is available for the United States and for Europe. The obstacle database must be updated every 56 days. (e) Safetaxi 1 Safetaxi diagrams give detailed taxiway, runway, and ramp data at more than 2,500 airports in the United States, Canada, and Europe. A close up view of the airport layout can be seen in detail if you zoom in on an airport that has a Safetaxi diagram available. The flight crew can configure the zoom range at which the Safetaxi data is shown. When it is zoomed in close enough to show the airport detail, the map shows runways with numbers, taxiways with identifying letters/numbers, and airport landmarks that include ramps, buildings, control towers, and other important features. 2 When the airplane location is within the screen boundary and within Safetaxi ranges, an airplane symbol is shown on the navigation map views for enhanced situational awareness. During ground operations, the airplane's position is shown in reference to taxiways and runways. 3 The Safetaxi diagrams also show intersection hot spots. These are the FAA-designated taxi areas for which additional caution and awareness are necessary. They are not at every airport. 4 Safetaxi is an extension of the basemap. It is also used by the SurfaceWatch option (if available). Safetaxi must be updated every 56 days. (f) Chart (Jeppesen Chartview) 1 ChartView is similar to the paper version of Jeppesen terminal procedures charts. The charts are shown in full color and high-resolution. The MFD shows the airplane position on the moving map in the plan view of approach charts and on airport diagrams. 2 The ChartView database is available from Jeppesen that includes: • Arrivals (STAR) • Departure Procedures (DP) • Approaches • Airport Diagrams

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• Notice to Airmen (NOTAMs) • Geo-Referenced Charts (an airplane spotter is shown over the chart). 3 Chartview must be updated every 14 days. Functionality will disable after 70 days if the customer does not purchase updates. (g) Navigation 1 The Jeppesen Navigation database has the aeronautical data that is used by the G5000 system for the flight management and flight plan functions. It includes detailed data for waypoints, procedures (arrivals, departures, and approaches) and airways. This database must be updated every 28 days. (h) Airport Directory 1 The Airport Directory database comes from either the AOPA Airport Directory for domestic users or AC-U-KWIK for international users. The data is accessed through the airport waypoint pages and includes detailed supplementary data for airports. 2 The available data includes data on: • Traffic Pattern Altitudes • Runways (dimensions, surface, and lighting) • Airport Fixed Base Operators (fuel types, airplane maintenance services, rental car services, and other available services) • FSS and Weather Contacts • Navaids that serve the airport • Fuel prices • Nearby hotels and restaurants. 3 The Airport Directory database must be updated every 56 days. (i) Performance (PERF) and Takeoff and Landing (TOLD), Airplanes with G5000 software version 58 and higher. 1 The PERF/TOLD database is uploaded from the base software configuration SD card. Refer to this Chapter, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test and Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting for software loading and troubleshooting information. 2 Performance and prediction functions of this database include: • Takeoff and Landing Data • Weight and Fuel • Required Reserves • Climb Performance • Cruise Performance • Descent Performance • Flight Plan Legs • Targets (Singe engine and Drift-down data) 3 The TOLD function is a subset of the performance and prediction function that is based on the FAA Approved Airplane Flight Manual data. For more information, refer to the FAA Approved Model 700 Airplane Flight Manual. 4 The TOLD function calculates and displays V-speeds and takeoff and landing distances that based on current aircraft configuration, operational state, and sensed parameters used by the flight crew. C. Pilot Profiles (1) The G5000 system is a flexible system that lets the flight crew customize many flightdeck parameters. Any pilot can create a custom profile. Each profile has a log of settings that set up the flight deck configuration for the pilot's preference. These settings are keptinthe profile configuration and can include (but are not limited to) map settings, avionics settings, PFD settings, user waypoints, and weight and balance data. It is possible to import and export profiles off of the airplane with an SD card in the top slot of the MFD. This lets a flight crew take their custom profiles from one airplane with a G5000 system to another similarly equipped airplane. A profile that is created with a different version of the G5000 system software cannot beimported to the new system. (2) After the G5000 system powers on, the Initialization screen on the GTC shows the default pilot profile. The flight crew can select a different pilot profile on the Initialization screen ortheCrew Profile screen.

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(3) The pilot profiles are kept in the internal memory of the MFD. When a profile is activated, the settings are applied to the other displays in the system. Up to 18 profiles can be saved in the system. (4) A default pilot profile is supplied by Garmin that is always available to the flight crew. Thedefault pilot profile will be updated when a new G5000 software version is available.

3. Operation A. Garmin G5000 Integrated Avionics System Software (1) The Garmin G5000 Integrated Avionics System is a highly integrated avionics system that has its primary functions distributed throughout the various LRU's within the system. For more data about the Garmin G5000 Integrated Avionics System, refer to Chapter 42, Garmin G5000 Integrated Avionics System - Description and Operation. (2) Garmin LRU's within the G5000 system do not come loaded with the software and configurations for the intended installation. When a Garmin LRU is replaced with a new unit, the applicable software and configurations must be loaded to it. (3) There are three types of G5000 software configuration loading procedures. If the necessary software configurations are not loaded correctly, certain aircraft systems can be inoperable. (a) LRU Software Configuration 1 The LRU software configuration includes loading procedures for the various Garmin LRU's that are part of the core G5000 system. It is necessary to do the loading procedures for a specific LRU when that LRU has been replaced with a new unitor interchanged with another unit. (b) Option Software Configuration 1 The option software configuration includes loading procedures for the various options that can be installed on the airplane that interact with the G5000 system. It is not typically necessary to do the option loading procedures unless a specific option must be initially unlocked. (c) Base Software Configuration 1 The base software configuration includes loading procedures for the baseline G5000 system. It is not typically necessary to do the base software configuration loading procedures unless the entire G5000 system software must be loaded. Contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected] before any base software configuration loading procedures are tried. (4) The Garmin G5000 Integrated Avionics System can be updated to a newer version as necessary. On the pilot's right or copilot's left Garmin GTC 575 Touchscreen Control Unit, do as follows to see what software version is on your airplane: (a) Select Home. (b) Select Utilities. (c) Select Setup. (d) Select Avionics Status. (e) Select the Airframe tab. (5) On the pilot's right or copilot's left GTC, do as follows to access the pilot profiles: (a) Select Home. (b) Select Utilities. (c) Select Crew Profile.

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GARMIN G5000 INTEGRATED AVIONICS SYSTEM SOFTWARE - ADJUSTMENT/TEST

2. Garmin LRU Software Configuration Check A. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 42, Integrated Modular Avionics - General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List.

(1) Tools and Equipment • None. (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 37 Configuration - Adjustment/Test. • Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test. B. Prepare the Airplane for the Garmin LRU Software Configuration Check. (1) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. C. Do the Garmin LRU Software Configuration Check. (1) On the pilot's right Garmin GTC 575 Touchscreen Control Unit, do as follows to find the Garmin G5000 system software level: (a) Select Home. (b) Select Utilities. (c) Select Setup. (d) Select Avionics Status. (e) Select the Airframe tab. 1 Record the G5000 software version number that shows on the 'SYS SW Vers' line. (2) Choose the correct Software and Configuration Loading based on the software version recorded above: (a) Garmin G5000 Software Version 37. 1 Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 37 Configuration - Adjustment/Test. (b) Garmin G5000 Software Version 58. 1 Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test. D. Put the Airplane Back to its Initial Condition. (1) Disconnect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

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GARMIN G5000 INTEGRATED AVIONICS SYSTEM SOFTWARE (VERSION 58) - TROUBLESHOOTING (Airplanes -0033 and On)

1. General A. This section gives the troubleshooting procedures for the Garmin G5000 Integrated Avionics System Software (Version 58). For a general description of the Garmin G5000 Integrated Avionics System, refer to Chapter 42, Garmin G5000 Integrated Avionics System - Description and Operation. For a general description of the Garmin G5000 Integrated Avionics System Software, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Description and Operation B. The two Garmin GTC 575 Touchscreen Control Units installed on the pedestal (pilot's right and copilot's left) are the primary controllers of the Garmin G5000 Integrated Avionics System. For a general description of the GTC's, refer to Chapter 42, Garmin G5000 Integrated Avionics System - Description and Operation. C. For a more detailed overview of the crew alerting system (CAS) data, refer to the Garmin G5000 Integrated Avionics System Line Maintenance Manual found in the Introduction - Supplier Publication List. D. For the Garmin G5000 Integrated Avionics System block diagram, refer to txtavsupport.com as follows: (1) Access the website txtavsupport.com and log on with your User Name and Password. (2) Under the MY MODELS section, select 'Citation 700'. (3) Under the AVIONICS section (right side of the screen), select Model 700 G5000 System Block Diagram.

2. Garmin G5000 Integrated Avionics System Software (Version 58) Troubleshooting A. Tools and Equipment.

(1) Tools and Equipment • Multimeter • Software Loader Card. (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 27, Aileron Control System - Adjustment/Test • Chapter 27, Horizontal Stabilizer Trim Control System - Adjustment/Test • Chapter 31, Flight Data Recorder System - Adjustment/Test • Chapter 34, Angle-of-Attack (AOA) System - Adjustment/Test • Chapter 34, Garmin GWX 80 Weather Radar System - Adjustment/Test • Chapter 34, Garmin GRA 5500 Radio Altimeter System - Adjustment/Test • Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices • Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test • Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test. B. Garmin G5000 In-Air Configuration Lockout. (1) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (2) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select GDU Controls.

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NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(e) Turn the right inner knob to highlight the System Status page. (f) Select MISC KEYS. (g) Enter the key sequence that follows: 1. SKEY12 2. SKEY11 3. SKEY10 4. SKEY12. (3) Make sure that the IN-AIR CONFIGURATION LOCKOUT annunciation does not show on the pilot's primary flight display (PFD). (4) If necessary, do the steps again for the multifunction display (MFD) and the copilot's PFD. C. Avionics Status Shows Amber Checkbox. (1) Remove the applicable line replaceable unit (LRU) from its mounting tray or disconnect the electrical connector(s) from the LRU. (2) Do a check of the electrical connector(s) for bent pin contacts or pushed back pin contacts/ sockets. (a) Repair the unserviceable pin contacts as necessary. (3) Install the applicable LRU to the mounting tray or connect the electrical connector(s) to the LRU. (4) Make sure that electrical power is at the LRU and the electrical connector(s). (5) Make sure that ground signals are at the electrical connector(s). (6) Make sure that the data bus lines are correctly installed. (a) Use a multimeter to do a check for continuity between the electrical wires.

NOTE: Do a continuity check for all high-speed data bus (HSDB) connections and ARINC 429 connections between the Garmin components.

NOTE: ARINC 429 data bus to third party LRU's will not have an effect on the software loading procedure.

(7) If applicable, make sure that location configuration strapping wiring is present and correct. (8) Make sure that all other configuration strapping wiring is present and correct. (9) For more assistance, contact Textron Aviation Customer Service. For contact information, refer to the Introduction D. Fuel Quantity Shows in Kilograms Instead of Pounds. (1) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (2) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select GDU Controls. (c) Make sure that PFD1 is selected. (d) Turn the right outer knob until the System tab is selected.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(e) Turn the right inner knob to highlight the System Setup page. (f) Push the right inner knob to activate the cursor. (g) Turn the right outer knob until the FUEL line is selected under the DISPLAY UNITS field. (h) Turn the right inner knob to select the POUNDS selection.

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(3) Cycle the electrical power to the airplane into normal mode.

NOTE: To put the G5000 Avionics System into Normal Mode, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices, Garmin G5000 Integrated Avionics System Configuration Mode Maintenance Practices, Put the Garmin G5000 Integrated Avionics System into Normal Mode.

(4) As the airplane powers on, make sure that the fuel display shows pounds. E. Software Not Loading to LRU. (1) Cycle the electrical power to the airplane. (2) Try to load the software again. (3) Disengage any redundant components and try to load the software.

NOTE: For example, if you cannot load the software to the GIA #1, disengage the circuit breakers for the GIA #2.

(4) Cycle the electrical power to the airplane. (5) Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (6) Try to load the software again. (7) Make sure that the electrical wiring installation and the data bus communication to the LRU is correct. Refer to Avionics Status Shows Amber Checkbox, in this section. (8) Move the LRU that you think is unserviceable to its redundant location and load the software again. (9) Move the LRU that you think is unserviceable back to its initial location when complete. (10) Remove and replace the LRU that you think is unserviceable. (11) For more assistance, contact Textron Aviation Customer Service. For contact information, refer to the Introduction F. Transaction Log Does Not Show Passed for Base Configuration. (1) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select GDU Controls. (c) Make sure that PFD1 is selected. (d) Turn the right inner and outer knob until the System tab is selected. (e) Select the TRANSACTION LOG page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(f) Select the Left and Right arrows until Detail is highlighted at the bottom of the pilot's PFD. (g) Select Detail. (h) Push the right inner knob to activate the cursor. (i) Highlight the Model 700 Base item. 1 Select Enter to expand the list. (j) Turn the right outer knob to scroll down the list to find which item failed. (k) Go back to the System Upload page. 1 Load the line item that failed again. (l) Go back to the TRANSACTION LOG page. 1 Make sure that the Model 700 Base shows PASS. (2) If the line item still shows not passed, do as follows: (a) Do the Software Reconfiguration as follows: 1 Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. 2 Delete Unwanted Enablement Cards from Internal Memory. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test.

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3 Do the Base Configuration Load Procedure. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 4 Do the Airplane Options Load Procedure with Base Software Loader Card. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 5 Do the Airplane Options Load Procedure with Enablement Loader Card(s). Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 6 Do the CMC Configuration Transaction ID Verification. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 7 Do the Airframe Configuration Setup. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 8 Do the Configuration Module Programing. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 9 Do the Configuration Confirmation. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. 10 Do the Software Verification - Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. G. Transaction ID Status Troubleshooting.

NOTE: The Transaction Log Summary page reports a status for each configuration item that is loaded to the system. This section will explain the different statuses that the system will report and what each means to help do the troubleshooting of the system. The Transaction Log Summary page has four columns: Loader Image, Group, Item, and Status.

(1) Loader Image will show which SD card the configuration was loaded from. (2) Group shows which entry in the Group field on the System Upload page was selected. (3) Item shows which entry in the Item field on the System Upload page was selected. The system uses the Item field to determine which pieces of configuration should be loaded to the system. (4) Status shows the status for all configuration pieces of an Item. Each loader card comes preloaded with the expected transaction ID for each configuration item. As you load the configuration items, the transaction ID is compared to the preloaded expected transaction ID. Refer to Table 101 for a description of each Status.

Table 101. Definition of Transaction ID Status

Transaction ID Status Definition Green PASS Shows all configuration for the applicable Item was loaded and passed. Amber INCOMPLETE Shows there was a(were) piece(s) of configuration for the applicable Item that was not loaded. This is most likely because a piece of configuration was unchecked and not loaded. Red FAIL Shows there was a(were) piece(s) of configuration for the applicable Item that failed during loading. This could be because the configuration failed and would never load to the system or it did not return to the correct transaction ID.

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Table 101. Definition of Transaction ID Status (continued) Transaction ID Status Definition White NO TRANS ID Shows the Item loaded did not come preloaded with the expected transaction ID, so no comparison was done. You must do the manual comparison of the transaction ID for each piece of configuration. White AIRCRAFT ID UPDATED Shows the CNFM AC softkey was pushed and the Expected Aircraft ID was updated to match the Actual Aircraft ID on the CONFIGURATION MANAGER page. This is usual operation when known airplane specific configuration changes, such as rigging, radar tilt, AOA calibration, etc. Amber FLEET ID UPDATED Shows unauthorized configuration items have changed outside of loading bas SW or options. Do the Software Reconfiguration, in this section, to make sure that the Fleet ID's correctly agree.

H. Airplane Icon Does Not Look Like a Longitude (Model 700). (1) Turn the dimming switches that follow fully counterclockwise to the OFF position: • Pilot's PFD • MFD • Copilot's PFD. (2) If necessary, connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (3) Put the applicable software loader card into the top SD card slot of the copilot's PFD. (4) Turn the copilot's PFD dimming switch clockwise to the full bright position.

NOTE: The copilot's PFD will automatically load the airplane icon.

(5) After the copilot's PFD boots up, it will be in configuration mode. (6) Remove the software loader card from the copilot's PFD. (7) Do the steps again for the MFD and the pilot's PFD. (8) Remove the software loader card from the pilot's PFD. (9) Disconnect external electrical power from the airplane and connect it again. Refer to Chapter 24, External Electrical Power - Maintenance Practices. (10) Make sure that the airplane icon looks like a Longitude on the two PFD's and the MFD's moving map. I. An Item on the Configuration Manager Does Not Report Valid (1) If the Status field for a Configuration Item is blank, give the system more time to report aStatus. Possibly switch to another page and then go back. (2) If the Status is still not Valid, Load the Software and Configurations to the Garmin LRU's for that applicable item. Refer to Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test. (3) If the Status is still not Valid, do the Software Reconfiguration, in this section. J. During Software Loading, a GSD Continuously Resets.

NOTE: If a GSD continuously resets during software loading, software loading failures can occur. During the software load, the GSD reset will show on the MFD's System Status page in the GIA's/GSD's ONLINE window. One of the check boxes next to a GSD will go between a red X and a green check a few times before the software load eventually fails.

(1) If possible, record the Software/Configuration item at which the software failure occurred. (2) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices.

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(3) Do as follows: (a) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (b) On the pilot's right GTC use the inner and outer knobs to navigate to the GDU tab on the AIRCRAFT CONFIGURATION page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

NOTE: The cursor will show in the GAUGES window.

(d) Turn the outer knob on the pilot's right GTC to move the cursor in the AIRFRAME WINDOW in the AIRCRAFT SN field. (e) Enter the Aircraft Serial Number with pilot's right GTC. • The inner knob changes the character in the selected field. • The outer knob changes the selected field.

NOTE: The serial number must be entered as 7005858. The 5858 signifies the serial number.

(f) Touch ENTER to accept the changes made to the Aircraft Serial Number.

CAUTION: If the Aircraft Serial Number that was entered was changed after the rudder control system (SECU) rigging was completed, the rigging must be completed again.

(4) Confirm Configuration. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. (5) Do the Configuration Module Programming. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. (6) Continue with Software Loading at the item where the FAIL message was recorded. K. A System Message Reports a Database Problem. (1) Make sure that the G5000 Avionics System is on, in normal mode, and in an on ground condition.

(2) On the pilot's right GTC, do as follows: • Select Home • Select Utilities • Select Setup • Select Database Status.

NOTE: Most database errors can be corrected by cycling the power to the system and waiting for synchronization to complete.

(3) Do the Loading Database procedure. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test, Database Card Loading Procedures. (4) If the database error is corrected, the troubleshooting is complete. If not, continue with the troubleshooting.

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CAUTION: The steps that follow will erase all databases. You should only do this when all other attempts have failed.

(5) On the pilot's right GTC, do as follows: • Select Home • Select Utilities • Select Setup • Select Database Status • Select Database Options • Select Delete Databases • Select OK • Select Select All for the Standby and the Active columns. (6) Remove electrical power from the system. (7) After 20 seconds, connect the electrical power. (8) If you do not see the message that follows on the GDU's during the power on, it can be necessary to cycle the electrical power again: • INITIALIZING SYSTEM • DELETING SELECTED INTERNAL DATABASES. (9) To confirm that the databases have been deleted, do as follows from the pilot's rightGTC: • Select Home • Select Utilities • Select Setup • Select Database Status.

NOTE: All Active databases will show MISSING.

NOTE: All Standby databases will show NONE.

NOTE: The Checklist will show NONE in the two columns.

(10) Do the Database Card Loading Procedures. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. L. Applicable Steps to Clear a SYSTEM CONFIG System Message. (1) If the MANIFEST system message shows, do the Applicable Steps to Clear a MANIFEST System Message procedure, in this section. (2) If the AVIONICS CONFIG crew alerting system (CAS) message shows, do the Applicable Steps to Clear an AVIONICS CONFIG Crew Alerting System (CAS) Message procedure, in this section. (3) Do the Expected Airplane ID Does Not Match the Actual Airplane ID procedure, in this section. M. Expected Airplane ID Does Not Match the Actual Airplane ID. (1) Make sure that the G5000 Avionics System is in configuration mode. (a) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (2) Make sure that the settings that follow are correct: (a) Do the Airplane Configuration Setup. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. (b) Do the Airframe Configuration Setup. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test. (c) If you made any corrections to the settings, do the Configuration Confirmation. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test.

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(3) If there were changes to the systems that follow (that is a sensor replacement), it will be necessary to do the rigging for that applicable system again.

NOTE: If the cause of the Airplane ID change is unknown, the rigging for all of the systems must be done again.

(a) For changes to the weather radar system (roll trim and tilt), do the Garmin GWX 80 Weather Radar System Operational Check. Refer to Chapter 34, Garmin GWX 80 Weather Radar System - Adjustment/Test. (b) For changes to the aileron trim pointer, do the Aileron Trim Pointer Rigging. Refer to Chapter 27, Aileron Control System - Adjustment/Test. (c) For changes to the rudder trim, do the Rudder Trim Rigging. Refer to Chapter 27, Rudder Trim Control System - Adjustment/Test. (d) For changes to the horizontal stabilizer electrical trim, do the Horizontal Stabilizer Trim Electrical Rigging. Refer to Chapter 27, Horizontal Stabilizer Trim Control System - Adjustment/Test. (e) For changes to the optional control wheel position sensor, do the Control Wheel Position Sensor Rigging. Refer to Chapter 31, Flight Data Recorder System - Adjustment/Test. (f) For changes to the optional control column position sensor, do the Control Column Position Sensor Rigging. Refer to Chapter 31, Flight Data Recorder System - Adjustment/Test. (g) For changes to the stall warning/angle-of-attack (AOA) system, do the Angle-of-Attack (AOA) System Calibration and the Angle-of-Attack (AOA) System Functional Check. Refer to Chapter 34, Angle-of-Attack (AOA) System - Adjustment/Test. (h) For changes to the radio altimeter system, do the Garmin GRA 5500 Radio Altimeter System Calibration. Refer to Chapter 34, Garmin GRA 5500 Radio Altimeter System - Adjustment/Test. N. Applicable Steps to Clear a MANIFEST System Message.

NOTE: The MANIFEST system message tells the operator when there is incorrect or missing software.

(1) Examine for LRU installation issues as follows: (a) Record the LRU listed in the MANIFEST system message. (b) If the LRU is missing because an option was removed but the software option is still installed, do the Software Reconfiguration, in this section. (c) Examine the applicable LRU to make sure that it is the correct part number for the airplane model. (d) If you replaced an LRU, do the Load the Software and Configurations to the Garmin LRU's for the applicable LRU. Refer to Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test. (e) If the problem stays, continue with the troubleshooting. (2) If incorrect software is found on an LRU, do as follows: (a) Do the Software Reconfiguration, in this section. 1 During the Base Configuration Load Procedure and after CHK CFG is highlighted, make sure that the software box adjacent to the applicable LRU stays checked. 2 If the system did not automatically check the software box next to the applicable LRU, manually add the check.

NOTE: Not every line item related to an LRU will have a software box that can be checked.

NOTE: The Software Reconfiguration will replace the missing/old software and make sure that the new software is correctly loaded. O. Applicable Steps to Clear an AVIONICS CONFIG Crew Alerting System (CAS) Message. (1) Do the Software Reconfiguration, in this section. P. During Software Loading, GCU #2 Fails to Load Configuration. (1) Disengage the L PFD GCU circuit breaker on the left circuit breaker panel.

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(2) Disengage the MFD and the MFD AUX circuit breakers on the right circuit breaker panel. (3) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select the Left and Right arrows until CLR ALL is highlighted at the bottom of the pilot's PFD. (c) Select CLR ALL. (4) If necessary, push the right inner knob on the pilot's right GTC to activate the cursor. (5) On the pilot's right GTC, do as follows: (a) Turn the outer knob to put a check in the box related with the GCU #2 configuration.

NOTE: This should be the only item checked.

(b) Select the Left and Right arrows until Load is highlighted at the bottom of the pilot's PFD. (c) Select Load.

NOTE: The GCU #2 should now have the configuration correctly loaded, but UPLOAD and CROSSFILL will fail because the MFD is not energized. If the GCU #2 shows PASS, this is permitted.

(d) Select OK. (6) Engage the L PFD GCU circuit breaker on the left circuit breaker panel. (7) Engage the MFD and the MFD AUX circuit breakers on the right circuit breaker panel. (8) On the pilot's right GTC, do as follows: (a) Turn the outer knob to put a check in every box. 1 Make sure that you start with GCU275 1 software. (b) Select the Left and Right arrows until Load is highlighted at the bottom of the pilot's PFD. (c) Select Load.

NOTE: The GCU #2 should now have the configuration correctly loaded, but UPLOAD and CROSSFILL will fail because the MFD is not energized. If the GCU #2 shows PASS, this is permitted.

(d) Select OK. (9) If necessary, continue with the Base Software/Configuration Load Procedures. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Adjustment/Test.

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GARMIN G5000 INTEGRATED AVIONICS SYSTEM SOFTWARE (VERSION 58) - ADJUSTMENT/TEST (Airplanes -0033 and On)

1. General A. This section gives the adjustments and test necessary for the Garmin G5000 Integrated Avionics System software. For a general description of the Garmin G5000 Integrated Avionics System software, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Description and Operation. B. The procedures to upload the Garmin G5000 Integrated Avionics System software and configuration files are included in this section. For more data applicable to the Model 700 G5000 softwareand configuration uploading procedures, refer to Section 6 and Section 8 of the most current revisionof the Garmin G5000 Integrated Avionics System Line Maintenance Manual, P/N 190-02403-00, found in the Introduction, Supplier Publication List.

NOTE: Each Garmin G5000 system software version has unique procedures. It is necessary to make sure that the correct procedures are used for the software version that is installed on the airplane. C. The software upload and the G5000 configuration file system upload procedures are given inthis section for the Garmin display units (GDUs) and the Garmin Touchscreen Controllers (GTCs). The GDUs include the pilot's and copilot's Primary Flight Displays (PFD 1 and PFD 2), respectively, the multifunction display (MFD), and the pilot's left and right GTCs and copilot's left and right GTCs. This section also gives the G5000 system LRU and optional system LRU software and configuration files upload procedures. D. The GTCs and the PFDs and MFD are used in the software and configuration upload procedures. Each display unit has secure digital (SD) card slots in the top right portion of the display bezel. The SD cards are inserted for the software/configuration uploads. For more data applicable to the GTCs, PFDs, and MFD refer to Garmin G5000 Integrated Avionics System - Description and Operation. E. Garmin G5000 Integrated Avionics System line replaceable units (LRUs) do not need software or configuration files uploaded that are removed and installed again in the same airframe position (same location). Garmin LRUs must have software and configuration files uploaded when the conditions that follow occur: • Garmin LRUs that are replaced • Garmin LRUs that are swapped in airframe position or in a different location • For troubleshooting and to restore correct operation of the affected system. F. Tools and Equipment

NOTE: Software must be ordered from Textron Aviation.

• Garmin G5000, Cessna 700 Software Loader Card - PN# 010-02010-14 • Cessna G5000 Default Pilot Profile Software Loader Card - PN# 8203142-8 • CMC Viewer Card - PN# 8204541-21 • Database Loader Card - PN# 010-00474-50

Table 501. Approved Transaction ID Items for Software Version 58

Loader Image Group Item 006-B2257-58 Model 700 Base Configuration Model 700 Base 006-B2257-58 Model 700 Base Configuration Load Default GEA Rigging Table 006-B2257-58 Options ACARS – ARINC Direct 006-B2257-58 Options ACARS – Honeywell GDC 006-B2257-58 Options ACARS – Satcom Direct

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Table 501. Approved Transaction ID Items for Software Version 58 (continued) Loader Image Group Item 006-B2257-58 Options FK632D- Second HF (Full Up) 006-B2257-58 Options FK632L- SiriusXM (Weather/ Music) 006-B2257-58 Options FK658A- ADF 006-B2257-58 Options FK658E- ADF2 006-B2257-58 Options FK676B- Iridium Data Radio 006-B2257-58 Options FK676D- Laseref VI 006-B2257-58 Options FK738G – Crew Jumpseat 006-D4506-FB Enable_Link2000CPDLC Enable Link 2000+ CPDLC 010-00330-J5 Enable_FANS FANS 1/A Enable 010-00330-5K Enable_SurfaceWatch Enable SurfaceWatch 006-D4506-FG Enable_SAR Enable Enhanced Search and Rescue Reserved 8204542-17 V2.60 Model 700 CMC Config (Note 1) None None CNFRM CFG (Note 2)

NOTE 1: Longitude CMC must only have a STATUS of white NO TRANS ID. Refer to Chapter 45, Update CMC Configuration/CMC Viewer Version - Maintenance Practices for CMC verification.

NOTE 2: CNFRM CFG must only have a STATUS of white AIRCRAFT ID UPDATED or not be listed. G. Reference Material • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 33, Flight Compartment Lighting - Description and Operation • Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices • Chapter 42, Garmin G5000 Integrated Avionics System - Troubleshooting • Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test • Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting • Chapter 45, View CMC Diagnostics System Version Numbers - Maintenance Practices • Chapter 45, Update CMC Configuration/CMC Viewer Version - Maintenance Practices.

2. Garmin G5000 System Useful Specifics A. Before you continue with the Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration, the specifics that follow are useful to know: (1) The pilot's right Garmin GTC 575 Touchscreen Control Unit is the primary control unit when the G5000 is in configuration mode. (2) The dual concentric knobs on the lower right of the GTC are used and are referred to as the small and large flight management system (FMS) knobs. (3) In the G5000 configuration mode, the GDU Controls screen on the GTC is used to control the system. (a) On the GTC Home (Config Mode) screen, select GDU Controls on the left side of thescreen to show the GDU Controls screen. (b) Make sure that PFD 1 on the left side of the GDU Controls screen on the GTC is selected to control the pilot's primary flight display (PFD). (c) On the GDU Controls screen, use Enter on the lower right section of the screen along with the FMS knobs to navigate and select items on the PFD and the multifunction display (MFD).

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(d) On the GDU Controls screen, use Select and the Left and Right arrows to select the soft key items on the bottom of the PFD and the MFD. (4) The PFD's and the MFD can be individually powered down if you turn the outer knob of the left PFD-GTC DIM switch, MFD-GTC DIM switch, or the right PFD-GTC DIM switch counterclockwise to shut off the display unit. Refer to Chapter 33, Flight Compartment Lighting - Description and Operation for the location of the left PFD-GTC DIM switch, MFD-GTC DIM switch, and the right PFD-GTC DIM switch.

3. Airplane Setup A. The airplane setup must be competed before loading or verifying any software loads. (1) Make sure that the circuit breakers in Table 502 are engaged.

Table 502. Circuit Breakers

LRU CB Name Model 700 Requirement NAV IAU 1 Core Component NAV IAU 1 AUX Core Component GIA 64E #1 COM 1 Core Component COM 1 AUX Core Component NAV IAU 2 Core Component GIA 64E #2 NAV IAU 2 AUX Core Component COM 2 Core Component GDU 1450W (PFD 1) R PFD Core Component PFD 1 Core Component GDU 1450W (PFD 2) PFD 1 AUX Core Component MFD Core Component GDU 1450W (MFD) MFD AUX Core Component GDL 59 MAINT Core Component GSD 41 #1 DCU 1 Core Component DCU 2 Core Component GSD 41 #2 DCU 2 AUX Core Component DCU 3 Core Component GSD 41 #3 DCU 3 AUX Core Component ENGINE INTER 1 Core Component GEA 7100 #1 ENGINE INTER 1 AUX Core Component ENGINE INTER 2 Core Component GEA 7100 #2 ENGINE INTER 2 AUX Core Component ENGINE INTER 3 Core Component GEA 7100 #3 ENGINE INTER 3 AUX Core Component AUDIO 1 Core Component GMA 36B #1 AUDIO 1 AUX Core Component

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Table 502. Circuit Breakers (continued) LRU CB Name Model 700 Requirement AUDIO 2 Core Component GMA 36B #2 AUDIO 2 AUX Core Component GTC 575 #1 MFD L GTC Core Component GTC 575 #2 MFD R GTC Core Component GTC 575 #3 PFD 1 GTC Core Component GTC 575 #4 R PFD GTC Core Component GTX 3000 #1 XPDR 1 Core Component GTX 3000 #2 XPDR 2 Core Component GDC 7400 #1 ADC 1 Core Component GDC 7400 #2 ADC 2 Core Component GCU 275 #1 PFD 1 GCU Core Component GCU 275 #2 R PFD GCU Core Component GDR 66 DATA COM Core Component GMC 7200 AFCS CONT Core Component GSA 9000 ROLL SERVO Core Component PITCH SERVO Core Component GSA 9000 PITCH SERVO AUX Core Component GTS 8000 TCAS Core Component GWX 80 WEATHER RADAR Core Component GSR 56 #1 IRIDIUM DATA 1 Core Component GRA 5500 RAD ALT Core Component MISSION FEED #1 Necessary for Electrical Power MISSION FEED #2 Necessary for Electrical Power MISSION FEED #3 Necessary for Electrical Power Right Electrical EMER FEED #1 Necessary for Electrical Power EMER FEED #2 Necessary for Electrical Power EMER FEED #3 Necessary for Electrical Power MISSION FEED #1 Necessary for Electrical Power MISSION FEED #2 Necessary for Electrical Power MISSION FEED #3 Necessary for Electrical Power Left Electrical EMER FEED #1 Necessary for Electrical Power EMER FEED #2 Necessary for Electrical Power EMER FEED #3 Necessary for Electrical Power

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Table 502. Circuit Breakers (continued) LRU CB Name Model 700 Requirement GSR 56 #2 IRIDIUM DATA 2 Optional Component GHD 2100 HUD Optional Component GDL 69A XM DATALINK Optional Component

NOTE: The circuit breakers for the optional components must be engaged if the component is installed.

(2) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

4. Complete Software Loading Overview A. General (1) This section gives the steps necessary to complete the Garmin G5000 Complete Software Loading procedure and is necessary to be completed when the installed aircraft system software is not the correct software load.

NOTE: The steps must be completed in the sequence given.

(2) The Garmin G5000 Base Software Complete Software Loading includes the steps as given in Table 503.

Table 503. Complete Software Loading Procedures Overview

Complete Software Loading Mode Airplane Setup N/A Put the Garmin G5000 Integrated Avionics System into Configuration Mode Refer to N/A Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices Delete Unwanted Software and Options from Internal Memory Configuration PFD 1 Software Load Configuration Base Software/Configuration Installation Configuration Default Electronic Rigging Tables Load Procedure Configuration Airplane Options Load Procedure with Base Software Loader Card Configuration Airplane Options Load Procedure with Enablement Loader Card(s) Configuration CMC Configuration Configuration Airplane Configuration Setup Configuration Airframe Configuration Setup (Complete Software Load) Configuration Configuration Module Programing Configuration Configuration Confirmation Configuration Software Verification - Configuration Mode Configuration Load the Default Pilot Profile Normal Wi-Fi Favorite Setup Normal

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Table 503. Complete Software Loading Procedures Overview (continued) Complete Software Loading Mode CMC Viewer/CDMS Install Normal Software Verification - Normal Mode Normal End Software Load N/A

5. Configuration Loading Overview A. General (1) This section gives the steps necessary to complete the Garmin G5000 Configuration Loading procedure and is necessary to be completed when the base configuration must be reached for troubleshooting or other reasons as given in Table 504.

NOTE: The steps must be completed in the sequence given.

Table 504. Configuration Loading Procedures Overview

Configuration Loading Mode Airplane Setup N/A Put the Garmin G5000 Integrated Avionics System into Configuration Mode Refer to N/A Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices Delete Unwanted Enablement Cards from Internal Memory Configuration Base Configuration Load Procedure Configuration Airplane Options Load Procedure with Base Software Loader Card Configuration Airplane Options Load Procedure with Enablement Loader Card(s) Configuration CMC Configuration Configuration Airframe Configuration Setup (Configuration Loading) Configuration Configuration Module Programing Configuration Configuration Confirmation Configuration Software Verification - Configuration Mode Configuration Load the Default Pilot Profile Normal Wi-Fi Favorite Setup Normal CMC Viewer/CDMS Install Normal Software Verification - Normal Mode Normal End Software Load N/A

6. LRU Replacement Overview A. General (1) For the software replacement information, Refer to Chapter 42, Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration - Adjustment/Test.

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7. System Preparation and PFD 1 Software Loading A. Delete Unwanted Software and Options from Internal Memory

NOTE: The Garmin system copies installed software and options to internal memory for easy future reloading and to support the LRU replacement feature. The system also removes old copies that are not "in-use" when newer versions are installed. However, sometimes the system keeps old data. The following steps will make sure that the LRU replacement feature only has data from the current software version.

(1) Do the Airplane Setup in this section.

NOTE: All steps below will use the pilot's right GTC for control of the system.

(2) If not already on the GDU controls page, select HOME and then select GDU CONTROLS. (a) Make sure that PFD 1 is selected. (3) Turn the right inner and outer knobs to navigate to the SYSTEM tab, then the LRU REPLACEMENT page (Refer to Figure 501).

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(4) Select the LEFT and RIGHT ARROWS until MANAGE is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will show the Card Copy Management window (Refer to Figure 502).

(5) Turn the right inner knob to highlight the item you want to delete. (6) Select the LEFT and RIGHT ARROWS until DELETE is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will delete the item highlighted in the Card Copy Management window.

(7) Do the steps again until all items are deleted. (8) Select the LEFT and RIGHT ARROWS until CANCEL is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will close the Card Copy Management window. B. Delete Unwanted Enablement Cards from Internal Memory

NOTE: The Garmin system copies installed software and options to internal memory for easy future reloading and to support the LRU replacement feature. Options loaded from an Enablement Card must be deleted when they are no longer necessary.

(1) Do the Airplane Setup in this section.

NOTE: All steps below will use the pilot's right GTC for control of the system.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

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LRU Replacement Figure 501 (Sheet 1)

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Copy Card Management Window Figure 502 (Sheet 1)

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(4) Select the LEFT and RIGHT ARROWS until MANAGE is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will show the Card Copy Management window (Refer to Figure 502).

(5) Turn the right inner knob to highlight the item you want to delete. Refer to Table 505 to find the items to delete.

Table 505. Types of Software Stored in Internal SD Memory

Software Item Listed Type of Software Notes 06-B2257-58 Software Loader Card Keep the current software version. 8204542-17 CMC Configuration Card Keep the CMC version. 006-D4506-58 or 010-00330-58 Enablement Card Delete enablement cards that are not necessary. (6) Select the LEFT and RIGHT ARROWS until DELETE is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will delete the item highlighted in the Card Copy Management window.

(7) Do the steps again until all unnecessary software is removed. (8) Select the LEFT and RIGHT ARROWS until CANCEL is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will close the Card Copy Management window. C. PFD 1 Software Load (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) Turn the dimming switch on the PFD 1 fully counter-clockwise to the Off position. (4) If installed, remove any software SD card from the PFD 1 top slot. (5) Install the 010-02010-14 loader card in the PFD 1 top slot. (a) Make sure that the card stays in the PFD 1 top slot for the full software loading procedure. (6) Turn the dimming switch on the PFD 1 fully clockwise to the full bright position. (a) Make sure that the INITIALIZING SYSTEM message shows in the top left corner of the PFD 1 after the PFD 1 initialization is complete. (7) Make sure that the SYSTEM UPLOAD page is shown on the PFD 1 (Refer to Figure 503).

NOTE: When the SYSTEM UPLOAD page is shown on the PFD 1, the software load for the PFD 1 is complete.

8. Airplane Base Software/Configuration A. Base Software/Configuration Installation

NOTE: All steps below will use the pilot's right GTC for control of the system.

(1) Make sure that the SD loader card is in the PFD 1 top slot for the full software loading procedure. (2) Do the Airplane Setup in this section. (3) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (4) If not already on the GDU controls page, select HOME and then select GDU CONTROLS. (a) Make sure that PFD 1 is selected.

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Garmin Display Unit (GDU) Configuration Mode Displays Figure 503 (Sheet 1)

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(5) Make sure that the SYSTEM UPLOAD page is shown on the PFD 1. (Refer to Figure 503). (a) If not, turn the right inner and outer knobs to navigate to the SYSTEM tab then the SYSTEM UPLOAD page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(6) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated. (7) Turn the inner knob to highlight the SD CARD line in the CARD window.

NOTE: If the software that you want to load has been loaded before, you can select that version from the drop down CARD window. Make sure to not use software versions before the current version.

(a) Select the ENTER button to select the card item. (8) On the pilot's right GTC, turn the right inner knob to highlight the 700 BASE CONFIGURATION line item in the GROUP window. (Refer to Figure 504). (a) Push the ENTER button to select the GROUP item. (b) Make sure that MODEL 700 BASE CONFIGURATION is found under the ITEM window. (9) On the pilot's right GTC turn the inner knob to highlight MODEL 700 BASE. (Refer to Figure 504). (a) Push the ENTER button to select the ITEM. (b) Make sure that the correct model is shown the ITEM window after the PRODUCT window is populated with data. (Refer to Figure 504). (c) Make sure that a list of software items are displayed in the PRODUCT window. (10) Select the LEFT and RIGHT ARROWS until CHK ALL is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will check all of the check boxes.

(11) Select the LEFT and RIGHT ARROWS until LOAD is highlighted at the bottom of PFD 1. (a) Select the LOAD softkey on PFD 1 to install the full base software and configuration.

NOTE: Do not cancel a software load in progress. If a failure occurs, wait until the fail message appears before proceeding.

(12) Monitor the upload status. (13) If the software or configuration upload fails do the steps that follow:

NOTE: The upload must be completed from the file that failed. The check boxes for the items that failed will stay checked.

(a) Push the inner knob to acknowledge the Load Fail prompt. (b) Do the LOAD steps again. (c) If the upload fails again, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. (14) Make sure that the 'Upload and Crossfill Complete' window shows on the display. (Refer to Figure 504). (a) On the pilot's right GTC select the ENTER button to acknowledge the message. (15) On the pilot's right GTC, press the right inner knob to deactivate the cursor. (16) On the pilot's right GTC, turn the right inner and outer knobs to navigate to the SYSTEM tab then the TRANSACTION LOG page. (17) Select the LEFT and RIGHT ARROWS until SUMMARY is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will show the Transaction Log Summary Page.

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Base Software/Configuration Screens Figure 504 (Sheet 1)

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Base Software/Configuration Screens Figure 504 (Sheet 2)

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(18) Make sure that there is only one entry for ITEM Model 700 Base Configuration and the STATUS is PASS. (a) If the STATUS is not PASS, refer to Garmin G5000 Integrated Avionics System Software - Troubleshooting. B. Default Electronic Rigging Tables Load Procedure

CAUTION: This procedure will erase all rigging values stored before on the GEA. This section must only be completed during the initial software load to the airplane or if a GEA Configuration module is replaced.

NOTE: All steps below will use the pilot's right GTC for control of the system.

(1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) If not already on the GDU controls page, select HOME and then select GDU CONTROLS. (a) Make sure that PFD 1 is selected. (4) Make sure that the SYSTEM UPLOAD page is shown on the PFD 1. (Refer to Figure 503). (a) If not, turn the right inner and outer knobs to navigate to the SYSTEM tab then the SYSTEM UPLOAD page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated. (6) Turn the inner knob to highlight the software's part number line item in the CARD window.

NOTE: If the software line item that you want to load will include the software part number. Refer to Table 501 for the correct software number.

(a) Select the ENTER button to select the card item. (7) On the pilot's right GTC, turn the right inner knob to highlight the 700 BASE CONFIGURATION line item in the GROUP window. (Refer to Figure 504). (a) Push the ENTER button to select the GROUP item. (b) Make sure that MODEL 700 BASE CONFIGURATION is found under the ITEM window. (8) On the pilot's right GTC, turn the right inner knob to highlight LOAD DEFAULT GEA RIGGING TABLE (Erase Current Rigging Values). (a) Push the ENTER button to select the ITEM. (b) Make sure that the correct model is shown the ITEM window after the PRODUCT window is populated with data. (Refer to Figure 505). (c) Make sure that a list of software items are displayed in the PRODUCT window. (9) Select the LEFT and RIGHT ARROWS until CHK CFG is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will check all of the configuration check boxes.

(10) Select the LEFT and RIGHT ARROWS until LOAD is highlighted at the bottom of PFD 1. (a) Select the LOAD softkey on PFD 1 to load the Default GEA Rigging Tables.

NOTE: Do not cancel a software load in progress. If a failure occurs, wait until the fail message appears before proceeding.

(11) Monitor the upload status.

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System Upload – Electronic Rigging Figure 505 (Sheet 1)

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(12) If the software or configuration upload fails do the steps that follow:

NOTE: The upload must be completed from the file that failed. The check boxes for the items that failed will stay checked.

NOTE: All steps below will use the pilot's right GTC for control of the system.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(6) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated. (7) Turn the inner knob to highlight the software's part number line item in the CARD window.

NOTE: If the software line item that you want to load will include the software part number. Refer to Table 501 for the correct software number.

(a) Select the ENTER button to select the card item. (8) On the pilot's right GTC, turn the right inner knob to highlight the 700 BASE CONFIGURATION line item in the GROUP window. (Refer to Figure 504). (a) Push the ENTER button to select the GROUP item. (b) Make sure that MODEL 700 BASE CONFIGURATION is found under the ITEM window. (9) On the pilot's right GTC turn the inner knob to highlight MODEL 700 BASE. (Refer to Figure 504). (a) Push the ENTER button to select the ITEM. (b) Make sure that the correct model is shown the ITEM window after the PRODUCT window is populated with data. (Refer to Figure 506). (c) Make sure that a list of software items are displayed in the PRODUCT window. (10) Select the LEFT and RIGHT ARROWS until CHK CFG is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will check all of the configuration check boxes.

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Garmin Display Unit (GDU) System Upload – Model Upload Figure 506 (Sheet 1)

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(11) Select the LEFT and RIGHT ARROWS until LOAD is highlighted at the bottom of PFD 1. (a) Select the LOAD softkey on PFD 1 to install the full base software and configuration.

NOTE: Do not cancel a software load in progress. If a failure occurs, wait until the fail message appears before proceeding.

(12) Monitor the upload status. (13) If the software or configuration upload fails do the steps that follow:

NOTE: The upload must be completed from the file that failed. The check boxes for the items that failed will stay checked.

NOTE: This will show the Transaction Log Summary Page.

9. Airplane Options Load Procedure

NOTE: Some options are available on the Base Software Loader card while others are located on individual “unlock” or "enablement" SD cards. A. Airplane Options Load Procedure with Base Software Loader Card

NOTE: All steps below will use the pilot's right GTC for control of the system.

(1) Identify the options to load. (2) Make sure that the SD loader card is in the PFD 1 top slot for the full software loading procedure. (3) Do the Airplane Setup in this section. (4) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (5) If not already on the GDU controls page, select HOME and then select GDU CONTROLS. (a) Make sure that PFD 1 is selected. (6) Make sure that the SYSTEM UPLOAD page is shown on the PFD 1. (Refer to Figure 503). (a) If not, turn the right inner and outer knobs to navigate to the SYSTEM tab then the SYSTEM UPLOAD page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(7) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated.

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(8) Turn the inner knob to highlight the software's part number line item in the CARD window.

NOTE: If the software line item that you want to load will include the software part number. Refer to Table 501 for the correct software number.

(a) Select the ENTER button to select the card item. (9) On the pilot's right GTC, turn the outer and inner knob to highlight the Options line item in the GROUP window. (Refer to Figure 507). (a) Push the ENTER button to select the GROUP item. (b) Make sure that Option is found under the ITEM window. (10) On the pilot's right GTC turn the outer and inner knob to highlight the applicable option (Refer to Figure 507). (a) Push the ENTER button to select the ITEM. (b) Make sure that the correct option is shown the ITEM window after the PRODUCT window is populated with data. (Refer to Figure 507). (c) Make sure that a list of software items are displayed in the PRODUCT window. (11) Select the LEFT and RIGHT ARROWS until CHK ALL is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will check all of the check boxes.

(12) Select the LEFT and RIGHT ARROWS until LOAD is highlighted at the bottom of PFD 1. (a) Select the LOAD softkey on PFD 1 to install the option software and configuration.

