TEXTRON AVIATION INC. DIVISION WICHITA, KANSAS 67277

EASA PITOT PROBE OPTION ICA Supplement

MODEL NO: 700

SUPPLEMENT NO: ICA-700-34-00001 SUPPLEMENT DATE: 11/24/2020

© TEXTRON AVIATION INC. Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

REVISIONS

ICA-700-34-00001 Rev: - Date: 11/24/2020 ICA Summary Pages 1-6 Manuals Affected Description Title Model 700 Maintenance 06-40-00 pages Access Plates and Panels Identification - Description Manual 1-53 and Operation 34-10-00 pages Pitot-Static System - Description and Operation 1-4 34-10-07 pages EASA Pitot Probe - Removal/Installation 401-403 34-15-00 pages Standby Instrument System - Description and Operation 1-4 34-15-07 pages EASA Standby Pitot Probe - Removal/Installation 401-403 • These ATA's contain the Instructions for Continued Airworthiness for the addition of the EASA pitot probe option and the EASA standby pitot probe option. Appendix A: Illustrated Parts Refer to Appendix A, Table 1 Catalog Appendix B: Wiring Diagram 30-31-01 EASA Pitot Probe Figure 01 pages 1-3 Manual

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. • 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.

Page 1 of 6 Nov 24/2020 © TEXTRON AVIATION INC. ICA-700-34-00001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

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:

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.

Page 2 of 6 Nov 24/2020 © TEXTRON AVIATION INC. ICA-700-34-00001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

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.

Page 3 of 6 Nov 24/2020 © TEXTRON AVIATION INC. ICA-700-34-00001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

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 EASA PITOT PROBES 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 0036 and On

3. Complete ICA Documents A. The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the EASA PITOT PROBE OPTION on the Cessna Model 700. All items must be available to the operator at initial delivery. (1) Model 700 Maintenance Manual (2) Model 700 Wiring Diagram Manual

4. System Components A. Refer to Appendix B: Wiring Diagram Manual

Page 4 of 6 Nov 24/2020 © TEXTRON AVIATION INC. ICA-700-34-00001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 700 Maintenance Manual A. Chapter 6, Dimensions and Areas (1) Refer to 06-40-00, Access Plates and Panels Identification- Description and Operation B. Chapter 34, Navigation (1) Refer to 34-10-00, Pitot-Static System - Description and Operation (2) Refer to 34-10-07, EASA Pitot Probe - Removal/Installation (3) Refer to 34-15-00, Standby Instrument System - Description and Operation (4) Refer to 34-15-07, EASA Standby Pitot Probe - Removal/Installation

2. Model 700 Wiring Diagram Manual Supplement, Appendix B A. Chapter 30, Ice and Rain Protection (1) Refer to 30-31-01, EASA Pitot Probe, Figure 01, pages 1-3

Page 5 of 6 Nov 24/2020 © TEXTRON AVIATION INC. ICA-700-34-00001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

1. Continuous Inspection Program A. This ICA Supplement does not affect the current inspection program.

2. Airworthiness Limitations A. Cessna Aircraft Company Model 700 Airworthiness Limitations Manual contains the system and 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 no new (or additional) airworthiness limitations associated with this equipment and/or installation.

Page 6 of 6 Nov 24/2020 © TEXTRON AVIATION INC. ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

ACCESS PLATES AND PANELS IDENTIFICATION - DESCRIPTION AND OPERATION

1. General A. All the access plates, panels, and doors are identified by using the airplane zoning number plus one or two suffix letters. The first suffix letter is the primary identifier. The primary identifier identifies the plate, panel, or door in a logical sequence, that is, inboard, outboard, forward, or aft, starting with the letter "A" within each zone. B. The second suffix letter identifies the plate, panel, or door in its relation to the airplane such as top, bottom, left, right, or internal.

C. Remove and install access plates, panels, and doors in accordance with the applicable chapter. Refer to Nose Wheel Well Access Panels Figure 1, Cockpit Floorboard Access Panels Figure 2, Cockpit Side Console/Center Pedestal Access Panels Figure 3, Cabin Floorboard Access Panels Figure 4, Baggage Compartment Access Panels Figure 5, Access Panels Figure 6 Pylon Access Panels Figure 7, and Thrust Reverser Access Panels Figure 8, Vertical Access Panels Figure 9, Fuel Access Panels Figure 10, Access Panels Figure 11, Wing Access Panels Figure 12, Horizontal Stabilizer Access Panels Figure 13, Stinger Access Panels Figure 14, Main Wheel Well Access Panels Figure 15, and Winglet Access Panels Figure 16.