NOTE: Do not cancel a software load in progress. If a failure occurs, wait until the fail message appears before proceeding.

(13) Monitor the upload status. (14) If the optional software or configuration upload fails do the steps that follow:

NOTE: The upload must be completed from the file that failed. The check boxes for the items that failed will stay checked.

(a) Push the inner knob to acknowledge the Load Fail message. (b) Do the LOAD steps again. (c) If the upload fails again, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. (15) Make sure that the 'Upload and Crossfill Complete' window shows on the display. (Refer to Figure 504). (a) On the pilot's right GTC select the ENTER button to acknowledge the message. (16) Do the steps again to load more options. B. Airplane Options Load Procedure with Enablement Loader Card(s) (1) Identify the options to load. (2) Do the Airplane Setup in this section. (3) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (4) Turn the dimming switch on the PFD 1 fully counter-clockwise to the Off position. (5) If installed, remove any software SD card from the PFD 1 top slot. (6) Install the applicable Enablement loader card in the PFD 1 top slot. (a) Make sure that the card stays in the PFD 1 top slot for the full software loading procedure. (7) Turn the dimming switch on the PFD 1 fully clockwise to the full bright position. (a) Make sure that the INITIALIZING SYSTEM message shows in the top left corner of the PFD 1 after the PFD 1 initialization is complete. (8) Make sure that the SYSTEM UPLOAD page is shown on the PFD 1. (Refer to Figure 503).

NOTE: All steps below will use the pilot's right GTC for control of the system.

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System Upload Page Figure 507 (Sheet 1)

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(9) If not already on the GDU controls page, select HOME and then select GDU CONTROLS. (a) Make sure that PFD 1 is selected. (10) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated. (11) Turn the inner knob to highlight the SD CARD line in the CARD window.

NOTE: If the software that you want to load has been loaded before, you can select that version from the drop down CARD window. Make sure to not use software versions before the current version.

(a) Select the ENTER button to select the card item. (12) On the pilot's right GTC, turn the inner knob to highlight the Option line item in the GROUP window. (a) Push the ENTER button to select the GROUP item. (b) Make sure that an Option is found under the ITEM window(Refer to Figure 508). (13) On the pilot's right GTC, turn the inner knob to the select the item field and highlight the applicable option. (a) Push the ENTER button to select the highlighted option. (b) Make sure that the correct option is shown the ITEM window after the PRODUCT window is populated with data. (Refer to Figure 508). (c) Make sure that a list of software items are displayed in the PRODUCT window. (14) Select the LEFT and RIGHT ARROWS until CHK ALL is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1.

NOTE: This will check all of the check boxes.

(15) Select the LEFT and RIGHT ARROWS until LOAD is highlighted at the bottom of PFD 1. (a) Touch Select the LOAD softkey on PFD 1 to install the option software and configuration.

NOTE: Do not cancel a software load in progress. If a failure occurs, wait until the fail message appears before proceeding.

(16) Monitor the upload status. (17) If the software or configuration upload fails do the steps that follow:

NOTE: The upload must be completed from the file that failed. The check boxes for the items that failed will stay checked.

NOTE: This will show the Transaction Log Summary Page.

(22) Make sure that there is only one entry for ITEM Model 700 Base Configuration and the STATUS is PASS. (a) If the STATUS is not PASS, refer to Garmin G5000 Integrated Avionics System Software - Troubleshooting.

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System Upload – Enablement Loader Card Figure 508 (Sheet 1)

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C. CMC Configuration (1) Update the CMC Configuration. Refer to Chapter 45, Update CMC Configuration/CMC Viewer Version - Maintenance Practices.

10. Airplane Configuration A. Airplane Configuration Setup (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC select PFD 1 in the GDU CONTROLS page. (4) On the pilot's right GTC use the inner and outer knobs to navigate to the SYSTEM tab on the AIRCRAFT CONFIGURATION page (Refer to Figure 509).

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) Push the inner knob on the pilot's right GTC to activate the cursor in the AIRCRAFT CONFIGURATION page.

NOTE: The cursor will show in the aircraft registration line.

(6) Enter the airplane registration number on pilot's right GTC. (a) Use the inner knob to change the character in the selected field. (b) Use the outer knob to change the selected field. (c) Push ENTER to select the entry.

NOTE: If the airplane registration begin with 'N', the ICAO Address will be auto-populated once the aircraft registration is entered. If the ICAO address is not auto-populated, it must be manually entered.

(7) On the pilot's right GTC, turn the outer knob to move the cursor to the ICAO REGION field. (8) On the pilot's right GTC, turn the inner knob to highlight NONE. (a) Select ENTER. (9) On the pilot's right GTC, turn the outer knob to move the cursor to the DOMAIN IDENTIFIER field. (10) Do the steps that follow to enter the Domain Identifier. (a) Find and input the correct alpha-3 Country Code for the country where the airplane will be registered.

NOTE: The alpha-3 Country Code for the Domain Identifier can be found at http://www.iso.org/obp/ui/#home.

(b) Select the Country Codes Radio button. (c) Select the Search button. (d) Under the Code Type, select Officially Assigned Codes to apply a filter. (e) Find the correct alpha-3 Country Code from the list. (f) Do the steps that follow on the pilot's right GTC: 1 Use the right inner knob to change the character in the selected field. 2 Use the outer knob to change the selected field. 3 Select ENTER to accept the changes to the Domain Identifier. (11) On the pilot's right GTC, turn the outer knob to move the cursor to the VFR CODE field.

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Aircraft Configuration Page Figure 509 (Sheet 1)

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(12) Do the steps that follow to enter the VFR CODE.

NOTE: Use code 1200 for airplanes registered in any country not in Europe, and code 7000 for airplanes registered in Europe.

(a) Do the steps that follow on the pilot's right GTC: 1 Use the right inner knob to change the character in the selected field. 2 Use the outer knob to change the selected field. 3 Select ENTER to accept the changes to the Domain Identifier. (13) On the pilot's right GTC, press the right inner knob to deactivate the cursor. (14) Select the LEFT and RIGHT ARROWS until SET GTX is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1. (b) Select ENTER to select OK when the pop up shows.

NOTE: This will set up Transponder #1 and Transponder #2 with the registration information that was entered.

(c) Select ENTER on the confirmation window. (15) Select the LEFT and RIGHT ARROWS until SET GTS is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1. (b) Select ENTER to select OK when the pop up shows.

NOTE: This will set up TCAS with the registration information that was entered.

(c) Select ENTER on the confirmation window. (16) The Transponders and TCAS programming is complete. B. Airframe Configuration Setup (Complete Software Load)

NOTE: The airplane and engine serial numbers are needed to complete this step. If the correct airplane and engine serial numbers are present it is not necessary to enter the numbers again.

(1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (4) On the pilot's right GTC use the inner and outer knobs to navigate to the GDU tab on the AIRCRAFT CONFIGURATION page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) Push the inner knob on the pilot's right GTC to activate the cursor in the AIRFRAME CONFIGURATION page (Refer to Figure 510).

NOTE: The cursor will show in the GAUGES window.

(6) Turn the outer knob on the pilot's right GTC to move the cursor in the AIRFRAME WINDOW in the AIRCRAFT SN field. (7) Enter the Aircraft Serial Number with pilot's right GTC. • The inner knob changes the character in the selected field. • The outer knob changes the selected field.

NOTE: The serial number must be entered as 7005858. The 5858 signifies the serial number.

(a) Touch ENTER to accept the changes made to the Aircraft Serial Number.

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Airframe Configuration Setup Figure 510 (Sheet 1)

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Airframe Configuration Setup Figure 510 (Sheet 2)

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CAUTION: If the Aircraft Serial Number that was entered was changed after the rudder control system (SECU) rigging was completed, the rigging must be completed again.

(8) Turn the outer knob on the pilot's right GTC to move the cursor in the L ENGINE SN field. (9) Enter the Left Engine Serial Number with pilot's right GTC. • The inner knob changes the character in the selected field. • The outer knob changes the selected field.

NOTE: The serial number must be entered exactly as it is entered on the engine data plates.

(a) Touch ENTER to accept the changes made to the Left Engine Serial Number. (10) Turn the outer knob on the pilot's right GTC to move the cursor in the R ENGINE SN field. (11) Enter the Right Engine Serial Number with pilot's right GTC. • The inner knob changes the character in the selected field. • The outer knob changes the selected field.

NOTE: The serial number must be entered exactly as it is entered on the engine data plates.

(a) Touch ENTER to accept the changes made to the Right Engine Serial Number. (12) Turn the outer knob on the pilot's right GTC to move the cursor in the LDR CARD ID field.

NOTE: Use the software version that was loaded to enter the Loader Card ID.

(13) Enter the LDR CARD ID with pilot's right GTC.

NOTE: The software image part number must be entered as 006-5858-YY. This can be found at the top of the MANIFEST CONFIGURATION Page (Refer to Figure 510).

(a) Use the inner knob to change the character in the selected field. (b) Use the outer knob to change the selected field. (c) Touch ENTER to accept the changes made to the LDR CARD ID. (14) Turn the outer knob on the pilot's right GTC to move the cursor in the CONFIG ID field. (15) Use the pilot's right GTC to enter the Fleet ID number in the CONFIG ID field (Refer to Figure 510).

NOTE: The Fleet ID number can be found on the SYSTEM tab, CONFIGURATION MANAGER page.

(a) Use the inner knob to change the character in the selected field. (b) Use the outer knob to change the selected field. (c) Touch ENTER to accept the changes made to the CONFIG ID. (16) On the pilot's right GTC, press the right inner knob to deactivate the cursor. (17) The entry of the Aircraft and Engine Serial Numbers is complete. C. Airframe Configuration Setup (Configuration Loading) (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (4) On the pilot's right GTC use the inner and outer knobs to navigate to the GDU tab on the AIRCRAFT CONFIGURATION page (Refer to Figure 510).

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

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(5) Push the inner knob on the pilot's right GTC to activate the cursor in the AIRFRAME CONFIGURATION page.

NOTE: The cursor will show in the GAUGES window.

(6) Turn the outer knob on the pilot's right GTC to move the cursor in the CONFIG ID field. (7) Use the pilot's right GTC to enter the Fleet ID number in the CONFIG ID field (Refer to Figure 510).

NOTE: The Fleet ID number can be found on the SYSTEM tab, CONFIGURATION MANAGER page.

11. Configuration Module Programming A. Program the configuration module. (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (4) Make sure that the SYSTEM UPLOAD page is shown on the PFD 1. (Refer to Figure 503). (a) If not, turn the right inner and outer knobs to navigate to the SYSTEM tab then the SYSTEM UPLOAD page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) Select the LEFT and RIGHT ARROWS until UPDT CFG is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1. (6) On the pilot's right GTC, turn the right outer knob to highlight Yes. (a) Select Enter on the PFD 1 to confirm the message. (Refer to Figure 511). (7) Monitor the status of the update. (8) Push the ENTER key to confirm a successful update (Refer to Figure 511). (9) If the update is unsuccessful do the Configuration Module Programming again.

NOTE: If the second attempt to update the configuration module is unsuccessful replace the configuration module and complete this step again.

(10) The configuration module update and programming are now complete. B. Configuration Confirmation (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page.

NOTE: This step must be done from the PFD 1 or the Confirming configuration will not be tracked on the Transaction ID page.

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Configuration Module Update Windows Figure 511 (Sheet 1)

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(4) Turn the right inner and outer knobs to navigate to the SYSTEM tab then the CONFIGURATION MANGER page (Refer to Figure 512).

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) Select the LEFT and RIGHT ARROWS until CNFM AC is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1. (6) On the pilot's right GTC, turn the right inner and outer knobs to highlight OK. (a) Select Enter on the PFD 1 to confirm the message. (Refer to Figure 512). (7) Make sure that the EXPECTED Aircraft ID is the same as the ACTUAL Aircraft ID. (Refer to Figure 512). (8) The configuration module update and programming are now complete.

12. Normal Mode Setup A. Load the Default Pilot Profile. (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in normal mode. If not, Put the Garmin G5000 Integrated Avionics System into Normal Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select Aircraft Systems. (c) Select Maintenance. (d) Select Start Maintenance. 1 Use the key pad to enter CACCDMS as the maintenance password. 2 Select Enter. (4) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select Aircraft Systems. (c) Select Maintenance. (d) Select Set Default Profile. (e) Select Cessna 700 Profile. (f) Select OK when prompted. (g) Select Home. (h) Select Utilities. (i) Select Crew Profile. (j) Select Restore Defaults. (k) Select OK when prompted. (l) In the Default Profile icon, make sure that the Pilot Profile CRC number is listedas 25C9C665. 1 If the Pilot Profile CRC number is NOT listed as 25C9C665, do the CrewProfile Loading again. 2 Please contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected] if you have any questions about the correct Pilot Profile CRC number. B. Wi-Fi Favorite Setup (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in normal mode. If not, Put the Garmin G5000 Integrated Avionics System into Normal Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) Push the HOME button on the pilot's right GTC. (4) Push the UTILITES button on the pilot's right GTC. (5) Push the SETUP button on the pilot's right GTC. (6) Select the Wi-Fi setup icon. (7) Select the FAVORITES tab.

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Configuration Confirmation Figure 512 (Sheet 1)

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Configuration Confirmation Figure 512 (Sheet 2)

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(8) Select the ADD FAVORITE NETWORK bar on the GTC (Refer to Figure 513). (a) Set up the network that follows: • SSID - OEMDIAG • AIRPORT - NONE • SECURITY - WPA • PASSPHRASE - CESSNADIAG01 • MODE - Infrastructure • COUNTRY - United States

NOTE: Do not associate the connection with an airport identifier.

(9) Select Create. (10) Wait two minutes and then make sure that OEMDIAG is connected automatically with a signal strength of 4 to 5 bars.

NOTE: This step will need to be completed at a location with a Textron Aviation wireless network to get a connection.

(a) If not, select the newly created SSID and then select the CONNECT button. (11) The Wi-Fi Favorite Setup is complete. C. CMC Viewer/CDMS Install (1) Find the correct version of the CMC Viewer Card document. Refer to Chapter 45, View CMC Diagnostics System Version Numbers - Maintenance Practices. (a) If necessary, do the Update the CMC Configuration or CMC Viewer Version procedure. Refer to Chapter 45, Update CMC Configuration/CMC Viewer Version - Maintenance Practices.

13. Software Verification - Configuration Mode A. Transaction ID Verification (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (4) Turn the right inner and outer knobs to navigate to the SYSTEM tab then the TRANSACTION LOG page (Refer to Figure 514).

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) Select the LEFT and RIGHT ARROWS until SUMMARY is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1. (6) Make sure the bottom entry in the list is labeled MODEL 700 BASE in the ITEM column and the STATUS is PASS (Refer to Figure 514). (7) Make sure the software options loaded are the same as the software identified in the Approved Transaction ID Items for Software Version 58 table (Ref. Table 501). (8) Make sure for every software option there is a line ITEM entry and the STATUS is PASS. (9) Make sure there is NOT a line ITEM entry marked CNFM CFG with an AMBER STATUS of FLEET ID UPDATED. If an amber FLEET ID UPDATED is shown, the software and configuration must be loaded again. Refer to Base Software/Configuration Load Procedures.

NOTE: A line item entry on CNFM CFG with a white STATUS of AIRCRAFT ID UPDATED or no line item entry with CNFM CFG is acceptable.

(10) Make sure there are no entries with an AMBER or RED status in the list. Green and White are the only acceptable colors for status.

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Wi-Fi Setup Figure 513 (Sheet 1)

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Transaction Log Page Figure 514 (Sheet 1)

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B. Base Configuration, Fleet ID (CRC) Verification (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (4) Turn the right inner and outer knobs to navigate to the SYSTEM tab then the TRANSACTION LOG page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) Select the LEFT and RIGHT ARROWS until DETAIL is highlighted at the bottom of PFD 1. (a) Touch Select at the bottom of PFD 1. (6) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated. (7) On the pilot's right GTC, turn the outer knob to move the cursor to the first item not grayed out labeled MODEL 700 BASE in the INFORMATION column (Refer to Figure 515). (8) In the CONFIGURATION ACTIVITY ENTRY window, find the NEW FLEET ID entry. (a) Make sure that the NEW FLEET ID entry is 0x304C4395. C. Configuration Manager All LRU's Valid (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Integrated Avionics System is in software configuration mode. If not, Put the Garmin G5000 Integrated Avionics System into Configuration Mode. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices. (3) On the pilot's right GTC, select PFD 1 in the GDU CONTROLS button section of the page. (4) Turn the right inner and outer knobs to navigate to the SYSTEM tab then the CONFIGURATION MANAGER page.

NOTE: If the cursor is already active, push the right inner knob to deactivate it. The cursor must be deactivated to navigate to a new page.

(5) On the pilot's right GTC, push the right inner knob. (a) The PFD 1 cursor is activated. (6) On the pilot's right GTC, turn the outer knob to move the cursor to make sure all item show a green VALID except for GSR 1 and GSR 2 (Refer to Figure 516). (a) If an item does not show VALID, do the An Item on the Configuration Manager Page Does Not Report Valid troubleshooting. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. D. CMC Configuration Transaction ID Verification (1) Refer to Chapter 45, Update CMC Configuration/CMC Viewer Version - Maintenance Practices to make sure that the Transaction ID values are correct.

14. Software Verification - Normal Mode A. System Status Verification (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Avionics System is on, in normal mode, and in an on ground condition.

(3) Do as follows on the pilot's right GTC: (a) Select Home. (b) Select Utilities. (c) Select Setup.

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Transaction Log – Detail Page, Base CRC Figure 515 (Sheet 1)

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Configuration Manager Page Figure 516 (Sheet 1)

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(d) Select Avionics Status. (4) Make sure that there is a green check ( ) next to each LRU listed (Refer to Figure 517). (a) If an LRU shows an amber X, do the Avionics Status Shows Amber Checkbox troubleshooting. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. (5) Make sure that the Fuel Quantity on the EIS Strip is shown in pounds. (a) If the Fuel Quantity on the EIS Strip is not shown in pounds, do the Fuel Quantity is Shown in Kilograms Instead of Pounds troubleshooting. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting.

NOTE: All MANIFEST, SYSTEM CONFIG, and AVIONICS CONFIG messages must be addressed and corrected before continuing. B. Software Status Verification (1) Push the MSG button on the pilot's right GTC. (2) Make sure that there are no MANIFEST messages. (a) If there are MANIFEST messages, do the Appropriate Steps to Take to Clear a MANIFEST System Message troubleshooting. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. (3) Make sure that there are no SYSTEM CONFIG messages. (a) If there are SYSTEM CONFIG messages, do the do the Appropriate Steps to Take to Clear a SYSTEM CONFIG System Message troubleshooting. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. (4) Make sure that the AVIONICS CONFIG CAS message is not shown. (a) If there are AVIONICS CONFIG CAS messages, do the do the Appropriate Steps to Take to Clear a AVIONICS CONFIG Crew Alerting System (CAS) Message troubleshooting. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. C. Software Version Verification. (1) Do the Airplane Setup in this section. (2) Make sure that the G5000 Avionics System is on, in normal mode, and in an on ground condition.

(3) Avionics Status (Airframe) Check (Refer to Figure 518). (a) Push the buttons, in the sequence that follows on the pilot's right GTC: • HOME • UTILITIES • SETUP • AVIONICS STATUS • AIRFRAME (4) Make sure that the Sys SW Vers. reported on the Airframe tab is 2257.58. D. Pilot Profile Verification (1) On the pilot's right GTC, do as follows: (a) Select Home. (b) Select Aircraft Systems. (c) Select Maintenance. (d) Select Set Default Profile. (e) Select Cessna 700 Profile. (f) Select OK when prompted. (g) Select Home. (h) Select Utilities. (i) Select Crew Profile. (j) Select Restore Defaults. (k) Select OK when prompted.

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GTC Avionics Status Function Figure 517 (Sheet 1)

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Avionics System Software Function Figure 518 (Sheet 1)

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(l) In the Default Profile icon, make sure that the Pilot Profile CRC number is listedas 25C9C665. 1 If the Pilot Profile CRC number is NOT listed as 25C9C665, do the CrewProfile Loading again. 2 Please contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected] if you have any questions about the correct Pilot Profile CRC number.

15. Database Card Loading Procedures A. Tools and Equipment

(1) Tools and Equipment • PC Laptop Computer • Software Loader SD Card. (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 33, Flight Compartment Lighting - Description and Operation • Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices • Chapter 42, Garmin G5000 Integrated Avionics System - Troubleshooting. B. Prepare the Airplane for the Database Card Loading Procedures. (1) Do the Airplane Setup, in this section. C. Download the Updated Databases (Refer to Figure 519).

NOTE: The 010-00474-50 Software Loader SD Card is necessary for this procedure.

(1) Connect a computer to the internet and direct a browser window to www.FlyGarmin.com. (2) At the GARMIN Account Sign In field found in the top right corner of the display, type inthe username and password or register a new account with FlyGarmin and add the airplane data to the website. (a) For assistance with the username and password, contact Textron Aviation Customer Service. For contact information, refer to the Introduction. (3) When you are logged in, do as follows: (a) Select the Devices tab. (b) Scroll down until you find the airplane that needs the update. (c) Select the airplane name to go to the Aircraft Details page. (d) If the airplane has expired or database products not purchased, a red circle containing the number of updates necessary will show. (e) Select the Device that needs a database update. (4) Install the software loader SD card into the computer card reader slot. (5) Select Install Updates and follow the prompts to choose the database(s) to update.

NOTE: Do not select install for Jeppesen Charts, it is recommended to download the Jeppesen Charts directly from Jeppesen. Reference Upload Jeppessen Chartview (Alternative Procedures) in this procedure.

(6) Record the cycle number of each database that is to be installed. (7) Select the LAUNCH FLYGARMIN DESKTOP button near the bottom of the page.

NOTE: After a few moments, the FlyGarmin for Windows application will show. If it does not show, use the prompts to install the application.

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flyGarmin for Windows Tool Figure 519 (Sheet 1)

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(8) Follow the on-screen prompts and let the databases download and install onto the SD card.

NOTE: Ignore prompts to switch database cards. D. Download Jeppessen Chartview (Alternative Procedure).

NOTE: The 010-00474-50 Software Loader SD Card is necessary for this procedure.

(1) Download the Jeppesen Distribution Manager from https://support.jeppesen.com/ by choosing Products and selecting the applicable operating system. (2) Install the database SD card into the computer and activate the Jeppessen Distribution Manager. (a) Enter in the username and password and select OK (b) For assistance with the username and password, contact Textron Aviation Customer Service. For contact information, refer to the Introduction. E. Loading Databases (Refer to Figure 520). (1) Make sure that the G5000 Avionics System is on, in normal mode, and in an on ground condition.

(2) Turn the MFD dimming knob fully counterclockwise to the OFF position to turn the MFD off. (3) Put the database card in the bottom slot of the MFD. (4) Turn the MFD dimming knob clockwise past the OFF position to turn the MFD on. (5) All of the updated databases will be uploaded to all the displays from the MFD. (a) To watch the progress, do as follows on the pilot's right GTC: • Select Home • Select Utilities • Select Setup • Select Database Status.

NOTE: Allow five minutes to two hours for the databases to fully sync with the system, depending on the size and the quantity of the databases that require an update.

(6) When all of the downloaded databases have synchronized to the Standby column and the system shows Activate database with on ground restart, do as follows:

NOTE: Databases without an effective date in the Standby column may not be automatically selected to Swap from the Standby to Active column after a newer cycle number has been loaded to Standby.

(a) If the Standby date is newer than the Active date for the Basemap database, do as follows: • Select the Database line item • Select Swap • Select Ok. (b) Make sure that the cyan double arrow shows in the Database between the Standby and the Active columns. (c) If necessary, do this again for the Terrain database. (d) Wait two minutes for the swap commands to be completed. (7) Remove the electrical power from the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

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Database Status Pages Figure 520 (Sheet 1)

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(8) Remove database card from the bottom slot of the MFD.

NOTE: Garmin databases lock to a specific airplane once they are installed. These cards can be used again with the same airplane for future database updates. The current cycle of Garmin databases can be downloaded again if the card is lost or overwritten. If the airplane should need a Jeppesen database loaded again, a new Jeppesen database will have to be purchased if the card is lost or overwritten.

(9) Connect the electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices.

NOTE: Multiple power cycles can be necessary for all database swaps to be completed. Wait two minutes or more after you apply power to the airplane before you remove electrical power for each cycle. F. Database Verification (Refer to Figure 521). (1) Make sure that the G5000 Avionics System is on and in Normal Mode.

(2) On the pilot's right GTC, do as follows: • Select Home • Select Utilities • Select Setup • Select Database Status. (3) Make sure that the top of the Database Status screen is not amber and shows Databases Ready. (4) Make sure that each updated database shows the correct cycle number and that none of the dates are shown in amber text. (5) Select the Back button. (6) Select the MSG button and make sure that the system messages that follow do not show: • DB MISMATCH • [LRU] DB ERR • DATABASES EXPIRED • DATABASES MISMATCHED. (7) If any of the system messages show, refer to Chapter 42, Garmin G5000 Integrated Avionics System - Troubleshooting.

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Database Status - Databases Ready Figure 521 (Sheet 1)

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GARMIN G5000 INTEGRATED AVIONICS SYSTEM LRU SOFTWARE VERSION 58 CONFIGURATION - ADJUSTMENT/TEST (Airplanes -0033 and On)

1. General A. This section gives the adjustments and tests necessary to update or change the Garmin G5000 Integrated Avionics System LRU software and configuration files for software Version 58. For more data about the Garmin G5000 Integrated Avionics System, refer to the Garmin G5000 Integrated Avionics System Pilot's Guide for the Cessna Citation Longitude and the Garmin G5000 Integrated Avionics System Line Maintenance Manual - Cessna Citation Longitude 700.

CAUTION: These procedures only apply to airplanes that operate with Garmin G5000 software Version 58. The use of these procedures for any other software version can cause errors or faults in the operation of the Garmin G5000 software.

WARNING: DO NOT use the SYSTEM UPLOAD screen when you replace or interchange line replaceable units (LRU's) in software Version 58. Failure to follow the steps given in this section will cause issues in the G5000 system that will need a full configuration load with all options. B. This section is applicable for the conditions that follow: (1) When a G5000 Integrated Avionics System LRU has failed, is replaced, or is interchanged from one position to another position.

NOTE: Garmin LRU's that are removed and installed again (without any work done on them) in the same airframe position do not need software or configuration files uploaded. C. Below is a list of the procedures in the order of appearance in this section: • Garmin G5000 System Useful Specifics • Garmin G5000 Integrated Avionics System LRU Software Configuration (Version 58) • LRU Maintenance Procedure • Load the Software and Configurations to the Garmin LRU's • Troubleshooting.

2. Garmin G5000 System Useful Specifics A. Before you continue with the Garmin G5000 Integrated Avionics System LRU Software Version 58 Configuration, the specifics that follow are useful to know: (1) The pilot's right Garmin GTC 575 Touchscreen Control Unit is the primary control unit when the G5000 is in configuration mode. (2) The dual concentric knobs on the lower right of the GTC are used and are referred to as the small and large flight management system (FMS) knobs. (3) In the G5000 configuration mode, the GDU Controls screen on the GTC is used to control the system. (a) On the GTC Home (Config Mode) screen, select GDU Controls on the left side of thescreen to show the GDU Controls screen. (b) Make sure that PFD1 on the left side of the GDU Controls screen on the GTC is selected to control the pilot's primary flight display (PFD). (c) On the GDU Controls screen, use Enter on the lower right section of the screen along with the FMS knobs to navigate and select items on the PFD and the multifunction display (MFD). (d) On the GDU Controls screen, use Select and the Left and Right arrows to select the soft key items on the bottom of the PFD and the MFD.

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(4) The PFD's and the MFD can be individually powered down if you turn the outer knob of the left PFD-GTC DIM switch, MFD-GTC DIM switch, or the right PFD-GTC DIM switch counterclockwise to shut off the display unit. Refer to Chapter 33, Flight Compartment Lighting - Description and Operation for the location of the left PFD-GTC DIM switch, MFD-GTC DIM switch, and the right PFD-GTC DIM switch.

3. Garmin G5000 Integrated Avionics System LRU Software Configuration (Version 58) A. General

(1) This section gives the adjustments and test necessary to do the Garmin G5000 Integrated Avionics System LRU Software Configuration for software Version 58. B. Tools and Equipment

NOTE: For the tool, equipment, and special consumable part numbers and the manufacturer data, refer to Chapter 42, Integrated Modular Avionics- General. For the supplier publication part number and manufacturer data, refer to the Introduction - Supplier Publication List.

(1) Tools and Equipment • Cessna G5000 Default Pilot Profile SD Card (Part Number: 8203142-8) • Cessna Longitude CMC Viewer SD Card (Part Number: 8204541-21) • Software Loader SD Card (Part Number: 010-00474-50). (2) Special Consumables • None. (3) Reference Material • Chapter 24, External Electrical Power - Maintenance Practices. C. Prepare the Airplane for the Garmin G5000 Integrated Avionics System LRU Software Configuration (Version 58). (1) Make sure that airplane batteries are installed and connected. (2) Set the L MAIN and R MAIN switch/lights to the ON position (recessed).

4. LRU Maintenance Procedure A. Do the LRU Maintenance Procedure as follows: (1) Refer to the applicable section in the Model 700 Maintenance Manual to remove and install the affected Garmin LRU. (2) Connect external electrical power to the airplane. Refer to Chapter 24, External Electrical Power - Maintenance Practices. B. Put the Airplane in Configuration Mode as follows: (1) For the GDU 1450W Flight Displays (PFD 1, PFD 2, or MFD), do as follows: (a) Put the Garmin G5000 Integrated Avionics System into Configuration Mode but keep the replaced display off. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices.

NOTE: Turn the GTC dimming knob fully counterclockwise to the OFF position.

(b) Put the software loader SD card (part number: 010-00474-50) into the top slot of the applicable flight display.

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NOTE: The applicable flight display will automatically load the GDU software and configuration.

(2) Push and hold the right knob on the pilot's right GTC and turn on external power. (a) Release the right knob on the pilot's right GTC when you see INITIALIZING or the Garmin logo on the GTC screen. (3) On the pilot's right GTC Home (Config Mode) screen, select Restart Options. (4) On the GTC Restart Options screen, select System to Config Mode.

NOTE: This will reboot the system in configuration mode.

(5) After the system is rebooted, make sure that: (a) The SYSTEM STATUS screen shows on the copilot's PFD and the MFD. (b) The SYSTEM UPLOAD screen shows on the pilot's PFD. (c) All GTC's show the Home (Config Mode) screen. (d) If the screens don't show the correct items, repeat the necessary steps to put the Garmin G5000 Integrated Avionics System into configuration mode.

5. Load the Software and Configurations to the Garmin LRU's A. Garmin LRU's. (1) Below is a list of the Garmin LRU replacement procedures that are included in this section. • GCU 275 Display Controller • GDC 7400 Air Data Computer • GDL 59 Data Link • GDL 69A Data Link Receiver • GDR 66 VHF Data Link Radio • GDU 1450W Flight Display • GEA 7100 Engine/Airframe Interface Unit • GIA 64E Integrated Avionics Unit • GMA 36B Audio Processor • GMC 7200 AFCS Mode Controller • GRA 5500 Radio Altimeter • GSA 9000 Autopilot Servo Actuator • GSD 41 Data Concentrator Unit • GSD 41HE Data Concentrator Unit (Harsh Environment) • GSR 56 Iridium Transceiver • GTC 575 Touchscreen Control Unit • GTS 8000 Traffic Collision Avoidance System (TCAS II) Processor • GTX 3000 Mode S Transponder • GWX 80 Weather Radar. B. GCU 275 Display Controller Software/Configuration Loading Instructions. (1) Replace the GCU 275 #1 (Left) Display Controller and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

(b) Make sure that PFD1 is selected on the GTC to control the pilot's PFD. (c) Turn the small FMS knob to the right until the LRU REPLACEMENT screen shows. (d) Push the FMS knob to activate the cursor. (e) Turn the small FMS knob to the right to drop the menu down. (f) Turn the small FMS knob to the right to scroll until highlighted on GCU 1 (may be amber in color).

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(g) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GCU 1 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GCU 275 #2 (Right) Display Controller and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

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(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GCU 2 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Swap the GCU 275 #1 (Left) and GCU 275 #2 (Right) Display Controllers and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Turn the small FMS knob to the right to drop the menu down. (n) Turn the small FMS knob to the right to scroll until highlighted on GCU 2 (may be amber in color).

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(o) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. C. GDC 7400 Air Data Computer Software/Configuration Loading Instructions. (1) Replace the GDC 7400 #1 (Left) Air Data Computer and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display.

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(i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 22.5 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GDC 1 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GDC 7400 #2 (Right) Air Data Computer and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 22.5 minutes.

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(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GDC 2 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Swap the GDC 7400 #1 (Left) Air Data Computer and the GDC 7400 #2 (Right) Air Data Computer and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 22.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

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(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 22.5 minutes.

NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. D. GDL 59 Data Link Software/Configuration Loading Instructions. (1) Replace the GDL 59 Data Link and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display.

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(k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 10 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GDL59 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. E. GDL 69A Data Link Receiver Software/Configuration Loading Instructions. (1) Replace the GDL 69A Data Link Receiver and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4.5 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GDL69 shows Valid (in green). (p) Select Home on the GTC.

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(q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

NOTE: These ID values changed with the new GDL 69A Data Link Receiver installed.

(u) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (v) Contact SiriusXM or have the customer contact SiriusXM to give them the new Data Radio and Audio Radio ID's for their subscription. Note that their subscription may only be using one of the two radios.

NOTE: SiriusXM support can be contacted at 1-855-796-9847. F. GDR 66 VHF Data Link Radio Software/Configuration Loading Instructions. (1) Replace the GDR 66 VHF Data Link Radio and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown.

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(m) Push the FMS knob to deactivate the cursor. (n) Turn the large FMS knob to the left until the cursor is in the LRU box in the top left corner of the screen. (o) Turn the small FMS knob to the right to drop the menu down. (p) Turn the small FMS knob to the right to scroll until highlighted on GDR AUX (may be amber in color). (q) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(r) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(t) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (u) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(v) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (w) Push the FMS knob to deactivate the cursor. (x) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (y) Make sure that in the CONFIGURATION ITEMS box that GDR shows Valid (in green). (z) Select Home on the GTC. (aa) Select Restart Options. (ab) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(ac) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ad) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. G. GDU 1450W Flight Display Software/Configuration Loading Instructions. (1) Replace the GDU 1450W Flight Display (PFD 1) and load the software/configuration files as follows: (a) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode but keep the replaced display off. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices.

NOTE: Turn the GTC dimming knob fully counterclockwise to the OFF position.

1 Put the software loader SD card (part number: 010-00474-50) into the top slot of the PFD 1. 2 Turn the dimming knob on the GTC clockwise to the full bright position.

NOTE: The L PFD will automatically load the GDU software and configuration.

3 After the software loads, the SYSTEM UPLOAD page will show.

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4 Remove the software loader SD card from the top slot of the PFD 1. (b) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: The LRU Replacement procedures that follow must be done on the MFD because the PFD 1 was changed.

(d) Turn the small FMS knob to the right until the LRU REPLACEMENT screen shows. (e) Push the FMS knob to activate the cursor. (f) Turn the small FMS knob to the right to drop the menu down. (g) Turn the small FMS knob to the right to scroll until highlighted on PFD 1 (may be amber in color). (h) Select Enter on the GTC. 1 Make sure that the software list shows in the product window.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(i) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the MFD. (j) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Push the FMS knob to deactivate the cursor. (o) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (p) Make sure that in the CONFIGURATION ITEMS box that PFD 1 shows Valid (in green). (q) Select Home on the GTC. (r) Select Restart Options. (s) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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(2) Replace the GDU 1450W Flight Display (MFD) and load the software/configuration files as follows:

NOTE: The CMC diagnostic configuration will automatically load as part of theMFD LRU replacement.

(a) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode but keep the replaced display off. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices.

NOTE: Turn the GTC dimming knob fully counterclockwise to the OFF position.

1 Put the software loader SD card (part number: 010-00474-50) into the top slot of the MFD. 2 Turn the dimming knob on the GTC clockwise to the full bright position.

NOTE: The MFD will automatically load the GDU software and configuration.

3 After the software loads, the SYSTEM STATUS page will show. 4 Remove the software loader SD card from the top slot of the MFD. (b) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

(c) Make sure that PFD1 is selected on the GTC to control the pilot's PFD. (d) Turn the small FMS knob to the right until the LRU REPLACEMENT screen shows. (e) Push the FMS knob to activate the cursor. (f) Turn the small FMS knob to the right to drop the menu down. (g) Turn the small FMS knob to the right to scroll until highlighted on MFD 1 (may be amber in color). (h) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(i) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (j) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Push the FMS knob to deactivate the cursor. (o) Turn the small FMS knob until the CONFIGURATION MANAGER screen shows. (p) Make sure that in the CONFIGURATION ITEMS box that MFD 1 shows Valid (in green). (q) Make sure that the CMC diagnostic configuration upload was successful as follows: 1 Turn the small FMS knob to the left until the TRANSACTION LOG screen shows. 2 Make sure that the top of the GROUP column shows 'Model 700 CMC Config'. 3 Make sure that the top of the ITEM column shows '8204542-17 V2.6'. 4 Make sure that the top of the STATUS column shows 'NO TRANS ID' in white. 5 Make sure that there are no amber or red items in the STATUS column. a If there are any amber or red items in the STATUS column, please contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected].

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6 Use the Left and Right arrows on the GTC to highlight DETAIL at the bottom of the display. 7 Select the Select icon on the GTC. 8 Push the FMS knob to activate the cursor. 9 Turn the small FMS knob to drop the menu down and highlight '8204542-17 V2.6'. 10 Select Enter on the GTC to expand the entry for '8204542-17 V2.6'. 11 Record the value shown in the TRANSACTION ID column next to each line in Table 501 below. • Logging • Phase of Flight Blobs • OEM Alerts • OEM Blobs.

NOTE: CLEAR CMC CONFIGURATION does not require verification.

Table 501. TRANSACTION ID Values

TRANSACTION ID Logging Phase of Flight OEM Alerts OEM Blobs Blobs TRANSACTION ID (Right column) TRANSACTION ID 0x8C706755 0x17AFDC6B 0xB2D1DEBE 0x053AC8F7B (Expected value) 12 Make sure that the four TRANSACTION ID values match the expected values. 13 If the TRANSACTION ID values recorded in Table 501 are not correct, load the MFD LRU replacement software/configuration files again.

CAUTION: If the TRANSACTION ID values are not correct, do not continue. The CMC diagnostic configuration upload is not correct.

(r) Remove the Cessna Longitude CMC Viewer SD card (part number: 8204541-21) from the top slot of the MFD.

NOTE: The Cessna Longitude CMC Viewer SD card part number is dependent on what SD card was supplied with your airplane.

(s) Put the Cessna G5000 Default Pilot Profile SD card (part number: 8203142-8) into thetop slot of the MFD. (t) Select Home on the GTC. (u) Select Restart Options. (v) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(w) On the pilot's right GTC, do as follows: 1 Select Home. 2 Select Aircraft Systems. 3 Select Maintenance. 4 Select Set Default Profile. 5 Select Cessna 700 Profile. 6 Select OK when prompted. 7 Select Home. 8 Select Utilities. 9 Select Crew Profile. 10 Select Restore Defaults.

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11 Select OK when prompted. 12 In the Default Profile icon, make sure that the Pilot Profile CRC number is listedas 25C9C665. a If the Pilot Profile CRC number is NOT listed as 25C9C665, do the CrewProfile Loading again. b Please contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected] if you have any questions about the correct Pilot Profile CRC number. (x) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (y) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (z) Remove the Cessna G5000 Default Pilot Profile SD card (part number: 8203142-8) from the top slot of the MFD. (aa) Put the Cessna Longitude CMC Viewer SD card (part number: 8204541-21) into the top slot of the MFD.

NOTE: The Cessna Longitude CMC Viewer SD card part number is dependent on what SD card was supplied with your airplane.

(3) Replace the GDU 1450W Flight Display (PFD 2) and load the software/configuration files as follows: (a) If necessary, Put the Garmin G5000 Integrated Avionics System into Configuration Mode but keep the replaced display off. Refer to Chapter 42, Garmin G5000 Integrated Avionics System Software - Maintenance Practices.

NOTE: Turn the GTC dimming knob fully counterclockwise to the OFF position.

1 Put the software loader SD card (part number: 010-00474-50) into the top slot of the PFD 2. 2 Turn the dimming knob on the GTC clockwise to the full bright position.

NOTE: The PFD 2 will automatically load the GDU software and configuration.

3 After the software loads, the SYSTEM STATUS page will show. 4 Remove the software loader SD card from the top slot of the PFD 2. (b) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

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(h) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(i) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (j) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Push the FMS knob to deactivate the cursor. (o) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (p) Make sure that in the CONFIGURATION ITEMS box that PFD 2 shows Valid (in green). (q) Select Home on the GTC. (r) Select Restart Options. (s) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(t) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (u) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (4) Swapping the GDU 1450W Flight Display (PFD 1) with the GDU 1450W Flight Display (MFD) is not recommended. (5) Swapping the GDU 1450W Flight Display (PFD 1) with the GDU 1450W Flight Display (PFD 2) is not recommended. (6) Swap the GDU 1450W Flight Display (PFD 2) with the GDU 1450W Flight Display (MFD) and load the software/configuration files as follows:

NOTE: The CMC diagnostic configuration will automatically load as part of theMFD LRU replacement.

(a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

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(g) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (u) Push the FMS knob to deactivate the cursor. (v) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (w) Make sure that in the CONFIGURATION ITEMS box that PFD 2 and MFD 1 show Valid (in green). (x) Make sure that the CMC diagnostic configuration upload was successful as follows: 1 Turn the small FMS knob to the left until the TRANSACTION LOG screen shows. 2 Make sure that the top of the GROUP column shows 'Model 700 CMC Config'. 3 Make sure that the top of the ITEM column shows '8204542-17 V2.6'. 4 Make sure that the top of the STATUS column shows 'NO TRANS ID' in white. 5 Make sure that there are no amber or red items in the STATUS column. a If there are any amber or red items in the STATUS column, please contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected]. 6 Use the Left and Right arrows on the GTC to highlight DETAIL at the bottom of the display. 7 Select the Select icon on the GTC. 8 Push the FMS knob to activate the cursor. 9 Turn the small FMS knob to drop the menu down and highlight '8204542-17 V2.6'. 10 Select Enter on the GTC to expand the entry for '8204542-17 V2.6'. 11 Record the value shown in the TRANSACTION ID column next to each line in Table 502 below. • Logging • Phase of Flight Blobs • OEM Alerts

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• OEM Blobs.

NOTE: CLEAR CMC CONFIGURATION does not require verification.

Table 502. TRANSACTION ID Values

TRANSACTION ID Logging Phase of Flight OEM Alerts OEM Blobs Blobs TRANSACTION ID (Right column) TRANSACTION ID 0x8C706755 0x17AFDC6B 0xB2D1DEBE 0x053AC8F7B (Expected value) 12 Make sure that the four TRANSACTION ID values match the expected values. 13 If the TRANSACTION ID values recorded in Table 502 are not correct, load the MFD LRU replacement software/configuration files again.

CAUTION: If the TRANSACTION ID values are not correct, do not continue. The CMC diagnostic configuration upload is not correct.

(y) Remove the Cessna Longitude CMC Viewer SD card (part number: 8204541-21) from the top slot of the MFD.

NOTE: The Cessna Longitude CMC Viewer SD card part number is dependent on what SD card was supplied with your airplane.

(z) Put the Cessna G5000 Default Pilot Profile SD card (part number: 8203142-8) into thetop slot of the MFD. (aa) Select Home on the GTC. (ab) Select Restart Options. (ac) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(ad) On the pilot's right GTC, do as follows: 1 Select Home. 2 Select Aircraft Systems. 3 Select Maintenance. 4 Select Set Default Profile. 5 Select Cessna 700 Profile. 6 Select OK when prompted. 7 Select Home. 8 Select Utilities. 9 Select Crew Profile. 10 Select Restore Defaults. 11 Select OK when prompted. 12 In the Default Profile icon, make sure that the Pilot Profile CRC number is listedas 25C9C665. a If the Pilot Profile CRC number is NOT listed as 25C9C665, do the CrewProfile Loading again. b Please contact Team Longitude at 1-316-517-9335, 1-888-508-2379, or [email protected] if you have any questions about the correct Pilot Profile CRC number. (ae) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities.

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3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (af) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (ag) Remove the Cessna G5000 Default Pilot Profile SD card (part number: 8203142-8) from the top slot of the MFD. (ah) Put the Cessna Longitude CMC Viewer SD card (part number: 8204541-21) into the top slot of the MFD.

NOTE: The Cessna Longitude CMC Viewer SD card part number is dependent on what SD card was supplied with your airplane. H. GEA 7100 Engine/Airframe Interface Unit Software/Configuration Loading Instructions. (1) Replace the GEA 7100 #1 (Forward) Engine/Airframe Interface Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Push the FMS knob to deactivate the cursor. (o) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (p) Make sure that in the CONFIGURATION ITEMS box that GEA 1 shows Valid (in green). (q) Select Home on the GTC. (r) Select Restart Options.

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(s) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(t) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (u) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GEA 7100 #2 (Aft Left) Engine/Airframe Interface Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GEA 2 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Replace the GEA 7100 #3 (Aft Right) Engine/Airframe Interface Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Push the FMS knob to deactivate the cursor. (o) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (p) Make sure that in the CONFIGURATION ITEMS box that GEA 3 shows Valid (in green). (q) Select Home on the GTC. (r) Select Restart Options. (s) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(t) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities.

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3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (u) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (4) Swap the GEA 7100 #1 (Forward) Engine/Airframe Interface Unit with the GEA 7100 #2 (Aft Left) Engine/Airframe Interface Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Turn the small FMS knob to the right to drop the menu down. (o) Turn the small FMS knob to the right to scroll until highlighted on GEA 2 (may be amber in color). (p) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(q) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (r) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

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(s) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(t) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (u) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(v) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (w) Push the FMS knob to deactivate the cursor. (x) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (y) Make sure that in the CONFIGURATION ITEMS box that GEA 1 and GEA 2 show Valid (in green). (z) Select Home on the GTC. (aa) Select Restart Options. (ab) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(ac) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ad) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (5) Swap the GEA 7100 #1 (Forward) Engine/Airframe Interface Unit with the GEA 7100 #3 (Aft Right) Engine/Airframe Interface Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

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(j) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Turn the small FMS knob to the right to drop the menu down. (o) Turn the small FMS knob to the right to scroll until highlighted on GEA 3 (may be amber in color). (p) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(q) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (r) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(s) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(t) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (u) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(v) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (w) Push the FMS knob to deactivate the cursor. (x) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (y) Make sure that in the CONFIGURATION ITEMS box that GEA 1 and GEA 3 show Valid (in green). (z) Select Home on the GTC. (aa) Select Restart Options. (ab) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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(6) Swap the GEA 7100 #2 (Aft Left) Engine/Airframe Interface Unit with the GEA 7100 #3 (Aft Right) Engine/Airframe Interface Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(k) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (l) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

(m) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (n) Turn the small FMS knob to the right to drop the menu down. (o) Turn the small FMS knob to the right to scroll until highlighted on GEA 3 (may be amber in color). (p) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(q) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (r) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(s) Select the configuration box adjacent to the GEA7100 x Rigging Table line item toremove the check mark.

NOTE: If the check mark stays, it will be necessary to do the rigging of the related surfaces again.

(t) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (u) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 4 minutes.

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(v) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (w) Push the FMS knob to deactivate the cursor. (x) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (y) Make sure that in the CONFIGURATION ITEMS box that GEA 2 and GEA 3 show Valid (in green). (z) Select Home on the GTC. (aa) Select Restart Options. (ab) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(ac) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ad) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. I. GIA 64E Integrated Avionics Unit Software/Configuration Loading Instructions. (1) Replace the GIA 64E #1 (Left) Integrated Avionics Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1.5 minutes.

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(o) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GIA 1 below the GIA software and configurations.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 6 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (u) Turn the small FMS knob to the right to drop the menu down. (v) Turn the small FMS knob to the right to scroll until highlighted on GPS 1 (may be amber in color). (w) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(x) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (y) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(z) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (aa) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

(ab) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ac) Turn the small FMS knob to the right to drop the menu down. (ad) Turn the small FMS knob to the right to scroll until highlighted on NAV 1 (may be amber in color). (ae) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(af) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (ag) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ah) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (ai) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(aj) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ak) Push the FMS knob to deactivate the cursor.

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(al) Copy the angle of attack (AOA) rigging as follows: 1 Turn the right outer FMS knob to go to the CAL tab.

NOTE: If the cursor is already active, push the right inner FMS knob to deactivate it. The cursor must be deactivated to go to a new page.

2 Set the AOA rigging switch on the aft side of the pedestal to the ACTIVE position. 3 Select the Left and Right arrows until Restore is highlighted at the bottom of the pilot's PFD.

NOTE: If the Restore tab is grayed out, go to step X.

4 Select the Select button to copy the AOA rigging to the new GIA from the configuration module. 5 Select Enter to confirm the restore AOA message. 6 After the calibration is saved to the two GIA's, select Enter. 7 Set the AOA rigging switch on the aft side of the pedestal to the INACTIVE position. 8 At the top of the page, in the LRU RIGGING STATUS window, make sure that the two GIA's have a green check mark. (am) Turn the large FMS knob to the left to select the System tab (bottom right of the PFD screen). (an) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (ao) Make sure that in the CONFIGURATION ITEMS box that COM 1 and GIA 1 show Valid (in green). (ap) Select Home on the GTC. (aq) Select Restart Options. (ar) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(as) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (at) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GIA 64E #2 (Right) Integrated Avionics Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

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(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GIA 2 below the GIA software and configurations.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 6 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (u) Turn the small FMS knob to the right to drop the menu down. (v) Turn the small FMS knob to the right to scroll until highlighted on GPS 2 (may be amber in color). (w) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(x) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (y) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(z) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (aa) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

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(ae) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(af) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (ag) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ah) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (ai) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1.5 minutes.

(aj) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ak) Push the FMS knob to deactivate the cursor. (al) Copy the angle of attack (AOA) rigging as follows: 1 Turn the right outer FMS knob to go to the CAL tab.

NOTE: If the cursor is already active, push the right inner FMS knob to deactivate it. The cursor must be deactivated to go to a new page.

2 Set the AOA rigging switch on the aft side of the pedestal to the ACTIVE position. 3 Select the Left and Right arrows until Restore is highlighted at the bottom of the pilot's PFD.

NOTE: If the Restore tab is grayed out, go to step X.

4 Select the Select button to copy the AOA rigging to the new GIA from the configuration module. 5 Select Enter to confirm the restore AOA message. 6 After the calibration is saved to the two GIA's, select Enter. 7 Set the AOA rigging switch on the aft side of the pedestal to the INACTIVE position. 8 At the top of the page, in the LRU RIGGING STATUS window, make sure that the two GIA's have a green check mark. (am) Turn the large FMS knob to the left to select the System tab (bottom right of the PFD screen). (an) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (ao) Make sure that in the CONFIGURATION ITEMS box that COM 2 and GIA 2 show Valid (in green). (ap) Select Home on the GTC. (aq) Select Restart Options. (ar) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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(3) Swap the GIA 64E #1 (Left) Integrated Avionics Unit and the GIA 64E #2 (Right) Integrated Avionics Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GIA 1 below the GIA software and configurations.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 6 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

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(x) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (y) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(z) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (aa) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(af) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (ag) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ah) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (ai) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(aj) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ak) Turn the small FMS knob to the right to drop the menu down. (al) Turn the small FMS knob to the right to scroll until highlighted on COM 2 (may be amber in color). (am) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(an) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (ao) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ap) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (aq) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1.5 minutes.

(ar) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (as) Turn the small FMS knob to the right to drop the menu down. (at) Turn the small FMS knob to the right to scroll until highlighted on GIA 2 (may be amber in color).

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(au) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GIA 2 below the GIA software and configurations.

(av) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (aw) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ax) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (ay) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 6 minutes.

(az) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ba) Turn the small FMS knob to the right to drop the menu down. (bb) Turn the small FMS knob to the right to scroll until highlighted on GPS 2 (may be amber in color). (bc) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(bd) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (be) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(bf) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (bg) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6.5 minutes.

(bh) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (bi) Turn the small FMS knob to the right to drop the menu down. (bj) Turn the small FMS knob to the right to scroll until highlighted on NAV 2 (may be amber in color). (bk) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(bl) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (bm) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(bn) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (bo) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1.5 minutes.

(bp) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (bq) Push the FMS knob to deactivate the cursor.

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(br) Copy the angle of attack (AOA) rigging as follows: 1 Turn the right outer FMS knob to go to the CAL tab.

NOTE: If the cursor is already active, push the right inner FMS knob to deactivate it. The cursor must be deactivated to go to a new page.

2 Set the AOA rigging switch on the aft side of the pedestal to the ACTIVE position. 3 Select the Left and Right arrows until Restore is highlighted at the bottom of the pilot's PFD.

NOTE: If the Restore tab is grayed out, go to step X.

4 Select the Select button to copy the AOA rigging to the new GIA from the configuration module. 5 Select Enter to confirm the restore AOA message. 6 After the calibration is saved to the two GIA's, select Enter. 7 Set the AOA rigging switch on the aft side of the pedestal to the INACTIVE position. 8 At the top of the page, in the LRU RIGGING STATUS window, make sure that the two GIA's have a green check mark. (bs) Turn the large FMS knob to the left to select the System tab (bottom right of the PFD screen). (bt) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (bu) Make sure that in the CONFIGURATION ITEMS box that COM 1, COM 2, GIA 1, and GIA 2 show Valid (in green). (bv) Select Home on the GTC. (bw) Select Restart Options. (bx) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(by) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (bz) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. J. GMA 36B Audio Processor Software/Configuration Loading Instructions. (1) Replace the GMA 36B #1 (Left) Audio Processor and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

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(g) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

NOTE: The airplane will power up in Normal mode.

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(2) Replace the GMA 36B #2 (Right) Audio Processor and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

NOTE: The airplane will power up in Normal mode.

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(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Swap the GMA 36B #1 (Left) Audio Processor and the GMA 36B #2 (Right) Audio Processor and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

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(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (u) Turn the small FMS knob to the right to drop the menu down. (v) Turn the small FMS knob to the right to scroll until highlighted on GMA 2 (may be amber in color). (w) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(x) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (y) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(z) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (aa) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

(ab) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ac) Turn the small FMS knob to the right to drop the menu down. (ad) Turn the small FMS knob to the right to scroll until highlighted on GMA 2 AUX (may be amber in color). (ae) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(af) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (ag) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ah) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (ai) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

(aj) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ak) Push the FMS knob to deactivate the cursor. (al) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (am) Make sure that in the CONFIGURATION ITEMS box that GMA 1 and GMA 2 show Valid (in green). (an) Select Home on the GTC. (ao) Select Restart Options. (ap) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(aq) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark.

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(ar) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. K. GMC 7200 AFCS Mode Controller Software/Configuration Loading Instructions. (1) Replace the GMC 7200 AFCS Mode Controller and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 1 minute.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GMC 1 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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L. GRA 5500 Radio Altimeter Software/Configuration Loading Instructions. (1) Replace the GRA 5500 Radio Altimeter and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GRA 1 shows Valid (in green). (p) Push the FMS knob to deactivate the cursor. (q) Calibrate the GRA 5500 Radio Altimeter as follows:

CAUTION: The airplane must be physically on the ground for this procedure or the system will not calibrate correctly.

1 Turn the large FMS knob to select the GRA tab (bottom right of the PFD screen). 2 Use the Left and Right arrows on the GTC to highlight CALIBRATE at the bottom of the display. 3 Select the Select icon on the GTC. 4 Turn the large FMS knob to highlight YES when prompted to 'CALIBRATE GRA?'. 5 Select Enter on the GTC. 6 Make sure that the CALIBRATION BOX under the FAULTS window is green. (r) Select Home on the GTC. (s) Select Restart Options. (t) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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(v) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. M. GSA 9000 Autopilot Servo Actuator Software/Configuration Loading Instructions. (1) Replace the GSA 9000 Autopilot (Pitch) Servo Actuator and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown.

NOTE: There is no validation necessary for the pitch servo on the CONFIGURATION MANAGER screen. This step has been deliberately left out.

(u) Select Home on the GTC.

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(v) Select Restart Options. (w) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(x) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (y) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GSA 9000 Autopilot (Roll) Servo Actuator and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

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(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown.

NOTE: There is no validation necessary for the roll servo on the CONFIGURATION MANAGER screen. This step has been deliberately left out.

(u) Select Home on the GTC. (v) Select Restart Options. (w) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(x) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (y) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Swap the GSA 9000 Autopilot (Pitch) Servo Actuator with the GSA 9000 Autopilot (Roll) Servo Actuator and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Turn the small FMS knob to the right to drop the menu down.

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(n) Turn the small FMS knob to the right to scroll until highlighted on GSA PTCH MON (may be amber in color). (o) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (u) Turn the small FMS knob to the right to drop the menu down. (v) Turn the small FMS knob to the right to scroll until highlighted on GSA ROLL CTL (may be amber in color). (w) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(x) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (y) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(z) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (aa) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

(ab) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (ac) Turn the small FMS knob to the right to drop the menu down. (ad) Turn the small FMS knob to the right to scroll until highlighted on GSA ROLL MON (may be amber in color). (ae) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(af) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (ag) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(ah) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (ai) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 2.5 minutes.

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(aj) Select Enter when the ‘Upload and Crossfill Complete’ message is shown.

NOTE: There is no validation necessary for the pitch and roll servos on the CONFIGURATION MANAGER screen. This step has been deliberately left out.

(ak) Select Home on the GTC. (al) Select Restart Options. (am) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(an) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ao) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. N. GSD 41 Data Concentrator Unit Software/Configuration Loading Instructions. (1) Replace the GSD 41 #1 (Forward) Data Concentrator Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 3 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GSD 1 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options.

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(r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. O. GSD 41HE Data Concentrator Unit (Harsh Environment) Software/Configuration Loading Instructions. (1) Replace the GSD 41HE #2 (Aft Left) Data Concentrator Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GSD 2 below the GSD software and configurations.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 3.5 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GSD 2 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GSD 41HE #3 (Aft Right) Data Concentrator Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GSD 3 below the GSD software and configurations.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 3 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GSD 3 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status.

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5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Swap the GSD 41HE #2 (Aft Left) Data Concentrator Unit with the GSD 41HE #3 (Aft Right) Data Concentrator Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GSD 2 below the GSD software and configurations.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 3.5 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

NOTE: The system will automatically populate the options related to GSD 3 below the GSD software and configurations.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: Depending on options, the loading process will take approximately 3 minutes.

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NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. P. GSR 56 Iridium Transceiver Software/Configuration Loading Instructions. (1) To Replace a GSR 56 #1 (Right) Iridium Transceiver, no software or configuration needs to be loaded but the GSR 56 must be registered as follows:

NOTE: On the CONFIGURATION MANAGER screen, GSR1 will show "Status Not Supported" in gray.

(a) Call Garmin Connext Services at +1-913-440-1135. 1 Give the aircraft serial number, and the registration number. 2 Give the original GSR 56 serial number, and the new GSR 56 serial number. 3 Garmin Connext Services will give you a pass key. (b) Make sure that the airplane is in range of a recognized Wi-Fi network or in view of Iridium satellites (as applicable). (c) Power up the airplane in normal mode. (d) On the pilot's right GTC, do as follows: 1 Select Home. 2 Select Utilities. 3 Select Setup. 4 Select Connext Registration. 5 Select Register. 6 Enter the pass key given by Garmin Connext Services. (e) Within approximately 1-2 minutes, the new information should be shown on the right side of the GTC Connext Registration screen. (f) If using ACARS, the service provider must be contacted to tell them the new pass key (sometimes referred to as the activation code), as this will affect the subscription service through them. Contact the service provider as follows: 1 ARINC Direct: • Email: [email protected] • United States: 1-866-321-6060 • International: +1-410-266-2266. 2 Honeywell GDC: • Email: [email protected] • United States: 1-888-634-3330 • International: +1-602-365-7020. 3 SATCOM Direct: • Email: [email protected]

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• United States: 1-888-448-9003 • International: +441252-554-460. (2) To Replace a GSR 56 #2 (Left) Iridium Transceiver, no software or configuration needs to be loaded but the GSR 56 must be registered as follows:

NOTE: On the CONFIGURATION MANAGER screen, GSR2 will show "Status Not Supported" in gray.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display.

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(i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GTC 1 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (2) Replace the GTC 575 #2 (Copilot's Left) Touchscreen Control Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

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(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GTC 2 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (3) Replace the GTC 575 #3 (Pilot's Left) Touchscreen Control Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GTC 3 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options.

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(r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (4) Replace the GTC 575 #4 (Copilot's Right) Touchscreen Control Unit and load the software/ configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GTC 4 shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(s) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup.

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4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (t) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (5) Swap the GTC 575 #1 (Pilot's Right) Touchscreen Control Unit and the GTC 575 #2 (Copilot's Left) Touchscreen Control Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

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(w) Make sure that in the CONFIGURATION ITEMS box that GTC 1 and GTC 2 show Valid (in green). (x) Select Home on the GTC. (y) Select Restart Options. (z) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (6) Swap the GTC 575 #1 (Pilot's Right) Touchscreen Control Unit and the GTC 575 #3 (Pilot's Left) Touchscreen Control Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display.

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(q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (7) Swap the GTC 575 #1 (Pilot's Right) Touchscreen Control Unit and the GTC 575 #4 (Copilot's Right) Touchscreen Control Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display.

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(k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (8) Swap the GTC 575 #2 (Copilot's Left) Touchscreen Control Unit and the GTC 575 #3 (Pilot's Left) Touchscreen Control Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

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(f) Turn the small FMS knob to the right to scroll until highlighted on GTC 2 (may be amber in color). (g) Select Enter on the GTC.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: The airplane will power up in Normal mode.

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c Make sure that no Config message shows. (9) Swap the GTC 575 #2 (Copilot's Left) Touchscreen Control Unit and the GTC 575 #4 (Copilot's Right) Touchscreen Control Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: The airplane will power up in Normal mode.

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(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. (10) Swap the GTC 575 #3 (Pilot's Left) Touchscreen Control Unit and the GTC 575 #4 (Copilot's Right) Touchscreen Control Unit and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 8 minutes.

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NOTE: The airplane will power up in Normal mode.

(aa) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (ab) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no DB Mismatch message shows. b Make sure that no Manifest message shows. c Make sure that no Config message shows. R. GTS 8000 Traffic Collision Avoidance System (TCAS II) Processor Software/Configuration Loading Instructions. (1) Replace the GTS 8000 Traffic Collision Avoidance System (TCAS II) Processor and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 3 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Load the TCAS Configuration as follows: 1 Turn the small FMS knob to the right until the AIRCRAFT CONFIGURATION screen shows.

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2 Make sure that the registration and the VFR code are correct. If not, do as follows: a Push the FMS knob to activate the cursor.

NOTE: The cursor should be on the Aircraft Registration line.

b Select Keyboard on the GTC GDU Controls screen. c Enter the aircraft tail number.

NOTE: A Hexadecimal code needs to be entered for non-US registered aircraft.

d The VFR code should be set to the correct value for the country of registry. 3 Make sure that the Domain Identifier is correct as follows: a Find the correct ISO 3166-1 ALPHA-3 code for the country of registry as follows: • Access the website txtavsupport.com and log on with your User Name and Password. • Under MY MODELS, select 'Citation 700'. • Under AVIONICS, select 'Domain Identifier'. • Find the necessary country and the associated three letter Identifier.

NOTE: An example of a three letter Identifier is "USA" for the United States.

b If the value is not correct, enter the three letter Identifier into the Domain Identifier line with Keyboard on the GTC GDU Controls screen. (o) Complete the TCAS Configuration as follows:

NOTE: These steps are necessary whether changes were made to the TCAS settings or not.

1 Use the Left and Right arrows on the GTC to highlight SET GTS at the bottom of the display. 2 Select the Select icon on the GTC. 3 When prompted to 'Save parameters to GTS?', select Enter to select OK. 4 Select Enter when the 'GTS CONFIGURED COMPLETE' message is shown. (p) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (q) Make sure that in the CONFIGURATION ITEMS box that GTS shows Valid (in green). (r) Select Home on the GTC. (s) Select Restart Options. (t) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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S. GTX 3000 Mode S Transponder Software/Configuration Loading Instructions. (1) Replace the GTX 3000 #1 (Left) Mode S Transponder and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 11 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Load the Transponder Configuration as follows: 1 Turn the small FMS knob to the right until the AIRCRAFT CONFIGURATION screen shows. 2 Make sure that the registration and the VFR code are correct. If not, do as follows: a Push the FMS knob to activate the cursor.

NOTE: The cursor should be on the Aircraft Registration line.

b Select Keyboard on the GTC GDU Controls screen. c Enter the aircraft tail number.

NOTE: A Hexadecimal code needs to be entered for non-US registered aircraft.

NOTE: An example of a three letter Identifier is "USA" for the United States.

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b If the value is not correct, enter the three letter Identifier into the Domain Identifier line with Keyboard on the GTC GDU Controls screen. (o) Complete the Transponder Configuration as follows:

NOTE: These steps are necessary whether changes were made to the transponder 1 settings or not.

1 Use the Left and Right arrows on the GTC to highlight SET GTX at the bottom of the display. 2 Select the Select icon on the GTC. 3 When prompted to 'Save parameters to GTX #1 and GTX #2?', select Enter to select OK. 4 Select Enter when the 'COMPLETE' message is shown. (p) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (q) Make sure that in the CONFIGURATION ITEMS box that GTX 1 shows Valid (in green). (r) Select Home on the GTC. (s) Select Restart Options. (t) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(u) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status. 5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (v) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (2) Replace the GTX 3000 #2 (Right) Mode S Transponder and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display.

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(k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 11 minutes.

NOTE: The cursor should be on the Aircraft Registration line.

b Select Keyboard on the GTC GDU Controls screen. c Enter the aircraft tail number.

NOTE: A Hexadecimal code needs to be entered for non-US registered aircraft.

NOTE: An example of a three letter Identifier is "USA" for the United States.

b If the value is not correct, enter the three letter Identifier into the Domain Identifier line with Keyboard on the GTC GDU Controls screen. (o) Complete the Transponder Configuration as follows:

NOTE: These steps are necessary whether changes were made to the transponder 2 settings or not.

1 Use the Left and Right arrows on the GTC to highlight SET GTX at the bottom of the display. 2 Select the Select icon on the GTC. 3 When prompted to 'Save parameters to GTX #1 and GTX #2?', select Enter to select OK. 4 Select Enter when the 'COMPLETE' message is shown. (p) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (q) Make sure that in the CONFIGURATION ITEMS box that GTX 2 shows Valid (in green). (r) Select Home on the GTC. (s) Select Restart Options. (t) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

(u) Check the LRU status as follows: 1 Select Home on the pilot's right GTC. 2 Select Utilities. 3 Select Setup. 4 Select Avionics Status.

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5 Select the LRU Info tab on the left side. a Make sure that all the LRU's show a green check mark. (v) Check the Message Status as follows: 1 Select MSG on the pilot's right GTC. a Make sure that no Manifest message shows. b Make sure that no Config message shows. (3) Swap the GTX 3000 #1 (Left) Mode S Transponder with the GTX 3000 #2 (Right) Mode S Transponder and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 11 minutes.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(p) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (q) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(r) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (s) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 11 minutes.

(t) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (u) Push the FMS knob to deactivate the cursor. (v) Load the Transponder Configuration as follows: 1 Turn the small FMS knob to the right until the AIRCRAFT CONFIGURATION screen shows.

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2 Make sure that the registration and the VFR code are correct. If not, do as follows: a Push the FMS knob to activate the cursor.

NOTE: The cursor should be on the Aircraft Registration line.

b Select Keyboard on the GTC GDU Controls screen. c Enter the aircraft tail number.

NOTE: A Hexadecimal code needs to be entered for non-US registered aircraft.

NOTE: An example of a three letter Identifier is "USA" for the United States.

b If the value is not correct, enter the three letter Identifier into the Domain Identifier line with Keyboard on the GTC GDU Controls screen. (w) Complete the Transponder Configuration as follows:

NOTE: These steps are necessary whether changes were made to the transponder settings or not.

1 Use the Left and Right arrows on the GTC to highlight SET GTX at the bottom of the display. 2 Select the Select icon on the GTC. 3 When prompted to 'Save parameters to GTX #1 and GTX #2?', select Enter to select OK. 4 Select Enter when the 'COMPLETE' message is shown. (x) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (y) Make sure that in the CONFIGURATION ITEMS box that GTX 1 and GTX 2 show Valid (in green). (z) Select Home on the GTC. (aa) Select Restart Options. (ab) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

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T. GWX 80 Weather Radar Software/Configuration Loading Instructions. (1) Replace the GWX 80 Weather Radar and load the software/configuration files as follows: (a) Select GDU Controls on the pilot's right GTC Home (Config Mode) screen.

NOTE: The GDU Controls screen will show on the GTC. The steps that follow use this screen and the FMS knob on the GTC to control the pilot's PFD.

NOTE: ‘LOADING FILES’ will show for a few moments in the center of the screen as the system retrieves the data from the internal memory.

(h) Use the Left and Right arrows on the GTC to highlight CHK ALL at the bottom of the display. (i) Select the Select icon on the GTC.

NOTE: All check boxes should be checked.

(j) Use the Left and Right arrows on the GTC to highlight LOAD at the bottom of the display. (k) Select the Select icon on the GTC.

NOTE: The loading process will take approximately 6 minutes.

(l) Select Enter when the ‘Upload and Crossfill Complete’ message is shown. (m) Push the FMS knob to deactivate the cursor. (n) Turn the small FMS knob to the right until the CONFIGURATION MANAGER screen shows. (o) Make sure that in the CONFIGURATION ITEMS box that GWX shows Valid (in green). (p) Select Home on the GTC. (q) Select Restart Options. (r) Select System to Normal Mode.

NOTE: The airplane will power up in Normal mode.

6. Troubleshooting A. If there is a FAIL message during any software or configuration loading procedure, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting. B. For issues that are seen after the software is loaded, refer to Chapter 42, Garmin G5000 Integrated Avionics System Software (Version 58) - Troubleshooting.

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GARMIN G5000 INTEGRATED AVIONICS SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a description and the operation of the Garmin G5000 Integrated Avionics System. The line replaceable units (LRU's) in the Garmin G5000 Integrated Avionics System are the Garmin GIA 64E Integrated Avionics Unit, Garmin GSD 41 Data Concentrator Unit (DCU), Garmin GSD 41HE Harsh Environment DCU, Garmin GEA 7100 Engine/Airframe Interface Unit, Garmin GDU 1450W Multifunction Display (MFD), Garmin GDU 1450W Primary Flight Display (PFD), Garmin GTC 575 Touchscreen Control Unit, Garmin GCU 275 Display Controller, and DISPLAY REV switch/light. B. Refer to Figure 1 for a general view of the Garmin G5000 Integrated Avionics System. C. For the Garmin G5000 Integrated Avionics System block diagram, refer to txtavsupport.com as follows: (1) Access the website txtavsupport.com and log on with your User Name and Password. (2) Under the MY MODELS section, select 'Citation 700'. (3) Under the AVIONICS section (right side of the screen), select 'Model 700 G5000 System Block Diagram'.

2. Description A. Garmin GIA 64E Integrated Avionics Unit (1) There are two Garmin GIA 64E Integrated Avionics Units installed in the airplane. They are installed in the cockpit behind the pilot's and copilot's primary flight displays (PFD's), forward of FS 114.39. Each GIA is installed in a mounting rack that is attached to the instrument panel support. (2) The GIA is the primary processor that interfaces with all other LRU's in the G5000 system. It communicates with these LRU's through a high-speed data bus (HSDB), RS-232, RS-485/422, and ARNIC 429. (3) The GIA contains the subassemblies that follow: (a) A primary processor that interfaces with all LRU's in the G5000 system. (b) A satellite based augmentation system (SBAS) twelve channel parallel global navigation satellite system (GNSS) receiver that tracks and uses up to twelve satellites at the same time. (c) A VHF communication transceiver that tunes from 118.000 to 136.992 MHz and gives 760 channels at 25 kHz spacing or 3040 channels at 8.33 kHz spacing. (d) A VHF omnidirectional radio (VOR)/instrument landing system (ILS) localizer receiver that tunes from 108.000 to 117.950 MHz in 50 kHz increments. (e) An ILS glideslope receiver that tunes from 328.600 to 335.400 MHz as paired with the frequency tuned on the VOR/ILS localizer receiver. (f) A flight director processor that interfaces with the G5000 automatic flight control system (AFCS) system. B. Garmin GSD 41 Data Concentrator Unit (DCU) (1) There is one Garmin GSD 41 DCU (unit #1) installed on the airplane. It is installed in the cockpit behind the pilot's PFD, forward of FS 114.39. The GSD 41 DCU is installed in a mounting rack that is attached to the instrument panel support. (2) The GSD 41 DCU is a microprocessor-based input/output (I/O) digital data concentrator that is the interface between different digital airplane systems and the G5000 system. The DCU expands the I/O functions of the G5000 system. An HSDB connection is used to communicate with LRU's in the G5000 system, while an ARINC 429 connection is used to communicate with non-Garmin LRU's and systems. (3) The GSD 41 DCU has two circuit boards with dedicated connectors: (a) The first circuit board contains the processor, power supply, four Ethernet controllers, all of the memory, and a field programmable gate array (FPGA). The FPGA processes approximately half of the discrete inputs and ARINC 429 I/O. (b) The second circuit board contains fourteen RS-485/RS-422 ports and a second FPGA. The second FPGA processes the other half of the discrete inputs and ARINC 429 I/O as well as the ARINC 717 I/O.

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Garmin G5000 Integrated Avionics System Figure 1 (Sheet 1)

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Garmin G5000 Integrated Avionics System Figure 1 (Sheet 2)

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C. Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU) (1) There are two Garmin GSD 41HE Harsh Environment DCU's (units #2 and #3) installed on the airplane. They are installed in the forward section of the tailcone, aft of FS 539.58 and between LBL 15.25 and RBL 15.18. The GSD 41HE DCU's are installed in mounting racks and are attached to the forward tailcone support shelf. (2) The GSD 41HE DCU is of the harsh environment variety and has a larger environmentally hardened enclosure for added protection. Its functions and internal specifications are the same as what is described for the GSD 41 DCU. D. Garmin GEA 7100 Engine/Airframe Interface Unit (1) There are three Garmin GEA 7100 Engine/Airframe Interface Units installed in the airplane. The forward GEA 7100 (unit #1) is installed in the cockpit behind the multifunction display (MFD), forward of FS 114.39. The forward GEA 7100 unit is installed in a mounting rack that is attached to the instrument panel support. The aft GEA 7100 (units #2 and #3) are installed in the forward section of the tailcone, aft of FS 539.58 and between LBL 15.25 and RBL 15.18. The aft GEA 7100 units are also installed in mounting racks and are attached to the forward tailcone support shelf. (2) The GEA 7100 is a microprocessor-based I/O analog data concentrator that is used to measure analog, digital, and discrete sensor inputs as well as to drive annunciator outputs for airframe and engine systems. The GEA 7100 units are connected to the GIA's with a dedicated and isolated RS-485 data bus. (3) Similar to the GSD 41 DCU, the GEA 7100 expands the I/O functions of the G5000 system. E. Garmin GDU 1450W Flight Display (1) Garmin GDU 1450W Multifunction Display (MFD) (a) There is one Garmin GDU 1450W MFD installed in the airplane. It is installed in the center of the cockpit instrument panel at approximately FS 118.516. It is mounted flush to the instrument panel with four pawl latches. (2) Garmin GDU 1450W Primary Flight Display (PFD) (a) There are two Garmin GDU 1450W PFD's installed in the airplane. They are installed in the left and the right sides of the cockpit instrument panel in front of the crew seats at approximately FS 118.516. They are mounted flush to the instrument panel with four pawl latches. The left PFD is the pilot's PFD and the right PFD is the copilot's PFD. (3) Each GDU has a 14-inch light emitting diode (LED) backlit widescreen display with a WUXGA (1920x1200) resolution. (4) The flight displays are the primary interface for the pilot and the copilot for the G5000system. These flight displays give the data that follows to the crew: • Airplane attitude, rate of turn, slip/skid, heading, airspeed, altitude, position, ground speed, and vertical speed • Engine/airframe instrumentation and crew alerting system data • AFCS flight director command bars and modes • Display of airplane position and ground speed • Navigation and map databases • Control and display of the course deviation indicator (CDI), radio magnetic indicator (RMI), and selected heading • Area navigation functions that use the determined position/velocity and stored navigation data • Airplane approach navigation functions and databases • Interface capabilities with the GIA, other GDU's, GSD 41 DCU's, and GTC 575 touchscreen control units • Control and display of the dual communication transceivers and the dual VOR/ILS receivers • Display of the automatic direction finder (ADF) and the distance measuring equipment (DME) systems • Display of the map, weather radar, terrain awareness and warning system (TAWS), traffic collision avoidance system (TCAS II), and flight planning data • G5000 and airplane diagnostics.

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F. Garmin GTC 575 Touchscreen Control Unit (1) There are four Garmin GTC 575 Touchscreen Control Units installed in the airplane. The pilot's right and the copilot's left GTC's are installed forward of the center pedestal in the cockpit. The pilot's left and the copilot's right GTC's are installed outboard of the crews seats in the instrument panel fascia. (2) The GTC's have a 5.7-inch VGA (640 x 460 pixels) color display with an infrared touchscreen. The units also have a dual concentric knob, push knob, and joystick controller to select and control the functions on the GTC's. (3) If a PFD GTC unit is unserviceable, the functionality of that unit will move to the MFD GTC unit on its related side. Likewise, if a MFD GTC unit is unserviceable, the functionality of that unit will move to the PFD GTC unit on its related side. (4) The GTC's are used as the primary point of data entry for the G5000 system. The crew can control the functions with the GTC's as follows: • Radio management • Audio panel controls • Checklists • Electronic document viewer • Intercom control • MFD control and data entry • Alphanumeric keypad data entry • Flight plan entry and editing • Synoptic Controls • Airplane system page control • Takeoff and landing data entry and control • Performance planning data entry and control. (5) It can be necessary to clean the GTC unit's glass screen face at different intervals. Make sure that you follow the correct cleaning procedures. Refer to Chapter 34, Garmin GTC 575 Touchscreen Control Unit - Maintenance Practices. G. Garmin GCU 275 Display Controller (1) There are two Garmin GCU 275 Display Controllers installed in the airplane. The GCU's are installed in the cockpit instrument panel above the pilot's and copilot's PFD's. Each GCU is used to control the PFD on it's related side. (2) The GCU is a PFD controller used to adjust the barometric setting, to control the pan and range features on the inset map, and to control much used and high-workload flight planning functions such as the active flight plan on the lower right inset window on thePFD. H. DISPLAY REV Switch/Light (1) There are two DISPLAY REV switch/lights installed in the airplane. The switch/lights are installed on the outboard sides of the left and the right switch panels. (2) The left DISPLAY REV switch/light sets the pilot's PFD and the MFD to 60/40 reversionary mode, and the right DISPLAY REV switch/light sets the copilot's PFD and the MFD to 60/40 reversionary mode. During reversionary mode, all important flight data is shown on one of the flight displays.

3. Operation A. Garmin G5000 Integrated Avionics System (1) The Garmin G5000 Integrated Avionics System is the core of the Citation Model 700 avionics suite. The G5000 system is a highly integrated system with primary divided throughout different LRU's within the system. (2) The G5000 system includes the electronic flight display, air data, communication and navigation, automatic flight control, flight management, engine indication, airframe systems indication, weather radar, terrain awareness warning display, traffic collision avoidance system (TCAS), and graphical weather systems. The G5000 system gives a list of messages that are used by the technician to help in troubleshooting and diagnostic procedures. B. Garmin GIA 64E Integrated Avionics Unit (1) The Garmin GIA 64E Integrated Avionics Units operate as the primary communications hub that links several LRU's with each on-side PFD. Each GIA contains a GPS satellite-based augmentation system (SBAS) receiver, a VHF communication/navigation/glideslope

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(COM/NAV/GS) receiver, a flight director (FD) and system integration microprocessors. The GIA units also communicate directly with each other through the controller area network (CAN) protocol if the HSDB communication path is unserviceable. (2) Airplanes with the G5000 system software version 58 and higher, communicate the following on-side CAS messages to the on-side PFD. (a) Information is routed separately on the HSDB for on-side CAS messages from GIA #1 and HYD PUMP A for CAS Messages “ENGINE FIRE R”, “ENG EXCEEDENCE R”, “OIL PRESSURE LOW R”, and “HYD O’TEMP R" (b) Information is routed separately on the HSDB for on-side CAS messages from GIA #2 and HYD PUMP B for CAS Messages “ENGINE FIRE L”, “ENG EXCEEDENCE L”, “OIL PRESSURE LOW L”, and “HYD O’TEMP L" (c) On-side failure events trigger only on-side CAS messages from the on-side GIA as described above, and from either side only after the loss of one GIA. (3) The interface functions of the GIA are with the GNSS/SBAS receiver (15 channel), VHF communications transceiver, VOR/localizer receiver, ILS glideslope receiver, I/O processing, aural alert generation, and flight director. (4) The GIA supplies the avionics functions that follow: (a) The glideslope system. 1 The glideslope function is part of the instrument landing system (ILS). 2 The glideslope antenna receives a VOR signal which is displayed on the PFD's for the flight crew. 3 The indication gives the flight crew reference points for nose up or nosedown corrections on final approach to the runway. (b) Dual VHF NAV System. 1 The VOR NAV antenna receives VHF radio signals that are sent through the VOR NAV coupler to be used by the VOR receiver circuits in the GIA units, which supplies navigation data to the GDU's. 2 The navigation system is available during all airplane operations, which include taxi, takeoff, climb, cruise, descent, and landing. There is a navigation receiver module in each of the two GIA 64E units. (c) GPS system. 1 The GPS system supplies satellite-based navigational and wide area augmentation system (WAAS) data to the pilots and displays it graphically on the PFD and the MFD in the cockpit. 2 The Garmin GIA 64E units have a 15-channel GPS receiver subassembly installed in them that receives a signal from up to 12 satellites at one time. The color map display on the MFD shows terrain, airports, navigational aids, airspace, and other navigational waypoints. (d) VHF COMM system. 1 The VHF transceivers are controlled with the GTC 575 touchscreen control units. 2 The GIA 64E VHF communications transceiver gives tuning in 25 kHz or 8.33 kHz increments. C. Garmin GSD 41 Data Concentrator Unit (DCU) (1) The Garmin GSD 41 DCU receives from and sends signals to third party LRU's and other airplane systems through ARINC 429, ARINC 717 (for flight data recording), RS-422/485, and discrete inputs. The GSD 41 DCU receives from and sends signals to the G5000 system through an HSDB connection. Each GSD 41 DCU uses 15 ARINC 429 inputs, eight ARINC 429 outputs, one ARINC 717 input and output, 14 RS-422/485 ports, 33 on-state low discrete inputs, and 12 on-state high discrete inputs. (2) The GSD 41 DCU receives airplane system signals that use many different protocols (for example, ARINC 429 or discrete) and reformats the data to transmit on the HSDB bus to the G5000 system components. The GSD 41 DCU transmits data from the G5000 system components along the HSDB bus to the non-Garmin airplane systems. (3) All data bus inputs and discrete interface inputs are electrically isolated and operate independently. If one input or output has failure, then the failure is isolated to that data bus or discrete interface and will only effect the equipment that use that bus or discrete interface.

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(4) Navigation and Flight Management Systems. (a) The GSD 41 DCU's give the input/output (I/O) interface for the Dual Collins DME-4000 System and the Collins ADF 4000 System. Data goes between the Collins systems and the Garmin GSD 41 DCU's through ARINC 429. The G5000 system controls and tunes the DME and ADF systems. The DME and ADF systems give navigation signals and status to the GSD 41 DCU's. D. Garmin GSD 41HE Harsh Environment Data Concentrator Unit (DCU) (1) The Garmin GSD 41HE Harsh Environment DCU operates the same as the GSD 41 DCU. E. Garmin GEA 7100 Engine/Airframe Interface Unit (1) The Garmin GEA 7100 Engine/Airframe Interface Unit gives an analog interface between the airplane and the G5000 system. The only data bus interface in the GEA 7100 is a RS-485 data bus. This is used by the GEA 7100 to receive from and send signals to the GIA. The other interfaces are discrete inputs and outputs, annunciator outputs, analog signal inputs and outputs, and RVDT inputs and outputs from engine and airframe sensors. (2) All data bus inputs and discrete interface inputs are electrically isolated and operate independently. If one input or output has failure, then that failure is isolated to that data bus or discrete interface and will only affect the equipment that use that bus or discrete interface. F. Garmin GDU 1450W Flight Display (1) The Garmin GDU 1450W Flight Displays are the user interface for the G5000 system. The primary function of the pilot and copilot PFD's is to show graphical flight instrumentation (attitude, heading, airspeed, altitude, and vertical speed). The primary function of the MFD is to show the engine indicating system (EIS) as well as a dedicated window to show flight-related data in a multifunction area. The EIS is on the left side of the MFD and shows the engine, fuel, electrical, cabin pressurization, oxygen, landing gear, trim, and flaps indications. The multifunction area is on the right side of the MFD and can show one or two Display Panes that are controlled by the pilot's right and the copilot's left GTC's. (2) If there is a PFD failure, the MFD is used to show the PFD data. If there is an MFD failure, the PFD is used to show the MFD data. If there is an LRU failure, a large red X shows on a window related to that LRU's data. (3) When electrical power is supplied to the airplane, the GDU's start to initialize. After approximately one minute, all GDU windows will be operational. (4) The GDU's communicate with each other, the GTC's, and with the on-side GIA's through a HSDB Ethernet connection. G. Garmin GTC 575 Touchscreen Control Unit (1) The G5000 system uses four Garmin GTC 575 Touchscreen Control Units to give easy data entry, Display Pane operation, and NAV/COM tuning. (2) The pilot's right and the copilot's left GTC's that are installed forward of the center pedestal in the cockpit control the Display Panes of each GDU as well as flight management system (FMS) functions. When the pilot's right GTC is in control of a Display Pane, the Display Pane is highlighted in cyan. When the copilot's left GTC is in control of a Display Pane, the Display Pane is highlighted in dark purple. (3) The pilot's left and the copilot's right GTC's control the related PFD's if the user selects the Nav Source and omni-bearing selector (OBS), Bearing Pointers, Speed Bugs, Timers, setting minimums, Inset Map Settings, FMS Sensors, and PFD Settings. The PFD's can be set between a full PFD display and split mode, where a condensed PFD and a Display Pane are displayed. (4) There are three physical controls on each GTC: a joystick on the left side, a volume knob in the middle, and a dual concentric knob on the right side. The operations of the joystick and the knobs on the GTC's are context-sensitive. The Label Bar above each related control shows which functions currently apply to each control. (a) The joystick can be turned to increase or decrease detail on some system displays. When the joystick is pushed, the Map Pointer is activated for Map Panning. It can be pushed again to stop the Map Pointer. (b) The volume knob is turned to increase or decrease the selected audio source volume. If a COM radio is selected, the volume knob can be pushed to start or stop squelch. If a NAV radio is selected on the AUDIO & RADIOS screen on the GTC, the volume knob can be pushed to let NAV audio be heard for identification.

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(c) The dual concentric knob is used for radio tuning and selection, frequency transfer, and data entry. Turn the large knob to tune the selected radio frequency in 1 MHz increments. Turn the small knob to tune the selected radio frequency in 1 KHz increments. Push the small knob momentarily to change the selected COM radio source (COM 1 or COM 2) to be tuned. Push and hold the small knob for 1.5 seconds to move the selected Standby COM frequency to the active COM frequency. H. Garmin GCU 275 Display Controller (1) The GCU 275 Display Controller is a panel mounted user interface. The left GCU controls the pilot's PFD and the right GCU 275 controls the copilot's PFD. Each GCU is connected to it's PFD and to the MFD with an RS-232 connection. (2) The GCU display controllers can control the MFD unit when it operates in reversionary mode to show primary flight data. The GCU will also control the GDU that is used as the MFD unitwhen the MFD operates in PFD reversionary mode to show primary flight data. I. DISPLAY REV Switch/Light (1) When the left or right DISPLAY REV switch/light is pushed, the MFD will display a 60/40 reversionary mode that lets the crew view the PFD attitude directional indicator (ADI), horizontal situational indicator (HSI), altitude, airspeed, heading, a multifunction window and the engine indication strip.

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SUPPLEMENT NO: ICA-700-42-00001 APPENDIX A: ILLUSTRATED PARTS CATALOG

Nomenclature Part Number Quantity Control Wheel Switch 10S1048 02 Garmin Database SD Card 010-00474-50 01 Garmin Software Loader SD Card 010-02010-14 [(8203141-3) 01 Software Version 006-B2257-58) Default Pilot Profile -- 8203142-11 01 CMC Viewer Card -- 8204541-21 (Version 1.326) 01 CMC Configuration SD Card -- 8204542-17 (Version 2.60) 01 ARES Configuration SD Card -- 8204546-5 01 ARES II Software Installation Card -- 8204547-1 01 Flight Data Recorder (V. 1.10H) -- 8203132-1 01

SUPPLEMENT NO: ICA-700-42-00001 APPENDIX B: WIRING DIAGRAM MANUAL

22-30-01

THROTTLE QUADRANT AIRPLANES 0034 & ON

Figure 02 Page 1 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UI001 THROTTLE QUADRANT AFT TAIL / R ENGINE ENG TOP DISC PED / R CABIN J2 PI081 R CABIN / FWD TAIL FWD TAIL / AFT TAIL JE047 PXM047 PXM048 JE048 PE049 R FADEC B PF137 JF137 JA018 PA018 JT144 PT144 BCK BCK BCK BCK BCK BCK BCK BA V W RH B RVDT OUT VB 52 2 50 17 31 22WH 31 22WH 17 TLA VB 50160RBR78-22WH 50101RBR114-22WH 50319RBR136-22WH 50302RBR46-22WH BA V W RH B RVDT OUT LO 51 3 51 18 33 22BL 33 22BL 19 TLA RTN 50160RBR78-22BL 50101RBR114-22BL 50319RBR136-22BL 50302RBR46-22BL BA V W RH B RVDT OUT VA 50 50160RBR78-22OR 4 50101RBR114-22OR 52 50319RBR136-22OR 19 50302RBR46-22OR 32 22OR 32 22OR 18 TLA VA

BA V W RH B RVDT IN (+) 55 5 53 20 22 22WH 22 22WH 20 TLA EXC 50160RBR81-22WH 50101RBR117-22WH 50319RBR137-22WH 50302RBR47-22WH BA V W RH B RVDT IN (-) 54 50160RBR81-22BL 6 50101RBR117-22BL 54 50319RBR137-22BL 21 50302RBR47-22BL 23 22BL 23 22BL 21 TLA EXC RTN

BA RH T/R SOLENOID (-) 27 50160RXS151-22 7 50101RXS99-22 55 50319RXS468-22 3 50302RXS226-22 4 REFER TO 76-11-01

RH T/R SOLENOID (+) 26 50160RXS152-22 8 50101RXS98-22 56 RH T/R S2 (NC) 10 RH T/R S2 (NO) 12 50160RXS153-22 9 50101RXS101-22 57 RH T/R S2 (C) 11 REFER TO 78-30-01

RH T/R S4 (NC) 16 RH T/R S4 (NO) 18 50160RXS154-22 10 50101RXS104-22 58 RH T/R S4 (C) 17 50160RXS155-22 11 50101RXS105-22 59 AFT TAIL / R ENGINE RH TO/GA 20 E 50160XXP157-22 JA030 PA030 BA JE045 PE045 50101RXS1190-22 P 50326RXS22-22 4 REFER TO 76-11-01 GICB04 ENG TOP DISC RH TO/GA 21 50160XXS156-22 AFT TAIL / L ENGINE PED / L CABIN L CABIN / FWD TAIL FWD TAIL / AFT TAIL JD045 PXM047 PXM048 JD046 PD047 L FADEC A PC142 JC142 JA017 PA017 JT145 PT145 BCK BCK BCK BCK BCK BCK BCK BA BE V W LH A RVDT OUT VB 4 14 34 2 31 31 22WH 17 TLA VB 50160LAR83-22WH 50101LAR119-22WH 50319LAR143-22WH 50301LAR77-22WH BA 50703LAR6-22WH BE V W LH A RVDT OUT LO 5 15 35 3 33 33 22BL 19 TLA RTN 50160LAR83-22BL 50101LAR119-22BL 50319LAR143-22BL 50301LAR77-22BL BA 50703LAR6-22BL BE V W LH A RVDT OUT VA 6 50160LAR83-22OR 16 50101LAR119-22OR 36 50319LAR143-22OR 4 50301LAR77-22OR 32 50703LAR6-22OR 32 22OR 18 TLA VA

BA BE V W LH A RVDT IN (+) 2 17 37 5 22 22 22WH 20 TLA EXC 50160LAR86-22WH 50101LAR122-22WH 50319LAR144-22WH 50301LAR78-22WH BA 50703LAR7-22WH BE V W LH A RVDT IN (-) 1 50160LAR86-22BL 18 50101LAR122-22BL 38 50319LAR144-22BL 6 50301LAR78-22BL 23 50703LAR7-22BL 23 22BL 21 TLA EXC RTN

J3 PI082 FWD TAIL / R ENGINE PED / R CABIN R CABIN / FWD TAIL JE045 PE045 PE046 R FADEC A

PF137 JF137 JA030 PA030 BA BE RH A RVDT IN (+) 2 12 A 22 20 TLA EXC 50160RAR88-22WH 50101RAR124-22WH 50326RAR10-22WH BA 50708RAR7-22WH BE RH A RVDT IN (-) 1 50160RAR88-22BL 13 50101RAR124-22BL B 50326RAR10-22BL 23 50708RAR7-22BL 21 TLA EXC RTN

BA BE RH A RVDT OUT VB 6 14 C 31 17 TLA VB 50160RAR90-22WH 50101RAR126-22WH 50326RAR11-22WH BA 50708RAR6-22WH BE RH A RVDT OUT LO 5 15 D 33 19 TLA RTN 50160RAR90-22BL 50101RAR126-22BL 50326RAR11-22BL BA 50708RAR6-22BL BE RH A RVDT OUT VA 4 50160RAR90-22OR 16 50101RAR126-22OR E 50326RAR11-22OR 32 50708RAR6-22OR 18 TLA VA BCK BCK BCK BCK BCK

PED / L CABIN L CABIN / FWD TAIL FWD TAIL / AFT TAIL AFT TAIL / L ENGINE

PC142 JC142 JA017 PA017 JT145 PT145 BA JD045 PXM047 LH T/R SOLENOID (-) 27 50160LXS158-22 19 50101LXS107-22 39 50319LXS469-22 7 50301LXS214-22 4 REFER TO 76-11-01

JA029 PA029 BA 50101LXS1191-22 U 50325LXS52-22 JA017 PA017 AFT TAIL / L ENGINE LH T/R SOLENOID (+) 26 50160LXS159-22 20 50101LXS106-22 40 JD048 PD048 4 REFER TO 76-11-01 LH T/R S1 (NC) 10 LH T/R S1 (NO) 12 50160LXS109-22 21 50101LXS624-22 41 LH T/R S1 (C) 11 50160LXS110-22 22 50101LXS625-22 42 REFER TO 78-30-01

LH T/R S3 (NC) 16 LH T/R S3 (NO) 18 50160LXS112-22 23 50101LXS626-22 43 LH T/R S3 (C) 17 AFT TAIL / L ENGINE L CABIN / FWD TAIL JD048 PD048 PD049 L FADEC B JA029 PA029 BCK BCK BCK BCK BCK BA BE LH B RVDT IN (+) 55 24 A 22 20 TLA EXC 50160LBR93-22WH 50101LBR129-22WH 50325LBR14-22WH BA 50707LBR7-22WH BE LH B RVDT IN (-) 54 50160LBR93-22BL 25 50101LBR129-22BL B 50325LBR14-22BL 23 50707LBR7-22BL 21 TLA EXC RTN

BA BE LH B RVDT OUT VB 50 26 C 31 17 TLA VB 50160LBR95-22WH 50101LBR131-22WH 50325LBR15-22WH BA 50707LBR6-22WH BE LH B RVDT OUT LO 51 27 D 33 19 TLA RTN 50160LBR95-22BL 50101LBR131-22BL 50325LBR15-22BL BA 50707LBR6-22BL BE LH B RVDT OUT VA 52 50160LBR95-22OR 28 50101LBR131-22OR E 50325LBR15-22OR 32 50707LBR6-22OR 18 TLA VA

LH TO/GA 21 50160XXP161-22 F GICB04 PC143 JC143 28 LH TO/GA 20 50160XXS160-22 29

UI301 GARMIN INTEGRATED AVIONICS #1

P604 PI303 8207610-2C1

LH TOGA 19 50103XXS255-22

UI302 GARMIN INTEGRATED AVIONICS #2

P604 PI304

RH TOGA 21 50103XXS254-22

XXXXXXX_X THROTTLE QUADRANT Figure 02. (Sheet 1) Figure 02 Page 2 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

THROTTLE QUADRANT

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GICB04 S3521-7 GROUND STUD KIT (ZONE 229) 0034 & ON 01 J2 CONNECTOR RF J3 MS27497T8F98PA CONNECTOR 96906 0034 & ON 01 S3744-14 . BACKSHELL 96906 01 JA017 D38999/24FJ35PN CONNECTOR (ZONE 281) 0034 & ON 01 S3627-25 . BACKSHELL 01 JA018 D38999/24FJ35PN CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JA029 MS27474T20F39PA CONNECTOR (ZONE 281) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JA030 MS27474T20F39PA CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JC142 MS27497T24F35SB CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JC143 MS27497T24F35S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JD045 D38999/20KH35SN RECEPTACLE (ZONE 417) 0034 & ON 01 S3627-23 . BACKSHELL 01 JD046 D38999/20KH35PN RECEPTACLE 0034 & ON 01 S2800-1413 . BACKSHELL 01 JD048 D38999/20KH35SN RECEPTACLE (ZONE 417) 0034 & ON 01 S3627-23 . BACKSHELL 01 JE045 D38999/20KH35SN RECEPTACLE (ZONE 418) 0034 & ON 01 S3627-23 . BACKSHELL 01 JE047 D38999/20KH35SN RECEPTACLE (ZONE 418) 0034 & ON 01 S3627-23 . BACKSHELL 01 JE048 D38999/20KH35PN RECEPTACLE 0034 & ON 01 S2800-1413 . BACKSHELL 01 JF137 MS27497T24F35SA CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 JT145 MS27497T24F35SA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 P604 APU MASTER SW IN RF PA017 D38999/26FJ35SN PLUG (ZONE 367) 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PA018 D38999/26FJ35SN PLUG (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PA029 MS27484T20F39SA CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PA030 MS27484T20F39SA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PC142 MS27484T24F35PB PLUG (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC143 MS27484T24F35P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PD047 D38999/26FH35SN PLUG 0034 & ON 01 448HX177M2308 . BACKSHELL 06324 01

Figure 02 Page 3 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

THROTTLE QUADRANT

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PD048 D38999/26KH35PN CONNECTOR (ZONE 415) 0034 & ON 01 448HY166Z12308 . BACKSHELL 06324 01 PD049 D38999/26FH35SN PLUG (ZONE 415) 0034 & ON 01 448HS177M2308-10 . BACKSHELL 06324 01 PE045 D38999/26KH35PN CONNECTOR (ZONE 418) 0034 & ON 01 448HY166Z12308 . BACKSHELL 06324 01 PE046 D38999/26FH35SN PLUG (ZONE 416) 0034 & ON 01 448HS177M2308-10 . BACKSHELL 06324 01 PE049 D38999/26FH35SN PLUG 0034 & ON 01 448HX177M2308 . BACKSHELL 06324 01 PF137 MS27484T24F35PA CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PI081 D38999/26FE35SC PLUG (ZONE 229) 0034 & ON 01 S3627-17 . BACKSHELL 01 PI082 D38999/26FE35SA PLUG (ZONE 229) 0034 & ON 01 S3627-17 . BACKSHELL 01 PI303 M39029/58-360 PIN - CONTACT (ZONE 225) 0TRC3 0034 & ON 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 330-00185-44 . DSUB CONNECTOR 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 M23053/5-103-9 . SLEEVING 01 PI304 M39029/58-360 PIN - CONTACT (ZONE 225) 0TRC3 0034 & ON 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 330-00185-44 . DSUB CONNECTOR 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 PT145 MS27484T24F35PA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PXM047 D38999/26KH35PN CONNECTOR (ZONE 415) 0034 & ON 01 448HY166Z12308 . BACKSHELL 06324 01 PXM048 D38999/26KH35SN CONNECTOR (ZONE 415) 0034 & ON 01 S2800-1413 . BACKSHELL 01 UI001 AUTO-THROTTLE RF UI301 GARMIN INTEGRATED AVIONICS RF UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF

Figure 02 Page 4 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

UI301 GARMIN INTEGRATED AVIONICS #1 UI001 THROTTLE QUADRANT

P603 PI301 CABIN / PED JC142 PC142 PI080 J1 BCK BCK BCK A429 OUT (A429 OUT 1A) 71 50101XXB706-22WH 59 50160XXB178-22WH 1 BUS #1 INPUT HI

A429 OUT (A429 OUT 1B) 70 50101XXB706-22BL 60 50160XXB178-22BL 2 BUS #1 INPUT LO

TQA A429 IN (A429 IN 6A) 14 50101XXB708-22WH 61 50160XXB180-22WH 3 BUS #1 OUTPUT HI

TQA A429 IN (A429 IN 6B) 15 50101XXB708-22BL 62 50160XXB180-22BL 4 BUS #1 OUTPUT LO

P604 PI303 JC143 PC143

L A/T ENGAGE REQUEST (DISC IN 6) 14 50103XXS249-22 24 50160XXS182-22 5 LH ENGAGE REQUEST

L A/T DISC (DISC IN 7) 17 50103XXS250-22 25 50160XXS183-22 6 LH A/T DISCONNECT BCK BCK

P605 PI305 JC142 PC142

L A/T ENABLE (SUPF 4A) 64 50101XXS1864-22 50101XXS1849-22 65 50160XXS184-22 7 LH ENABLE

NZ120 AVIONICS J-BOX J1 PI120 GICB04 K 50160XXP280-22 20 GROUND

26 25 9 27 K3 24 11

10 GICB06 UI302 GARMIN INTEGRATED AVIONICS #2 8 50101XXS1850-22 N CABIN / PED P605 PI306 JF137 PF137 PI083 J4

R A/T ENABLE (SUPF 4A) 64 50101XXS1865-22 50101XXS1851-22 56 50160XXS185-22 7 RH ENABLE

P603 PI302

BCK BCK BCK

A429 OUT (A429 OUT 1A) 71 50101XXB712-22WH 49 50160XXB186-22WH 1 BUS #2 IN PUT HI

A429 OUT (A429 OUT 1B) 70 50101XXB712-22BL 50 50160XXB186-22BL 2 BUS #2 INPUT LO

REFER TO 45-40-01 TQ A429 IN (A429 IN 6A) 14 50101XXB714-22WH 51 50160XXB188-22WH 3 BUS #2 OUTPUT HI

TQ A429 IN (A429 IN 6B) 15 50101XXB714-22BL 52 50160XXB188-22BL 4 BUS #2 OUTPUT LO REFER TO 45-40-01 P604 PI304 JC143 PC143

R A/T ENGAGE REQUEST (DISC IN 9) 19 50103XXS251-22 83 50160XXS190-22 5 RH ENGAGE REQUEST

R A/T DISC (DISC IN 12) 24 50103XXS252-22 84 50160XXS191-22 6 RH A/T DISCONNECT BCK BCK

J 50160XXP281-22 20 GROUND GICB01 K 50160XXP282-22 25 POWER GROUND

LH CB PANEL AUTO THROTTLE JC993 PC993 CABIN / PED JC144 PC144 REFER TO 24-61-01 5 4 50102XXP316-22 Y 50160XXP192-22 24 +28VDC IN

8207610-2C2

THROTTLE QUADRANT Figure 02. (Sheet 2) Figure 02 Page 5 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

THROTTLE QUADRANT

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GICB01 GROUND (ZONE 229) RF GICB04 S3521-7 GROUND STUD KIT (ZONE 229) 0034 & ON 01 GICB06 S2526-4 GROUNDING CONNECTOR (ZONE 225) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): S2800-39 S2800-39 CONNECTOR KIT 28198 0034 & ON 01 FC120N2 . CRIMP CONTACT 28198 01 J1 CONNECTOR RF J4 CONNECTOR RF JC142 MS27497T24F35SB CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JC143 MS27497T24F35S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JC144 MS27497T24F61S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JC993 MS27497T12F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 JF137 MS27497T24F35SA CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 NZ120 8909111-11 PCB ASSEMBLY 0034 & ON 01 P603 CONNECTOR RF P604 APU MASTER SW IN RF P605 SWITCH - R ENG FIRE RF PC142 MS27484T24F35PB PLUG (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC143 MS27484T24F35P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC144 MS27484T24F61P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC993 MS27484T12F35P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 PF137 MS27484T24F35PA CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PI080 D38999/26FC35SA PLUG (ZONE 229) 0034 & ON 01 S3627-13 . BACKSHELL 01 PI083 D38999/26FD35SN PLUG (ZONE 229) 0034 & ON 01 S3627-15 . BACKSHELL 01 PI120 M24308/2-5F CONNECTOR (ZONE 225) 0034 & ON 01 M85049/48-2-5 . STRAIN RELIEF 01 PI301 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI302 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI303 M39029/58-360 PIN - CONTACT (ZONE 225) 0TRC3 0034 & ON 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 330-00185-44 . DSUB CONNECTOR 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 M23053/5-103-9 . SLEEVING 01

Figure 02 Page 6 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

THROTTLE QUADRANT

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI304 M39029/58-360 PIN - CONTACT (ZONE 225) 0TRC3 0034 & ON 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 330-00185-44 . DSUB CONNECTOR 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PI305 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI306 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 UI001 AUTO-THROTTLE RF UI301 GARMIN INTEGRATED AVIONICS RF UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF

Figure 02 Page 7 22-30-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

23-15-01

BROADBAND SWIFT AIRPLANES 0001 & ON

Figure 01 Page 1 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UC507 UC505 SWIFT BB HLD IRIDIUM PC505B RF FILTER PC507B 2 500-665516-02-2314-XXC ANT TX - X2

PC505A 1 500-665516-01-2314-XXC

UC592 P/N = SWIFT-BB-SBU-700 SWIFT BB SBU J1 PC511A

RF TX A1 PC507C RF RX A3 500-665516-03-2314-XXC ANT RX - X3

CABIN/TAILCONE RH J-BOX BROADBAND 2 HZ230 JT912 BA JA015 PA015 BA PT912 BA +28VDC POWER 1 50101XXP448-20 Z 50319XXP53-20 F 50316XXP580-20 REFER TO 24-60-01 2 7.5 JF321 PF321 ANNUNCIATOR #3 27 62 REFER TO 23-16-01 50101XXS450-22 BA 28VDC GND 2 50101XXP446-20 GCDS47 SBU OFF/ON 3 20 SBU ENABLE 8 20 J2 PC511B PC507A CHASSIS GND 3 500-665516-05-2314-XXC 20 50101XXP447-20 E2 GCCS05 SATCOM ANT - X1 ETHERNET 4 TX + 10 50101XXB443-24RD E2 ETHERNET 4 TX - 11 50101XXB443-2420 E2 ETHERNET 4 RX + 16 50101XXB443-24BL E2 ETHERNET 4 RX - 6 50101XXB443-2460

SWIFT - ATG PLUG SWIFT - CTR PLUG INSTALLED WHEN ATG OPTION IS ORDERED INSTALLED WHEN ATG OPTION IS NOT ORDERED P0018 JC527 P0019 JC527

A A A 22 14 22 14 22

E2 E2 1 1 50180XXB2-2460 E2 50181XXB2-2460 E2 2 2 50180XXB2-24BL E2 50181XXB2-24BL E2 3 3 50180XXB2-2420 E2 50181XXB2-2420 E2 50180XXB2-24RD 4 50181XXB2-24RD 4

E2 5 5 40 50101XXB444-24RD E2 6 6 41 50101XXB444-2420 E2 7 7 42 REFER TO 23-16-01 50101XXB444-24BL E2 8 8 50101XXB444-2460 43

E2 9 9 28 50101XXB445-24RD E2 A 10 10 29 REFER TO 23-18-01 YF590 50101XXB445-2420 E2 11 11 30 50101XXB445-24BL E2 JC521 TT-5006A 22 12 12 50101XXB445-2460 31 PC521B ANTENNA

A BLUE-AFT

22 BCK

A 13 13 22 JC519 PC519B

GPS A4 500-665516-04-2314-XXC RED - FORWARD

IRS #1 A 5 50101XXB449-22WH IRS #1 B 8 50101XXB449-22BL

50101XXP1761-16 A GCSS13

UI410 P/N = GSD-41 (#1)-700 GARMIN DATA CONCENTRATOR #1 P411 PI410 REFER TO 23-16-01

CRQ'S/INT LH HS (A429 OUT 2B) 75 CRQ'S/INT LH HS (A429 OUT 2A) 74 BCK REFER TO 23-16-01 8202314-1B1

BROADBAND SWIFT Figure 01. (Sheet 1) Figure 01 Page 2 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND SWIFT

AIRPLANES 0001 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GCCS05 S3521-8 GROUND STUD KIT (ZONE 175) 0001 & ON 01 GCDS47 S3521-8 GROUND STUD KIT (ZONE 175) 0001 & ON 01 GCSS13 S3521-8 GROUND STUD KIT (ZONE 175) 0001 & ON 01 HZ230 S2899-7.5 CIRCUIT BREAKER (ZONE 366) 82647 0001 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 J1 MS27497E12F98S CONNECTOR 96906 0001 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0001 & ON 01 J2 MS27497E20F39S CONNECTOR 96906 0001 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0001 & ON 01 S3627-20 . BACKSHELL 01 JA015 D38999/24FG39PN CONNECTOR (ZONE 281) 0001 & ON 01 S3627-21 . BACKSHELL 01 JC519 CONNECTOR RF JC521 CONNECTOR RF JC527 MS27497T12F35S CONNECTOR (ZONE 275) 96906 0001 & ON 01 S3627-12 . BACKSHELL 01 JF321 MS27497T20F35S CONNECTOR (ZONE 282) 96906 0001 & ON 01 S3627-20 . BACKSHELL 01 JT912 MS27497T18F28S CONNECTOR (ZONE 366) 96906 0001 & ON 01 S3627-18 . BACKSHELL 01 P0018 MS27484T12F35P CONNECTOR 96906 0001 & ON 01 S3627-12 . BACKSHELL 01 P0019 MS27484T12F35P CONNECTOR 96906 0001 & ON 01 S3627-12 . BACKSHELL 01 P411 CONNECTOR RF PA015 D38999/26FG39SN PLUG (ZONE 367) 0001 & ON 01 S3627-21 . BACKSHELL 01 PC505A PLUG (ZONE 275) RF PC505B PLUG (ZONE 275) RF PC507A PLUG (ZONE 282) RF PC507B PLUG (ZONE 282) RF PC507C PLUG (ZONE 282) RF PC511A CONNECTOR (ZONE 275) RF PC519B PLUG (ZONE 276) RF PC521B PLUG (ZONE 276) RF PF321 MS27484T20F35P CONNECTOR (ZONE 282) 96906 0001 & ON 01 S3627-20 . BACKSHELL 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0001 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01

Figure 01 Page 3 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND SWIFT

AIRPLANES 0001 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT912 MS27484T18F28P CONNECTOR (ZONE 366) 96906 0001 & ON 01 S3627-18 . BACKSHELL 01 UC505 405019A IRIDIUM FILTER 0U8J3 0001 & ON 01 UC507 405016A HI-POWER INMARSAT LNA 0U8J3 0001 & ON 01 UC592 405040A THRANE & THRANE SWIFT SBU 0U8J3 0001 & ON 01 UI410 GSD 41 (ZONE 225) RF YF590 405006A-PMA INMARSAT SATCOM IGA 0U8J3 0001 & ON 01

Figure 01 Page 4 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

23-15-01

BROADBAND SWIFT AIRPLANES 0031 & ON

Figure 02 Page 1 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UC507 UC505 SWIFT BB HLD IRIDIUM PC505B RF FILTER PC507B 2 500-665516-02-2314-XXC J1

PC505A

1 500-665516-01-2314-XXC

UC592 J1 PC511A SWIFT BB SBU RF TX A1 PC507C RF RX A3 500-665516-03-2314-XXC J1

RH J-BOX CABIN/TAILCONE BROADBAND 2 JA015 PA015 PT912 JT912 HZ230

BA Z BA BA +28VDC POWER 1 50101XXP448-20 50319XXP53-20 F 50316XXP580-20 2 REFER TO 24-60-01 7.5 BA 28VDC GND 2 50101XXP446-20 GCDS47 JF321 PF321 JA018 PA018 PT128 JT128 REFER TO 23-16-01 63 50101XXS1818-22 103 50319XXS1393-22 96 REFER TO 23-16-01 64 50101XXS1819-22 104 50319XXS1394-22 97 REFER TO 23-16-01 REFER TO 23-16-01

JT144 PT144

ANNUNCIATOR #3 27 50101XXS450-22 62 50101XXS1737-22 35 50319XXS17-22 58

SBU ENABLE 8 20 SBU OFF/ON 3 20

J2 PC511B GCCS05 REFER TO 23-16-01 PC507A CHASSIS GND 3 500-665516-05-2314-XXC J1 20 50101XXP447-20 E2 E2 E2 ETHERNET 4 TX + 10 40 107 63 50101XXB443-24RD E2 50101XXB1720-24RD E2 50319XXB18-24RD E2 ETHERNET 4 TX - 11 41 108 64 50101XXB443-2420 E2 50101XXB1720-2420 E2 50319XXB18-2420 E2 ETHERNET 4 RX + 16 42 109 65 50101XXB443-24BL E2 50101XXB1720-24BL E2 50319XXB18-24BL E2 ETHERNET 4 RX - 6 50101XXB443-2460 43 50101XXB1720-2460 110 50319XXB18-2460 66 BCK BCK BCK

UI410 GARMIN DATA CONCENTRATOR #1

YF590 REFER TO 23-16-01 PI410 P411 TT-5006A PC521B JC521 ANTENNA IRS #1 B 8 50101XXB449-22BL 75 CRQ'S/INT LH HS (A429 OUT 2B) IRS #1 A 5 50101XXB449-22WH 74 CRQ'S/INT LH HS (A429 OUT 2A) BLUE-AFT BCK A 50101XXP1761-22 GCSS13 REFER TO 23-16-01

PC519B JC519

GPS A4 500-665516-04-2314-XXC J1

8202314-2E1

BROADBAND SWIFT Figure 02. (Sheet 1) Figure 02 Page 2 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND SWIFT

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GCCS05 S3521-8 GROUND STUD KIT (ZONE 175) 0031 & ON 01 GCDS47 S3521-8 GROUND STUD KIT (ZONE 175) 0031 & ON 01 GCSS13 S3521-8 GROUND STUD KIT (ZONE 175) 0031 & ON 01 HZ230 S2899-7.5 CIRCUIT BREAKER (ZONE 366) 82647 0031 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 J1 CONNECTOR RF J2 CONNECTOR RF JA015 D38999/24FG39PN CONNECTOR (ZONE 281) 0031 & ON 01 S3627-21 . BACKSHELL 01 JA018 D38999/24FJ35PN CONNECTOR (ZONE 282) 0031 & ON 01 S3627-25 . BACKSHELL 01 JC519 CONNECTOR RF JC521 CONNECTOR RF JF321 MS27497T20F35S CONNECTOR (ZONE 282) 96906 0031 & ON 01 S3627-20 . BACKSHELL 01 JT128 MS27497T24F35S CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 JT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0031 & ON 01 JT912 MS27497T18F28S CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-18 . BACKSHELL 01 P411 CONNECTOR RF PA015 D38999/26FG39SN PLUG (ZONE 367) 0031 & ON 01 S3627-21 . BACKSHELL 01 PA018 D38999/26FJ35SN PLUG (ZONE 368) 0031 & ON 01 S3627-25 . BACKSHELL 01 PC505A PLUG (ZONE 275) RF PC505B PLUG (ZONE 275) RF PC507A PLUG (ZONE 282) RF PC507B PLUG (ZONE 282) RF PC507C PLUG (ZONE 282) RF PC511A CONNECTOR (ZONE 275) RF PC519B PLUG (ZONE 276) RF PC521B PLUG (ZONE 276) RF PF321 MS27484T20F35P CONNECTOR (ZONE 282) 96906 0031 & ON 01 S3627-20 . BACKSHELL 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0031 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PT128 MS27484T24F35P CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 PT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0031 & ON 01 PT912 MS27484T18F28P CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-18 . BACKSHELL 01 UC505 405019A IRIDIUM FILTER 0U8J3 0031 & ON 01 UC507 405016A HI-POWER INMARSAT LNA 0U8J3 0031 & ON 01 Figure 02 Page 3 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND SWIFT

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UC592 405040A THRANE & THRANE SWIFT SBU 0U8J3 0031 & ON 01 UI410 GSD 41 (ZONE 225) RF YF590 405006A-PMA INMARSAT SATCOM IGA 0U8J3 0031 & ON 01

Figure 02 Page 4 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

23-15-01

BROADBAND SWIFT AIRPLANES 909049 & ON

Figure 03 Page 1 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UC507 UC505 SWIFT BB HLD IRIDIUM PC505B RF FILTER PC507B 2 500-665516-02-2314-XXC J1

PC505A 1 500-665516-01-2314-XXC

UC592 J1 PC511A SWIFT BB SBU RF TX A1 PC507C RF RX A3 500-665516-03-2314-XXC J1

RH J-BOX CABIN/TAILCONE BROADBAND 2 JA015 PA015 PT912 JT912 HZ230

BA BA BA +28VDC POWER 1 50101XXP448-20 Z 50319XXP53-20 F 50316XXP580-20 REFER TO 24-60-01 2 7.5 BA 28VDC GND 2 50101XXP446-20 GCDS47 JF321 PF321 JA018 PA018 PT128 JT128 REFER TO 23-16-01 SBU ENABLE 8 20 50101XXS1852-22 63 50101XXS1818-22 103 50319XXS1393-22 96 REFER TO 23-16-01 SBU OFF/ON 3 20 50101XXS1853-22 64 50101XXS1819-22 104 50319XXS1394-22 97 REFER TO 23-16-01 REFER TO 23-16-01

JT144 PT144

ANNUNCIATOR #3 27 50101XXS450-22 62 50101XXS1737-22 35 50319XXS17-22 58

J2 PC511B GCCS05 REFER TO 23-16-01 PC507A CHASSIS GND 3 500-665516-05-2314-XXC J1 50101XXP447-20 E2 E2 E2 ETHERNET 4 TX + 10 40 107 63 50101XXB443-24RD E2 50101XXB1720-24RD E2 50319XXB18-24RD E2 ETHERNET 4 TX - 11 41 108 64 50101XXB443-2420 E2 50101XXB1720-2420 E2 50319XXB18-2420 E2 ETHERNET 4 RX + 16 42 109 65 50101XXB443-24BL E2 50101XXB1720-24BL E2 50319XXB18-24BL E2 ETHERNET 4 RX - 6 50101XXB443-2460 43 50101XXB1720-2460 110 50319XXB18-2460 66 BCK BCK BCK

UI410 GARMIN DATA CONCENTRATOR #1 YF590 REFER TO 23-16-01 PI410 P411 TT-5006A PC521B JC521 ANTENNA IRS #1 B 8 50101XXB449-22BL 75 CRQ'S/INT LH HS (A429 OUT 2B) IRS #1 A 5 50101XXB449-22WH 74 CRQ'S/INT LH HS (A429 OUT 2A) BLUE-AFT BCK A 50101XXP1761-22 GCSS13 REFER TO 23-16-01

PC519B JC519

GPS A4 500-665516-04-2314-XXC J1

8202314-3E1

BROADBAND SWIFT Figure 03. (Sheet 1) Figure 03 Page 2 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND SWIFT

AIRPLANES 909049 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GCCS05 S3521-8 GROUND STUD KIT (ZONE 175) 909049 & ON 01 GCDS47 S3521-8 GROUND STUD KIT (ZONE 175) 909049 & ON 01 GCSS13 S3521-8 GROUND STUD KIT (ZONE 175) 909049 & ON 01 HZ230 S2899-7.5 CIRCUIT BREAKER (ZONE 366) 82647 909049 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 J1 CONNECTOR RF J2 CONNECTOR RF JA015 D38999/24FG39PN CONNECTOR (ZONE 281) 909049 & ON 01 S3627-21 . BACKSHELL 01 JA018 D38999/24FJ35PN CONNECTOR (ZONE 282) 909049 & ON 01 S3627-25 . BACKSHELL 01 JC519 CONNECTOR RF JC521 CONNECTOR rf JF321 MS27497T20F35S CONNECTOR (ZONE 282) 96906 909049 & ON 01 S3627-20 . BACKSHELL 01 JT128 MS27497T24F35S CONNECTOR (ZONE 366) 96906 909049 & ON 01 S3627-24 . BACKSHELL 01 JT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 909049 & ON 01 JT912 MS27497T18F28S CONNECTOR (ZONE 366) 96906 909049 & ON 01 S3627-18 . BACKSHELL 01 P411 CONNECTOR RF PA015 D38999/26FG39SN PLUG (ZONE 367) 909049 & ON 01 S3627-21 . BACKSHELL 01 PA018 D38999/26FJ35SN PLUG (ZONE 368) 909049 & ON 01 S3627-25 . BACKSHELL 01 PC505A PLUG (ZONE 275) RF PC505B PLUG (ZONE 275) RF PC507A PLUG (ZONE 282) RF PC507B PLUG (ZONE 282) RF PC507C PLUG (ZONE 282) RF PC511A CONNECTOR (ZONE 275) RF PC519B PLUG (ZONE 276) RF PC521B PLUG (ZONE 276) RF PF321 MS27484T20F35P CONNECTOR (ZONE 282) 96906 909049 & ON 01 S3627-20 . BACKSHELL 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 909049 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PT128 MS27484T24F35P CONNECTOR (ZONE 366) 96906 909049 & ON 01 S3627-24 . BACKSHELL 01 PT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 909049 & ON 01 PT912 MS27484T18F28P CONNECTOR (ZONE 366) 96906 909049 & ON 01 S3627-18 . BACKSHELL 01 UC505 405019A IRIDIUM FILTER 0U8J3 909049 & ON 01 UC507 405016A HI-POWER INMARSAT LNA 0U8J3 909049 & ON 01 Figure 03 Page 3 23-15-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND SWIFT

AIRPLANES 909049 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UC592 405040A THRANE & THRANE SWIFT SBU 0U8J3 909049 & ON 01 UI410 GSD 41 (ZONE 225) RF YF590 405006A-PMA INMARSAT SATCOM IGA 0U8J3 909049 & ON 01

23-16-01

BROADBAND - ATG AIRPLANES 0031 & ON

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UT524 P/N = GOGO-SCS-700

UT522 AVANCE L5 UT403 GARMIN ENGINE / AIRFRAME I/O #2

P71003 PT409 JT152 PT152 JT578 PT578 PT596 J1

INTERNET OPTION ENABLE 100 50323XXS548-22 GTDS67 50319XXP41-16 DD 50302XXP135-16 Z 50357XXP1-16 A28V

CABIN INTERNET ENABLE 22 50323XXS549-22 GTDS02 50357XXP3-16 DAIRCRAFT GND INTERNET RESET 6 50323XXS550-22 JF039 PF039 GTCS20 50357XXP4-16 16 BCHASSIS GND

50101XXP1255-22 D REFER TO INTERIORS 16 CCHASSIS GND PT569 JT569

A RH J-BOX REFER TO 23-18-01 5 22 JT914 PT914 PT598 J3

E2 *G UT580 1 89 ETHERNET 4 RX+ 50316XXS789-22 50357XXB17-24RD E2 *H ATG4000 CONFIG MODULE 2 90 ETHERNET 4 RX- 50316XXS788-22 50357XXB17-2420 E2 3 101 ETHERNET 4 TX+ 50357XXB17-24BL E2 4 50357XXB17-2460 78 ETHERNET 4 TX- J1 PT580

E2 LAN-TX-A 10 109 ETHERNET 1 RX+ 50357XXB6-24RD E2 LAN-TX-B 2 88 ETHERNET 1 RX- 50357XXB6-2420 E2 LAN-RX-A 9 110 ETHERNET 1 TX+ 50357XXB6-24BL E2 LAN-RX-B 1 50357XXB6-2460 87 ETHERNET 1 TX- BROADBAND 1 BCK HZ201 JT912 PT912 2 REFER TO 24-60-01 50316XXP578-16 Z CHASSIS GND 7 50357XXP5-22 GTDS02 10 28VDC GND 15 PA016 JA016 28VDC PWR 8 BROADBAND 1 CONFIG HZ202 JT114 PT114 50319XXP44-22 V JT144 PT144 2 REFER TO 24-60-01 50316XXP579-22 37 50319XXP40-22 2 50302XXP140-22 A 50357XXP2-22 5 E2 E2 63 C 42 ETHERNET 3 RX+ 50302XXB88-24RD E2 50357XXB7-24RD E2 REFER TO 23-15-01 64 D 19 ETHERNET 3 RX- 50302XXB88-2420 E2 50357XXB7-2420 E2 65 E 41 ETHERNET 3 TX+ 50302XXB88-24BL E2 50357XXB7-24BL E2 66 50302XXB88-2460 F 50357XXB7-2460 20 ETHERNET 3 TX- BCK BCK BCK

JT128 PT128

96 50319XXS1391-22 70 50302XXS334-22 U 97 50319XXS1392-22 71 50302XXS335-22 V SPARE REFER TO 23-15-01 REFER TO 23-15-01 PT597 J2

REFER TO 23-15-01 58 50302XXS94-22 B 50357XXS8-22 77 SBB ENABLE UI410 GARMIN DATA CONCENTRATOR #1 P411 PI410 REFER TO 23-15-01 JF321 PF321 JA028 PA028 BCK CRQ'S/INT LH HS (A429 OUT 2A) 74 50101XXB1302-22WH 18 50101XXB1721-22WH 68 50319XXB21-22WH 99 50302XXB96-22WH R 50357XXB12-22WH 33 A429 1 RX+ CRQ'S/INT LH HS (A429 OUT 2B) 75 50101XXB1302-22BL 19 50101XXB1721-22BL 69 50319XXB21-22BL 100 50302XXB96-22BL S 50357XXB12-22BL 23 A429 1 RX- BCK BCK BCK BCK BCK REFER TO 23-15-01 79 ATG ENABLE GTCS10 50357XXS10-22 57 FAN ENABLE 55 HEATER ENABLE PZ012 JT128 PT128 71 POWER ENABLE REFER TO 32-60-01 WOW JUNCTION 6 50316XXS770-22 94 50319XXS1390-22 1 50302XXS333-22 T 50357XXS9-22 78 WEIGHT ON WHEELS (GROUND ON GROUND) 104 WIFI 2 ENABLE GTCS10 50357XXS11-22 70 WIFI 1 ENABLE 69 TM ENABLE J1 PK502 84 GND

E2 MAINTENANCE ETHERNET PORTTX+ A 53 ETHERNET 10 RX+ 50357XXB13-24RD E2 UK502 TX- B 30 ETHERNET 10 RX- 50357XXB13-2420 E2 RX+ C 41 ETHERNET 10 TX+ 50357XXB13-24BL E2 RX- D 42 ETHERNET 10 TX- A 50357XXB13-2460 E 22 BCK AFT CABIN / TAILCONE FEEDTHROUGH P2 JK501

USB PORT VCC 1 50357XXB14-22RD 21 USB 1 VCC UK501 D- 2 50357XXB14-24WH 44 USB 1 D- D+ 3 50357XXB14-24GN 32 USB 1 D+ GND 4 56 USB 1 GND A 50357XXB14-22BK UF2004 22 BCK MEDIA SERVER RJ1 PF609 AFT CABIN / TAILCONE FEEDTHROUGH PT598 J3

E2 ETH_TX+ 1 80 ETHERNET 5 RX+ 50357XXB15-24RD E2 ETH_TX- 2 57 ETHERNET 5 RX- 50357XXB15-2420 E2 ETH_RX+ 3 68 ETHERNET 5 TX+ 50357XXB15-24BL E2 ETH_RX- 6 50357XXB15-2460 69 ETHERNET 5 TX- BCK BCK AFT CABIN / TAILCONE FEEDTHROUGH

8202313-2J1

BROADBAND - ATG Figure 02. (Sheet 1) Figure 02 Page 2 23-16-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND - ATG

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GTCS10 S3521-8 GROUND STUD KIT 0031 & ON 01 GTCS20 S3521-8 GROUND STUD KIT (ZONE 366) 0031 & ON 01 GTDS02 S3521-8 GROUND STUD KIT (ZONE 366) 0031 & ON 01 HZ201 S2899-10.0 CIRCUIT BREAKER (ZONE 366) 01295 0031 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 HZ202 S2899-5.0 CIRCUIT BREAKER (ZONE 366) 82647 0031 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 J1 MS27497E12F98S CONNECTOR 96906 0031 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0031 & ON 01 J2 MS27497E20F39S CONNECTOR 96906 0031 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0031 & ON 01 S3627-20 . BACKSHELL 01 J3 MS27497T8F98PA CONNECTOR 96906 0031 & ON 01 S3744-14 . BACKSHELL 96906 01 JA016 D38999/24FG39PN CONNECTOR (ZONE 282) 0031 & ON 01 S3627-21 . BACKSHELL 01 JA018 D38999/24FJ35PN CONNECTOR (ZONE 282) 0031 & ON 01 S3627-25 . BACKSHELL 01 JA028 D38999/24FJ35PA CONNECTOR (ZONE 282) 0031 & ON 01 S3627-25 . BACKSHELL 01 JF039 MS27497T22F53S CONNECTOR (ZONE 282) 96906 0031 & ON 01 S3627-22 . BACKSHELL 01 JF321 MS27497T20F35S CONNECTOR (ZONE 282) 96906 0031 & ON 01 S3627-20 . BACKSHELL 01 JK501 S2216-4 SOCKET 0031 & ON 01 03-06-1044 . RECEPTACLE 27264 01 JT114 MS27497T24F35SA CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-24-90 . BACKSHELL 01 JT128 MS27497T24F35S CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 JT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0031 & ON 01 JT152 MS27497T24F4S CONNECTOR (ZONE 368) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 JT569 M39029/58-360 PIN - CONTACT 0TRC3 0017 - 9999 01 SJS860500 . INLINE RECEPTACLE 58982 0017 - 9999 01 JT578 MS27497T16F99S CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-16 . BACKSHELL 01 JT912 MS27497T18F28S CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-18 . BACKSHELL 01 P2 PIN RF P411 CONNECTOR RF P71003 CONNECTOR RF PA016 D38999/26FG39SN PLUG (ZONE 368) 0031 & ON 01 S3627-21 . BACKSHELL 01

BROADBAND - ATG

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PA018 D38999/26FJ35SN PLUG (ZONE 368) 0031 & ON 01 S3627-25 . BACKSHELL 01 PA028 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0031 & ON 01 S3627-25 . BACKSHELL 01 PF039 MS27484T22F53P CONNECTOR (ZONE 282) 96906 0031 & ON 01 S3627-22 . BACKSHELL 01 PF321 MS27484T20F35P CONNECTOR (ZONE 282) 96906 0031 & ON 01 S3627-20 . BACKSHELL 01 PF609 95043-2891 RJ45 PLUG - SHIELDED 27264 0031 & ON 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0031 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PK502 M39029/57-354 CONTACT - SOCKET 81590 0031 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 PT114 MS27484T24F35PA CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 PT128 MS27484T24F35P CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 PT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0031 & ON 01 PT152 MS27484T24F4P CONNECTOR (ZONE 368) 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 PT409 D38999/26MJ35SD PLUG (ZONE 365) 0031 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0031 & ON 01 M85049/39S25N . BACKSHELL 01 PT569 M39029/57-354 CONTACT - SOCKET 81590 0031 & ON 01 SJS860510 . INLINE PLUG 58982 0017 - 0030 01 PT578 MS27484T16F99P CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-16 . BACKSHELL 01 PT580 M24308/2-2F CONNECTOR 0031 & ON 01 M24308/25-9F . CLIP ASSEMBLY 01 M85049/48-2-2F . STRAIN RELIEF 01 PT596 MS27467T13F4S CONNECTOR 96906 0031 & ON 01 S3627-12 . BACKSHELL 01 PT597 MS27467T25F35PA CONNECTOR 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 PT598 MS27467T25F35P CONNECTOR 96906 0031 & ON 01 S3627-24 . BACKSHELL 01 PT912 MS27484T18F28P CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-18 . BACKSHELL 01 PT914 MS27484T16F99P CONNECTOR (ZONE 366) 96906 0031 & ON 01 S3627-16 . BACKSHELL 01 PZ012 CONNECTOR (ZONE 366) RF RJ1 RESISTOR - (JUMPER) RF

BROADBAND - ATG

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UF2004 DMS655-11 DIGITAL MEDIA SERVER 0GZF3 0031 & ON 01 UI410 GSD 41 (ZONE 225) RF UK501 MSP100-01 MEDIA SHARE PORT 0GZF3 0031 & ON 01 UK502 106204-2 ETHERNET PORT 3YHW1 0031 & ON 01 UT403 011-02635-01 GEA 7100 (ZONE 365) 0TRC3 0031 & ON 01 UT522 P34110-002 GOGO AVANCE L5 1NQ67 0031 & ON 01 UT524 P28950 SMART CABIN SYSTEM 1NQ67 0031 & ON 01 UT580 SYSTEM RF

UT524 P/N = GOGO-SCS-700

UT522 AVANCE L5

FWD ANTENNA AFT FAIRING FEEDTHRU FAIRING / TAILCONE PY608 PT633A PT633B PT638 J2 500-105865-05-2313-LXC 500-105865-01-2313-LXC FWDH1 JT633 YY592 PY610 PT635A PT635B PT640 J4 500-105865-07-2313-RXC 500-105865-03-2313-RXC RIGHTH2 JT635 PY607 PT636A PT636B PT637 J1 500-105865-06-2313-LXC 500-105865-02-2313-LXC FWDV1 JT636 PY609 PT634A PT634B PT639 J3 500-105865-08-2313-RXC 500-105865-04-2313-RXC RIGHTV2

AFT ANTENNA JT634

PY604 PT642 J2 500-105865-09-2313-RXC AFTH3

YY593 PY606 PT644 J4 500-105865-11-2313-RXC LEFTH4

PY603 PT641 J1 500-105865-10-2313-RXC AFTV3

PY605 PT643 J3 500-105865-12-2313-RXC LEFTV4

AFT BULKHEAD 5GHZ AFT BULKHEAD / TAILCONE PC600 PA519A PA519B PT645 500-105864-11-2313-LXC 500-105864-03-2313-RXC WIFI1 YC516 JA519 PC601 PA521A PA521B PT646 500-105864-12-2313-LXC 500-105864-04-2313-RXC WIFI2 YC517 JA521 PC602 PA523A PA523B PT647 500-105864-13-2313-LXC 500-105864-05-2313-RXC WIFI3 YC518 JA523 2.4GHZ PF611 PA522A PA522B PT648 500-105864-14-2313-RXC 500-105864-06-2313-RXC WIFI4 YF516 JA522 PF612 PA524A PA524B PT649 500-105864-15-2313-RXC 500-105864-07-2313-RXC WIFI5 YF517 JA524 PF613 PA526A PA526B PT650 500-105846-16-2313-RXC 500-105864-08-2313-RXC WIFI6 YF518 JA526 TM 1 PF614 PA528A PA528B PT652 500-105864-09-2313-RXC 500-105864-01-2313-RXC TM1 YF519 JA528

TM 2 PF615 PA527A PA527B PT653 500-105864-10-2313-RXC 500-105864-02-2313-RXC TM2 YF520 JA527

8202313-2J2

BROADBAND - ATG Figure 02. (Sheet 2) Figure 02 Page 6 23-16-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND - ATG

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

J1 MS27497E12F98S CONNECTOR 96906 0031 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0031 & ON 01 J2 MS27497E20F39S CONNECTOR 96906 0031 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0031 & ON 01 S3627-20 . BACKSHELL 01 J3 MS27497T8F98PA CONNECTOR 96906 0031 & ON 01 S3744-14 . BACKSHELL 96906 01 J4 D38999/24FA98PA CONNECTOR 0031 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497E10F98P MS27497E10F98P CONNECTOR 96906 0031 & ON 01 S3627-9 . BACKSHELL 01 42878-8410 . MODULAR JACK, VERT-RJ45 27264 01 JA519 132170-10 ADAPTOR 49367 0031 & ON 01 JA521 132170-10 ADAPTOR 49367 0031 & ON 01 JA522 132170-10 ADAPTOR 49367 0031 & ON 01 JA523 132170-10 ADAPTOR 49367 0031 & ON 01 JA524 132170-10 ADAPTOR 49367 0031 & ON 01 JA526 132170-10 ADAPTOR 49367 0031 & ON 01 JA527 132170-10 ADAPTOR 49367 0031 & ON 01 JA528 132170-10 ADAPTOR 49367 0031 & ON 01 JT633 5-70-30 ADAPTER 05209 0031 & ON 01 JT634 5-70-30 ADAPTER 05209 0031 & ON 01 JT635 5-70-30 ADAPTER 05209 0031 & ON 01 JT636 5-70-30 ADAPTER 05209 0031 & ON 01 PA519A CTS922 CONNECTOR 66197 0031 & ON 01 PA519B CONNECTOR-RT ANGLE RF PA521A CONNECTOR RF PA521B CONNECTOR-RT ANGLE RF PA522A CONNECTOR-RT ANGLE RF PA522B CONNECTOR-RT ANGLE RF PA523A CONNECTOR-RT ANGLE RF PA523B CONNECTOR-RT ANGLE RF PA524A CONNECTOR-RT ANGLE RF PA524B CONNECTOR-RT ANGLE RF PA526A CONNECTOR-RT ANGLE RF PA526B CONNECTOR-RT ANGLE RF PA527A CONNECTOR-RT ANGLE RF PA527B CONNECTOR-RT ANGLE RF PA528A CONNECTOR-RT ANGLE RF PA528B CONNECTOR-RT ANGLE RF PC600 CONNECTOR KIT RF PC601 CONNECTOR KIT RF PC602 CONNECTOR KIT RF PF611 CONNECTOR KIT RF

BROADBAND - ATG

AIRPLANES 0031 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PF612 CONNECTOR KIT RF PF613 CONNECTOR KIT RF PF614 CONNECTOR KIT RF PF615 CONNECTOR KIT RF PT633A CONNECTOR-RT ANGLE RF PT633B CONNECTOR-RT ANGLE RF PT634A CONNECTOR-RT ANGLE RF PT634B CONNECTOR-RT ANGLE RF PT635A CONNECTOR-RT ANGLE RF PT635B CONNECTOR-RT ANGLE RF PT636A CONNECTOR-RT ANGLE RF PT636B CONNECTOR-RT ANGLE RF PT637 CONNECTOR KIT RF PT638 CONNECTOR-RT ANGLE RF PT639 CONNECTOR-RT ANGLE RF PT640 CONNECTOR-RT ANGLE RF PT641 CONNECTOR-RT ANGLE RF PT642 CONNECTOR-RT ANGLE RF PT643 CONNECTOR-RT ANGLE RF PT644 CONNECTOR-RT ANGLE RF PT645 CONNECTOR-RT ANGLE RF PT647 CONNECTOR-RT ANGLE RF PT648 CONNECTOR-RT ANGLE RF PT649 CONNECTOR-RT ANGLE RF PT650 CONNECTOR-RT ANGLE RF PT652 CONNECTOR-RT ANGLE RF PT653 CONNECTOR-RT ANGLE RF PY603 CONNECTOR-RT ANGLE RF PY604 CONNECTOR RF PY605 CONNECTOR RF PY606 CONNECTOR RF PY607 CONNECTOR RF PY608 CONNECTOR RF PY609 CONNECTOR RF PY610 CONNECTOR RF UT522 P34110-002 GOGO AVANCE L5 1NQ67 0031 & ON 01 UT524 P28950 SMART CABIN SYSTEM 1NQ67 0031 & ON 01 YC516 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0031 & ON 01 YC517 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0031 & ON 01 YC518 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0031 & ON 01 YF516 P16917-001 ANTENNA 1NQ67 0031 & ON 1 YF517 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0031 & ON 01 YF518 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0031 & ON 01 YF519 P18350-001 TERRESTRIAL MODEM ANTENN 1NQ67 0031 & ON 01 YF520 P18350-001 TERRESTRIAL MODEM ANTENN 1NQ67 0031 & ON 01 YY592 P35500 DUAL DIRECTIONAL ANT 1NQ67 0031 & ON 01 YY593 P35500 DUAL DIRECTIONAL ANT 1NQ67 0031 & ON 01

23-16-01

BROADBAND - ATG AIRPLANES 0034 & ON

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UT524 P/N = GOGO-SCS-700

UT522 AVANCE L5 UT403 GARMIN ENGINE / AIRFRAME I/O #2

P71003 PT409 JT152 PT152 JT578 PT578 PT596 J1

INTERNET OPTION ENABLE 100 50323XXS548-22 GTDS67 50319XXP41-16 DD 50302XXP135-16 Z 50357XXP1-16 A28V

CABIN INTERNET ENABLE 22 50323XXS549-22 GTDS02 50357XXP3-16 DAIRCRAFT GND INTERNET RESET 6 50323XXS550-22 JF039 PF039 GTCS20 50357XXP4-16 16 BCHASSIS GND

50101XXP1255-22 D REFER TO INTERIORS 16 CCHASSIS GND PT569 JT569

A RH J-BOX REFER TO 23-16-02 5 22 JT914 PT914 PT598 J3

E2 *G UT580 1 89ETHERNET 4 RX+ 50316XXS789-22 50357XXB17-24RD E2 *H ATG4000 CONFIG MODULE 2 90ETHERNET 4 RX- 50316XXS788-22 50357XXB17-2420 E2 3 101 ETHERNET 4 TX+ 50357XXB17-24BL E2 4 50357XXB17-2460 78ETHERNET 4 TX- J1 PT580

2 REFER TO 24-60-01 50316XXP579-22 37 50319XXP40-22 2 50302XXP140-22 A 50357XXP2-22 5 E2 E2 63 C 42 ETHERNET 3 RX+ 50302XXB88-24RD E2 50357XXB7-24RD E2 REFER TO 23-15-01 64 D 19 ETHERNET 3 RX- 50302XXB88-2420 E2 50357XXB7-2420 E2 65 E 41 ETHERNET 3 TX+ 50302XXB88-24BL E2 50357XXB7-24BL E2 66 50302XXB88-2460 F 50357XXB7-2460 20 ETHERNET 3 TX- BCK BCK BCK

JT128 PT128 PT597 J2

96 50319XXS1391-22 70 50302XXS334-22 U 50357XXS18-22 79 ATG ENABLE 97 50319XXS1392-22 71 50302XXS335-22 V 50357XXS19-22 71 POWER ENABLE REFER TO 23-15-01 REFER TO 23-15-01

58 50302XXS94-22 B 50357XXS8-22 77 SBB ENABLE UI410 GARMIN DATA CONCENTRATOR #1 P411 PI410 REFER TO 23-15-01 JF321 PF321 JA028 PA028

CRQ'S/INT LH HS (A429 OUT 2A) 74 50101XXB1302-22WH 18 50101XXB1721-22WH 68 50319XXB21-22WH 99 50302XXB96-22WH R 50357XXB12-22WH 33 A429 1 RX+ CRQ'S/INT LH HS (A429 OUT 2B) 75 50101XXB1302-22BL 19 50101XXB1721-22BL 69 50319XXB21-22BL 100 50302XXB96-22BL S 50357XXB12-22BL 23 A429 1 RX- BCK BCK BCK BCK BCK BCK REFER TO 23-15-01 GTCS10 50357XXS10-22 57 FAN ENABLE PZ012 JT128 PT128 55 HEATER ENABLE REFER TO 32-60-01 WOW JUNCTION 6 50316XXS770-22 94 50319XXS1390-22 1 50302XXS333-22 T 50357XXS9-22 78 WEIGHT ON WHEELS (GROUND ON GROUND) 104 WIFI 2 ENABLE GTCS10 50357XXS11-22 70 WIFI 1 ENABLE 69 TM ENABLE 84 GND J1 PK502

E2 MAINTENANCE ETHERNET PORT TX+ A 53 ETHERNET 10 RX+ 50357XXB13-24RD E2 UK502 TX- B 30 ETHERNET 10 RX- 50357XXB13-2420 E2 RX+ C 41 ETHERNET 10 TX+ 50357XXB13-24BL E2 RX- D 42 ETHERNET 10 TX- A 50357XXB13-2460 E 22 BCK AFT CABIN / TAILCONE FEEDTHROUGH P2 JK501

8202313-3J1

BROADBAND - ATG Figure 03. (Sheet 1) Figure 03 Page 2 23-16-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND - ATG

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GTCS10 S3521-8 GROUND STUD KIT 0034 & ON 01 GTCS20 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTDS02 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTDS67 S3521-8 GROUND STUD KIT (ZONE 365) 0034 & ON 01 HZ201 S2899-10.0 CIRCUIT BREAKER (ZONE 366) 01295 0034 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 HZ202 S2899-5.0 CIRCUIT BREAKER (ZONE 366) 82647 0034 & ON 01 10237-2 . CIRCUIT BREAKER LOCK OUT 0CUF4 01 J1 CONNECTOR RF J2 CONNECTOR RF J3 CONNECTOR RF JA016 D38999/24FG39PN CONNECTOR (ZONE 282) 0034 & ON 01 S3627-21 . BACKSHELL 01 JA028 D38999/24FJ35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JF039 MS27497T22F53S CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JF321 MS27497T20F35S CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JK501 S2216-4 SOCKET 0034 & ON 01 03-06-1044 . RECEPTACLE 27264 01 JT114 MS27497T24F35SA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT128 MS27497T24F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 JT152 MS27497T24F4S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT569 M39029/58-360 PIN - CONTACT 0TRC3 0017 - 9999 01 SJS860500 . INLINE RECEPTACLE 58982 0017 - 9999 01 JT578 MS27497T16F99S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JT912 MS27497T18F28S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 JT914 MS27497T16F99S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 P2 PIN RF P411 CONNECTOR RF P71003 CONNECTOR RF PA016 D38999/26FG39SN PLUG (ZONE 368) 0034 & ON 01 S3627-21 . BACKSHELL 01 PA028 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PF039 MS27484T22F53P CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PF321 MS27484T20F35P CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PF609 95043-2891 RJ45 PLUG - SHIELDED 27264 0034 & ON 01

BROADBAND - ATG

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PK502 M39029/57-354 CONTACT - SOCKET 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 PT114 MS27484T24F35PA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT128 MS27484T24F35P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT144 MS27497T24F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 PT152 MS27484T24F4P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT409 D38999/26MJ35SD PLUG (ZONE 365) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/39S25N . BACKSHELL 01 PT569 M39029/57-354 CONTACT - SOCKET 81590 0034 & ON 01 SJS860510 . INLINE PLUG 58982 0017 - 0030 01 PT578 MS27484T16F99P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PT580 M24308/2-2F CONNECTOR 0034 & ON 01 M24308/25-9F . CLIP ASSEMBLY 01 M85049/48-2-2F . STRAIN RELIEF 01 PT596 MS27467T13F4S CONNECTOR 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 PT597 MS27467T25F35PA CONNECTOR 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT598 MS27467T25F35P CONNECTOR 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT912 MS27484T18F28P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 PT914 MS27484T16F99P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PZ012 CONNECTOR (ZONE 366) RF RJ1 RESISTOR - (JUMPER) RF UF2004 DMS655-11 DIGITAL MEDIA SERVER 0GZF3 0034 & ON 01 UI410 GSD 41 (ZONE 225) RF UK501 MSP100-01 MEDIA SHARE PORT 0GZF3 0034 & ON 01 UK502 106204-2 ETHERNET PORT 3YHW1 0034 & ON 01 UT403 011-02635-01 GEA 7100 (ZONE 365) 0TRC3 0034 & ON 01 UT522 P34110-002 GOGO AVANCE L5 1NQ67 0034 & ON 01 UT524 P28950 SMART CABIN SYSTEM 1NQ67 0034 & ON 01 UT580 SYSTEM RF

UT524 P/N = GOGO-SCS-700

UT522 AVANCE L5

AFT ANTENNA JT634

PY604 PT642 J2 500-105865-09-2313-RXC AFTH3

YY593 PY606 PT644 J4 500-105865-11-2313-RXC LEFTH4

PY603 PT641 J1 500-105865-10-2313-RXC AFTV3

PY605 PT643 J3 500-105865-12-2313-RXC LEFTV4

TM 2 PF615 PA527A PA527B PT653 500-105864-10-2313-RXC 500-105864-02-2313-RXC TM2 YF520 JA527

8202313-3J2

BROADBAND - ATG Figure 03. (Sheet 2) Figure 03 Page 5 23-16-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND - ATG

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

J1 CONNECTOR RF J2 CONNECTOR RF J3 CONNECTOR RF J4 CONNECTOR RF JA519 132170-10 ADAPTOR 49367 0034 & ON 01 JA521 132170-10 ADAPTOR 49367 0034 & ON 01 JA522 132170-10 ADAPTOR 49367 0034 & ON 01 JA523 132170-10 ADAPTOR 49367 0034 & ON 01 JA524 132170-10 ADAPTOR 49367 0034 & ON 01 JA526 132170-10 ADAPTOR 49367 0034 & ON 01 JA527 132170-10 ADAPTOR 49367 0034 & ON 01 JA528 132170-10 ADAPTOR 49367 0034 & ON 01 JT633 5-70-30 ADAPTER 05209 0034 & ON 01 JT634 5-70-30 ADAPTER 05209 0034 & ON 01 JT635 5-70-30 ADAPTER 05209 0034 & ON 01 JT636 5-70-30 ADAPTER 05209 0034 & ON 01 PA519A CTS922 CONNECTOR 66197 0034 & ON 01 PA519B CONNECTOR-RT ANGLE RF PA521A CONNECTOR RF PA521B CONNECTOR-RT ANGLE RF PA522A CONNECTOR-RT ANGLE RF PA522B CONNECTOR-RT ANGLE RF PA523A CONNECTOR-RT ANGLE RF PA523B CONNECTOR-RT ANGLE RF PA524A CONNECTOR-RT ANGLE RF PA524B CONNECTOR-RT ANGLE RF PA526A CONNECTOR-RT ANGLE RF PA526B CONNECTOR-RT ANGLE RF PA527A CONNECTOR-RT ANGLE RF PA527B CONNECTOR-RT ANGLE RF PA528A CONNECTOR-RT ANGLE RF PA528B CONNECTOR-RT ANGLE RF PC600 CONNECTOR KIT RF PC601 CONNECTOR KIT RF PC602 CONNECTOR KIT RF PF611 CONNECTOR KIT RF PF612 CONNECTOR KIT RF PF613 CONNECTOR KIT RF PF614 CONNECTOR KIT RF PF615 CONNECTOR KIT RF PT633A CONNECTOR-RT ANGLE RF PT633B CONNECTOR-RT ANGLE RF PT634A CONNECTOR-RT ANGLE RF PT634B CONNECTOR-RT ANGLE RF PT635A CONNECTOR-RT ANGLE RF PT635B CONNECTOR-RT ANGLE RF PT636A CONNECTOR-RT ANGLE RF PT636B CONNECTOR-RT ANGLE RF PT637 CONNECTOR KIT RF Figure 03 Page 6 23-16-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

BROADBAND - ATG

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT638 CONNECTOR-RT ANGLE RF PT639 CONNECTOR-RT ANGLE RF PT640 CONNECTOR-RT ANGLE RF PT641 CONNECTOR-RT ANGLE RF PT642 CONNECTOR-RT ANGLE RF PT643 CONNECTOR-RT ANGLE RF PT644 CONNECTOR-RT ANGLE RF PT645 CONNECTOR-RT ANGLE RF PT647 CONNECTOR-RT ANGLE RF PT648 CONNECTOR-RT ANGLE RF PT649 CONNECTOR-RT ANGLE RF PT650 CONNECTOR-RT ANGLE RF PT652 CONNECTOR-RT ANGLE RF PT653 CONNECTOR-RT ANGLE RF PY603 CONNECTOR-RT ANGLE RF PY604 CONNECTOR RF PY605 CONNECTOR RF PY606 CONNECTOR RF PY607 CONNECTOR RF PY608 CONNECTOR RF PY609 CONNECTOR RF PY610 CONNECTOR RF UT522 P34110-002 GOGO AVANCE L5 1NQ67 0034 & ON 01 UT524 P28950 SMART CABIN SYSTEM 1NQ67 0034 & ON 01 YF516 P16917-001 ANTENNA 1NQ67 0034 & ON 1 YF517 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0034 & ON 01 YF518 P16917-001 REMOTE WIFI ANTENNA 1NQ67 0034 & ON 01 YF519 P18350-001 TERRESTRIAL MODEM ANTENN 1NQ67 0034 & ON 01 YF520 P18350-001 TERRESTRIAL MODEM ANTENN 1NQ67 0034 & ON 01 YY592 P35500 DUAL DIRECTIONAL ANT 1NQ67 0034 & ON 01 YY593 P35500 DUAL DIRECTIONAL ANT 1NQ67 0034 & ON 01

23-50-01

DUAL AUDIO AND VOICE AIRPLANES 0034 & ON

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

AVIONICS J-BOX PI120 J1 REFER TO 34-54-01 REFER TO 34-43-01 34 REFER TO 34-43-01 1

UI505 REFER TO 34-54-01 37 GARMIN AUDIO PROCESSOR #1 REFER TO 34-54-01 19

P3471 PI557 REFER TO 23-11-01 3 REFER TO 23-11-01 TRANSCEIVER 4 MIC KEY OUT 2 50101XXS504-22 35 WHT BLK DI003

42 D5 REFER TO 23-11-01 40

SUMMED AUDIO OUT HI 72 REFER TO 23-70-01 SUMMED AUDIO OUT LOW 53

PI501 P601 UI301 BCK GARMIN INTEGRATED AVIONICS #1 RECEIVER 1 AUDIO IN HI 6 50101LXS452-22WH 1UNSQUELCHED COM AUDIO OUT HI RECEIVER 1 AUDIO IN LO 25 50101LXS452-22BL 36UNSQUELCHED COM AUDIO OUT LO ONSIDE COM MIC AUDIO OUT HI 26 50101LXS453-22WH 7COM MIC AUDIO IN HI ONSIDE COM MIC KEY OUT 27 50101LXS453-22BL 4COM MIC KEY ONSIDE COM AUDIO IN LO 8 50101LXS453-22OR 8COM MIC AUDIO IN LO 50101LXS454-22BL 10COM 500 OHM AUDIO OUT LO ONSIDE COM AUDIO IN HI 7 50101LXS454-22WH 9COM 500 OHM AUDIO OUT HI

TRANSCEIVER 4 MIC AUDIO OUT HI 23 PI301 P603 TRANSCEIVER 4 MIC AUDIO OUT LO 62 BCK TRANSCEIVER 4 AUDIO IN HI (DIFF) 42 REFER TO 23-11-01 50101LXB457-22WH 65 AUDIO PROCESSOR (R232 OUT) TRANSCEIVER 4 AUDIO IN LO (DIFF) 43 50101LXB457-22BL 64 AUDIO PROCESSOR (R232 GND) RECEIVER 2 AUDIO IN HI (DIFF) 14 50101LXB457-22OR 63 AUDIO PROCESSOR (R232 IN) RECEIVER 2 AUDIO IN LO (DIFF) 34

RECEIVER 3 AUDIO IN HI 35 REFER TO 23-11-01 RECEIVER 3 AUDIO IN LO 36

PI556 P3471 UI504 BCK BCK GARMIN AUDIO PROCESSOR #2 E1 CROSS-SIDE BUS OUT 1A 41 60 CROSS-SIDE BUS IN 1A 50101XXB455-2296 E1 CROSS-SIDE BUS OUT 1B 40 61 CROSS-SIDE BUS IN 1B 50101XXB455-22BL E1 CROSS-SIDE BUS IN 1A 60 41 CROSS-SIDE BUS OUT 1A 50101XXB455-2293 E1 CROSS-SIDE BUS IN 1B 61 50101XXB455-22OR 40 CROSS-SIDE BUS OUT 1B

P3472 PI555

BCK RS-232 IN 1 7 PROGRAM GROUND 67 RS-232 OUT 1 6 PI554 P3472 BCK RS-232 IN 2 39 50101XXB458-22WH 38 RS-232 OUT 2 PROGRAM GROUND 18 50101XXB458-22BL 18 PROGRAM GROUND RS-232 OUT 2 38 50101XXB458-22OR 39 RS-232 IN 2

L CKPT OVERHEAD DISC JC985 PC985 JC573 PC573

A A H 22 22 VW SPEAKER AUDIO OUT HI 42 A A 1 50101LXS459-22WH 50129LXS5-22WH 22 VW SPEAKER AUDIO OUT LO 41 50101LXS459-22BL B 50129LXS5-22BL B 22 2 UC501 PILOTS SPEAKER PC971 LH CB PANEL JC971 AUDIO 1

AIRCRAFT POWER 1 53 R REFER TO 24-61-01 50101LXP460-22 5 REFER TO SHEET 6 PC991 JC991 AUDIO 1 AUX REFER TO 24-61-01 AIRCRAFT POWER 2 30 50101LXP461-22 *D 5 POWER GROUND 14 50101LXP462-22 N REFER TO SHEET 8 GIDB01 POWER GROUND 16 50101LXP463-22 R

8202350-2G1

DUAL AUDIO AND VOICE Figure 02. (Sheet 1) Figure 02 Page 2 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

DI003 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 GIDB01 204814-1 CONNECTOR (ZONE 225) 00779 0034 & ON 01 J1 MS27497E12F98S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0034 & ON 01 JC573 SJS830270 RECEPTACLE 58982 0034 & ON 01 M39029/58-360 . CONTACT PIN 0TRC3 01 JC971 MS27497T16F26S CONNECTOR (ZONE 235) 96906 0034 & ON 01 JC985 M39029/57-354 CONTACT - SOCKET (ZONE 239) 81590 0034 & ON 01 JC991 MS27497E24F4S CONNECTOR (ZONE 235) 96906 0034 & ON 01 P3471 CONNECTOR RF P3472 CONNECTOR RF P601 CONNECTOR RF P603 CONNECTOR RF PC573 CONNECTOR RF PC971 MS27484T16F26P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PC985 M39029/57-354 CONTACT - SOCKET (ZONE 239) 81590 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 M39029/58-360 . CONTACT PIN 0TRC3 01 PC991 MS27484T24F4P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PI120 M24308/2-5F CONNECTOR (ZONE 225) 0034 & ON 01 M85049/48-2-5 . STRAIN RELIEF 01 PI301 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI501 330-00185-44 CONNECTOR - DSUB (ZONE 225) 0TRC3 0034 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 PI554 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI555 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI557 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UC501 SPEAKER RF UI301 011-03711-40 GARMIN INTEGRATED AVIONICS 0TRC3 0034 & ON 01 UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 UI505 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01

UI504 GARMIN AUDIO PROCESSOR #2

P3471 PI556

TRANSCEIVER 4 MIC KEY OUT 2 TRANSCEIVER 4 MIC AUDIO OUT HI 23 TRANSCEIVER 4 MIC AUDIO OUT LO 62 TRANSCEIVER 4 AUDIO IN LO (DIFF) 43 REFER TO 23-11-01 TRANSCEIVER 4 AUDIO IN HI (DIFF) 42 RECEIVER 2 AUDIO IN HI (DIFF) 14 RECEIVER 2 AUDIO IN LO (DIFF) 34

RECEIVER 3 AUDIO IN HI 35 REFER TO 34-54-01 RECEIVER 3 AUDIO IN LO 36 UI302 GARMIN INTEGRATED AVIONICS #2 SUMMED AUDIO OUT HI 72 REFER TO 23-70-01 SUMMED AUDIO OUT LOW 53 PI502 P601 BCK RECEIVER 1 AUDIO IN HI 6 50101RXS464-22WH 1 UNSQUELCHED COM AUDIO OUT HI RECEIVER 1 AUDIO IN LO 25 50101RXS464-22BL 36 UNSQUELCHED COM AUDIO OUT LO ONSIDE COM MIC AUDIO OUT HI 26 50101RXS465-22WH 7 COM MIC AUDIO IN HI ONSIDE COM MIC KEY OUT 27 50101RXS465-22BL 4 COM MIC KEY ONSIDE COM AUDIO IN LO 8 50101RXS465-22OR 8 COM MIC SIGNAL GROUND 50101RXS466-22BL 10 COM 500 OHM AUDIO OUT LO ONSIDE COM AUDIO IN HI 7 50101RXS466-22WH 9 COM 500 OHM AUDIO OUT HI

P3472 PI554 PI302 P603 BCK BCK RS-232 IN 1 7 50101RXB467-22WH 65 AUDIO PROCESSOR (R232 OUT) PROGRAM GROUND 67 50101RXB467-22BL 64 AUDIO PROCESSOR (R232 GND) RS-232 OUT 1 6 50101RXB467-22OR 63 AUDIO PROCESSOR (R232 IN)

RH COCKPIT OVERHEAD DISC PF986 JF986 JF574 PF574

A A H 22 22 VW SPEAKER AUDIO OUT HI 42 A A 1 50101RXS468-22WH 50128RXS3-22WH 22 VW SPEAKER AUDIO OUT LO 41 50101RXS468-22BL B 50128RXS3-22BL B 22 2 UF502 PF972 JF972 COPILOTS SPEAKER AUDIO 2 RH CB PANEL

REFER TO 24-61-01 AIRCRAFT POWER 1 53 50101RXP469-22 J 5 REFER TO SHEET 7 PF992 JF992 AUDIO 2 AUX REFER TO 24-61-01 AIRCRAFT POWER 2 30 50101RXP470-22 D 5 GMA SYS ID PROG 24 BCK

POWER GROUND 14 50101RXP471-22 B GIDB02

POWER GROUND 16 50101RXP472-22 C 8202350-2G2

DUAL AUDIO AND VOICE Figure 02. (Sheet 2) Figure 02 Page 5 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GIDB02 204814-1 CONNECTOR (ZONE 225) 00779 0034 & ON 01 6-203736-0 . CONNECTOR KIT 00779 01 S2099-6 . CONTACT 00779 01 JF574 SJS830270 RECEPTACLE 58982 0034 & ON 01 M39029/58-360 . CONTACT PIN 0TRC3 01 JF972 MS27497T14F15S CONNECTOR (ZONE 236) 96906 0034 & ON 01 JF986 M39029/57-354 CONTACT - SOCKET (ZONE 239) 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 JF992 MS27497E24F4S CONNECTOR (ZONE 236) 96906 0034 & ON 01 P3471 CONNECTOR RF P3472 CONNECTOR RF P601 CONNECTOR RF P603 CONNECTOR RF PF574 CONNECTOR RF PF972 MS27484T14F15P CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 PF986 M39029/58-360 PIN - CONTACT (ZONE 239) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 PF992 MS27484T24F4P CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PI302 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI502 330-00185-44 CONNECTOR - DSUB (ZONE 225) 0TRC3 0034 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 PI554 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 UF502 SPEAKER RF UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01

UI505 UI301 GARMIN AUDIO PROCESSOR #1 GARMIN INTEGRATED AVIONICS #1

P3472 PI555 PI501 P601

BCK BCK

ON-SIDE COM MIC DIGITAL AUD OUT 8 50101XXS481-22WH 14 COM MIC DIGITAL AUDIO IN ON-SIDE COM DIGITAL AUDIO IN 9 50101XXS481-22BL 13 COM DIGITAL AUDIO OUT

50101XXS489-22 18 X-SIDE COM MIC DIGITAL AUDIO IN

PI601 P602

BCK

POWER GND 71 50101XXS482-22WH 61 POWER GROUND ON-SIDE NAV DIGITAL AUDIO IN 28 50101XXS482-22BL 59 VOR/LOC DIGITAL AUDIO OUT

UI504 GARMIN AUDIO PROCESSOR #2

PI554 P3472

BCK

47 CROSS-SIDE COM MIC DIG AUDIO OUT

50101XXS483-22OR 48 CROSS-SIDE COM DIGITAL AUDIO IN 50101XXS483-22WH 69 POWER GROUND 50101XXS483-22BL 68 CROSS-SIDE NAV DIGITAL AUDIO IN BCK

CROSS-SIDE COM DIGITAL AUDIO IN 48 50101XXS484-22WH 9 ON-SIDE COM DIGITAL AUDIO IN POWER GROUND 69 50101XXS484-22BL 71 POWER GND

CROSS-SIDE NAV DIGITAL AUDIO IN 68 50101XXS485-22 28 ON-SIDE NAV DIGITAL AUDIO IN

50101XXS490-22 8 ON-SIDE COM MIC DIGITAL AUD OUT

UI302 GARMIN INTEGRATED AVIONICS #2

PI502 P601

14 COM MIC AUDIO IN

50101XXS486-22 13 COM DIGITAL AUDIO OUT BCK

CROSS-SIDE COM MIC DIG AUDIO OUT 47 50101XXS487-22 18 XSIDE COM MIC DIGITAL AUDIO IN BCK

PI602 P602

BCK

50101XXS488-22WH 61 POWER GROUND 50101XXS488-22BL 59 VOR/LOC DIGITAL AUDIO OUT

8202350-2G3

DUAL AUDIO AND VOICE Figure 02. (Sheet 3) Figure 02 Page 7 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

P3472 CONNECTOR RF P601 CONNECTOR RF P602 CONNECTOR RF PI501 330-00185-44 CONNECTOR - DSUB (ZONE 225) 0TRC3 0034 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 PI502 330-00185-44 CONNECTOR - DSUB (ZONE 225) 0TRC3 0034 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 PI554 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI555 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI601 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-03 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-62 . DSUB CONNECTOR 0TRC3 01 M23053/5-103-9 . SLEEVING 01 PI602 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-03 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-62 . DSUB CONNECTOR 0TRC3 01 M23053/5-103-9 . SLEEVING 01 UI301 011-03711-40 GARMIN INTEGRATED AVIONICS 0TRC3 0034 & ON 01 UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 UI505 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01

MAIN PEDESTAL UI301 UI505 GARMIN INTEGRATED AVIONICS #1 GARMIN AUDIO PROCESSOR #1 P3471 PI557

BCK JC142 PC142 PC143 JC143 PI303 P604

ALERT 5 AUDIO IN HI (DIFF) 20 50101XXS491-22WH 109 50160XXS397-22WH 79 50103XXS433-22WH 2VOICE ALERT 500 OHM AUDIO OUT HI

ALERT 3,4,5 AUDIO IN LO 39 50101XXS491-22BL 110 50160XXS397-22BL 80 50103XXS433-22BL 3VOICE ALERT 500 OHM AUDIO OUT LO

ALERT 3 AUDIO IN HI 38 BCK BCK

RH TILT PANEL UI302 50101XXS1500-22BL 50101XXS1500-22OR UI504 50101XXS1500-22WH GARMIN INTEGRATED AVIONICS #2 GARMIN AUDIO PROCESSOR #2 P3471 PI556 JF140 PF140 PF141 JF141 PI304 P604

ALERT 3 AUDIO IN HI 38 50101XXS492-22WH S 50150XXS75-22WH 19 50103XXS434-22WH 2VOICE ALERT 500 OHM AUDIO OUT HI

ALERT 3,4,5 AUDIO IN LO 39 50101XXS492-22BL T 50150XXS75-22BL 20 50103XXS434-22BL 3VOICE ALERT 500 OHM AUDIO OUT LO ALERT 5 AUDIO IN HI (DIFF) 20 BCK BCK BCK

MAIN PEDESTAL

UI505 GARMIN AUDIO PROCESSOR #1 P3471 PI557 JC142 PC142 PC143 JC143 JB003 PB003

RECEIVER 5 AUDIO IN HI 15 50101XXS493-22WH 111 50160XXS398-22WH 81 50103XXS435-22WH *H REFER TO 34-51-01 RECEIVER 5 AUDIO IN LO 16 50101XXS493-22BL 112 50160XXS398-22BL 82 50103XXS435-22BL *I

BCK BCK

JA028 PA028

RECEIVER 6 AUDIO IN HI 74 50101XXS494-22WH 18 REFER TO 34-51-01 RECEIVER 6 AUDIO IN LO 75 50101XXS494-22BL 19

BCK

UI504 GARMIN AUDIO PROCESSOR #2 50101XXS496-22WH 50101XXS495-22WH 50101XXS496-22BL P3471 PI556 50101XXS495-22BL

RECEIVER 6 AUDIO IN LO 75 RECEIVER 6 AUDIO IN HI 74 RECEIVER 5 AUDIO IN LO 16 RECEIVER 5 AUDIO IN HI 15

8202350-2G4

DUAL AUDIO AND VOICE Figure 02. (Sheet 4) Figure 02 Page 9 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JA028 D38999/24FJ35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JB003 MS27474T20F39S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JC142 MS27497T24F35SB CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JC143 MS27497T24F35S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JF140 MS27497T20F41S CONNECTOR (ZONE 224) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JF141 MS27497T12F35S CONNECTOR (ZONE 224) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 P3471 CONNECTOR RF P604 APU MASTER SW IN RF PA028 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PB003 MS27484T20F39P CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PC142 MS27484T24F35PB PLUG (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC143 MS27484T24F35P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PF140 MS27484T20F41P CONNECTOR (ZONE 224) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PF141 MS27484T12F35P CONNECTOR (ZONE 224) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 PI303 M39029/58-360 PIN - CONTACT (ZONE 225) 0TRC3 0034 & ON 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 330-00185-44 . DSUB CONNECTOR 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 M23053/5-103-9 . SLEEVING 01 PI304 M39029/58-360 PIN - CONTACT (ZONE 225) 0TRC3 0034 & ON 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 330-00185-44 . DSUB CONNECTOR 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI557 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 UI301 011-03711-40 GARMIN INTEGRATED AVIONICS 0TRC3 0034 & ON 01 UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF Figure 02 Page 10 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 UI505 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01

LH NOSE LH NOSE MAINT JACKS MAINT JACK DISCONNECT NOSE CABIN PN503 JN503 PB001 JB001

JN502 1 50015XXS1-22BL C 50001XXS21-22BL 35 50101XXS473-22BL MAINT PHONE 3 50015XXS1-22WH B 50001XXS21-22WH 36 50101XXS473-22WH

JN501 1 50015XXS2-22BL F 50001XXS22-22BL 37 50101XXS474-22BL MAINT MIC 2 E 38 50015XXS2-22WH A A 50001XXS22-22WH 50101XXS474-22WH 22 H 22 BCK

UI504 GARMIN AUDIO PROCESSOR #2 P3471 PI556

BCK SEC CREW MIC AUDIO IN HI 49 SEC CREW MIC AUDIO IN LO 51 SEC CREW HEADSET AUDIO OUT LH 69 LH TAIL MAINTENANCE AFT BHD TAILCONE DISC JACK DISCONNECT

CABIN TAILCONE TAIL TAIL JT507 PT507 LH TAIL MAINT JACKS JA017 PA017 JT143 PT143

A A BCK BCK 22 H 22 3 JT512 SEC CREW HEADSET AUDIO OUT RH 70 50101XXS475-22WH 52 50319XXS703-22WH 5 50301XXS303-22WH B 50327XXS6-22WH MAINT PHONE 1 SEC CREW HEADSET AUDIO OUT LO 71 50101XXS475-22BL 53 50319XXS703-22BL 6 50301XXS303-22BL C 50327XXS6-22BL

2 JT511 PASS 1 MIC AUDIO IN HI 46 50101XXS476-22WH 54 50319XXS704-22WH 7 50301XXS304-22WH E 50327XXS7-22WH MAINT MIC 1 PASS 1 MIC AUDIO IN LO 47 50101XXS476-22BL 55 50319XXS704-22BL 8 50301XXS304-22BL F 50327XXS7-22BL

8202350-2G5

DUAL AUDIO AND VOICE Figure 02. (Sheet 5) Figure 02 Page 12 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JA017 D38999/24FJ35PN CONNECTOR (ZONE 281) 0034 & ON 01 S3627-25 . BACKSHELL 01 JB001 MS27474T22F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JN501 S1102-1 JACK (ZONE 215) 82389 0034 & ON 01 JN502 S1103-1 JACK (ZONE 215) 82389 0034 & ON 01 JN503 M39029/58-360 PIN - CONTACT (ZONE 215) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 JT143 MS27497T24F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT507 M39029/57-354 CONTACT - SOCKET (ZONE 367) 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 JT511 S1102-1 JACK (ZONE 367) 82389 0034 & ON 01 JT512 S1103-1 JACK (ZONE 367) 82389 0034 & ON 01 P3471 CONNECTOR RF PA017 D38999/26FJ35SN PLUG (ZONE 367) 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PB001 MS27484T22F35P CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PN503 M39029/57-354 CONTACT - SOCKET (ZONE 215) 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 PT143 MS27484T24F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT507 M39029/58-360 PIN - CONTACT (ZONE 367) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01

SC501

PC513 JXM515 1NC PILOT PTT 1C 50101LXS1384-22 A 50188XXS1-22 SXM501 B 50188XXS2-22 1NO GCCB01 P 50101LXP1399-22 ON CABIN CONTROL COLUMN JC138 PXM025

50101LXS1386-22OR 9 10 50101LXS1386-22WH PILOT 50101LXS1386-22BL 11 HAND REFER TO 27-10-01 UI505 MIC GARMIN AUDIO PROCESSOR #1 50101LXS1385-22 3 P3471 PI557 50101LXS1400-22 4 JC139 PXM026 BCK GCDB07 C 50103LXP662-22 15 REFER TO 27-10-01 ONSIDE CREW MIC KEY IN 29

PC523 JXM501

A BCK 10 22 2 MUSIC 2 AUDIO IN LH 56 50101LXS1387-22WH 1 WH LINE IN JACK MUSIC 2 AUDIO IN RH 57 2 3 50101LXS1387-22BL BL 1 MUSIC 2 AUDIO IN LO 76 50101LXS1387-22OR 3 OR JXM512 A 3 PILOT HEADSET 22 11 2 ONSIDE CREW MIC AUDIO IN HI 28 50101LXS1389-22WH 4 WH MIC JACK 1 JXM513

ONSIDE CREW MIC IN LO 30 50101LXS1389-22BL 5 BL

A BCK 22 12

3 ONSIDE CREW HEADSET AUDIO OUT LH 9 50101LXS1388-22WH 6 WH PILOT PHONE 2 JACK 1 ONSIDE CREW HEADSET AUDIO OUT RH 10 50101LXS1388-22BL 7 BL JXM514

ONSIDE CREW HEADSET AUDIO OUT LO 11 50101LXS1388-22OR 8 OR JXM500 POWERED HEADSET

26 6 MIC (L) P3472 PI555 26 5 MIC (H) 26 3 HDPH L (H) LH CB PANEL CABIN REFER TO SHEET 1 26 4 HDPH R (H) CWMS VOX/MIC SELECT IN 26 JC971 PC971 26 2 GND REFER TO 24-61-01 9 +28 VDC 5 R 50101LXP1390-22 26 1 AUDIO 1

SI001 50101LXP1391-22 LH MIC SEL SW PI001 7 BRIGHT/DIM COMMON

6 TEST INPUT

9 8 HEADSET 5 MASK 4 CABIN LH TILT REV PNL JC140 PC140 A2 10 50151LXP22-22 A3 BCK A1 6 50151LXS23-22 B2 50101LXS1392-22WH 7 50151LXS24-22 B3 50101LXS1392-22BL 8 50151LXS25-22 B1 AC503 C2 BCK C3 MASK OXYGEN MASK MIC SELECT IN 10 50101LXS1393-22 9 50151LXS26-22 C1 D2 GCCB01 N 50101LXP1395-22 5 50151LXP27-22 D3 ETHERNET IN A 22 D1 ETHERNET IN B 2 REFER TO 42-10-01 ALT ACTION ETHERNET OUT A 23 50101LXS1394-22BL ETHERNET OUT B 3 50101LXS1394-22WH

SI003 FORCED FAILSAFE (EMER COMM) IN 13 50101LXS1397-22 LH COM 1 TUNE SW PC525 JXM516 3 PI003 2 PILOT OXY A WH 7 BRIGHT/DIM COMMON 1 MASK MIC B A BL 22 H JXM517 JC516 6 TEST INPUT

9 8 NORM

5 4 121.5

UI301 A2 GARMIN INTEGRATED AVIONICS #1 50151LXP28-22 A3 P601 PI501 A1 B2 COM REMOTE TRANSFER 12 50101LXS1396-22 3 50151LXS29-22 B3 50151LXP30-22 B1 C2 GCCB01 R 50101LXP1398-22 4 C3 121.5 C1 D2 D3 XC001 D1 B 50101LXS1455-22 11 50151LXS31-22 ALT ACTION XC001 T 50101LXS1456-22 12 50151LXS32-22 XC002 C 50101LXS1457-22 13 50151LXS33-22 8202350-2G6

DUAL AUDIO AND VOICE Figure 02. (Sheet 6) Figure 02 Page 14 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AC503 SPLICE RF GCCB01 S3521-7 GROUND STUD KIT (ZONE 235) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 GCDB07 S3521-7 GROUND STUD KIT (ZONE 131) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 JC138 MS27497T10F35S CONNECTOR (ZONE 131) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 JC139 MS27474T12F35S CONNECTOR (ZONE 131) 96906 0034 & ON 01 S3627-12-90 . BACKSHELL 01 JC140 MS27497T14F35S CONNECTOR (ZONE 223) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 JC516 8969912-1 HA - MIC JACK ASSEMBLY (ZONE 235) 0034 & ON 01 JC971 MS27497T16F26S CONNECTOR (ZONE 235) 96906 0034 & ON 01 JXM500 PKG.M0.6SL.LN CONNECTOR (ZONE 235) S3013 0034 & ON 01 JXM501 LMD-4003-P CONNECTOR (ZONE 235) 49367 0034 & ON 01 LMD-4022-36LJ . PIN 49367 01 JXM512 161-3402-E 3.5MM STEREO JACK (ZONE 235) 0ZQ52 0034 & ON 01 JXM513 S1102-1 JACK (ZONE 235) 82389 0034 & ON 01 JXM514 S1102-3 MIC JACK (ZONE 235) 0034 & ON 01 JXM515 SJS820210 RECEPTACLE - WHITE (ZONE 235) 58982 0034 & ON 01 M39029/58-363 . CONTACT PIN 58982 01 JXM516 SJS830200 PLUG - 8 PIN 58982 0034 & ON 01 M39029/58-360 . CONTACT PIN 0TRC3 01 JXM517 S1102-4 JACK 0034 & ON 01 P3471 CONNECTOR RF P3472 CONNECTOR RF P601 CONNECTOR RF PC140 MS27484T14F35P CONNECTOR (ZONE 223) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 PC513 SJS820110 PLUG - WHITE (ZONE 235) 58982 0034 & ON 01 M39029/56-351 . CONTACT 58982 01 PC523 LMD-4003-S CONNECTOR (ZONE 235) 49367 0034 & ON 01 LMD-4122-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PC525 SJS830100 PLUG - 8 PIN (ZONE 235) 58982 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PC971 MS27484T16F26P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PI001 M39029/57-354 CONTACT - SOCKET (ZONE 227) 81590 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PI003 44387-001 CONNECTOR - SWITCH (ZONE 227) 81590 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI501 330-00185-44 CONNECTOR - DSUB (ZONE 225) 0TRC3 0034 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 PI555 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI557 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PXM025 MS27484T10F35P CONNECTOR (ZONE 131) 96906 0034 & ON 01 S3627-10 . BACKSHELL 01 PXM026 MS27484E12F35P CONNECTOR (ZONE 131) 96906 0034 & ON 01 S3627-12-45 . BACKSHELL 01 SC501 8250188-1 HA - PUSH TO TALK SWITCH (ZONE 235) 0034 & ON 01 SI001 46863-020 SWITCH - (HEADSET/MASK) (ZONE 227) 81590 0034 & ON 01 SI003 46863-019 SWITCH - (NORM/121.5) (ZONE 227) 81590 0034 & ON 01 SXM501 S3178-1 SWITCH - PUSHBUTTON (ZONE 235) 0034 & ON 01 UI301 011-03711-40 GARMIN INTEGRATED AVIONICS 0TRC3 0034 & ON 01 UI505 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 XC001 M81714/60-22-01 JUNCTION MODULE (ZONE 235) 0034 & ON 01 M39029/22-191 . CONTACT 96906 01 XC002 M81714/60-22-01 JUNCTION MODULE (ZONE 235) 0034 & ON 01 M39029/22-191 . CONTACT 96906 01

SF501

PF510 JXM515 COPILOT PTT 1NC 1C 50101RXS1412-22 A 22 SXM501 B 22 1NO GFCB02 A 50101RXP1428-22 ON CABIN CONTROL COLUMN JF130 PXM025 50101RXS1413-22OR 9 10 50101RXS1413-22WH COPILOT 50101RXS1413-22BL 11 UI504 HAND REFER TO 27-10-01 GARMIN AUDIO PROCESSOR #2 MIC 50101RXS1414-22 3 P3471 PI556 50101RXS1415-22 4 JF131 PXM026 BCK GFCB04 A 50103RXP1663-22 15 REFER TO 27-10-01 ONSIDE CREW MIC KEY IN 29

PF508 JXM501

A BCK 22 10 2 MUSIC 2 AUDIO IN LH 56 1 50101RXS1416-22WH WH 3 LINE IN JACK MUSIC 2 AUDIO IN RH 57 50101RXS1416-22BL 2 BL 1 MUSIC 2 AUDIO IN LO 76 50101RXS1416-22OR 3 OR JXM512 A 3 CO PILOT HEADSET 22 11 2 MIC JACK ONSIDE CREW MIC AUDIO IN HI 28 50101RXS1418-22WH 4 WH 1 JXM513

ONSIDE CREW MIC IN LO 30 50101RXS1418-22BL 5 BL

A BCK 22 12 3 ONSIDE CREW HEADSET AUDIO OUT LH 9 50101RXS1417-22WH 6 WH COPILOT PHONE 2 JACK 1 ONSIDE CREW HEADSET AUDIO OUT RH 10 50101RXS1417-22BL 7 BL JXM514

ONSIDE CREW HEADSET AUDIO OUT LO 11 50101RXS1417-22OR 8 OR JXM500 POWERED HEADSET

26 6 MIC (L) P3472 PI554 26 5 MIC (H) 26 3 HDPH L (H) CWMS VOX/MIC SELECT IN 26 RH CB PANEL CABIN REFER TO SHEET 2 26 4 HDPH R (H) JF972 PF972 26 2 GND REFER TO 24-61-01 J 9 1 +28 VDC 5 50101RXP1425-22 26 AUDIO 2

SI010 RH MIC SEL SW 50101RXP1426-22 PI010 7 BRIGHT/DIM COMMON

6 TEST INPUT

9 8 HEADSET 5 MASK 4 CABIN RH TILT REV PNL JF139 PF139 A2 13 50152RXP22-22 A3 BCK A1 9 50152RXS23-22 B2 50101RXS1419-22WH 10 50152RXS24-22 B3 50101RXS1419-22BL 11 50152RXS25-22 B1 AF504 C2 BCK C3 OXYGEN MASK MIC SELECT IN 10 50101RXS1420-22 12 50152RXS26-22 C1 MASK D2 GFCB02 H 50101RXP1421-22 8 50152RXP27-22 D3 D1 ETHERNET IN A 22 ALT ACTION ETHERNET IN B 2 50101RXS1422-22BL ETHERNET OUT A 23 REFER TO 42-10-01 50101RXS1422-22WH ETHERNET OUT B 3

SI012 FORCED FAILSAFE (EMER COMM) IN 13 50101RXS1423-22 PF516 JXM516 3 COPILOT OXY RH COM 2 TUNE SW PI012 2 MASK MIC A WH B 1 JF516 7 A BL BRIGHT/DIM COMMON 22 H JXM517 6 TEST INPUT

9 8 NORM

5 4 121.5

UI302 GARMIN INTEGRATED AVIONICS #2 A2 50152RXP28-22 A3 P601 PI502 A1 B2 COM REMOTE TRANSFER 12 50101RXS1424-22 27 50152RXS29-22 B3 50152RXP30-22 B1 C2 GFCB02 F 50101RXP1427-22 28 C3 C1 121.5 D2 D3 D1 ALT ACTION XF001 D 50101RXS1458-22 29 50152RXS31-22 XF001 H 50101RXS1459-22 30 50152RXS32-22 XF002 B 50101RXS1460-22 31 50152RXS38-22 8202350-2G7 .

DUAL AUDIO AND VOICE Figure 02. (Sheet 7) Figure 02 Page 17 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AF504 SPLICE RF GFCB02 S3521-7 GROUND STUD KIT (ZONE 236) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 GFCB04 S3521-7 GROUND STUD KIT (ZONE 132) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 JF130 MS27497T10F35S CONNECTOR (ZONE 132) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 JF131 MS27474T12F35S CONNECTOR (ZONE 132) 96906 0034 & ON 01 S3627-12-90 . BACKSHELL 01 JF139 MS27497T10F35S CONNECTOR (ZONE 224) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JF516 8969912-1 HA - MIC JACK ASSEMBLY (ZONE 236) 0034 & ON 01 JF972 MS27497T14F15S CONNECTOR (ZONE 236) 96906 0034 & ON 01 JXM500 PKG.M0.6SL.LN CONNECTOR (ZONE 235) S3013 0034 & ON 01 JXM501 LMD-4003-P CONNECTOR (ZONE 235) 49367 0034 & ON 01 LMD-4022-36LJ . PIN 49367 01 JXM512 161-3402-E 3.5MM STEREO JACK (ZONE 235) 0ZQ52 0034 & ON 01 JXM513 S1102-1 JACK (ZONE 235) 82389 0034 & ON 01 JXM514 S1102-3 MIC JACK (ZONE 235) 0034 & ON 01 JXM515 SJS820210 RECEPTACLE - WHITE (ZONE 235) 58982 0034 & ON 01 M39029/58-363 . CONTACT PIN 58982 01 JXM516 SJS830200 PLUG - 8 PIN 58982 0034 & ON 01 M39029/58-360 . CONTACT PIN 0TRC3 01 JXM517 S1102-4 JACK 0034 & ON 01 P3471 CONNECTOR RF P3472 CONNECTOR RF P601 CONNECTOR RF PF139 MS27484T16F35P CONNECTOR (ZONE 224) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PF508 LMD-4003-S CONNECTOR (ZONE 236) 49367 0034 & ON 01 LMD-4122-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PF510 SJS820110 PLUG - WHITE (ZONE 236) 58982 0034 & ON 01 M39029/56-351 . CONTACT 58982 01 PF516 SJS830100 PLUG - 8 PIN (ZONE 236) 58982 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PF972 MS27484T14F15P CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 PI010 44387-001 CONNECTOR - SWITCH (ZONE 226) 81590 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PI012 44387-001 CONNECTOR - SWITCH (ZONE 226) 81590 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI502 330-00185-44 CONNECTOR - DSUB (ZONE 225) 0TRC3 0034 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 01 011-00950-02 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01169-00 . GRND ADAPTR, SHELL 1-3 0TRC3 01 PI554 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PXM025 MS27484T10F35P CONNECTOR (ZONE 131) 96906 0034 & ON 01 S3627-10 . BACKSHELL 01 PXM026 MS27484E12F35P CONNECTOR (ZONE 131) 96906 0034 & ON 01 S3627-12-45 . BACKSHELL 01 SF501 8250188-1 HA - PUSH TO TALK SWITCH (ZONE 236) 0034 & ON 01 SI010 46863-020 SWITCH - (HEADSET/MASK) (ZONE 226) 81590 0034 & ON 01 SI012 46863-019 SWITCH (ZONE 226) 81590 0034 & ON 01 SXM501 S3178-1 SWITCH - PUSHBUTTON (ZONE 235) 0034 & ON 01 UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 XF001 M81714/60-22-01 JUNCTION MODULE (ZONE 236) 0034 & ON 01 M39029/22-191 . CONTACT 96906 01 XF002 M81714/60-22-01 JUNCTION MODULE (ZONE 236) 0034 & ON 01 M39029/22-191 . CONTACT 96906 01

AUDIO 1 AUX JC991 PC991 REFER TO SHEET 1 JC028 PC028 5 *D REFER TO 24-61-01 LH FWD CABIN INTERIOR DISC

GCCB01 E UI505 50101LXP1757-22 18 GARMIN AUDIO PROCESSOR #1 50101LXP1760-22 19 XC003 P3471 PI557 R 50101LXS1758-22 11

SEC CREW HEADSET AUDIO OUT LH 69 50101XXS1364-22WH 13 REFER TO INTERIORS SEC CREW HEADSET AUDIO OUT LO 71 50101XXS1364-22BL 15 REFER TO 23-70-01

SEC CREW MIC AUDIO IN HI 49 50101XXS1365-22WH 16 SEC CREW MIC AUDIO IN LO 51 50101XXS1365-22BL 17 50101LXS1866-22 12

AVIONICS INTERIORS JF512 PF512

PASS HEADSET AUDIO OUT LH 67 50101XXS1363-22WH 1 PASS HEADSET AUDIO OUT RH 68 50101XXS1363-22OR 2 PASS HEADSET AUDIO OUT LO 48 50101XXS1363-22BL 3 BCK BCK P3472 PI555

SEC CREW ICS KEY IN 12

CABIN TO COCKPIT CALL 77 50101XXS1366-22 16 COCKPIT TO CABIN CALL 75 50101XXS1367-22 17

PA KEY OUT 64 50101XXS1368-22 REFER TO INTERIORS AVIONICS INTERIORS JF504 PF504

50101XXS1383-22 A 50101XXS1380-22 B UI504 GARMIN AUDIO PROCESSOR #2 50101XXS1379-22BL J 50101XXS1379-22OR K 50101XXS1379-22WH L REFER TO INTERIORS P3471 PI556 50101XXS1378-22OR D 50101XXS1378-22WH C 50101XXS1378-22BL P AFT PASS 2 MIC AUDIO IN HI 65 50101XXS1370-22WH 18 PRESS PASS 2 MIC AUDIO IN LO 66 19 H 50101XXS1370-22BL 50101XXS1381-22 BHD 50101XXS1382-22 E RH EMER PWR J-BOX PASS 3 MIC AUDIO IN HI 44 50101XXS1371-22WH 20 JA028 PA028 PT902 JT902 PASS 3 MIC AUDIO IN LO 45 50101XXS1371-22BL 21 F PA AMP HZ022 PASS 4 MIC AUDIO IN HI 63 50101XXS1372-22WH 22 2 1 PASS 4 MIC AUDIO IN LO 64 23 38 *M REFER TO 24-60-01 50101XXS1372-22BL 50101XXP1568-22 50319XXP1107-22 50318XXP127-22 5 PASS HEADSET AUDIO OUT LH 67 50101XXS1373-22WH 24 REFER TO 24-60-01 PASS HEADSET AUDIO OUT RH 68 50101XXS1373-22OR 25 PASS HEADSET AUDIO OUT LO 48 50101XXS1373-22BL 26 BCK BCK

UF2016 CABIN/PA SPEAKER AMP

JF2036 J4

44 ORDINANCE INPUT 1- (GROUND BIAS) 23 AUX1 KEY-LINE INPUT - (BRIEFER)

50101XXS1369-22 BCK

AUDIO LO 59 50101XXS1374-22BL 15 MIC1 INPUT - (PA) AUDIO OUT HI 77 50101XXS1374-22WH 30 MIC1 INPUT + (PA)

10 AUX1 LEFT/MONO/SLAVE INPUT + 9 AUX1 RIGHT/SLAVE INPUT + 11 AUX1 LEFT/MONO/SLAVE INPUT - P3472 PI554 8 AUX1 RIGHT/SLAVE INPUT -

CABIN TO COCKPIT CALL 77 PA KEY OUT 64 50101XXS1375-22 17 MIC1 KEY-LINE INPUT - (PA)

42 28V BIAS (OPTO-LOGIC INPUTS) 16 MIC1 KEY-LINE INPUT + 22 AUX1 KEY-LINE INPUT + REF LIGHTING-COCKPIT/EMER PI916 REFER TO 33-50-01 J2 REFER TO 33-50-01 10 50101XXS1377-22 43 ORDINANCE INPUT 1+ (CHIME KEY)

PEDESTAL CABIN 41 WEIGHT ON WHEELS

REF WOW PF094 PF137 JF137

REFER TO 32-60-01 6 50160XXS399-22 100 50101XXS1376-22

8202350-2G8

DUAL AUDIO AND VOICE Figure 02. (Sheet 8) Figure 02 Page 20 23-50-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GCCB01 S3521-7 GROUND STUD KIT (ZONE 235) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 HZ022 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0034 & ON 01 J2 MS27497E20F39S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 J4 D38999/24FA98PA CONNECTOR 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497E10F98P MS27497E10F98P CONNECTOR 96906 0034 & ON 01 S3627-9 . BACKSHELL 01 42878-8410 . MODULAR JACK, VERT-RJ45 27264 01 JA028 D38999/24FJ35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JC028 MS27497T12F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 JC991 MS27497E24F4S CONNECTOR (ZONE 235) 96906 0034 & ON 01 JF137 MS27497T24F35SA CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JF2036 M24308/2-288F CONNECTOR (ZONE 282) 0034 & ON 01 D25000ANVL0 . EMI BACKSHELL 28198 01 JF504 MS27497E14F18S CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 JF512 MS27497T14F35S CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 JT902 MS27497T24F4S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 P3471 CONNECTOR RF P3472 CONNECTOR RF PA028 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PC028 MS27473T12F35P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 PC991 MS27484T24F4P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PF094 LMD-4001-S CONNECTOR (ZONE 229) 49367 0034 & ON 01 LMD-7103-P . DIODE MODULE 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PF137 MS27484T24F35PA CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PF504 MS27473T14F18P CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 PF512 MS27473T14F35 CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01

DUAL AUDIO AND VOICE

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI554 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI555 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI557 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI916 DD44S00000 CONNECTOR (ZONE 239) 28198 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): DD44S10HVL0 DD44S10HVL0 CONNECTOR 28198 0034 & ON 01 FC8022D2 . 22 AWG CRIMP 28198 01 D25000HVL0 . BACKSHELL 28198 01 PT902 MS27484T24F4P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 UF2016 S2800-1139 CABIN/PA SPEAKER AMP 0034 & ON 01 UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 UI505 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 XC003 M81714/60-22-02 JUNCTION MODULE (ZONE 235) 0034 & ON 01 M39029/22-191 . CONTACT 96906 01

23-70-01

COCKPIT VOICE RECORDER AIRPLANES 0034 & ON

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

AFT BULKHEAD CABIN TAILCONE

JA006 PA006

59 60 REFER TO SHEET 2

AFT BULKHEAD CABIN TAILCONE

JA028 PA028

UI308 P0003 JI512 CVR MICROPHONE U0002 CVR MICROPHONE ASSEMBLY VW MIC BIAS (RED) 1 51 50901XXS1-22RD VW 50101RXS1538-22WH MIC LOW (BLACK) 2 52 50901XXS2-22BK VW 50101RXS1538-22BL MIC HI WHITE) 3 53 50901XXS3-22WH VW A 50101RXS1538-22OR A SHIELD (GREEN) 50901XXS4-22GN 4 22 22 54

55 56 REFER TO SHEET 2 57 58

59 UI505 60 GARMIN AUDIO PROCESSOR #1 61 P3471 PI557 62 REFER TO 23-50-01 SEC CREW HEADSET AUDIO OUT RH 70 50101RXS1873-22WH BCK SEC CREW HEADSET AUDIO OUT LO 71 50101RXS1873-22BL

SUMMED AUDIO OUT HI 72 50101RXS1066-22WH SUMMED AUDIO OUT LOW 53 50101RXS1066-22BL BCK

UI504 GARMIN AUDIO PROCESSOR #2

P3471 PI556

SUMMED AUDIO OUT HI 72 50101RXS1067-22WH SUMMED AUDIO OUT LOW 53 50101RXS1067-22BL BCK

UI410 GARMIN DATA CONCENTRATOR #1 PI410 P411

CVR 429 RX (A429 IN HI) 30 50101RXB1068-22WH CVR 429 RX (A429 IN LO) 31 50101RXB1068-22BL

CVR (A429 OUT 1A) 72 50101RXB1069-22WH 8202370-2A1 CVR (A429 OUT 1B) 73 50101RXB1069-22BL BCK

COCKPIT VOICE RECORDER Figure 02. (Sheet 1) Figure 02 Page 2 23-70-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

COCKPIT VOICE RECORDER

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JA006 D38999/24FF35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-19 . BACKSHELL 01 JA028 D38999/24FJ35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JI512 S2349-2 PLUG (ZONE 225) 0034 & ON 01 S2351-2 . BACKSHELL 00779 01 P0003 S2350-5 RECEPTACLE (ZONE 225) 00779 0034 & ON 01 S2351-2 . BACKSHELL 00779 01 S2353-3 . PIN 00779 01 P3471 CONNECTOR RF P411 CONNECTOR RF PA006 D38999/26FF35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-19 . BACKSHELL 01 PA028 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PI556 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 PI557 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 011-01794-00 . GMA 36 BACK PLATE 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 U0002 S058-0148-10 CABIN AREA MICROPHONE (ZONE 225) 06141 0034 & ON 01 UI308 7418158-8 CVR MIC ASSEMBLY 0034 & ON 01 UI410 GSD 41 (ZONE 225) RF UI504 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01 UI505 011-04093-00 GARMIN AUDIO PROCESSOR (ZONE 225) 0TRC3 0034 & ON 01

AFT BULKHEAD CABIN TAILCONE JA006 PA006 59 REFER TO SHEET 1 60 FWD TAILCONE AFT TAILCONE UT302 AFT BULKHEAD DISC DISC COCKPIT VOICE RECORDER CABIN TAILCONE JT146 PT146 JA028 PA028 PT302 J1 GTSS04 50302RXP338-22 A 50319RXS1420-22WH 111 50302RXS336-22WH 9CHANNEL 1 HI 50319RXS1420-22BL 112 50302RXS336-22BL 8CHANNEL 1 LO BCK 51 50319RXS262-22WH 46 50302RXS170-22WH 37 MIC PWR OUT HOT 52 50319RXS262-22BL 47 50302RXS170-22BL 38 MIC SIGNAL IN LO 53 48 39 MIC SIGNAL IN HI A 50319RXS262-22OR A A 50302RXS170-22OR A 54 22 22 49 22 22 46 MIC SIGNAL GND RETURN GTSS04 50302RXP322-22 A

55 50319RXS263-22WH 50 50302RXS171-22WH 24 CHANNEL 3 HI 56 50319RXS263-22BL 51 50302RXS171-22BL 23 CHANNEL 3 LO

REFER TO SHEET 1 57 50319RXS264-22WH 52 50302RXS172-22WH 16 CHANNEL 2 HI 58 50319RXS264-22BL 53 50302RXS172-22BL 15 CHANNEL 2 LO

59 50319RXB265-22WH 54 50302RXB173-22WH 28 ARINC 429 OUT HI 60 50319RXB265-22BL 55 50302RXB173-22BL 27 ARINC 429 OUT LO

61 50319RXB266-22WH 56 50302RXB174-22WH 36 DATALINK IN A 429 HI 62 50319RXB266-22BL 57 50302RXB174-22BL 35 DATALINK IN B 429 LO

BCK XT310 GTSS04 50302RXP323-22 A

A 50319RXS267-22WH 58 50302XXS175-22WH 40 GMT IN A 429 HI B 50319RXS267-22BL 59 50302XXS175-22BL 32 GMT IN B 429 LO C A D 22 BCK J REFER TO A429 RX A E K GTCS36 50302RXP176-22 20 CHASSIS GND A429 RX B F L 32-40-01 SHIELD G M H T A429 RX B N W REFER TO A429 RX B P Y 27-60-01 SHIELD R Z S A B SPARE SHLD GTCS32 50302RXP178-22 13 DATA LINK VALID 50302RXP179-22 54 ATTENUATION COMMON

REF RH J-BOX CVR JT114 PT114 HZ260

1 2 REFER TO 24-60-01 5 50316RXP664-22 29

GTDS22 50302RXP180-22 53 28 VDC POWER (GND)

UT404 GARMIN ENGINE / AIRFRAME I/O #3

P71002 PT408 CVR POWER IN 126 50319RXP268-22 CVR POWER SHUTDOWN 128 50319RXS269-22 60 50302RXS181-22 55 28 VDC POWER IN

CVR ERASE A 93 50319RXS270-22 61 50302RXS182-22 5 VOICE ERASE "A" CVR ERASE C 114 50319RXS271-22 62 50302RXS183-22 11 VOICE ERASE "C"

P71003 PT410

CVR TEST OUT 22 50319RXS272-22 63 50302RXS184-22 47 PUSH TO TEST

LH TAIL MAINTENANCE JACK DISCONNECT AFT TAILCONE CVR AUDIO- LH TAIL BCK PT507 JT507 PT143 JT143

50327XXS8-22WH A 50301XXS311-22WH 96 50319XXS178-22WH 105 50302XXS295-22WH 4 AUDIO OUT HI

50327XXS8-22BL D 50301XXS311-22BL 97 50319XXS178-22BL 106 50302XXS295-22BL 10 AUDIO OUT LO

JT301 A A 22 G 22 BCK BCK GTSS04 50302RXP319-22 A

8202370-2A2

COCKPIT VOICE RECORDER Figure 02. (Sheet 2) Figure 02 Page 4 23-70-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

COCKPIT VOICE RECORDER

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GTCS32 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTCS36 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTDS22 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTSS04 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 HZ260 S2899-5.0 CIRCUIT BREAKER (ZONE 366) 82647 0034 & ON 01 J1 MS27497E12F98S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0034 & ON 01 JA006 D38999/24FF35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-19 . BACKSHELL 01 JA028 D38999/24FJ35PA CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JT114 MS27497T24F35SA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT143 MS27497T24F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT146 MS27497T24F35SA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT301 S1103-1 JACK (ZONE 367) 82389 0034 & ON 01 JT507 M39029/57-354 CONTACT - SOCKET (ZONE 367) 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 P71002 CONNECTOR RF P71003 CONNECTOR RF PA006 D38999/26FF35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-19 . BACKSHELL 01 PA028 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PT114 MS27484T24F35PA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT143 MS27484T24F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT146 MS27484T24F35PA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT302 MS27473E16F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PT408 D38999/26MJ35SB PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT410 D38999/26MJ35SD PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT507 M39029/58-360 PIN - CONTACT (ZONE 367) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 UT302 5003-5003-11 COCKPIT VOICE RECORDER 06141 0034 & ON 01

COCKPIT VOICE RECORDER

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UT404 011-02635-01 GEA 7100 (ZONE 366) 0TRC3 0034 & ON 01 XT310 M39029/22-191 CONTACT (ZONE 366) 96906 0034 & ON 01 M81714/60-22-04 . TERMINAL JUNCTION 01

27-70-01

CONTROL LOCK AIRPLANES 0001 THRU 0033

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UI411 GARMIN ENGINE / AIRFRAME I/O #1 CABIN PEDESTAL REF PROXIMITY SWITCH ASSY P71002 PI413 PF096 J0011 J0012 JC143 PC143 S0012

VW PIT/ROLL DISC T-HND (DISC IN 6) 58 50103XXS195-22 38 50160XXS66-22 A 24BK% BK OUTPUT (GND) 2 1

AILERON CONTROL LOCK 36 50103XXS309-22 D0002 VW GICB02 D 50160XXP69-22 C 24BL% BL GND SF016 ELEVATOR CONTROL LOCK 4 50103XXS341-22 2 1 T-HANDLE PITCH ROLL PROX SWITCH D0001 (N.O. WITH TARGET AWAY)

1 2 VW B 24BR% BR 28V IN R0001

REF PROXIMITY SWITCH ASSY PF099 J0013 J0014 S0014

VW 39 50160XXS71-22 A 24BK% BK OUTPUT (GND) 2 1

D0004 SF019 VW GICB02 E 50160XXP70-22 C 24BL% BL GND AILERON CONTROL LOCK 2 1 PROX SWITCH (N.O. WITH TARGET AWAY) D0003

2 1 VW 50160XXP68-22 B 24BR% BR 28V IN R0002

RH CB PANEL CONTROL LOCK JF996 PF996 UI001 THROTTLE QUADRANT REFER TO 24-61-01 N 40 5 50103XXP189-22 PI094 JI094 PI081 J2

GICB01 E 50160XXP443-22 A 50160XXP444-22 24GUST LOCK (-) 50160LXP441-22 B BLK DI081 THROTTLE LOCK WHT RELAY 50160LXP162-22 23GUST LOCK (+) PI093

7 1 50160LXP442-22 4 9 REF PROXIMITY SWITCH ASSY 3 6 J0014 8 PC012 J0013 S0014 V W 2 50160LXS245-22 A 24BK BK OUTPUT (GND) SC014 CONTROL LOCK LEVER D0004 PROX SWITCH V W (N.O. WITH TARGET AWAY) GICB01 R 50160LXP244-22 C 24BL BL GND

D0003

V W 50160XXP67-22 B 24BR BR 28V IN 50160XXP243-22 R0002

AVN J-BOX REF PROXIMITY SWITCH ASSY J1 PI120 JF137 PF137 PF098 J0011 J0012 26 50101XXS830-22 19 SPARE S0012 25 50101XXS832-22 21 SPARE V W 10 A 24BK BK OUTPUT (GND) 8 PF992 JF992 SF017 50101XXP831-22 P SPARE D0002 V W ELEVATOR CONTROL LOCK GCCB03 D 50103XXP340-22 C 24BL BL GND PROX SWITCH (N.O. WITH TARGET AWAY)

D0001 K5 V W 50103XXP339-22 B 24BR BR 28V IN R0001

8202770-1C1

CONTROL LOCK Figure 01. (Sheet 1) Figure 01 Page 2 27-70-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

CONTROL LOCK

AIRPLANES 0001 THRU 0033

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

D0001 1.5KE36A TRANSZORB 24444 0001 - 0033 01 D0002 1.5KE36A TRANSZORB 24444 0001 - 0033 01 D0003 1.5KE36A TRANSZORB 24444 0001 - 0033 01 D0004 1.5KE36A TRANSZORB 24444 0001 - 0033 01 GCCB03 S3521-7 GROUND STUD KIT (ZONE 131) 0001 - 0033 01 S2526-4 . GROUNDING CONNECTOR 01 GICB02 S3521-7 GROUND STUD KIT (ZONE 229) 0001 - 0033 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 J0011 M39029/58-360 PIN - CONTACT 0TRC3 0001 - 0033 01 SJS830270 . RECEPTACLE 58982 01 J0012 M39029/58-360 PIN - CONTACT 0TRC3 0001 - 0033 01 SJS830270 . RECEPTACLE 58982 01 J0013 M39029/58-363 CONTACT PIN 58982 0001 - 0033 01 SJS820210 . RECEPTACLE, WHITE 58982 01 J0014 PKW 3M-2/S90 PROX SWITCH CORD SET 61526 0001 - 0033 01 J1 MS27497E12F98S CONNECTOR 96906 0001 - 0033 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0001 - 0033 01 JC143 MS27497T24F35S CONNECTOR (ZONE 229) 96906 0001 - 0033 01 S3627-24 . BACKSHELL 01 JF137 MS27497T24F35SA CONNECTOR (ZONE 229) 96906 0001 - 0033 01 S3627-24 . BACKSHELL 01 JF992 MS27497E24F4S CONNECTOR (ZONE 236) 96906 0001 - 0033 01 JF996 MS27497T14F15S CONNECTOR (ZONE 236) 96906 0001 - 0033 01 P71002 CONNECTOR RF PC012 SJS820110 PLUG - WHITE (ZONE 229) 58982 0001 - 0033 01 M39029/56-351 . CONTACT 58982 01 PC143 MS27484T24F35P CONNECTOR (ZONE 229) 96906 0001 - 0033 01 S3627-24 . BACKSHELL 01 PF096 SJS820110 PLUG - WHITE (ZONE 229) 58982 0001 - 0033 01 M39029/56-351 . CONTACT 58982 01 PF098 SJS820110 PLUG - WHITE (ZONE 132) 58982 0001 - 0033 01 M39029/56-351 . CONTACT 58982 01 PF099 SJS820110 PLUG - WHITE (ZONE 132) 58982 0001 - 0033 01 M39029/56-351 . CONTACT 58982 01 PF137 MS27484T24F35PA CONNECTOR (ZONE 229) 96906 0001 - 0033 01 S3627-24 . BACKSHELL 01 PF992 MS27484T24F4P CONNECTOR (ZONE 236) 96906 0001 - 0033 01 S3627-24 . BACKSHELL 01 PF996 MS27484T14F15P CONNECTOR (ZONE 236) 96906 0001 - 0033 01 S3627-14 . BACKSHELL 96906 01 PI120 M24308/2-5F CONNECTOR (ZONE 225) 0001 - 0033 01 M85049/48-2-5 . STRAIN RELIEF 01 PI413 D38999/26MJ35SB PLUG (ZONE 225) 0001 - 0033 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01

CONTROL LOCK

AIRPLANES 0001 THRU 0033

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

R0001 RN55C4990F RESISTOR 0001 - 0033 01 R0002 RN55C4990F RESISTOR 0001 - 0033 01 S0012 SWITCH RF S0014 SWITCH RF SC014 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0001 - 0033 01 SF016 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0001 - 0033 01 SF017 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0001 - 0033 01 SF019 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0001 - 0033 01 UI411 GEA 7100 (ZONE 225) RF

27-70-01

CONTROL LOCK AIRPLANES 0034 & ON

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

UI411 GARMIN ENGINE / AIRFRAME I/O #1 CABIN PEDESTAL REF PROXIMITY SWITCH ASSY P71002 PI413 PF096 J0011 J0012 JC143 PC143 S0012

PIT/ROLL DISC T-HND (DISC IN 6) 58 50103XXS195-22 38 50160XXS66-22 A BK OUTPUT (GND) 2 1

AILERON CONTROL LOCK 36 50103XXS309-22 D0002 GICB02 D 50160XXP69-22 C BL GND SF016 ELEVATOR CONTROL LOCK 4 50103XXS341-22 2 1 T-HANDLE PITCH ROLL PROX SWITCH D0001 (N.O. WITH TARGET AWAY)

2 1 B BR 28V IN R0001

REF PROXIMITY SWITCH ASSY PF099 J0013 J0014 S0014

39 50160XXS71-22 A BK OUTPUT (GND) 2 1

D0004 SF019 GICB02 E 50160XXP70-22 C BL GND AILERON CONTROL LOCK 2 1 PROX SWITCH (N.O. WITH TARGET AWAY) D0003

2 1 50160XXP68-22 B BR 28V IN R0002

RH CB PANEL CONTROL LOCK JF996 PF996 UI001 THROTTLE QUADRANT REFER TO 24-61-01 5 N 50103XXP189-22 40 PI094 JI094 PI081 J2

GICB01 E A 24GUST LOCK (-) B BLK DI081 THROTTLE LOCK WHT RELAY 23GUST LOCK (+) PI093

7 1 4 9 REF PROXIMITY SWITCH ASSY 3 6 J0014 8 PC012 J0013 S0014 V W 2 A 24BK BK OUTPUT (GND) SC014 CONTROL LOCK LEVER D0004 PROX SWITCH V W (N.O. WITH TARGET AWAY) GICB01 R C 24BL BL GND

D0003

V W 50160XXP67-22 B 24BR BR 28V IN R0002

REF PROXIMITY SWITCH ASSY

PF098 J0011 J0012 S0012 V W A 24BK BK OUTPUT (GND)

SF017 D0002 V W ELEVATOR CONTROL LOCK GCCB03 D 50103XXP340-22 C 24BL BL GND PROX SWITCH (N.O. WITH TARGET AWAY)

D0001

V W 50103XXP339-22 B 24BR BR 28V IN R0001

8202770-2D1

CONTROL LOCK Figure 02. (Sheet 1) Figure 02 Page 2 27-70-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

CONTROL LOCK

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

D0001 1.5KE36A TRANSZORB 24444 0034 & ON 01 D0002 1.5KE36A TRANSZORB 24444 0034 & ON 01 D0003 1.5KE36A TRANSZORB 24444 0034 & ON 01 D0004 1.5KE36A TRANSZORB 24444 0034 & ON 01 DI081 S3106-4 DIODE ASSEMBLY 0034 & ON 1 GCCB03 S3521-7 GROUND STUD KIT (ZONE 131) 0034 & ON 01 S2526-4 . GROUNDING CONNECTOR 01 GICB01 GROUND (ZONE 229) RF GICB02 S3521-7 GROUND STUD KIT (ZONE 229) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 J0011 M39029/58-360 PIN - CONTACT 0TRC3 0034 & ON 01 SJS830270 . RECEPTACLE 58982 01 J0012 M39029/58-360 PIN - CONTACT 0TRC3 0034 & ON 01 SJS830270 . RECEPTACLE 58982 01 J0013 M39029/58-363 CONTACT PIN 58982 0034 & ON 01 SJS820210 . RECEPTACLE, WHITE 58982 01 J0014 PKW 3M-2/S90 PROX SWITCH CORD SET 61526 0034 & ON 01 J2 CONNECTOR RF JC143 MS27497T24F35S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JF996 MS27497T14F15S CONNECTOR (ZONE 236) 96906 0034 & ON 01 JI094 SJS830200 PLUG 58982 0034 & ON 1 P71002 CONNECTOR RF PC012 SJS820110 PLUG - WHITE (ZONE 229) 58982 0034 & ON 01 M39029/56-351 . CONTACT 58982 01 PC143 MS27484T24F35P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PF096 SJS820110 PLUG - WHITE (ZONE 229) 58982 0034 & ON 01 M39029/56-351 . CONTACT 58982 01 PF098 SJS820110 PLUG - WHITE (ZONE 132) 58982 0034 & ON 01 M39029/56-351 . CONTACT 58982 01 PF099 SJS820110 PLUG - WHITE (ZONE 132) 58982 0034 & ON 01 M39029/56-351 . CONTACT 58982 01 PF996 MS27484T14F15P CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 PI081 D38999/26FE35SC PLUG (ZONE 229) 0034 & ON 01 S3627-17 . BACKSHELL 01 PI093 LMD-4001-S CONNECTOR 49367 0034 & ON 1 PI094 M39029/57-354 CONNECTOR 81590 0034 & ON 0.01 PI413 D38999/26MJ35SB PLUG (ZONE 225) 0034 & ON 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01 R0001 RN55C4990F RESISTOR 0034 & ON 01 R0002 RN55C4990F RESISTOR 0034 & ON 01 S0012 SWITCH RF S0014 SWITCH RF SC014 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0034 & ON 01 Figure 02 Page 3 27-70-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

CONTROL LOCK

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

SF016 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0034 & ON 01 SF017 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0034 & ON 01 SF019 8969910-1 HA - BI2-EG08-AN6X PROX 61526 0034 & ON 01 UI411 GEA 7100 (ZONE 225) RF

29-10-01

HYDRAULIC SYSTEM AIRPLANES 0001 THRU 0021

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

EY001 LH JBOX SYS A HYD VOLUME WH NZ115 REMOTE INDICATOR 2WH UT401 SYS A HYDRAULIC PCB TAIL RD GSD 41HE (#2) 700 P411 PT411 TO HYD PCB 2RD PT125 JT125 JZ115 P1 BK BCK 2BK A HYD PCB (A429 IN HI) 3 50323XXB419-22WH M 50315XXB512-22WH 43GARMIN ARINC OUT (+) JY121 PY121 A HYD PCB (A429 IN LO) 2 50323XXB419-22BL L 50315XXB512-22BL 44GARMIN ARINC OUT (-) BCK VW 1WH A 50631XCS01-20WH 50609XCS114-22WH AY116 WH A GZSS01 LY002 SYSTEM A VW PT115 JT115 TO POT 1RD 50631XCS02-20RD B 50609XCS114-22OR AY117 B RESERVOIR RD C VOLUME POT 50321LCP131-22 45 50315LCP661-22 1PCB GND 46 30SYS GND VW GTCS03 50321LCP132-22 50315LCP531-22 1BK 50631XCS03-20BK C 50609XCS114-22BL AY118 BK JZ931 PZ931 L HYD FAIRING TAIL 43 G REMOTE INDICATOR VW 50315XCP676-22 3BK 50631XCP05-20BK E 50609XCP113-22 GYDS25 PT169 JT169 HZ141 POWER VW 2 1 3WH 50631XCP04-20WH D 50609XCP112-22 39 50321XCP91-22 50315XCP550-22 5 REFER TO 24-60-01 36RES VOL LO 50609XCS117-22BL 38 50321XCS92-22BL 42 50315XCS534-22BL 8RES VOL LO UY012 50609XCS117-22OR 37 50321XCS92-22OR 41 50315XCS534-22OR 7RES VOL WIPER SYSTEM A HYD MANIFOLD J1 PY122 50609XCS117-22WH 36 50321XCS92-22WH 40 50315XCS534-22WH 35RES VOL HI 39 EXC + A 50609LCS97-22WH 28 50321LCS103-22WH 25 50315LCS521-22WH 37SYS TEMP RTD EXC (+) EXC - C 50609LCS97-22BL 29 50321LCS103-22BL 26 50315LCS521-22BL 38SYS TEMP RTD EXC (-) TEMP SENSOR 50609LCS98-22WH 30 50321LCS102-22WH 27 50315LCS522-22WH 39SYS TEMP RTD RTN (+) RETURN B 50609LCS98-22BL 31 50321LCS102-22BL 28 50315LCS522-22BL 40SYS TEMP RTD RTN (-) BCK BCK BCK GZSS01 J3 PY126

B 26 31 10TS HYD PRESS SWITCH PRESS SW | LOW = OPN | 50609XXS103-22 50321XXS99-22 50315XXS525-22 C 50609XXP104-22 J2 PY124 GZSS01 REFER TO SHEET 3 GYDS13 SUPPLY - 2 50609XCP102-22 BCK BCK PRESS SENSOR SIGNAL + 3 50609XCS99-22WH 23 50321XCS100-22WH 29 50315XCS523-22WH 13TS PRSS XDUCER (+) SIGNAL - 4 50609XCS99-22BL 24 50321XCS100-22BL 30 50315XCS523-22BL 12TS PRSS XDUCER (-) SUPPLY + 1 50609XCP101-22 25 BCK REFER TO SHEET 3 PT903 JT903 LH EMER J-BOX

50321XCP89-22 F REFER TO SHEET 3 REFER TO SHEET 3 J4 PY128 | NORMALLY | BYPASS VALVE B 50609LCS105-22 27 50321LCS98-22 32 50315LCS526-22 60HEAT EXG BYPASS VLV | OPEN | A 50609LCP106-22 19 34 50315LCP529-22 59HYD CB LH EMER J-BOX PT903 JT903 HYD SYS A HZ043 VY303 J1 PY303 50321LCP87-22 B 50317LCP44-22 2 1 SYS A SPOILER VALVE 50321LCP88-22 C 50317LCP45-22 REFER TO 24-60-01 POWER A 50609LCP107-22 43 50321LCP90-22 D 50317LCP46-22 5 ENERGIZED TO OPEN GROUND B 50609LCS108-22 34 50321LCS97-22 35 50315LCS530-22 21SPOILER ISO VLV CMD

NZ204 7 50315XCS532-22 RH FADEC INTERFACE PCB 700 RH J-BOX TAIL TAIL FAIRING 5 50315XCS524-22WH P1 JZ204 JT116 PT116 JT170 PT170 6 50315XCS524-22BL BCK ENGINE RUNNING 13 50316XXS560-22 41 50322XXS227-22 54 50609XXS189-22 46 50321XXS120-22 10 50315XXS535-22 48ENGINE B STATUS ENG STARTING 2 50316XXS386-22 50315XXS628-22 28HYD VOLUME LOW 50315XXS537-22 18ENGINE A STATUS 50315XXS527-22 54WEIGHT ON WHEELS

NZ215 PZ017 SYS B HYDRAULIC PCB P1 JZ215 7 WOW

ENGINE B STATUS 48 REFER TO 32-60-01

NZ104 OS HYD PRESS SWITCH 9 50316XCS704-22 73 50322XCS228-22 64 50609XCS190-22 47 50321XCS121-22 LH FADEC INTERFACE PCB 700 BCK BCK BCK OS PRESS (+) 33 50316XCS698-22WH 98 50322XCS229-22WH 65 50609XCS191-22WH 50 50321XCS122-22WH JZ104 P1 OS PRESS (-) 34 50316XCS698-22BL 99 50322XCS229-22BL 66 50609XCS191-22BL 51 50321XCS122-22BL HYD A VOLUME LO 58 50316XXS590-22 96 50322XXS230-22 67 50609XXS192-22 48 50321XXS123-22 22 13ENGINE RUNNING ENGINE A STATUS 18 50316XXS384-22 97 50322XXS231-22 68 50609XXS193-22 49 50321XXS124-22 33 50315XXS552-22 2ENG STARTING GZSS02

LH CB PANEL L HYD FW SOV JC971 PC971

1 2 REFER TO 26-20-01 REFER TO 24-61-01 D 5 50101LMP1539-22

SI101 HYDRAULIC PEDESTAL CABIN PUMP A SW CABIN TAILCONE TAIL J-BOX 5 PF149 JF149 PC142 JC142 KZ107 JA033 PA033 PT127 JT127 PZ107 HYD SYS A 4 50166LMP46-22 1 50160LMP355-22 113 LOCKOUT NORM 50166LMS48-22 3 50160LMS357-22 102 50101LMS1541-22 43 50319LMS1047-22 16 50315LMS514-22 A3 6 MIN 1 50166LMS47-22 2 50160LMS356-22 101 50101LMS1540-22 46 50319LMS1046-22 8 50315LMS513-22 B1 B3 50166LMS49-22 4 50160LMS358-22 103 50101LMS1569-22 44 50319LMS1109-22 SHUTOFF 3 A1

2 UT403 50166LMP50-22 5 50160LMP359-22 D GICB01 GARMIN ENGINE / AIRFRAME I/O #2 X1 REFER TO (MIN POS) 26-20-01 PT407 P71002 X2 FAIRING CABIN 81A HYD DEPRESS SW B2 J1 PY004 PY076 JY076 A2 TY014 JA011 PA011 PT405 P71001 SYS A BCK BCK HYD TEMP A 50616LMS33-22WH 20 50104LMS63-22WH 2 50319LMS1044-22WH 9 A HYD TEMP HI B 21 3 10 A HYD TEMP LO MON RTD 50616LMS33-22BL 50104LMS63-22BL 50319LMS1044-22BL C 50616LMS37-22 16 50104LMS68-22 BCK BCK

8202910-1K1 GFCS20

HYDRAULIC SYSTEM Figure 01. (Sheet 1) Figure 01 Page 2 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AY116 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0001 - 0021 RF AY117 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0001 - 0021 01 AY118 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0001 - 0021 01 EY001 INDICATOR, RSVR VOLUME (ZONE 311) RF GFCS20 S3521-8 GROUND STUD KIT (ZONE 186) 0001 - 0021 01 GICB01 GROUND (ZONE 229) RF GTCS03 S3521-8 GROUND STUD KIT (ZONE 365) 0001 - 0021 01 GYDS13 S3521-8 GROUND STUD KIT (ZONE 318) 0001 - 0021 01 GYDS25 S3521-8 GROUND STUD KIT (ZONE 311) 0001 - 0021 01 GZSS01 GROUND STUD KIT RF GZSS02 GROUND STUD KIT RF HZ043 S2899-5.0 CIRCUIT BREAKER (ZONE 367) 82647 0001 - 0021 01 HZ141 S2899-5.0 CIRCUIT BREAKER (ZONE 365) 82647 0001 - 0021 01 J1 MS27497E12F98S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0001 - 0021 01 J2 MS27497E20F39S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 J3 MS27497T8F98PA CONNECTOR 96906 0001 - 0021 01 S3744-14 . BACKSHELL 96906 01 J4 D38999/24FA98PA CONNECTOR 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497E10F98P MS27497E10F98P CONNECTOR 96906 0001 - 0021 01 S3627-9 . BACKSHELL 01 42878-8410 . MODULAR JACK, VERT-RJ45 27264 01 JA011 D38999/24FC35PA CONNECTOR (ZONE 281) 0001 - 0021 01 S3627-13 . BACKSHELL 01 JA033 D38999/24FJ35PB CONNECTOR (ZONE 281) 0001 - 0021 01 S3627-25 . BACKSHELL 01 JC142 MS27497T24F35SB CONNECTOR (ZONE 229) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 JC971 MS27497T16F26S CONNECTOR (ZONE 235) 96906 0001 - 0021 01 JF149 MS27497E16F35S CONNECTOR (ZONE 229) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT116 MS27497T22F35S CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT125 MS27497T24F4S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 8250315-1 . BACKSHELL 01 JT127 MS27497T24F35S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT903 MS27497T20F39SA CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JY076 MS27474T16F35S CONNECTOR (ZONE 186) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 JY121 M39029/58-360 PIN - CONTACT (ZONE 311) 0TRC3 0001 - 0021 01 SJS830201 . RECEPTACLE 58982 01 JZ104 10-504934-001 CONNECTOR (ZONE 365) 77820 0001 - 0021 01 3417-6600 . SOCKET 76381 01 JZ115 10-504934-001 CONNECTOR (ZONE 365) 77820 0001 - 0021 01 3473-6600 . SOCKET 76381 01 JZ204 10-504934-001 CONNECTOR (ZONE 366) 77820 0001 - 0021 01 JZ215 10-504934-001 CONNECTOR (ZONE 366) 77820 0001 - 0021 01 JZ931 M39029/58-360 PIN - CONTACT (ZONE 365) 0TRC3 0001 - 0021 01 SJS830200 . 8 PIN PLUG 58982 01 KZ107 M83536/9-024 RELAY (ZONE 365) 2X920 0001 - 0021 01 LY002 RESISTER RF NZ104 7468183-1 PCB ASSEMBLY - FADEC INT (ZONE 365) 0001 - 0021 01 NZ115 PCB ASSEMBLY - HYDRAULIC CONTROL (ZONE 365) RF NZ204 7468183-1 PCB ASSEMBLY - FADEC INT (ZONE 366) 0001 - 0021 01 NZ215 PCB ASSEMBLY - HYDRAULIC CONTROL RF P411 CONNECTOR RF P71001 CONNECTOR RF P71002 CONNECTOR RF PA011 D38999/26FC35SA PLUG (ZONE 367) 0001 - 0021 01 S3627-13 . BACKSHELL 01 PA033 D38999/26FJ35SB STRAIGHT PLUG GROUNDED (ZONE 367) 0001 - 0021 01 S3627-25 . BACKSHELL 01 PC142 MS27484T24F35PB PLUG (ZONE 229) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PC971 MS27484T16F26P CONNECTOR (ZONE 235) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 PF149 MS27484E16F35P PLUG (ZONE 229) 96906 0001 - 0021 01 S3627-16-90 . BACKSHELL 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 PT116 MS27484T22F35P CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 PT125 MS27484T24F4P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 PT127 MS27484T24F35P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20-90 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT405 D38999/26MJ35SN PLUG (ZONE 365) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0001 - 0021 01 M85049/38S25N . BACKSHELL 01 PT407 D38999/26MJ35SB PLUG (ZONE 365) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0001 - 0021 01 M85049/38S25N . BACKSHELL 01 PT411 MS27488-22-2 PLUG (ZONE 365) 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): D38999/26FG35SA D38999/26FG35SA PLUG 0001 - 0021 01 S3627-21 . BACKSHELL 01 PT903 MS27484T20F39PA CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 PY004 D38999/26FA98SA PLUG (ZONE 318) 0001 - 0021 01 S3627-9 . BACKSHELL 01 PY076 MS27484T16F35P CONNECTOR (ZONE 318) 96906 0001 - 0021 01 S3627-16-90 . BACKSHELL 01 PY121 SJS830101 PLUG - 8 PIN (ZONE 311) 58982 0001 - 0021 01 M39029/57-354 . SOCKET CONTACT 81590 01 PY122 D38999/26FA98SA PLUG (ZONE 318) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PY124 D38999/26FB35SN PLUG (ZONE 318) 0001 - 0021 01 S3627-11-90 . BACKSHELL 01 PY126 D38999/26FA98SB CONNECTOR (ZONE 318) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PY128 D38999/26FA98SN PLUG (ZONE 318) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PY303 D38999/26FA98SN PLUG (ZONE 317) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PZ017 LMD-4001-S CONNECTOR (ZONE 365) 49367 0001 - 0021 01 LMD-7103-P . DIODE MODULE 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PZ107 JRS200300 RELAY SOCKET (ZONE 365) 58982 0001 - 0021 01 M39029/92-534 . CONTACT 01 PZ931 M39029/57-354 CONTACT - SOCKET (ZONE 365) 81590 0001 - 0021 01 SJS830100 . 8 PIN PLUG 58982 01 SI101 MS27754-34A SWITCH (ZONE 229) 96906 0001 - 0021 01 TY014 9916248-5 TEMPERATURE TRANSDUCER 0001 - 0021 01 UT401 GSD 41H (ZONE 365) RF UT403 011-02635-01 GEA 7100 (ZONE 365) 0TRC3 0001 - 0021 01 UY012 MANIFOLD ASSY, HYDRAULIC RF VY303 SPOILER ISOLATION VALVE RF

NZ115 RH JBOX SYS A HYDRAULIC PCB LH J-BOX TAIL TAIL FAIRING FAIRING TAIL TAIL P1 JZ115 JT115 PT115 JT169 PT169 PT170 JT170 PT116 JT116

NZ215 SYS B HYDRAULIC PCB VY309 FAIRING TAIL SYS B SPOILER VALVE J1 PY315 PT170 JT170 JZ215 P1 GROUND ENERGIZED B 50609RCS138-22 73 50322RCS171-22 95 50316RCS558-22 21SPOILER ISO VLV CMD TO OPEN POWER A 50609RCP139-22 75 50322RCP166-22 PT904 JT904 HYD SYS B RH EMER JBOX HZ042 PZ014 D 50318RCP84-22 2 1 50322RCP165-22 C 50318RCP83-22 5 REFER TO 24-60-01 WOW 1 50316XXS387-22 54WEIGHT ON WHEELS 50322XCP164-22 B 50318XCP82-22 UY014 REFER TO 32-60-01 SYSTEM B HYD MANIFOLD J4 PY158 | NORMALLY | A 50609RCP134-22 51 50322RCP163-22 100 50316RCP553-22 59HYD CB BYPASS VALVE B 43 90 60HEAT EXG BYPASS VLV | OPEN | 50609RCS133-22 50322RCS168-22 50316RCS561-22 J2 PY154 REFER TO SHEET 3 GZSS02 SUPPLY + 1 50609XCP129-22 4 SIGNAL + 3 6 87 13TS PRSS XDUCER (+) PRESS SENSOR 50609XCS127-22WH 50322XCS161-22WH 50316XCS564-22WH SIGNAL - 4 50609XCS127-22BL 7 50322XCS161-22BL 88 50316XCS564-22BL 12TS PRSS XDUCER (-) SUPPLY - 2 50609XCP130-22 BCK BCK BCK REFER TO SHEET 3 J3 PY156 GYDS16 PRESS SWITCH | LOW = OPN | C 50609XXP132-22 B 50609XXS131-22 5 50322XXS167-22 89 50316XXS562-22 10TS HYD PRESS SWITCH

J1 PY152 EY003 EXC + A 50609RCS125-22WH 8 50322RCS159-22WH 82 50316RCS566-22WH 37SYS TEMP RTD EXC (+) SYS B HYD VOLUME TEMP SENSOR EXC - C 50609RCS125-22BL 9 50322RCS159-22BL 83 50316RCS566-22BL 38SYS TEMP RTD EXC (-) REMOTE INDICATOR WH 50609RCS126-22WH 10 50322RCS160-22WH 85 50316RCS567-22WH 39SYS TEMP RTD RTN (+) 2WH RETURN B 50609RCS126-22BL 11 50322RCS160-22BL 86 50316RCS567-22BL 40SYS TEMP RTD RTN (-) RD BCK BCK BCK 36RES VOL LO TO HYD PCB 2RD 50609XCS135-22BL 70 50322XCS170-22BL 93 50316XCS559-22BL 8RES VOL LO BK 50609XCS135-22OR 71 50322XCS170-22OR 94 50316XCS559-22OR 7RES VOL WIPER 2BK 50609XCS135-22WH 72 50322XCS170-22WH 91 50316XCS559-22WH 35RES VOL HI JY151 PY151 74 VW 50316XCP731-22 3BK 50633XCP04-20BK E 50609XCP144-22 GYDS16

VW 3WH 50633XCP05-20WH D 50609XCP143-22 79 50322XCP176-22 PZ932 JZ932 POWER R HYD AY111 G VW WH 1WH 50633XCS01-20WH A 50609XCS145-22WH A LY004 REMOTE INDICATOR SYSTEM B 2 1 AY112 50316XCP389-22 REFER TO VW RD RESERVOIR 5 1RD 50633XCS02-20RD B 50609XCS145-22OR B C 24-60-01 TO POT AY113 VOLUME POT HZ234 VW BK 1BK 50633XCS03-20BK C 50609XCS145-22BL 50322RCP236-22 63 50316RCP725-22 1PCB GND GTCS04 50322RCP237-22 64 50316RCP568-22 30SYS GND PEDESTAL CABIN CABIN TAIL C1 REFER TO SHEET 3 1 50322XCS158-22 81 50316XCS569-22 24PTCU ISO VLV A REFER TO SHEET 3 33 50322XCS177-22 84 50316XCS549-22 25PTCU ISO VLV B C2 REFER TO SHEET 3 74 PTCU ROTARY SW C3 PF136 JF136 JA026 PA026 C4 C5 NORM 50166XCS77-22 R 50102XCS367-22 52 50322XCS254-22 CC 50166XCS78-22 S 50102XCS368-22

SPARE SPARE B1 B2 OFF ON B3 B4 SI044 B5 BC

A1 A2 50166XCS51-22 D 50102XCS321-22 20 50322XCS152-22 75 50316XCS550-22 4PTCU OFF E 21 76 2PTU NORM MODE A3 50166XCS52-22 50102XCS322-22 50322XCS153-22 50316XCS574-22 A4 50166XCS53-22 J 50102XCS323-22 22 50322XCS154-22 77 50316XCS573-22 31PTU NORM MODE K 23 78 32PTU NORM MODE A5 50166XCS54-22 50102XCS324-22 50322XCS155-22 50316XCS572-22 AC 50166XCS55-22 N 50102XCS325-22 24 50322XCS156-22 79 50316XCS571-22 3PTU NORM MODE 50166XCP56-22 P 50102XCP344-22

50166XCP63-22 U 50102XCP345-22 UT402 GICS04 GSD 41HE (#3) 700 P412 PT414 PT108 JT108 D1 GZSS02 D2 BCK BCK D3 R HYD (A429 IN A) 53 50319XXB1069-22WH 52 50316XXB551-22WH 43GARMIN ARINC OUT (+) B HYD (A429 IN B) 54 50319XXB1069-22BL 53 50316XXB551-22BL 44GARMIN ARINC OUT (-) D4 UI410 D5 GARMIN DATA CONCENTRATOR #1 DC PEDESTAL CABIN KZ219 PF138 JF138 PI410 P411 PT128 JT128 PZ219 HYD SYS B LOCKOUT 50166XXS60-22 3 50101XXS1545-22 39PTCU NOT NORM 10 50316RMS544-22 A3

B1 R HYD RH EMER CB PANEL 9 50316RMS543-22 B3 FW SOV JF972 PF972 1 2 REFER TO 26-20-01 A1 REFER TO 24-61-01 5 D REFER TO X1 26-20-01 X2 SI102 HYDRAULIC PUMP B SW PF138 JF138 CABIN TAIL B2 5 JA034 PA034 A2 4 50166RMP64-22 6 50101RMP1548-22 NORM 50166RMS66-22 8 50101RMS1550-22 99 50319RMS1053-22 6 MIN 1 50166RMS65-22 7 50101RMS1549-22 89 50319RMS1052-22 50166RMS67-22 9 50101RMS1551-22 101 50319RMS1055-22 UT404 GARMIN ENGINE / AIRFRAME I/O #3 SHUTOFF 3

2 50166RMP68-22 10 50101RMP1552-22 M PT410 P71003

(MIN POS) 100 B HYD DEPRESS SW TY016 J1 PY006 GICB06 FAIRING TAIL PT166 JT166 PT406 P71001 SYS B BCK HYD TEMP A 50601RMS154-22WH 58 50319RMS1063-22WH 9 B HYD TEMP HI MON RTD B 50601RMS154-22BL 59 50319RMS1063-22BL 10 B HYD TEMP LO C 50601RMS161-22 BCK BCK 8202910-1K2 GYCS20

HYDRAULIC SYSTEM Figure 01. (Sheet 2) Figure 01 Page 6 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AY111 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0001 - 0021 01 AY112 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0001 - 0021 01 AY113 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0001 - 0021 01 EY003 HYDRAULIC RSCR (ZONE 311) RF GICB06 S2526-4 GROUNDING CONNECTOR (ZONE 225) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): S2800-39 S2800-39 CONNECTOR KIT 28198 0001 - 0021 01 FC120N2 . CRIMP CONTACT 28198 01 GICS04 S3521-7 GROUND STUD KIT (ZONE 225) 0001 - 0021 01 GTCS04 S3521-8 GROUND STUD KIT (ZONE 366) 0001 - 0021 01 GYCS20 S3521-8 GROUND STUD KIT (ZONE 312) 0001 - 0021 01 GYDS16 S3521-8 GROUND STUD KIT (ZONE 318) 0001 - 0021 01 GZSS01 GROUND STUD KIT RF GZSS02 GROUND STUD KIT RF HZ042 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0001 - 0021 01 HZ234 S2899-5.0 CIRCUIT BREAKER (ZONE 366) 82647 0001 - 0021 01 J1 MS27497E12F98S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0001 - 0021 01 J2 MS27497E20F39S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 J3 MS27497T8F98PA CONNECTOR 96906 0001 - 0021 01 S3744-14 . BACKSHELL 96906 01 J4 D38999/24FA98PA CONNECTOR 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497E10F98P MS27497E10F98P CONNECTOR 96906 0001 - 0021 01 S3627-9 . BACKSHELL 01 42878-8410 . MODULAR JACK, VERT-RJ45 27264 01 JA026 D38999/24FH35PN RECEPTACLE (ZONE 282) 0001 - 0021 01 S3627-23 . BACKSHELL 01 JA034 D38999/24FJ35PB CONNECTOR (ZONE 282) 0001 - 0021 01 S3627-25 . BACKSHELL 01 JF136 MS27497T22F55S CONNECTOR (ZONE 229) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JF138 MS27497T12F35S CONNECTOR (ZONE 229) 96906 0001 - 0021 01 S3627-12-90 . BACKSHELL 01 JF972 MS27497T14F15S CONNECTOR (ZONE 236) 96906 0001 - 0021 01 JT108 MS27497T24F35SB CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-24-90 . BACKSHELL 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT116 MS27497T22F35S CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JT128 MS27497T24F35S CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 JT166 MS27497T22F35S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT904 MS27497T20F39S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JY151 M39029/58-360 PIN - CONTACT (ZONE 311) 0TRC3 0001 - 0021 01 SJS830200 . 8 PIN PLUG 58982 01 JZ115 10-504934-001 CONNECTOR (ZONE 365) 77820 0001 - 0021 01 3473-6600 . SOCKET 76381 01 JZ215 10-504934-001 CONNECTOR (ZONE 366) 77820 0001 - 0021 01 JZ932 M39029/58-360 PIN - CONTACT (ZONE 366) 0TRC3 0001 - 0021 01 SJS830200 . 8 PIN PLUG 58982 01 KZ219 RELAY (ZONE 366) RF LY004 RESISTANCE RF NZ115 PCB ASSEMBLY - HYDRAULIC CONTROL (ZONE 365) RF NZ215 PCB ASSEMBLY - HYDRAULIC CONTROL RF P1 M55302/57A60Y-0 CONNECTOR 0001 - 0021 01 P412 CONNECTOR RF P71001 CONNECTOR RF P71003 CONNECTOR RF PA026 D38999/26FH35SN PLUG (ZONE 368) 0001 - 0021 01 S3627-23 . BACKSHELL 01 PA034 D38999/26FJ35SB STRAIGHT PLUG GROUNDED (ZONE 368) 0001 - 0021 01 S3627-25 . BACKSHELL 01 PF136 MS27484T22F55P CONNECTOR (ZONE 229) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 PF138 MS27484T12F35P CONNECTOR (ZONE 229) 96906 0001 - 0021 01 S3627-12 . BACKSHELL 01 PF972 MS27484T14F15P CONNECTOR (ZONE 236) 96906 0001 - 0021 01 S3627-14 . BACKSHELL 96906 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0001 - 0021 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PT108 MS27484T24F35PB PLUG (ZONE 366) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 PT116 MS27484T22F35P CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT128 MS27484T24F35P CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PT166 MS27484T22F35P CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-22-90 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20-90 . BACKSHELL 01 PT406 D38999/26MJ35SN PLUG (ZONE 366) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0001 - 0021 01 M85049/38S25N . BACKSHELL 01 PT410 D38999/26MJ35SD PLUG (ZONE 366) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0001 - 0021 01 M85049/38S25N . BACKSHELL 01 PT414 D38999/26FG35SN PLUG (ZONE 366) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0001 - 0021 01 S3627-21 . BACKSHELL 01 PT904 MS27484T20F39P CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 PY006 D38999/26FA98SA PLUG (ZONE 318) 0001 - 0021 01 S3627-9 . BACKSHELL 01 PY151 M39029/57-354 CONTACT - SOCKET (ZONE 311) 81590 0001 - 0021 01 SJS830100 . 8 PIN PLUG 58982 01 PY152 D38999/26FA98SA PLUG (ZONE 318) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PY154 D38999/26FB35SN PLUG (ZONE 318) 0001 - 0021 01 S3627-11-90 . BACKSHELL 01 PY156 D38999/26FA98SB CONNECTOR (ZONE 318) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PY158 D38999/26FA98SN PLUG (ZONE 318) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PY315 D38999/26FA98SN PLUG (ZONE 317) 0001 - 0021 01 S3627-9-90 . BACKSHELL 01 PZ014 LMD-4001-S CONNECTOR (ZONE 366) 49367 0001 - 0021 01 PZ219 M39029/92-534 CONTACT (ZONE 366) 0001 - 0021 01 M83536/9-024 . RELAY 2X920 01 PZ932 M39029/57-354 CONTACT - SOCKET (ZONE 366) 81590 0001 - 0021 01 SJS830100 . 8 PIN PLUG 58982 01 SI044 S3200-7 SWITCH (ZONE 229) 0001 - 0021 RF SI102 SWITCH RF TY015 HYDRAULIC TEMPERATURE MONITOR RF UI410 GSD 41 (ZONE 225) RF UT402 011-01457-02 GSD 41H (ZONE 366) 0TRC3 0001 - 0021 01 UT404 011-02635-01 GEA 7100 (ZONE 366) 0TRC3 0001 - 0021 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

UY014 MANIFOLD ASSY, HYDRAULIC RF VY309 SPOILER ISOLATION VALVE RF

Figure 01

Page 11

ICA-700-42-00001 Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

PY055

LH EMER J-BOX TAIL FAIRING PTCU A SOV JT903 PT903 JT169 PT169 50609XCS219-22 2 2 4 PY061 J1 1 2 1 4 REFER TO 24-60-01 5 50317LCP47-22 E 50321LCP108-22 40 7 1 50609XXP221-22 A SOLENOID POWER HZ023 6 7 REFER TO SHEET 1 6 PWR 1 2 BLK WHT 3 REFER TO 24-60-01 5 50317XCP48-22 F 50609LCP154-22 9 3 SYSTEM A REFER TO SHEET 4 33 9 HZ015 DY029 SOLENOID VALVE PTCU A CONT 8 8 DY027 GND

AC120 50609XXP179-22 BLK WHT JA021 PA021 SOLENOID GND VC105 WH1 50609XCS153-22 B 50102XCP338-22 34 50321XCP143-22 32 50609XCS155-22 PTCU COOLING UY009 VALVE DC105 BCK 50102XCS337-22 25 50321XCS106-22 55 PY056 P/N = PTU-700 WH2 52 POWER TRANSFER UNIT

AC119 50609XCS220-22 2 2 4 PY060 J2 LH J-BOX 1 4 7 1 50609XXP222-22 A SOLENOID POWER UT401 6 7 GARMIN DATA CONCENTRATOR #2 P412 PT413 PT127 JT127 JT115 PT115 BLK WHT 3 6 PWR 50609XXP180-22 9 3 BCK BCK BCK 9 DY028 SYSTEM B PTCU ARINC IN A 73 50319XXB1370-22WH 71 50315XXB712-22WH 54 50321XXB144-22WH 8 8 PTCU ARINC IN B 61 50319XXB1370-22BL 72 50315XXB712-22BL 55 50321XXB144-22BL DY030 SOLENOID VALVE GND JT170 PT170 50609RCP156-22 BLK WHT

REFER TO SHEET 2 1 SOLENOID GND REFER TO SHEET 2 33 50609XCS161-22 B 50609XCS157-22

PY059 JY059

K E SPARE REFER TO SHEET 2 74 N 50609XCS158-22 M

REFER TO 45-40-01 50609XXB160-22BL G 50609XXB160-22WH F REFER TO 45-40-01 BCK

REFER TO SHEET 4 39 50609RCS169-22WH A 50635XXB1-22WH REFER TO SHEET 4 40 50609RCS169-22BL B 50635XXB1-22BL BCK BCK REFER TO SHEET 4 30 REFER TO SHEET 4 2 GYDS36 50609XCP171-22 J 50609XCP170-22 X

REFER TO SHEET 2 REFER TO SHEET 2 REFER TO SHEET 2 6 50609XCS163-22WH P REFER TO SHEET 2 7 50609XCS163-22BL R SPARE BCK BCK PY124 REFER TO SHEET 1 REFER TO SHEET 1 3 50609XCS172-22WH D REFER TO SHEET 1 4 50609XCS172-22BL C BCK BCK

50609XXS174-22 L 50609XCP175-22 V

50609XCS176-22WH S 50609XCS176-22BL T BCK

50609XCS177-22 U

REFER TO SHEET 4 44

REFER TO SHEET 4 45 REFER TO SHEET 4 46 UY009 REFER TO SHEET 4 47 POWER TRANSFER CONVERSION UNIT BCK REFER TO SHEET 4 48

PWR 2 BA REFER TO 24-60-01 50606XCD1-02 HZ908 GND UY009 50607XCD1-02 BA GYDS34

UI411 GARMIN ENGINE / AIRFRAME I/O #1 PI412 P71001 JT906 PT906 PA022 JA022 BCK *C 50323XCS434-22BL 19 50103XCS586-22BL 69 PTCU AMPS LO REFER TO SHEET 4 *D 50323XCS434-22WH 20 50103XCS586-22WH 68 PTCU AMPS HI BCK BCK 28 PTCU VOLT HI Z 50323XCS435-22 21 50103XCS588-22 26 PTCU CONT HI

D 50103XCP587-22 29 PTCU VOLT LO GICB07 F 50103XCP589-22 27 PTCU CONT LO 8202910-1K3

HYDRAULIC SYSTEM Figure 01. (Sheet 3) Figure 01 Page 12 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AC119 M81714/65-20-1 SPLICE (ZONE 281) 0A744 0001 - 0021 01 AC120 M81714/65-20-1 SPLICE (ZONE 281) 0A744 0001 - 0021 01 DC105 S3106-7 TRANSZORB ASSEMBLY 00779 0001 - 0021 01 DY027 S3106-3 DIODE ASSEMBLY 06090 0001 - 0021 01 DY028 S3106-3 DIODE ASSEMBLY 06090 0001 - 0021 01 DY029 S3106-3 DIODE ASSEMBLY 06090 0001 - 0021 01 DY030 S3106-3 DIODE ASSEMBLY 06090 0001 - 0021 01 GICB07 204814-1 CONNECTOR (ZONE 225) 00779 0001 - 0021 01 6-203736-0 . CONNECTOR KIT 00779 01 S2099-6 . CONTACT 00779 01 S3521-7 . GROUND STUD KIT 01 GYDS34 MS25036-127 TERMINAL (ZONE 317) 96906 0001 - 0021 01 GYDS36 S3521-8 GROUND STUD KIT (ZONE 317) 0001 - 0021 01 HZ015 S2899-5.0 CIRCUIT BREAKER (ZONE 367) 82647 0001 - 0021 01 HZ023 S2899-5.0 CIRCUIT BREAKER (ZONE 367) 82647 0001 - 0021 01 HZ908 ANL-250 FUSE LIMITER (ZONE 368) 71400 0001 - 0021 01 S1367X7-13 . TERMINAL 01 J1 MS27497E12F98S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0001 - 0021 01 J2 MS27497E20F39S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JA021 D38999/24FH35PA CONNECTOR (ZONE 281) 0001 - 0021 01 S3627-23 . BACKSHELL 01 JA022 MS27474T22F35P CONNECTOR (ZONE 282) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT127 MS27497T24F35S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT903 MS27497T20F39SA CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT906 MS27497T18F32S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-18 . BACKSHELL 01 JY059 340HS001M17-3N SHORTING CAP 06324 0001 - 0021 01 P412 CONNECTOR RF P71001 CONNECTOR RF PA021 D38999/26FH35SA PLUG (ZONE 367) 0001 - 0021 01 S3627-23 . BACKSHELL 01 PA022 MS27484T22F35S CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI412 D38999/26MJ35SN PLUG (ZONE 225) 0001 - 0021 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 PT127 MS27484T24F35P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20-90 . BACKSHELL 01 PT413 D38999/26FG35SN PLUG (ZONE 365) 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0001 - 0021 01 S3627-21 . BACKSHELL 01 PT903 MS27484T20F39PA CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 PT906 MS27484T18F32P CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-18 . BACKSHELL 01 PY055 LMD-5001-P RELAY MODULE 49367 0001 - 0021 01 LMD-4001-S . CONNECTOR 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PY056 LMD-5001-P RELAY MODULE 49367 0001 - 0021 01 LMD-4001-S . CONNECTOR 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PY059 D38999/26FE99SN PLUG (ZONE 317) 0001 - 0021 01 S3627-17 . BACKSHELL 01 PY060 M39029/57-357 CONTACT - SOCKET (ZONE 317) 96906 0001 - 0021 01 SJS862300 . PLUG 58982 01 PY061 M39029/57-357 CONTACT - SOCKET (ZONE 317) 96906 0001 - 0021 01 SJS862300 . PLUG 58982 01 PY124 D38999/26FB35SN PLUG (ZONE 318) 0001 - 0021 01 S3627-11-90 . BACKSHELL 01 UI411 GEA 7100 (ZONE 225) RF UT401 GSD 41H (ZONE 365) RF UY009 POWER TRANSFER CONVERSION UNIT (ZONE 317) RF VC105 VALVE RF

Page 15

ICA-700-42-00001 Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

RH MAIN J-BOX TAIL FAIRING PTCU A SOV AUX JT108 PT108 PT901 JT901 JT903 PT903 JT169 PT169 1 2 REFER TO 24-60-01 75 U G 33 REFER TO SHEET 3 5 50316XXP611-22 50319XXP1119-22 50317XXP51-22 50321XXP110-22 NZ209 RH AUX POWER DIST PCB HZ261 P1 JZ209

GEN POWER AVAILABLE 11

NZ215 SYSTEM B HYDRAULIC PCB P1 JZ215 JT170 PT170 JT116 PT116 GEN POWER AVAILABLE 52 50316RCS591-22 PTCU ARINC OUT (+) 45 50316RCS595-22WH 65 50322RCS187-22WH 39 REFER TO SHEET 3 PTCU ARINC OUT (-) 46 50316RCS595-22BL 66 50322RCS187-22BL 40 REFER TO SHEET 3 BCK BCK GZSS02

LH MAIN J-BOX PTCU B SOV AUX PZ931 JZ931 JT125 PT125 1 2 REFER TO 24-60-01 5 50315XXP462-22 B 50315XXP678-22 N 50323XXP472-22 NZ102 HZ150 POWER DISTRIBUTION PCB P1 JZ102 JT105 PT105

HYD GEN MOD 17 50315XXS554-22 39 50319XXS1110-22

JT902 PT902 RH EMER J-BOX 50318XXS85-22 *G

JT906 PT906 50318XXP97-22 W

KZ008 JT904 PT904 PTCU B SOV R 50322XXP194-22 30 REFER TO SHEET 3 A2 A1 1 2 REFER TO 24-60-01 50318RCP93-22 J 50322RCP178-22 2 REFER TO SHEET 3 5 HZ020 J1 PZ908

5 50318XXS86-22 K 50322XXS189-22 44 REFER TO SHEET 3 PTCU B CONT

1 1 2 REFER TO 24-60-01 5 50318XCP87-22 P 50322XCP190-22 45 REFER TO SHEET 3 50318XXP88-22 HZ060 4 REFER TO 24-60-01 KZ006 13 8 RZ902 7 REFER TO A2 A1 BZ032 BZ062 BZ064 REFER TO 24-60-01 24-60-01 9 11 10 J1 PZ906

12 5 BL WH JT904 PT904 BUS TIE CONT 1 50318XCS89-22WH E 50322XCS191-22WH 46 REFER TO SHEET 3 50318XCS89-22BL F 50322XCS191-22BL 47 REFER TO SHEET 3 BCK BCK

4 50318XCS90-22 H 50322XCS192-22 48 REFER TO SHEET 3

13 8 JT906 PT906 7 50318XCS91-22BL *C 9 50318XCS91-22WH *D REFER TO SHEET 3 11 10 50318XCS92-22 Z

12 8202910-1K4 PTCU CONT

HYDRAULIC SYSTEM Figure 01. (Sheet 4) Figure 01 Page 16 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GZSS02 GROUND STUD KIT RF HZ020 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0001 - 0021 01 HZ060 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0001 - 0021 01 HZ150 S2899-5.0 CIRCUIT BREAKER (ZONE 365) 82647 0001 - 0021 01 HZ261 S2899-5.0 CIRCUIT BREAKER (ZONE 366) 82647 0001 - 0021 01 HZ908 ANL-250 FUSE LIMITER (ZONE 368) 71400 0001 - 0021 01 S1367X7-13 . TERMINAL 01 J1 MS27497E12F98S CONNECTOR 96906 0001 - 0021 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0001 - 0021 01 JT105 MS27497T24F35SB CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-24-90 . BACKSHELL 01 JT108 MS27497T24F35SB CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-24-90 . BACKSHELL 01 JT116 MS27497T22F35S CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 JT125 MS27497T24F4S CONNECTOR (ZONE 365) 96906 0001 - 0021 01 8250315-1 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT901 MS27497T20F39S CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT902 MS27497T24F4S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 JT903 MS27497T20F39SA CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT904 MS27497T20F39S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 JT906 MS27497T18F32S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-18 . BACKSHELL 01 JZ102 10-504934-001 CONNECTOR (ZONE 365) 77820 0001 - 0021 01 3425-6600 . SOCKET, 50PIN 0.1" IDC 76381 01 JZ209 10-504934-001 CONNECTOR (ZONE 366) 77820 0001 - 0021 01 JZ215 10-504934-001 CONNECTOR (ZONE 366) 77820 0001 - 0021 01 JZ931 M39029/58-360 PIN - CONTACT (ZONE 365) 0TRC3 0001 - 0021 01 SJS830200 . 8 PIN PLUG 58982 01 KZ006 S3602-2 CONTACTOR (ZONE 368) 0001 - 0021 01 KZ008 CONTACTOR (ZONE 368) RF NZ102 7468185-5 PCB ASSEMBLY - PWR DIST (ZONE 365) 0001 - 0021 01 NZ209 7468186-1 PCB ASSEMBLY - AUX PWR DIST (ZONE 366) 0001 - 0021 01 NZ215 PCB ASSEMBLY - HYDRAULIC CONTROL RF P1 M55302/57A60Y-0 CONNECTOR 0001 - 0021 01 PT105 MS27484T24F35PB PLUG (ZONE 365) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PT108 MS27484T24F35PB PLUG (ZONE 366) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0001 THRU 0021

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT116 MS27484T22F35P CONNECTOR (ZONE 366) 96906 0001 - 0021 01 S3627-22 . BACKSHELL 01 PT125 MS27484T24F4P CONNECTOR (ZONE 365) 96906 0001 - 0021 01 S3627-16 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20-90 . BACKSHELL 01 PT901 MS27484T20F39P CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 PT902 MS27484T24F4P CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-24 . BACKSHELL 01 PT903 MS27484T20F39PA CONNECTOR (ZONE 367) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 PT904 MS27484T20F39P CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-20 . BACKSHELL 01 PT906 MS27484T18F32P CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-18 . BACKSHELL 01 PZ906 MS27484T10F35S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-10-90 . BACKSHELL 01 PZ908 MS27484T10F35S CONNECTOR (ZONE 368) 96906 0001 - 0021 01 S3627-10-90 . BACKSHELL 01 PZ931 M39029/57-354 CONTACT - SOCKET (ZONE 365) 81590 0001 - 0021 01 SJS830100 . 8 PIN PLUG 58982 01 RZ902 S2609-2 SHUNT ASSEMBLY (ZONE 368) 0001 - 0021 01

29-10-01

HYDRAULIC SYSTEM AIRPLANES 0034 & ON

LH EMER J-BOX TAIL FAIRING JT169 PT169 JT903 PT903 1 2 PY055 UY009 REFER TO 24-60-01 5 50317LCP47-22 E 50321LCP108-22 40 POWER TRANSFER CONVERSION UNIT HZ023 REFER TO SHEET 4 33 2 PTCU A SOV REFER TO SHEET 1 42 50609XCS219-22 2 4 PY061 J1 4 1 41 7 1 50609XXP221-22 A 32 6 7 55 BLK 6 WHT 3 PWR 52 50609LCP154-22 9 3 BCK DY029 9 SYSTEM A AC120 8 8 SOLENOID VALVE JA021 PA021 DY027 WH1 (NORMALLY OPEN) GND VC105 50609XXP179-22 BLK WHT PTCU COOLING 50102XCP338-22 34 50321XCP143-22 VALVE DC105 50609XCS153-22 B 50102XCS337-22 25 50321XCS106-22 50609XCS155-22 WH2 PY056 AC119

LH J-BOX 50609XCS220-22 2 2 4 PY060 J2 UT401 4 1 GARMIN DATA CONCENTRATOR #2 P412 PT413 PT127 JT127 JT115 PT115 7 1 50609XXP222-22 A 6 7 BCK BCK BCK BLK WHT 3 6 PWR PTCU ARINC IN A 73 71 54 9 3 50319XXB1370-22WH 50315XXB712-22WH 50321XXB144-22WH 50609XXP180-22 SYSTEM B PTCU ARINC IN B 61 50319XXB1370-22BL 72 50315XXB712-22BL 55 50321XXB144-22BL DY028 9 8 8 SOLENOID VALVE DY030 (NORMALLY OPEN) 50609RCP156-22 GND BLK WHT 50609XCS161-22 B TAIL FAIRING 50609XCS157-22 JT170 PT170 DY041 REFER TO SHEET 2 1 BLK PY059 J3 WHT REFER TO SHEET 2 33 KSOLENOID VALVE B CTRL ESOLENOID VALVE A CTRL

REFER TO SHEET 4 74 N28VDC IN 50609XCS158-22 MAIR_VALVE

REFER TO 45-40-01 50609XXB160-22WH FARES_429A 50609XXB160-22BL GARES_429B REFER TO 45-40-01 BCK

REFER TO SHEET 4 39 50609RCS169-22WH AMGCU_429A REFER TO SHEET 4 40 50609RCS169-22BL BMGCU_429B BCK BCK

REFER TO SHEET 4 30 REFER TO SHEET 4 2

50609XCP171-22 JLOGIC GND 50609XCP170-22 XMGCU_REF GYDS36

50609XXS224-22 HWEIGHT ON WHEELS REFER TO SHEET 4 34 50609XCS225-22 YPTCU_OFF REFER TO SHEET 2

REFER TO SHEET 2 6 50609XCS163-22WH PPSI_B REFER TO SHEET 2 7 50609XCS163-22BL RPSI_B_REF BCK REFER TO SHEET 2

PY124 REFER TO SHEET 1 REFER TO SHEET 1 3 50609XCS172-22WH DPSI_A REFER TO SHEET 1 4 50609XCS172-22BL CPSI_A_REF BCK BCK

REFER TO SHEET 4 44 50609XXS174-22 LPTCU_HOT

50609XCP223-22 REFER TO SHEET 4 45 50609XCP175-22 VBAT_BKUP REFER TO SHEET 4 46 50609XCS176-22WH SFDR_CUR_SNS+ REFER TO SHEET 4 47 50609XCS176-22BL TFDR_CUR_SNS- BCK BCK REFER TO SHEET 4 48 50609XCS177-22 UBUS_RLY HZ908 PWR 1 2 BA REFER TO SHEET 4 50606XCD1-02 250 GND UY009 50607XCD1-02 BA GYDS34

D 50103XCP587-22 29 PTCU VOLT LO 8202910-3K3 GICB07 F 50103XCP589-22 27 PTCU CONT LO

HYDRAULIC SYSTEM Figure 03. (Sheet 1) Figure 03 Page 2 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AY116 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0034 & ON RF AY117 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0034 & ON 01 AY118 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0034 & ON 01 EY001 INDICATOR, RSVR VOLUME (ZONE 311) RF GFCS20 S3521-8 GROUND STUD KIT (ZONE 186) 0034 & ON 01 GICB01 GROUND (ZONE 229) RF GTCS03 S3521-8 GROUND STUD KIT (ZONE 365) 0034 & ON 01 GYDS13 S3521-8 GROUND STUD KIT (ZONE 318) 0034 & ON 01 GYDS25 S3521-8 GROUND STUD KIT (ZONE 311) 0034 & ON 01 GZSS01 GROUND STUD KIT RF GZSS02 GROUND STUD KIT RF HZ015 S2899-5.0 CIRCUIT BREAKER (ZONE 367) 82647 0034 & ON 01 HZ043 S2899-5.0 CIRCUIT BREAKER (ZONE 367) 82647 0034 & ON 01 J1 CONNECTOR RF J2 CONNECTOR RF J3 CONNECTOR RF J4 CONNECTOR RF JA011 D38999/24FC35PA CONNECTOR (ZONE 281) 0034 & ON 01 S3627-13 . BACKSHELL 01 JA033 D38999/24FJ35PB CONNECTOR (ZONE 281) 0034 & ON 01 S3627-25 . BACKSHELL 01 JC142 MS27497T24F35SB CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JC971 MS27497T16F26S CONNECTOR (ZONE 235) 96906 0034 & ON 01 JF149 MS27497E16F35S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT116 MS27497T22F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT125 MS27497T24F4S CONNECTOR (ZONE 365) 96906 0034 & ON 01 8250315-1 . BACKSHELL 01 JT127 MS27497T24F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT903 MS27497T20F39SA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JY076 MS27474T16F35S CONNECTOR (ZONE 186) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JY121 M39029/58-360 PIN - CONTACT (ZONE 311) 0TRC3 0034 & ON 01 SJS830201 . RECEPTACLE 58982 01 JZ104 10-504934-001 CONNECTOR (ZONE 365) 77820 0034 & ON 01 3417-6600 . SOCKET 76381 01 JZ115 10-504934-001 CONNECTOR (ZONE 365) 77820 0034 & ON 01 3473-6600 . SOCKET 76381 01 JZ204 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 Figure 03 Page 3 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JZ215 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 KZ107 M83536/9-024 RELAY (ZONE 365) 2X920 0034 & ON 01 LY002 RESISTER RF NZ104 7468183-1 PCB ASSEMBLY - FADEC INT (ZONE 365) 0034 & ON 01 NZ115 PCB ASSEMBLY - HYDRAULIC CONTROL (ZONE 365) RF NZ204 7468183-1 PCB ASSEMBLY - FADEC INT (ZONE 366) 0034 & ON 01 NZ215 PCB ASSEMBLY - HYDRAULIC CONTROL RF P1 CONNECTOR RF P411 CONNECTOR RF P71001 CONNECTOR RF P71002 CONNECTOR RF PA011 D38999/26FC35SA PLUG (ZONE 367) 0034 & ON 01 S3627-13 . BACKSHELL 01 PA033 D38999/26FJ35SB STRAIGHT PLUG GROUNDED (ZONE 367) 0034 & ON 01 S3627-25 . BACKSHELL 01 PC142 MS27484T24F35PB PLUG (ZONE 229) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC971 MS27484T16F26P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PF149 MS27484E16F35P PLUG (ZONE 229) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT116 MS27484T22F35P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT125 MS27484T24F4P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PT127 MS27484T24F35P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20-90 . BACKSHELL 01 PT405 D38999/26MJ35SN PLUG (ZONE 365) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT407 D38999/26MJ35SB PLUG (ZONE 365) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT411 MS27488-22-2 PLUG (ZONE 365) 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): D38999/26FG35SA D38999/26FG35SA PLUG 0034 & ON 01 S3627-21 . BACKSHELL 01 PT903 MS27484T20F39PA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PY004 D38999/26FA98SA PLUG (ZONE 318) 0034 & ON 01 S3627-9 . BACKSHELL 01 PY076 MS27484T16F35P CONNECTOR (ZONE 318) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PY121 SJS830101 PLUG - 8 PIN (ZONE 311) 58982 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PY122 D38999/26FA98SA PLUG (ZONE 318) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PY124 D38999/26FB35SN PLUG (ZONE 318) 0034 & ON 01 S3627-11-90 . BACKSHELL 01 PY126 D38999/26FA98SB CONNECTOR (ZONE 318) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PY128 D38999/26FA98SN PLUG (ZONE 318) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PY303 D38999/26FA98SN PLUG (ZONE 317) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PZ017 LMD-4001-S CONNECTOR (ZONE 365) 49367 0034 & ON 01 LMD-7103-P . DIODE MODULE 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PZ107 JRS200300 RELAY SOCKET (ZONE 365) 58982 0034 & ON 01 M39029/92-534 . CONTACT 01 SI101 MS27754-34A SWITCH (ZONE 229) 96906 0034 & ON 01 TY014 9916248-5 TEMPERATURE TRANSDUCER 0034 & ON 01 UT401 GSD 41H (ZONE 365) RF UT403 011-02635-01 GEA 7100 (ZONE 365) 0TRC3 0034 & ON 01 UY012 MANIFOLD ASSY, HYDRAULIC RF VY303 SPOILER ISOLATION VALVE RF

NZ115 RH JBOX SYS A HYDRAULIC PCB LH J-BOX TAIL TAIL FAIRING FAIRING TAIL TAIL P1 JZ115 JT115 PT115 JT169 PT169 PT170 JT170 PT116 JT116

OS PRESS (+) 33 50315XCS645-22WH 3 50321XCS119-22WH 44 50609XCS188-22WH 52 50322XCS226-22WH 71 50316XCS705-22WH OS PRESS (-) 34 50315XCS645-22BL 4 50321XCS119-22BL 45 50609XCS188-22BL 53 50322XCS226-22BL 72 50316XCS705-22BL BCK BCK BCK BCK NZ215 SYS B HYDRAULIC PCB GZSS01 FAIRING TAIL JZ215 P1 PT170 JT170 36RES VOL LO 50609XCS135-22BL 70 50322XCS170-22BL 93 50316XCS559-22BL 8RES VOL LO EY003 JY151 PY151 50609XCS135-22OR 71 50322XCS170-22OR 94 50316XCS559-22OR 7RES VOL WIPER 72 91 35RES VOL HI SYS B HYD VOLUME VW 50609XCS135-22WH 50322XCS170-22WH 50316XCS559-22WH REMOTE INDICATOR 3BK 50633XCP04-20BK E 50609XCP144-22 GYDS16

VW 3WH 50633XCP05-20WH D 50609XCP143-22 POWER AY111 VW WH 1WH 50633XCS01-20WH A 50609XCS145-22WH A LY004 SYSTEM B AY112 VW RD RESERVOIR 1RD 50633XCS02-20RD B 50609XCS145-22OR B C TO POT AY113 VOLUME POT VW BK 1BK 50633XCS03-20BK C 50609XCS145-22BL

WH 2WH RD TO HYD PCB 2RD VY309 J1 PY315 SYS B SPOILER VALVE BK 2BK B 50609RCS138-22 73 50322RCS171-22 95 50316RCS558-22 21SPOILER ISO VLV CMD GROUND ENERGIZED TO OPEN PT904 JT904 POWER A 50609RCP139-22 75 50322RCP166-22 HYD SYS B RH EMER JBOX D 50318RCP84-22 HZ042 79 50322XCP176-22 2 1 50322RCP165-22 C 50318RCP83-22 REFER TO 24-60-01 50322XCP164-22 B 50318XCP82-22 5 UY014 SYSTEM B HYD MANIFOLD GZSS02 J4 PY158 | NORMALLY | A 50609RCP134-22 51 50322RCP163-22 100 50316RCP553-22 59HYD CB BYPASS VALVE B 43 90 60HEAT EXG BYPASS VLV | OPEN | 50609RCS133-22 50322RCS168-22 50316RCS561-22 J2 REFER TO SHEET 3 PY154 SUPPLY + 1 50609XCP129-22 4 SIGNAL + 3 6 87 13TS PRSS XDUCER (+) PRESS SENSOR 50609XCS127-22WH 50322XCS161-22WH 50316XCS564-22WH SIGNAL - 4 50609XCS127-22BL 7 50322XCS161-22BL 88 50316XCS564-22BL 12TS PRSS XDUCER (-) SUPPLY - 2 50609XCP130-22 BCK BCK BCK REFER TO SHEET 3 J3 PY156 GYDS16 PRESS SWITCH | LOW = OPN | C 50609XXP132-22 B 50609XXS131-22 5 50322XXS167-22 89 50316XXS562-22 10TS HYD PRESS SWITCH PY152 J1 EXC + A 50609RCS125-22WH 8 50322RCS159-22WH 82 50316RCS566-22WH 37SYS TEMP RTD EXC (+) TEMP SENSOR EXC - C 50609RCS125-22BL 9 50322RCS159-22BL 83 50316RCS566-22BL 38SYS TEMP RTD EXC (-) 50609RCS126-22WH 10 50322RCS160-22WH 85 50316RCS567-22WH 39SYS TEMP RTD RTN (+) RETURN B 50609RCS126-22BL 11 50322RCS160-22BL 86 50316RCS567-22BL 40SYS TEMP RTD RTN (-) BCK BCK BCK

C1 SI044 C2 GTCS04 50322RCP236-22 63 50316RCP725-22 1PCB GND 50322RCP237-22 64 50316RCP568-22 30SYS GND PTCU ROTARY SW C3 C4 REFER TO SHEET 4 C5 REFER TO SHEET 3 1 50322XCS158-22 81 50316XCS569-22 24PTCU ISO VLV A REFER TO SHEET 3 33 84 25PTCU ISO VLV B NORM CC 50322XCS177-22 50316XCS549-22

AUX A AUX B B1 B2 PZ014 OFF HYD B3 GEN WOW 1 50316XXS387-22 54WEIGHT ON WHEELS B4 B5 PEDESTAL CABIN CABIN TAIL REFER TO 32-60-01 BC PF136 JF136 JA026 PA026 A1 D 20 75 4PTCU OFF A2 50166XCS51-22 50102XCS321-22 50322XCS152-22 50316XCS550-22 A3 50166XCS52-22 E 50102XCS322-22 21 50322XCS153-22 76 50316XCS574-22 2PTU NORM MODE A4 50166XCS53-22 J 50102XCS323-22 22 50322XCS154-22 77 50316XCS573-22 31PTU NORM MODE K 23 78 32PTU NORM MODE A5 50166XCS54-22 50102XCS324-22 50322XCS155-22 50316XCS572-22 AC 50166XCS55-22 N 50102XCS325-22 24 50322XCS156-22 79 50316XCS571-22 3PTU NORM MODE 50166XCP56-22 P 50102XCP344-22 GICS04 50166XCP63-22 U 50102XCP345-22 UT402 GSD 41HE (#3) 700 P412 PT414 PT108 JT108 D1 GZSS02 D2 BCK BCK D3 R HYD (A429 IN A) 53 50319XXB1069-22WH 52 50316XXB551-22WH 43GARMIN ARINC OUT (+) B HYD (A429 IN B) 54 53 44GARMIN ARINC OUT (-) D4 50319XXB1069-22BL 50316XXB551-22BL UI410 D5 GARMIN DATA CONCENTRATOR #1 DC PEDESTAL CABIN KZ219 PF138 JF138 PI410 P411 PT128 JT128 PZ219 HYD SYS B LOCKOUT 50166XXS60-22 3 50101XXS1545-22 39PTCU NOT NORM 10 50316RMS544-22 A3

B1 R HYD RH EMER CB PANEL 9 50316RMS543-22 B3 FW SOV JF972 PF972 REFER TO 26-20-01 A1 REFER TO 24-61-01 2 D 15 REFER TO X1 26-20-01 X2 SI102 HYDRAULIC PUMP B SW PF138 JF138 CABIN TAIL B2 5 JA034 PA034 A2 4 50166RMP64-22 6 50101RMP1548-22 NORM 50166RMS66-22 8 50101RMS1550-22 99 50319RMS1053-22 6 MIN 1 50166RMS65-22 7 50101RMS1549-22 89 50319RMS1052-22 50166RMS67-22 9 50101RMS1551-22 101 50319RMS1055-22 UT404 GARMIN ENGINE / AIRFRAME I/O #3 SHUTOFF 3

2 50166RMP68-22 10 50101RMP1552-22 M PT410 P71003

(MIN POS) 100 B HYD DEPRESS SW TY016 J1 PY006 GICB06 FAIRING TAIL PT166 JT166 PT406 P71001 SYS B BCK 8202910-3K2 HYD TEMP A 50601RMS154-22WH 58 50319RMS1063-22WH 9 B HYD TEMP HI MON RTD B 50601RMS154-22BL 59 50319RMS1063-22BL 10 B HYD TEMP LO C 50601RMS161-22 BCK BCK

GYCS20

HYDRAULIC SYSTEM Figure 03. (Sheet 2) Figure 03 Page 6 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AY111 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0034 & ON 01 AY112 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0034 & ON 01 AY113 M81714/65-20-2 SPLICE (ZONE 312) 0A744 0034 & ON 01 EY003 HYDRAULIC RSCR (ZONE 311) RF GICB06 S2526-4 GROUNDING CONNECTOR (ZONE 225) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): S2800-39 S2800-39 CONNECTOR KIT 28198 0034 & ON 01 FC120N2 . CRIMP CONTACT 28198 01 GICS04 S3521-7 GROUND STUD KIT (ZONE 225) 0034 & ON 01 GTCS04 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GYCS20 S3521-8 GROUND STUD KIT (ZONE 312) 0034 & ON 01 GYDS16 S3521-8 GROUND STUD KIT (ZONE 318) 0034 & ON 01 GZSS01 GROUND STUD KIT RF GZSS02 GROUND STUD KIT RF HZ042 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0034 & ON 01 J1 MS27497E12F98S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0034 & ON 01 J1 CONNECTOR RF J2 MS27497E20F39S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 J3 MS27497T8F98PA CONNECTOR 96906 0034 & ON 01 S3744-14 . BACKSHELL 96906 01 J4 D38999/24FA98PA CONNECTOR 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497E10F98P MS27497E10F98P CONNECTOR 96906 0034 & ON 01 S3627-9 . BACKSHELL 01 42878-8410 . MODULAR JACK, VERT-RJ45 27264 01 JA026 D38999/24FH35PN RECEPTACLE (ZONE 282) 0034 & ON 01 S3627-23 . BACKSHELL 01 JA034 D38999/24FJ35PB CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JF136 MS27497T22F55S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JF138 MS27497T12F35S CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-12-90 . BACKSHELL 01 JF972 MS27497T14F15S CONNECTOR (ZONE 236) 96906 0034 & ON 01 JT108 MS27497T24F35SB CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT116 MS27497T22F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JT128 MS27497T24F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT166 MS27497T22F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT904 MS27497T20F39S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JY151 M39029/58-360 PIN - CONTACT (ZONE 311) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 JZ115 10-504934-001 CONNECTOR (ZONE 365) 77820 0034 & ON 01 3473-6600 . SOCKET 76381 01 JZ215 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 KZ219 RELAY (ZONE 366) RF LY004 RESISTANCE RF NZ115 PCB ASSEMBLY - HYDRAULIC CONTROL (ZONE 365) RF NZ215 PCB ASSEMBLY - HYDRAULIC CONTROL RF P1 M55302/57A60Y-0 CONNECTOR 0034 & ON 01 P411 CONNECTOR RF P412 CONNECTOR RF P71001 CONNECTOR RF P71003 CONNECTOR RF PA026 D38999/26FH35SN PLUG (ZONE 368) 0034 & ON 01 S3627-23 . BACKSHELL 01 PA034 D38999/26FJ35SB STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PF136 MS27484T22F55P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PF138 MS27484T12F35P CONNECTOR (ZONE 229) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 PF972 MS27484T14F15P CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PT108 MS27484T24F35PB PLUG (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT116 MS27484T22F35P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT128 MS27484T24F35P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT166 MS27484T22F35P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-22-90 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20-90 . BACKSHELL 01 PT406 D38999/26MJ35SN PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT410 D38999/26MJ35SD PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT414 D38999/26FG35SN PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 S3627-21 . BACKSHELL 01 PT904 MS27484T20F39P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PY006 D38999/26FA98SA PLUG (ZONE 318) 0034 & ON 01 S3627-9 . BACKSHELL 01 PY151 M39029/57-354 CONTACT - SOCKET (ZONE 311) 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 PY152 D38999/26FA98SA PLUG (ZONE 318) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PY154 D38999/26FB35SN PLUG (ZONE 318) 0034 & ON 01 S3627-11-90 . BACKSHELL 01 PY156 D38999/26FA98SB CONNECTOR (ZONE 318) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PY158 D38999/26FA98SN PLUG (ZONE 318) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PY315 D38999/26FA98SN PLUG (ZONE 317) 0034 & ON 01 S3627-9-90 . BACKSHELL 01 PZ014 CONNECTOR (ZONE 366) RF PZ219 M39029/92-534 CONTACT (ZONE 366) 0034 & ON 01 M83536/9-024 . RELAY 2X920 01 SI044 S3200-7 SWITCH (ZONE 229) 0034 & ON RF SI102 SWITCH RF TY016 TEMPERATURE TRANSDUCER RF UI410 GSD 41 (ZONE 225) RF UT402 011-01457-02 GSD 41H (ZONE 366) 0TRC3 0034 & ON 01 UT404 011-02635-01 GEA 7100 (ZONE 366) 0TRC3 0034 & ON 01 UY014 MANIFOLD ASSY, HYDRAULIC RF VY309 SPOILER ISOLATION VALVE RF

REFER TO SHEET 4 74 N28VDC IN 50609XCS158-22 MAIR_VALVE

REFER TO 45-40-01 50609XXB160-22WH FARES_429A 50609XXB160-22BL GARES_429B REFER TO 45-40-01 BCK

REFER TO SHEET 4 39 50609RCS169-22WH AMGCU_429A REFER TO SHEET 4 40 50609RCS169-22BL BMGCU_429B BCK BCK

REFER TO SHEET 4 30 REFER TO SHEET 4 2

50609XCP171-22 JLOGIC GND 50609XCP170-22 XMGCU_REF GYDS36

50609XXS224-22 HWEIGHT ON WHEELS REFER TO SHEET 4 34 50609XCS225-22 YPTCU_OFF REFER TO SHEET 2

REFER TO SHEET 2 6 50609XCS163-22WH PPSI_B REFER TO SHEET 2 7 50609XCS163-22BL RPSI_B_REF BCK REFER TO SHEET 2

PY124 REFER TO SHEET 1 REFER TO SHEET 1 3 50609XCS172-22WH DPSI_A REFER TO SHEET 1 4 50609XCS172-22BL CPSI_A_REF BCK BCK

REFER TO SHEET 4 44 50609XXS174-22 LPTCU_HOT

50609XCP223-22 REFER TO SHEET 4 45 50609XCP175-22 VBAT_BKUP REFER TO SHEET 4 46 50609XCS176-22WH SFDR_CUR_SNS+ REFER TO SHEET 4 47 50609XCS176-22BL TFDR_CUR_SNS- BCK BCK REFER TO SHEET 4 48 50609XCS177-22 UBUS_RLY HZ908 SHEET 3 PWR 1 2 BA REFER TO SHEET 4 50606XCD1-02 250 GND UY009 50607XCD1-02 BA GYDS34

D 50103XCP587-22 29 PTCU VOLT LO 8202910-3K3 GICB07 F 50103XCP589-22 27 PTCU CONT LO

HYDRAULIC SYSTEM Figure 03. (Sheet 3) Figure 03 Page 10 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AC119 M81714/65-20-1 SPLICE (ZONE 281) 0A744 0034 & ON 01 AC120 M81714/65-20-1 SPLICE (ZONE 281) 0A744 0034 & ON 01 DC105 S3106-7 TRANSZORB ASSEMBLY 00779 0034 & ON 01 DY027 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 DY028 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 DY029 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 DY030 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 DY041 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 GICB07 204814-1 CONNECTOR (ZONE 225) 00779 0034 & ON 01 6-203736-0 . CONNECTOR KIT 00779 01 S2099-6 . CONTACT 00779 01 S3521-7 . GROUND STUD KIT 01 GYDS34 MS25036-127 TERMINAL (ZONE 317) 96906 0034 & ON 01 GYDS36 S3521-8 GROUND STUD KIT (ZONE 317) 0034 & ON 01 HZ023 S2899-5.0 CIRCUIT BREAKER (ZONE 367) 82647 0034 & ON 01 HZ908 ANL-250 FUSE LIMITER (ZONE 368) 71400 0034 & ON 01 S1367X7-13 . TERMINAL 01 J1 MS27497E12F98S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0034 & ON 01 J2 MS27497E20F39S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 J3 MS27497T8F98PA CONNECTOR 96906 0034 & ON 01 S3744-14 . BACKSHELL 96906 01 JA021 D38999/24FH35PA CONNECTOR (ZONE 281) 0034 & ON 01 S3627-23 . BACKSHELL 01 JA022 MS27474T22F35P CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT127 MS27497T24F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT903 MS27497T20F39SA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT906 MS27497T18F32S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 P412 CONNECTOR RF PA021 D38999/26FH35SA PLUG (ZONE 367) 0034 & ON 01 S3627-23 . BACKSHELL 01 PA022 MS27484T22F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI412 D38999/26MJ35SN PLUG (ZONE 225) 0034 & ON 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT127 MS27484T24F35P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20-90 . BACKSHELL 01 PT413 D38999/26FG35SN PLUG (ZONE 365) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 S3627-21 . BACKSHELL 01 PT903 MS27484T20F39PA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PT906 MS27484T18F32P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 PY055 LMD-5001-P RELAY MODULE 49367 0034 & ON 01 LMD-4001-S . CONNECTOR 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PY056 LMD-5001-P RELAY MODULE 49367 0034 & ON 01 LMD-4001-S . CONNECTOR 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PY059 D38999/26FE99SN PLUG (ZONE 317) 0034 & ON 01 S3627-17 . BACKSHELL 01 PY060 M39029/57-357 CONTACT - SOCKET (ZONE 317) 96906 0034 & ON 01 SJS862300 . PLUG 58982 01 PY061 M39029/57-357 CONTACT - SOCKET (ZONE 317) 96906 0034 & ON 01 SJS862300 . PLUG 58982 01 PY124 D38999/26FB35SN PLUG (ZONE 318) 0034 & ON 01 S3627-11-90 . BACKSHELL 01 UI411 GEA 7100 (ZONE 225) RF UT401 GSD 41H (ZONE 365) RF UY009 POWER TRANSFER CONVERSION UNIT (ZONE 317) RF VC105 VALVE RF

TAIL FAIRING RH MAIN J-BOX JT169 PT169 PTCU A SOV AUX JT108 PT108 PT901 JT901 JT903 PT903 21 REFER TO SHEET 3 REFER TO 24-60-01 5 50316XXP611-22 75 50319XXP1119-22 U 50317XXP51-22 G 50321XXP110-22 33 NZ209 HZ261 RH AUX POWER DIST PCB P1 JZ209

GEN POWER AVAILABLE 11

NZ215 SYSTEM B HYDRAULIC PCB P1 JZ215 JT116 PT116 JT170 PT170 GEN POWER AVAILABLE 52 50316RCS591-22 50322XCS253-22 PTU LOCK 26 50316XCS771-22 49 50322XCS252-22 74 REFER TO SHEET 3 PTCU ARINC OUT (+) 45 50316RCS595-22WH 65 50322RCS187-22WH 39 REFER TO SHEET 3 PTCU ARINC OUT (-) 46 50316RCS595-22BL 66 50322RCS187-22BL 40 REFER TO SHEET 3 BCK BCK GZSS02

LH MAIN J-BOX PTCU B SOV AUX PZ931 JZ931 JT125 PT125

1 2 REFER TO 24-60-01 5 50315XXP462-22 B 50315XXP678-22 N 50323XXP472-22 NZ102 HZ150 POWER DISTRIBUTION PCB P1 JZ102 JT105 PT105

HYD GEN MOD 17 50315XXS554-22 39 50319XXS1110-22

RH EMER J-BOX

KZ008

A2 A1

J1 PZ908

5 JT902 PT902

50318XXS85-22 *G 1 JT906 PT906 50318XXP97-22 W 4 REFER TO 24-60-01 13 JT904 PT904 8 PTCU B SOV R 50322XXP194-22 30 REFER TO SHEET 3 7 1 2 REFER TO 24-60-01 50318RCP93-22 J 50322RCP178-22 2 REFER TO SHEET 3 9 5 11 HZ020 10

12 50318XXS86-22 K 50322XXS189-22 44 REFER TO SHEET 3 PTCU B CTRL BUS TIE CONT 1 2 REFER TO 24-60-01 50318XCP87-22 P 50322XCP190-22 45 REFER TO SHEET 3 5 50318XCP88-22 HZ060 JT906 PT906

50318XCS91-22BL *C 50318XCS91-22WH *D REFER TO SHEET 3

KZ006 50318XCS92-22 Z RZ902 HZ908 1 REFER TO A2 A1 2 BZ032 BZ062 BZ064 REFER TO 46 REFER TO SHEET 3 24-60-01 250 SHEETREFER 3SHEET 3TO 47 REFER TO SHEET 3 BCK J1 PZ906 REFER TO SHEET 2 5 1 REFER TO SHEET 3

PZ052 KZ052 BL WH PZ052 34 REFER TO SHEET 3 1 50318XCS141-22 A3 48 REFER TO SHEET 3 A2 A1 B3 4 B2 B1 13 WH1 JT904 PT904 8 X1 7 DZ052 50318XCS89-22WH E 50322XCS191-22WH X2 50318XCS89-22BL F 50322XCS191-22BL WH2 9 BCK BLK WHT 11 50318XCS139-22 20 *M 20 10 DT061

12 WHT BLK 50322XCS257-22 PTCU CONT DT062 8202910-3K4 50318XCS142-22 20 *R 20 50322XCS256-22 50318XCS90-22 H 50322XCS192-22

HYDRAULIC SYSTEM Figure 03. (Sheet 4) Figure 03 Page 13 29-10-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

DT061 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 DT062 S3106-3 DIODE ASSEMBLY 06090 0034 & ON 01 DZ052 S3106-7 TRANSZORB ASSEMBLY 00779 0034 & ON 01 GZSS02 GROUND STUD KIT RF HZ020 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0034 & ON 01 HZ060 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0034 & ON 01 HZ150 S2899-5.0 CIRCUIT BREAKER (ZONE 365) 82647 0034 & ON 01 HZ261 S2899-5.0 CIRCUIT BREAKER (ZONE 366) 82647 0034 & ON 01 HZ908 ANL-250 FUSE LIMITER (ZONE 368) 71400 0034 & ON 01 S1367X7-13 . TERMINAL 01 J1 MS27497E12F98S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F98P MS27497T8F98P CONNECTOR 96906 0034 & ON 01 JT105 MS27497T24F35SB CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT108 MS27497T24F35SB CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT116 MS27497T22F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT125 MS27497T24F4S CONNECTOR (ZONE 365) 96906 0034 & ON 01 8250315-1 . BACKSHELL 01 JT169 MS27497T16F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JT170 MS27497T20F35SA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT901 MS27497T20F39S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT902 MS27497T24F4S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT903 MS27497T20F39SA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT904 MS27497T20F39S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JT906 MS27497T18F32S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 JZ102 10-504934-001 CONNECTOR (ZONE 365) 77820 0034 & ON 01 3425-6600 . SOCKET, 50PIN 0.1" IDC 76381 01 JZ209 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 JZ215 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 JZ931 M39029/58-360 PIN - CONTACT (ZONE 365) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 KZ006 S3602-2 CONTACTOR (ZONE 368) 0034 & ON 01 KZ008 CONTACTOR (ZONE 368) RF KZ052 M83536/9-024 RELAY 2X920 0034 & ON 01 NZ102 7468185-5 PCB ASSEMBLY - PWR DIST (ZONE 365) 0034 & ON 01 NZ209 7468186-1 PCB ASSEMBLY - AUX PWR DIST (ZONE 366) 0034 & ON 01 NZ215 PCB ASSEMBLY - HYDRAULIC CONTROL RF P1 M55302/57A60Y-0 CONNECTOR 0034 & ON 01

HYDRAULIC SYSTEM

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT105 MS27484T24F35PB PLUG (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT108 MS27484T24F35PB PLUG (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT116 MS27484T22F35P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT125 MS27484T24F4P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PT169 MS27484T16F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PT170 MS27484T20F35PA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20-90 . BACKSHELL 01 PT901 MS27484T20F39P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PT902 MS27484T24F4P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT903 MS27484T20F39PA CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PT904 MS27484T20F39P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PT906 MS27484T18F32P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 PZ052 M39029/92-534 CONTACT 0034 & ON 01 JRS200300 . RELAY SOCKET 58982 01 PZ906 MS27484T10F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 PZ908 MS27484T10F35S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 PZ931 M39029/57-354 CONTACT - SOCKET (ZONE 365) 81590 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 RZ902 S2609-2 SHUNT ASSEMBLY (ZONE 368) 0034 & ON 01

52-00-01

EXTERNAL DOORS AIRPLANES 0034 & ON

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

PB002 JB002 JC134 PC134 PXM013 PXM017 JN026 JC102 P1 3 NC102 50002XXS9-22WH 1 50101XXS867-22WH 67 50107XXS96-22WH 6PROX POWER RH NOSE EXTERNAL DOORS MONITOR PCB SN004 B 20WH A RH NOSE FWD 20BL L 50002XXS9-22BL 2 50101XXS867-22BL 68 50107XXS96-22BL 49GND UPPER DOOR C 20 B 3 69 53RH NOSE DR SW (FWD_UPPER) SWITCH 50002XXS10-22 50101XXS868-22 50107XXS97-22 N.O. WITH TARGET AWAY OSC A PXM014

B 20WH C SN006 20BL D RH NOSE FWD LOWER DOOR C 20 E 50002XXS11-22 4 50101XXS869-22 70 50107XXS98-22 52RH NOSE DR SW (FWD_LWR) N.O. WITH SWITCH TARGET AWAY OSC A

PXM015

SN008 B 20WH F RH NOSE AFT 20BL G UPPER DOOR N.O. WITH C 20 H 50002XXS12-22 5 50101XXS870-22 80 50107XXS99-22 29RH NOSE DR SW (AFT_UPPER) SWITCH TARGET AWAY OSC

A PXM016

SN010 B 20WH J RH NOSE AFT 20BL K LOWER DOOR SWITCH C 20 M 50002XXS13-22 6 50101XXS871-22 81 50107XXS100-22 54RH NOSE DR SW (AFT_LWR) N.O. WITH TARGET AWAY OSC A PN028

OPEN GNCS12 SN012 5 RH NOSE MECH 4 50002XXP14-22 DOOR SWITCH 6 50002XXS15-22 7 50101XXS872-22 73 50107XXS101-22 51RH NOSE DR SW (PLUNGER 2) 2 50002XXS16-22 8 50101XXS873-22 74 50107XXS102-22 41RH NOSE DR SW (PLUNGER 1) 1 50002XXP17-22 9 REFER TO SHEET 4 3 CLOSED

PN027 PB001 JB001 OPEN SN013 2 50001XXS27-22 1 50101XXS874-22 75 50107XXS103-22 40LH NOSE DR SW (PLUNGER 1) LH NOSE MECH 1 50001XXP28-22 2 REFER TO SHEET 4 DOOR SWITCH 3 GNCB01

5 D 4 50001XXP29-22 6 50001XXS30-22 3 50101XXS875-22 76 50107XXS104-22 45LH NOSE DR SW (PLUNGER 2) CLOSED PXM017 JN025 PXM013 SN001 LH NOSE FWD B 50021XXS1-20WH A 50021XXS1-20BL L UPPER DOOR SWITCH C 50021XXS2-20 B 50001XXS31-22 4 50101XXS876-22 77 50107XXS105-22 47LH NOSE DR SW (FWD_UPPER) N.O. WITH TARGET AWAY OSC A

PXM014 SN005 B 50021XXS3-20WH C LH NOSE FWD 50021XXS3-20BL D LOWER DOOR SWITCH C 50021XXS4-20 E 50001XXS32-22 5 50101XXS877-22 78 50107XXS106-22 46LH NOSE DR SW (FWD_LWR) N.O. WITH TARGET AWAY OSC A

PXM015 SN009 B 50021XXS5-20WH F LH NOSE AFT 50021XXS5-20BL G UPPER DOOR N.O. WITH SWITCH C 50021XXS6-20 H 50001XXS33-22 6 50101XXS878-22 79 50107XXS107-22 50LH NOSE DR SW (AFT_UPPER) TARGET AWAY OSC

A 14PROX POWER LH NOSE

60GND 48LH NOSE DR SW (AFT_LWR) PXM016 SN011 B 50021XXS7-20WH J 50001XXS34-22WH 8 50101XXS879-22WH 71 50107XXS108-22WH LH NOSE AFT 50021XXS7-20BL K LOWER DOOR 50001XXS34-22BL 9 50101XXS879-22BL 72 50107XXS108-22BL SWITCH C 50021XXS8-20 M 50001XXS35-22 7 50101XXS880-22 82 50107XXS109-22 N.O. WITH TARGET AWAY OSC A 8205200-3F1

EXTERNAL DOORS Figure 03. (Sheet 1) Figure 03 Page 2 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

GNCB01 S3521-7 GROUND STUD KIT (ZONE 215) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 GNCS12 S3521-7 GROUND STUD KIT (ZONE 216) 0034 & ON 01 JB001 MS27474T22F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JB002 MS27474T18F35S CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 JC102 10-504934-001 CONNECTOR (ZONE 235) 77820 0034 & ON 01 JC134 MS27497T24F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JN025 MS27497E14F18S CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-14-90 . BACKSHELL 01 JN026 MS27497E14F18S CONNECTOR (ZONE 216) 96906 0034 & ON 01 S3627-14-90 . BACKSHELL 01 NC102 7468193-1 PCB ASSEMBLY - EXTD MONITOR (ZONE 235) 0034 & ON 01 P1 M55302/57A60Y-0 CONNECTOR 0034 & ON 01 PB001 MS27484T22F35P CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PB002 MS27484T18F35P CONNECTOR (ZONE 216) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 PC134 MS27484T24F35P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PN027 MS27484E8F35S CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-8-90 . BACKSHELL 96906 01 PN028 MS27484E8F35S CONNECTOR (ZONE 216) 96906 0034 & ON 01 S3627-8-90 . BACKSHELL 96906 01 PXM013 M39029/57-358 SOCKET CONTACT (ZONE 851) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PXM014 M39029/57-358 SOCKET CONTACT (ZONE 851) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PXM015 M39029/57-358 SOCKET CONTACT (ZONE 851) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PXM016 M39029/57-358 SOCKET CONTACT (ZONE 851) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PXM017 MS27484E14F18P CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-14 . BACKSHELL 96906 01 SN001 PROXIMITY SWITCH ASSY (ZONE 851) RF SN004 PROXIMITY SWITCH ASSY (ZONE 852) RF SN005 PROXIMITY SWITCH ASSY (ZONE 851) RF SN006 PROXIMITY SWITCH ASSY (ZONE 852) RF SN008 PROXIMITY SWITCH ASSY (ZONE 852) RF SN009 PROXIMITY SWITCH ASSY (ZONE 851) RF SN010 PROXIMITY SWITCH ASSY (ZONE 852) RF SN011 PROXIMITY SWITCH ASSY (ZONE 851) RF SN012 SWITCH (ZONE 216) RF SN013 SWITCH (ZONE 215) RF

PC085 J2 TOP HINGED STEP LIGHT CABIN DOOR 50171XXP1-22 1 RED

50171XXP2-22 2 BLK JC048 PC048 FC020 REFER OPEN DOOR LED ASSY CABIN THRESHOLD PC027 JC027 THRESHOLD CABIN DOOR JC074 P0004 FC010 50113XXS1-22 A 5 EXTERNAL OPEN A 50113XXS2-22 B 4 DOOR LED ASSY REFER TO 33-50-01 A REFER TO 33-50-01 F0001 D B REFER TO 33-50-01

REFER OPEN DOOR LED ASSY

JC077 P0004 FC011 50113XXS3-22 A 5 INTERNAL OPEN 50113XXS4-22 B 4 DOOR LED ASSY F0001 50171XXS3-22RD 50171XXS3-22OR REFER TO SHEET 3 V 50171XXS3-22BK V W 50171XXS3-22BL W 50171XXS3-22WH REFER CABIN PRESSURE LED ASSY 50171XXS3-22GN PC076 J0011 FC012 A 5 EXTERNAL PRESSURE 50113XXS5-22 B 4 LED ASSY SPARE T T SPARE F0002

REFER CABIN PRESSURE LED ASSY PC075 J0011 X 50113XXS6-22 FC013 X 50113XXS7-22 A 5 INTERNAL PRESSURE 50113XXS8-22 B 4 LED ASSY F0002

AC017 1NO 2NO P P 50113XXS9-22 50113XXS10-20 SC009 INNER HANDLE 50113XXP12-22 50113XXP13-20 PUSH BUTTON (MOM) AC028

REFER DOOR LOCK SOLENOID ASSY PC078 J0012 R R 50113XXS15-22 A WH1 WH1 W0001 WC003 DC002 DOOR LOCK 50171XXS4-22BK SOLENOID 50171XXS4-22BL WH2 WH2 S 50171XXS4-22RD S 50113XXP16-22 B 50171XXS4-22OR 50171XXS4-22WH 50171XXS4-22GN PC054

AC113 VW C C 50113XXS17-20BR 1 E E VW J J 50113XXS18-20BK 4 SC004 N.O. WITH OSC INNER HANDLE TARGET AWAY AC114 VW CLOSED SWITCH 3 50113XXS19-20BL (S3)

PC057

VW REFER TO SHEET 3 50113XXS20-20BR 1 SC006

VW INNER HANDLE N N 50113XXS21-20BK 4 OPEN SWITCH N.O. WITH TARGET AWAY OSC (S5)

VW 50113XXS22-20BL 3

PC055

VW 50113XXS23-20BR 1 SC008

VW OUTER PADDLE M M 50113XXS24-20BK 4 DOOR SWITCH N.O. WITH OSC (S7) TARGET AWAY

VW 50113XXS25-20BL 3

50171XXS5-22BK PC056

50171XXS5-22BL AC117 VW F 50171XXS5-22RD F 50113XXS26-20BR 1 H H 50171XXS5-22OR VW K 50171XXS5-22WH K 50113XXS27-20BK 4 50171XXS5-22GN SC005 N.O. WITH OSC VENT DOOR TARGET AWAY AC118 VW CLOSED SWITCH 3 50113XXS28-20BL (S4)

PC058

VW 50113XXS29-20BR 1 SC007

VW SECURING PAWL L L 50113XXS30-20BK 4 DOOR SWITCH (S6) N.O. WITH OSC TARGET AWAY VW 50113XXS31-20BL 3

8205200-3F2

EXTERNAL DOORS Figure 03. (Sheet 2) Figure 03 Page 4 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AC017 M81714/65-20-1 SPLICE (ZONE 812) 0A744 0034 & ON 01 AC028 M81714/65-20-1 SPLICE (ZONE 812) 0A744 0034 & ON 01 AC113 SPLICE RF AC114 SPLICE RF AC117 SPLICE RF AC118 SPLICE RF DC002 S3106-7 TRANSZORB ASSEMBLY 00779 0034 & ON 01 F0001 1841-1-5620 CONTACT 11139 0034 & ON 01 35844-007 . AMBER LED INDICATOR 81590 01 F0002 1841-1-5620 CONTACT 11139 0034 & ON 01 35844-006 . RED LED INDICATOR 81590 01 FC010 HA - OPEN DOOR LED RF FC011 HA - OPEN DOOR LED RF FC012 HA - CABIN PRESSURE LED RF FC013 HA - CABIN PRESSURE LED RF FC020 TOP HINGED STEP LIGHT RF J0011 M39029/58-360 PIN - CONTACT 0TRC3 0034 & ON 01 SJS830270 . RECEPTACLE 58982 01 J0012 M39029/58-360 PIN - CONTACT 0TRC3 0034 & ON 01 SJS830270 . RECEPTACLE 58982 01 J2 MS27497E20F39S CONNECTOR 96906 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27497T8F35P MS27497T8F35P CONNECTOR 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 JC027 MS27474T16F26P CONNECTOR (ZONE 812) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 JC048 MS27474E16F26S CONNECTOR (ZONE 141) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 JC074 M39029/58-360 PIN - CONTACT (ZONE 812) 0TRC3 0034 & ON 01 SJS830270 . RECEPTACLE 58982 01 JC077 M39029/58-360 PIN - CONTACT (ZONE 812) 0TRC3 0034 & ON 01 SJS830270 . RECEPTACLE 58982 01 P0004 M39029/57-354 CONTACT - SOCKET 81590 0034 & ON 01 SJS830250 . PLUG 58982 01 PC027 MS27484T16F26S CONNECTOR (ZONE 812) 96906 0034 & ON 01 06F2008S16N . ADAPTER 07418 01 222D232-25/225 . BOOT 06090 01 PC048 MS27484T16F26P CONNECTOR (ZONE 241) 96906 0034 & ON 01 06F2008S16N . ADAPTER 07418 01 222D232-25/225 . BOOT 06090 01 PC054 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 812) 61526 0034 & ON 01 PC055 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 812) 61526 0034 & ON 01 PC056 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 812) 61526 0034 & ON 01 PC057 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 812) 61526 0034 & ON 01 PC058 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 812) 61526 0034 & ON 01 PC075 M39029/57-354 CONTACT - SOCKET (ZONE 812) 81590 0034 & ON 01 PC076 M39029/57-354 CONTACT - SOCKET (ZONE 812) 81590 0034 & ON 01 SJS830250 . PLUG 58982 01

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PC078 M39029/57-354 CONTACT - SOCKET (ZONE 812) 81590 0034 & ON 01 SJS830250 . PLUG 58982 01 PC085 43020-0201 MOLEX PLUG (ZONE 812) 27264 0034 & ON 01 43031-0009 . MICRO-FIT PIN 27264 01 SC004 PROXIMITY SWITCH (ZONE 812) RF SC005 PROXIMITY SWITCH (ZONE 812) RF SC006 PROXIMITY SWITCH (ZONE 812) RF SC007 PROXIMITY SWITCH (ZONE 812) RF SC008 PROXIMITY SWITCH (ZONE 812) RF SC009 PUSHBUTTON SWITCH (ZONE 812) RF W0001 70R10461-2 ROTARY SOLENOID (ZONE 812) 55725 0034 & ON 01 WC003 HA - DOOR LOCK SOLENOID RF

NC103 NC101 UI410 CABIN DOOR MONITOR PCB CABIN DOOR CONTROL PCB GARMIN DATA CONCENTRATOR #1 INTERIORS DISCONNECT P1 JC103 JC101 P1 P411 PI410 JF039 PF039

CED MOTOR CURRENT (-) 33 50107XXS119-22BL 6CED MOTOR CURRENT (-) FWD DVDR DOOR OPEN 45 50101XXS1624-22 *B REFER TO INTERIORS NZ209 CED MOTOR CURRENT (+) 3 50107XXS119-22WH 5CED MOTOR CURRENT (+) 50101XXS1625-22 *C REFER TO INTERIORS AUX POWER DISTRIBUTION PCB

IN FRAME CMD 9 50107XXS120-22 11IN FRAME DOOR CLOSE CMD 10 50107XXS121-22 10DOOR CLOSE CMD JA026 PA026 PT918 JT918 JZ209 P1 DR CONTROL FAULT 54 50107XXS122-22 8DOOR CONTROL FAULT BACK EMF PWR IN 35 50107XXS123-22 15BACK EMF PWR UI302 45 50322XXS234-22 28 50316XXS723-22 40CABIN DOOR REQUEST GARMIN INTEGRATED AVIONICS #2 50107XXS124-22 17CED MONITOR PWR 50107XXS344-22 12 50107XXS345-22 3CANCEL CMD P605 PI306 INTERNAL DOOR CONTROL PANEL JC042 PC042 LAV DOOR STATUS IN 40 1 PUSH CANCEL TO OPEN 8 INT PNL LTS INPUT (GND) NC102 7 +28VDC EXTERNAL DOORS MONITOR PCB 6 CLOSE CMD OUTPUT 5 CANCEL CMD OUTPUT JC102 P1 4 OVERRIDE OUTPUT 3 GND CONTROL PCB POWER 2 50107XXS125-22 17CED MONITOR PWR 2 CHECK HANDLE INPUT

PC137 JC137

EXTERNAL DOOR CONTROL PANEL 50107XXS357-22 93 50102XXS347-22 50102XXS220-22 50102XXS218-22 50102XXP219-22 50102XXS217-22 PUSH CANCEL TO OPEN LT 34 50107XXS126-22 13 50102XXS213-22 50102XXP215-22 50102XXS216-22 JC043 PC043 INTERIOR PANEL LT 16 50107XXS127-22 23 50102XXS214-22 P1 CHECK PINS LT 31 50107XXS128-22 24 50102XXS221-22 2 4 CHECK DOOR PINS 5 LIGHT (AMBER) FC009

GCDS13 50102XXP222-22 3 2

DR OVERRIDE SW 51 50107XXS129-22 25 50102XXS223-22 4 1 OVERRIDE CLOSE 2 DR CANCEL SW 50 50107XXS130-22 26 50102XXS224-22 5 1 DR CLOSE SW 39 50107XXS131-22 27 50102XXS225-22 6 5 6 CANCEL

AC019 V W 22 1 REF SHT 4 7 V W REFRIG SW 40 50107XXS132-22 28 50102XXS226-22 8 22 2 AC020 DOOR OPEN

P1 4 REFRIGERATOR DOOR EXTERIOR PANEL LT 11 50107XXS133-22 29 50102XXS227-22 9 5 LIGHT (WHITE) FC008

PC052

AC054 VW PROX POWER 14 50107XXS134-22WH 30 50102XXS228-22WH 20BR 1 SC002 GND 59 31 FWD UPPER DOOR 50107XXS134-22BL 50102XXS228-22BL AC055 VW LH DR POS SW 23 50107XXS135-22 32 50102XXS229-22 20BK 4 POSITION SWITCH (S1) N.O. WITH OSC TARGET AWAY AC056 VW 20BL 3

PC053

AC057 VW PROX POWER 8 50107XXS136-22WH 33 50102XXS230-22WH 20BR 1 SC003 GND 60 34 AFT UPPER DOOR 50107XXS136-22BL 50102XXS230-22BL AC058 VW RH DR POS SW 25 50107XXS137-22 35 50102XXS231-22 20BK 4 POSITION SWITCH (S2) N.O. WITH OSC TARGET AWAY AC059 VW 20BL 3

JC048 PC048

PROX POWER 22 50107XXS138-22WH 36 50102XXS232-22WH C 50107XXS138-22BL 37 50102XXS232-22BL E GND 49 50107XXS139-22BL 38 50102XXS233-22BL H PROX POWER 6 50107XXS139-22WH 39 50102XXS233-22WH F

INNER HANDLE CLOSED 43 50107XXS140-22 40 50102XXS234-22 J VENT DR CLOSED 44 50107XXS141-22 41 50102XXS235-22 K

INNER HANDLE OPEN 45 50107XXS142-22 42 50102XXS236-22 N REFER TO SHEET 2 SECURING PAWL SWITCH 46 50107XXS143-22 43 50102XXS237-22 L OUTER PADDLE CLOSED 47 50107XXS144-22 44 50102XXS238-22 M INNER HANDLE PUSH BUTTON 48 50107XXS145-22 45 50102XXS239-22 P SECURING PAWL SOL 24 50107XXS146-22 46 50102XXS240-22 R

DR WARN LT PWR 32 50107XXS147-22 47 50102XXS241-22 W PRESS WARN LT (DRIVE/TEST) 19 50107XXS148-22 48 50102XXS242-22 X CAB DR OPEN LT (DRIVE/TEST) 15 50107XXS149-22 49 50102XXS243-22 V BCK BCK GCDS13 50102XXP244-22 S 8205200-3F3

GCSS01

EXTERNAL DOORS Figure 03. (Sheet 3) Figure 03 Page 7 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

AC019 SPLICE RF AC020 SPLICE RF AC054 SPLICE RF AC055 SPLICE RF AC056 SPLICE RF AC057 SPLICE RF AC058 SPLICE RF AC059 SPLICE RF FC008 1841-1-5620 CONTACT (ZONE 241) 11139 0034 & ON 01 35844-010 . WHITE LED INDICATOR 81590 01 FC009 35844-007 AMBER LED INDICATOR (ZONE 241) 81590 0034 & ON 01 1841-1-5620 . CONTACT 11139 01 GCDS13 S3521-8 GROUND STUD KIT (ZONE 241) 0034 & ON 01 GCSS01 GROUND STUD KIT (ZONE 235) RF JA026 D38999/24FH35PN RECEPTACLE (ZONE 282) 0034 & ON 01 S3627-23 . BACKSHELL 01 JC042 MS27497E10F35S CONNECTOR (ZONE 241) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 JC043 MS27474T10F35S CONNECTOR (ZONE 241) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 JC048 MS27474E16F26S CONNECTOR (ZONE 141) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 JC101 DCA21WA4SA197F0 RECEPTACLE (ZONE 235) 71468 0034 & ON 01 JC102 10-504934-001 CONNECTOR (ZONE 235) 77820 0034 & ON 01 JC103 10-504934-001 CONNECTOR (ZONE 235) 77820 0034 & ON 01 JC137 MS27497T24F35SB CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JF039 MS27497T22F53S CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT918 MS27497T18F35S CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 JZ209 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 NC101 7468102-11 CED CONTROL PCB ASSEMBLY (ZONE 235) 0034 & ON 01 NC102 7468193-1 PCB ASSEMBLY - EXTD MONITOR (ZONE 235) 0034 & ON 01 NC103 7468194-1 CED MONITOR PCB ASSEMBLY (ZONE 235) 0034 & ON 01 NZ209 7468186-1 PCB ASSEMBLY - AUX PWR DIST (ZONE 366) 0034 & ON 01 P1 M55302/57A60Y-0 CONNECTOR 0034 & ON 01 P411 CONNECTOR RF P605 SWITCH - R ENG FIRE RF PA026 D38999/26FH35SN PLUG (ZONE 368) 0034 & ON 01 S3627-23 . BACKSHELL 01 PC042 INTERNAL DOOR CONTROL PANEL RF PC043 MS27484E10F35P CONNECTOR (ZONE 241) 96906 0034 & ON 01 PC048 MS27484T16F26P CONNECTOR (ZONE 241) 96906 0034 & ON 01 06F2008S16N . ADAPTER 07418 01 222D232-25/225 . BOOT 06090 01 PC052 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 241) 61526 0034 & ON 01 PC053 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 241) 61526 0034 & ON 01

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PC137 MS27484T24F35PB PLUG (ZONE 235) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 PF039 MS27484T22F53P CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PI306 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PT918 MS27484T18F35P CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 SC002 PROXIMITY SWITCH (ZONE 241) RF SC003 PROXIMITY SWITCH (ZONE 241) RF UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF UI410 GSD 41 (ZONE 225) RF

NC101 PC135 JC135 RH EMER J-BOX CABIN DOOR CONTROL PCB P1 JC101 PC095 HZ068 MC003 CABIN DOOR MOTOR MOTOR +28VDC A1 50107XXS204-12 A 50102XXS272-12 A 2 1 CABIN ENTRY REFER TO 24-60-01 MOTOR RETURN A4 50107XXS205-12 B 50102XXS273-12 B DOOR MOTOR 20 BCK GCSS01 BCK JA036 PA036 MOTOR GND A2 50107XXP206-12 C 50102XXP274-12 GCDS25 CABIN TAIL 50318XXP14-12 XZ004 MOTOR +28VDC A3 50107XXS207-12 D 50102XXS275-12 A 50322XXS89-12 2 1 50318XXS15-12

A1 PC137 JC137 JA026 PA026 PT904 JT904 A2 CABIN TAIL WH2 X2 READY 9 50107XXS208-22 54 50102XXS276-22 49 50322XXS90-22 N 50318XXS16-22 X1 M 50318XXS17-22 WH1 PCB PWR GND 1 50107XXP209-22 53 50102XXP277-22 B KZ026 DZ026 +28VDC (NORM BUS) 16 50107XXP210-22 GCDB05

PC993 JC993 LH CB PANEL NC103 P1 JC103 CABIN DOOR SYS CABIN DOOR MONITOR PCB +28VDC (NORM BUS) 37 50107XXP211-22 58 50102XXP278-22 2 REFER TO 24-61-01 5

POWER RELAY (+) 26 50107XXS213-22 59 50102XXS279-22 50 50322XXS91-22

GND 1GND 50107XXP214-22 60 50102XXP280-22 C GND 13 61 50102XXP281-22 D HZ066 GCDB05 CABIN DOOR

2 1 +28VDC (HOT BATT) 36 50107XXP215-22 62 50102XXP283-22 51 50322XXP92-22 U 50318XXP81-22 REFER TO 24-60-01 JC043 PC043 5 50102XXP282-22 REFER TO SHEET 3 7 REFER TO SHEET 3

JA021 PA021 CABIN TAIL 50107XXP217-22 50107XXP367-22 50107XXP216-22 50107XXP366-22

WOW 53 50107XXS224-22 95 50102XXS330-22 32

DC032 PC132 JC132 JB002 PB002 CABIN RH NOSE BLK WHT 1 50101XXP1303-22 9 REFER TO SHEET 1

BLK WHT DC034

JB001 PB001 DC035 CABIN LH NOSE BLK WHT UT402 GSD 41HE (#3) 700 50107XXP219-22 50107XXP218-22 50107XXP212-22 2 50101XXP1304-22 2 REFER TO SHEET 1 BLK WHT JA034 PA034 DC033 CABIN TAIL PT414 P412 CHECK DOORS (WHITE) 5 50107XXS220-22 3 50101XXS1305-22 78 50319XXS726-22 37CHECK DOORS (WHITE) DISC IN DIFF PRESS DISCRETE 57 50107XXS245-22 30 50101XXS1322-22 35

UT404 UI410 GARMIN ENGINE / AIRFRAME I/O #3 GARMIN DATA CONCENTRATOR #1 PI410 P411 PT408 P71002

CABIN DOOR OPEN (AMBER) 7 50107XXS221-22 4 50101XXS1306-22 44CBN DOOR OPEN 50319XXS799-22 123 DIFF PRESS OUT 5 50101XXS1307-22 18L NS DR OP FWD 2 6 50101XXS1308-22 19R NS DR OP FWD 1

7 50101XXS1309-22 20BAGGAGE DOOR OPEN 50321XXS104-22 AS > 80KTS 52 50107XXS222-22 8 CHECK DOORS (AMBER) 4 50107XXS223-22 UT403 GARMIN ENGINE / AIRFRAME I/O #2 JA027 PA027 CABIN TAIL PT407 P71002

NC102 9 50101XXS1310-22 78 50319XXS727-22 38TAILCONE DOOR OPEN EXTERNAL DOORS MONITOR PCB P1 JC102 UI411 GARMIN ENGINE / AIRFRAME I/O #1 +28VDC (HOT BATT) 36 LH J-BOX +28VDC (NORM BUS) 37 PI414 P71003 PT115 JT115 PZ141 GND 1GND GND 13 50101XXS1311-22 44 CABIN DOOR LOCK OUT 19 50315XXS551-22 1 JA025 PA025 REFER TO LH NOSE DR OPEN 7 50107XXS225-22 PC136 JC136 CABIN TAIL PT117 JT117 32-60-01 RH NOSE DR OPEN 5 50107XXS226-22 PI413 P71002 AFT BAGGAGE DR OPEN 15 50107XXS227-22 72 50323XXS242-22 66 50315XXS275-22 2 TAIL ACCESS DR OPEN 10 50107XXS228-22 71 50103XXS370-22 12 CHECK DOORS (CBN) 72 50103XXS371-22 23 CHECK DOORS (EXT) 73 50103XXS372-22 14 EMER EXIT OPEN IN (DISC IN 14)

CHECK DOORS (AMBER) 4 50107XXS229-22 BCK BCK EMER EXIT DR OPEN 9 50107XXS230-22

GCSS01

GIA 55 50107XXS231-22 74 50103XXS373-22 8205200-3F4

EXTERNAL DOORS Figure 03. (Sheet 4) Figure 03 Page 10 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

DC032 S3106-4 DIODE ASSEMBLY 0034 & ON 01 DC033 S3106-4 DIODE ASSEMBLY 0034 & ON 01 DC034 S3106-4 DIODE ASSEMBLY 0034 & ON 01 DC035 S3106-4 DIODE ASSEMBLY 0034 & ON 01 DZ026 S3106-7 TRANSZORB ASSEMBLY 00779 0034 & ON 01 GCDB05 S3521-7 GROUND STUD KIT (ZONE 131) 0034 & ON 01 S2800-39 . CONNECTOR KIT 28198 01 FC120N2 . CRIMP CONTACT 28198 01 S2526-4 . GROUNDING CONNECTOR 01 GCDS25 S3521-8 GROUND STUD KIT (ZONE 241) 0034 & ON 01 GCSS01 GROUND STUD KIT (ZONE 235) RF HZ066 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0034 & ON 01 HZ068 S2899-20.0 CIRCUIT BREAKER (ZONE 368) 0034 & ON 01 JA021 D38999/24FH35PA CONNECTOR (ZONE 281) 0034 & ON 01 S3627-23 . BACKSHELL 01 JA025 MS27474T22F35P CONNECTOR (ZONE 281) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JA026 D38999/24FH35PN RECEPTACLE (ZONE 282) 0034 & ON 01 S3627-23 . BACKSHELL 01 JA027 D38999/24FJ35PA CONNECTOR (ZONE 281) 0034 & ON 01 S3627-25 . BACKSHELL 01 JA034 D38999/24FJ35PB CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JA036 MS3454L12-5P CONNECTOR (ZONE 282) 96906 0034 & ON 01 S3744-12 . BACKSHELL 01 JB001 MS27474T22F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JB002 MS27474T18F35S CONNECTOR (ZONE 236) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 JC043 MS27474T10F35S CONNECTOR (ZONE 241) 96906 0034 & ON 01 S3627-10-90 . BACKSHELL 01 JC101 DCA21WA4SA197F0 RECEPTACLE (ZONE 235) 71468 0034 & ON 01 JC102 10-504934-001 CONNECTOR (ZONE 235) 77820 0034 & ON 01 JC103 10-504934-001 CONNECTOR (ZONE 235) 77820 0034 & ON 01 JC132 MS27497T16F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JC135 MS27497T16F6S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 JC136 MS27497T24F35SA CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24-45 . BACKSHELL 01 JC137 MS27497T24F35SB CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JC993 MS27497T12F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 JT115 MS27497T22F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT117 MS27497T24F35SA CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT904 MS27497T20F39S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 Figure 03 Page 11 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

KZ026 MS24166-D1 RELAY (ZONE 368) 96906 0034 & ON 01 MC003 CABIN ENTRY DOOR MOTOR RF NC101 7468102-11 CED CONTROL PCB ASSEMBLY (ZONE 235) 0034 & ON 01 NC102 7468193-1 PCB ASSEMBLY - EXTD MONITOR (ZONE 235) 0034 & ON 01 NC103 7468194-1 CED MONITOR PCB ASSEMBLY (ZONE 235) 0034 & ON 01 P1 M55302/57A60Y-0 CONNECTOR 0034 & ON 01 P411 CONNECTOR RF P412 CONNECTOR RF P71002 CONNECTOR RF P71003 CONNECTOR RF PA021 D38999/26FH35SA PLUG (ZONE 367) 0034 & ON 01 S3627-23 . BACKSHELL 01 PA025 MS27484T22F35S CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PA026 D38999/26FH35SN PLUG (ZONE 368) 0034 & ON 01 S3627-23 . BACKSHELL 01 PA027 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 367) 0034 & ON 01 S3627-25 . BACKSHELL 01 PA034 D38999/26FJ35SB STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PA036 MS3459L125S PLUG (ZONE 368) 96906 0034 & ON 01 S3744-12 . BACKSHELL 01 PB001 MS27484T22F35P CONNECTOR (ZONE 215) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PB002 MS27484T18F35P CONNECTOR (ZONE 216) 96906 0034 & ON 01 S3627-18 . BACKSHELL 01 PC043 MS27484E10F35P CONNECTOR (ZONE 241) 96906 0034 & ON 01 PC095 MS3456W16-11S CONNECTOR (ZONE 241) 96906 0034 & ON 01 M85049/51S-16W . BACKSHELL 01 PC132 MS27484T16F35P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PC135 MS27484T16F6P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16-90 . BACKSHELL 01 PC136 MS27484T24F35PA CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PC137 MS27484T24F35PB PLUG (ZONE 235) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 PC993 MS27484T12F35P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-12 . BACKSHELL 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PI413 D38999/26MJ35SB PLUG (ZONE 225) 0034 & ON 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PI414 D38999/26MJ35SD PLUG (ZONE 225) 0034 & ON 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01 PT115 MS27484T22F35P CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 PT117 MS27484T24F35PA CONNECTOR (ZONE 365) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT407 D38999/26MJ35SB PLUG (ZONE 365) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT408 D38999/26MJ35SB PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 M85049/38S25N . BACKSHELL 01 PT414 D38999/26FG35SN PLUG (ZONE 366) 0034 & ON 01 FOR SPARES ORDER (MUST REPLACE WITH): MS27488-22-2 MS27488-22-2 PLUG 96906 0034 & ON 01 S3627-21 . BACKSHELL 01 PT904 MS27484T20F39P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-20 . BACKSHELL 01 PZ141 LMD-4001-S CONNECTOR (ZONE 365) 49367 0034 & ON 01 LMD-7103-P . DIODE MODULE 49367 01 LMD-4120-96LD . SOCKET 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 UI410 GSD 41 (ZONE 225) RF UI411 GEA 7100 (ZONE 225) RF UT402 011-01457-02 GSD 41H (ZONE 366) 0TRC3 0034 & ON 01 UT403 011-02635-01 GEA 7100 (ZONE 365) 0TRC3 0034 & ON 01 UT404 011-02635-01 GEA 7100 (ZONE 366) 0TRC3 0034 & ON 01 XZ004 TERMINAL JUNCTION BLOCK (ZONE 368) RF

UI410 GARMIN DATA CONCENTRATOR #1 50101XXP1821-22 RH J-BOX PC040 JC040 JF040 PF040 FWD DIVIDER P411 PI410 JA034 PA034 PT108 JT108 HZ233 A 2 CABIN DIV DOOR OPT 54 50101XXS1854-22 E A 50101XXP1820-22 44 50319XXP1395-22 8 50316XXP772-22 REFER TO 24-60-01 GCDS19 50101XXP1823-22 B REFER TO 5 INTERIORSREFER TO INTERIORS B 50101XXP1822-22 GFDS02 50101XXS1855-22 C C UI411 GARMIN ENGINE/AIRFRAME I/O #1 50101XXS1856-22 P71003 PI414 PC136 JC136 PF002 JF002 SF002 CABIN DIV OPEN COMMAND 7 VW 1 80 50103XXS379-22 E 50190XXS4-22 22RD LAVATORY / BAGGAGE DOOR VW GFCS16 50103XXP709-22 F 50190XXP5-22 22RD 2 SWITCH NC102 EXTERNAL DOORS MONITOR PCB

P1 JC102 PF003 SF001 PROX POWER EMER EXIT 32 50107XXS239-22WH 67 50103XXS380-22WH 20 B 20OR EMERGENCY EXIT GND 59 50107XXS239-22BL 68 50103XXS380-22BL DOOR SWITCH EMER EXIT DR SW 57 50107XXS240-22 69 50103XXS381-22 20 C 20WH N.O. WITH OSC TARGET AWAY 20 A 20BL

DC017 PC017 REFER TO 33-30-01 BLK WHT PROX POWER AFT BAGGAGE 22 50107XXS235-22WH 77 50103XXS374-22WH 20 B 20OR SC017 GND 58 50107XXS235-22BL 78 50103XXS374-22BL BAGGAGE AFT BAGGAGE AFT LATCH 43 50107XXS236-22 79 50103XXS375-22 20 C 20WH DOOR SWITCH REFER TO 33-30-01 N.O. WITH OSC TARGET AWAY 20 A 20BL

PC016

50103XXS376-22WH 20 B 20OR SC016 50103XXS376-22BL BAGGAGE FWD BAGGAGE FWD LATCH 23 50107XXS238-22 75 50103XXS377-22 20 C 20WH DOOR SWITCH N.O. WITH OSC TARGET AWAY 20 A 20BL

UI302

50107XXS234-22 GARMIN INTEGRATED AVIONICS #2 PC132 JC132 PI306 P605

14 50101XXP1316-22 46INT BAGG DOOR STATUS IN

JA027 PA027 PY173 JY173 PY046

VW PROX POWER TAILCONE 31 50107XXS241-22WH 11 50101XXS1314-22WH 66 50319XXS743-22WH 79 50602XXS11-22WH 20BR 1 SY004 GND 28 12 67 78 TAILCONE ACCESS 50107XXS241-22BL 50101XXS1314-22BL 50319XXS743-22BL 50602XXS11-22BL VW TAILCONE PROX SWITCH 30 50107XXS242-22 13 50101XXS1315-22 68 50319XXS744-22 77 50602XXS12-22 20BK 4 DOOR SWITCH N.O. WITH OSC TARGET AWAY KZ038 VW TAILCONE RH EMER J-BOX 20BL 3 LIGHTS RELAY J1 PZ038

B3 JT020 P1 B2 AFT LTS FT007 AFT B1 HZ006 GTDS24 50302XXP43-22 2 TAILCONE A3 2 1 50302XXS40-22 1 MAINT LT A2 REFER TO 33-30-01 REFER TO 24-60-01 5 A1 50318XXS19-22 GTDS14 JT018 P1 FT006 X1 50318XXP20-22 JT902 PT902 JT146 PT146 50302XXP44-22 2 MID TAILCONE WH1 50302XXS41-22 1 MAINT LT X2 U 50319XXS753-22 1 DZ056 JT010 P1 FT005 FWD TAILCONE WH2 50302XXS42-22 1 MAINT LT PT902 JT902 GTDS10 50302XXP45-22 2

T 50318XXS21-22 SERVICE LIGHTS JT149 PT149 HZ070 PT057 JT057 ST012 TAILCONE MAINT 1 2 A1 A2 LIGHT SW REFER TO 24-60-01 V 1 B 5 50318XXP79-22 50319XXP754-22 50301XXP61-22 50327XXP4-22 REFER TO 33-30-01

2 50301XXS62-22 C 50327XXS5-22 RH J-BOX

NZ214 AUX POWER DISTRIBUTION PCB

50319XXS755-22 PT114 JT114 JZ209 P1 JA027 PA027 73 50316XXS269-22 29SB - TAILCONE MAINT LIGHT TAIL ACCESS DR LT 26 50107XXS243-22 15 50101XXS1317-22 79 50319XXS756-22 74 50316XXS270-22 58SB - TAILCONE DOOR

TAIL ACCESS DR LT SW 42 50107XXS244-22 16 50101XXS1318-22 80

8205200-3F5 50319XXS757-22

EXTERNAL DOORS Figure 03. (Sheet 5) Figure 03 Page 14 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

DC017 S3106-4 DIODE ASSEMBLY 0034 & ON 01 DZ056 S3106-7 TRANSZORB ASSEMBLY 00779 0034 & ON 01 FT005 OWL100-04 LED LIGHT ASSEMBLY (ZONE 365) 0GZF3 0034 & ON 01 FT006 OWL100-04 LED LIGHT ASSEMBLY (ZONE 366) 0GZF3 0034 & ON 01 FT007 OWL100-04 LED LIGHT ASSEMBLY (ZONE 366) 0GZF3 0034 & ON 01 GCDS19 S3521-7 GROUND STUD KIT (ZONE 131) 0034 & ON 01 GFCS16 S3521-8 GROUND STUD KIT (ZONE 176) 0034 & ON 01 GFDS02 S3521-7 GROUND STUD KIT (ZONE 236) 0034 & ON 01 GTDS10 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTDS14 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 GTDS24 S3521-8 GROUND STUD KIT (ZONE 366) 0034 & ON 01 HZ006 S2899-5.0 CIRCUIT BREAKER (ZONE 368) 82647 0034 & ON 01 HZ233 S2899-5.0 CIRCUIT BREAKER 82647 0034 & ON 01 J1 CONNECTOR RF JA027 D38999/24FJ35PA CONNECTOR (ZONE 281) 0034 & ON 01 S3627-25 . BACKSHELL 01 JA034 D38999/24FJ35PB CONNECTOR (ZONE 282) 0034 & ON 01 S3627-25 . BACKSHELL 01 JC040 SJS830200 PLUG - 8 PIN 58982 0034 & ON 01 M39029/58-360 . CONTACT PIN 0TRC3 01 JC102 10-504934-001 CONNECTOR (ZONE 235) 77820 0034 & ON 01 JC132 MS27497T16F35S CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 JC136 MS27497T24F35SA CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24-45 . BACKSHELL 01 JF002 M39029/58-360 PIN - CONTACT (ZONE 276) 0TRC3 0034 & ON 01 SJS830200 . 8 PIN PLUG 58982 01 JF040 SJS830200 PLUG - 8 PIN 58982 0034 & ON 01 M39029/58-360 . CONTACT PIN 0TRC3 01 JT010 S1636-1 SOCKET (ZONE 365) 0034 & ON 01 S2035-2 . HOUSING 01 JT018 S1636-1 SOCKET (ZONE 366) 0034 & ON 01 S2035-2 . HOUSING 01 JT020 S1636-1 SOCKET (ZONE 366) 0034 & ON 01 S2035-2 . HOUSING 01 JT057 M39029/58-360 PIN - CONTACT (ZONE 367) 0TRC3 0034 & ON 01 SJS830201 . RECEPTACLE 58982 01 JT108 MS27497T24F35SB CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT114 MS27497T24F35SA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24-90 . BACKSHELL 01 JT146 MS27497T24F35SA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JT149 MS27497T22F35S CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01 JT902 MS27497T24F4S CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 JY173 MS27497T20F35S CONNECTOR (ZONE 317) 96906 0034 & ON 01 S3627-20-90 . BACKSHELL 01 Figure 03 Page 15 52-00-01 ICA-700-42-00001 ©TEXTRON AVIATION INC. Sep 21/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

JZ209 10-504934-001 CONNECTOR (ZONE 366) 77820 0034 & ON 01 KZ038 M83536/9-024 RELAY (ZONE 368) 2X920 0034 & ON 01 NC102 7468193-1 PCB ASSEMBLY - EXTD MONITOR (ZONE 235) 0034 & ON 01 NZ214 7468171-8 PCB ASSEMBLY - WOW DIST (ZONE 366) 0034 & ON 01 P1 CONNECTOR RF P411 CONNECTOR RF P605 SWITCH - R ENG FIRE RF P71003 CONNECTOR RF PA027 D38999/26FJ35SA STRAIGHT PLUG GROUNDED (ZONE 367) 0034 & ON 01 S3627-25 . BACKSHELL 01 PA034 D38999/26FJ35SB STRAIGHT PLUG GROUNDED (ZONE 368) 0034 & ON 01 S3627-25 . BACKSHELL 01 PC016 M39029/57-358 SOCKET CONTACT (ZONE 281) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PC017 M39029/57-358 SOCKET CONTACT (ZONE 281) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PC040 SJS830100 PLUG - 8 PIN 58982 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PC132 MS27484T16F35P CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-16 . BACKSHELL 01 PC136 MS27484T24F35PA CONNECTOR (ZONE 235) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PF002 M39029/58-360 PIN - CONTACT (ZONE 276) 0TRC3 0034 & ON 01 SJS830100 . 8 PIN PLUG 58982 01 PF003 M39029/57-358 SOCKET CONTACT (ZONE 276) 58982 0034 & ON 01 SJS840340 . 2 PIN PLUG 58982 01 PF040 SJS830100 PLUG - 8 PIN 58982 0034 & ON 01 M39029/57-354 . SOCKET CONTACT 81590 01 PI306 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 PI410 011-01169-01 CONNECTOR (ZONE 225) 0TRC3 0034 & ON 01 011-00796-01 . BACKPLATE 0TRC3 01 011-00950-04 . BACKSHELL ASSEMBLY 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01 330-00185-78 . PLUG 0TRC3 01 MS35206-242 . SCREW 72914 01 M23053/5-103-9 . SLEEVING 01 PI414 D38999/26MJ35SD PLUG (ZONE 225) 0034 & ON 01 M85049/39S25N . 90 DEGREE BACKSHELL 01 MS27488-22-2 . PLUG 96906 01 PT057 M39029/57-354 CONTACT - SOCKET (ZONE 367) 81590 0034 & ON 01 SJS830101 . 8 PIN PLUG 58982 01 PT108 MS27484T24F35PB PLUG (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT114 MS27484T24F35PA CONNECTOR (ZONE 366) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT146 MS27484T24F35PA CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PT149 MS27484T22F35P CONNECTOR (ZONE 367) 96906 0034 & ON 01 S3627-22 . BACKSHELL 01

EXTERNAL DOORS

AIRPLANES 0034 & ON

UNITS NOMENCLATURE PER REF DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

PT902 MS27484T24F4P CONNECTOR (ZONE 368) 96906 0034 & ON 01 S3627-24 . BACKSHELL 01 PY046 RKV4T-2/S90 PROX SWITCH CORD SET (ZONE 323) 61526 0034 & ON 01 PY173 MS27484T20F35P CONNECTOR (ZONE 317) 96906 0034 & ON 01 S3627-20-90 . BACKSHELL 01 PZ038 JRS200300 RELAY SOCKET (ZONE 368) 58982 0034 & ON 01 M39029/92-534 . CONTACT 01 SC016 PROXIMITY SWITCH ASSY (ZONE 281) RF SC017 PROXIMITY SWITCH ASSY (ZONE 281) RF SF001 PROXIMITY SWITCH ASSY RF SF002 SWITCH SENSOR RF ST012 MS35058-22 SWITCH (ZONE 367) 96906 0034 & ON 01 SY004 TAILCONE ACCESS DOOR SWITCH (ZONE 323) RF UI302 GARMIN INTEGRATED AVIONICS (ZONE 225) RF UI410 GSD 41 (ZONE 225) RF UI411 GEA 7100 (ZONE 225) RF