Table 1. Nose Wheel Well Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 1) 213AZ Left Pitot Probe (TN001), MAINTENANCE MIC Jack (JN501), MAINTENANCE AUDIO Jack (JN502), Oxygen Pressure Transducer Line Assembly, Splices (AN001, AN003), Electrical Connectors (PN001, PN503, JN502, JN501, JN503, PN015, P0020 NOTE 1) 214AZ Right Pitot Probe (TN002), DME 1 Antenna (YN802), Electrical Connector (PN838, P0020 NOTE 1), Splices (AN002, AN004) 214BZ Airplane Structure

NOTE 1: Installed with the optional EASA pitot probes.

6-40-00 Page 1 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 2. Cockpit Floorboard Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 2) 131AT Wire Bundles, Nosewheel Steering Control Cable, Bob Weight 131ATC Nosewheel Steering Control Cables, Nosewheel Steering Pulleys, Wire Bundles 131BT Pitch Servo Cable, Roll Disconnect Position Sensors (UC325 Forward and UC326 Aft), Roll Disconnect Cable, Roll Disconnect Bell Crank, Roll Control Cables, Control Column, Forward Cabin Roll Spoiler Control Cable, Nosewheel Steering Control Cable, Power Steering Control Unit Control Cable, Nosewheel Steering Control Assembly, Wire Bundles, Torque Tube, Spoiler Disconnect Sector, Pulleys, Roll Feel Bungee, Electrical Connectors (JC138, JC139, JC325, JC326, JC327, JC328, PXM025, PXM026) Ground (GCDB01, GDCB05) 131BTC Nosewheel Steering Control Cables, Nosewheel Steering Control Assembly, Nosewheel Steering Pulleys, Wire Bundles 131CT Wire Bundles, Cockpit Sector, Pitch Servo Gearbox, Pitch Servo Cable, Cabin Elevator Control Cables, Roll Spoiler Control Cables, Emergency Gear Release Cable, Pulleys, Roll Feel Bungee, Cockpit Air Duct 131CTC Wire Bundles, Grounds (GCDS01, GCDS03), Control Lock Proximity Switch (SF019), Roll Servo Cable, Autopilot Roll Servo Actuator (UC312), Autopilot Pitch Servo Actuator (UC311), Roll Disconnect Cable, Pitch Disconnect Cable, Pulleys, Emergency/Parking Brake Control Cable, Aileron Forward Sector, Cockpit Air Duct, Cockpit and Cabin Aileron Control Cables, Emergency Gear Release Handle Assembly, Electrical Connectors (PC311, PC312) 131DT Oxygen Tubes, Wire Bundles, Nosewheel Steering Control Assembly, Ground (GCCB03) 131ET Wire Bundles, Lower Transponder Antenna Coaxial Cables and Connectors (PC805, PF800), Grounds (GCDB07, GCDB01, GCDS19, GCDB05), Cockpit Air Duct, Left Forward Emergency Battery Pack (UC019), Forward Emergency Lighting Fuse Box (UC901), Electrical Connectors (JC138, JC139) 132AT Wire Bundles, Bob Weight, Aft Nose Landing Gear Release Cable 132BT Wire Bundles, Ground (GFSS18), Cockpit Aileron Control Cables, Pulleys, Aileron Disconnect Sector, Torque Tube, Copilot Flight Data Recorder Position Sensor (UF042), Elevator Control Lock Proximity Switch (SF017), Aft Nose Landing Gear Release Cable, Electrical Connectors (JF130, JF131, JF098, PF098, PF316, PXM025, PXM026) 132CT Wire Bundles, Cockpit Air Duct, Pulleys, Cockpit Aileron Control Cables, Cockpit Elevator Sector, Cabin Elevator Control Cables, Aft Nose Landing Gear Release Cable 132DT Wire Bundles, Ground (GFDB08) 132ET Wire Bundles, Ground (GFCB04, GFDB04, GFDS16), Cockpit Air Duct, Right Forward Emergency Battery Pack (UF903), Electrical Connectors (JF130, JF131)

6-40-00 Page 2 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 3. Cockpit Side Console/Center Pedestal Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 3) 229AC Airplane Structure 229AL (UI001), Wire Bundles, Grounds (GICB01, GICB03, GIDS01, GIDS02), Nosewheel Steering Control Cables, MFD-GTC Dim Switch (RI005), Speed Brake Installation, Junction Modules (XI001, XI003), Electrical Connectors (PC034, PC041, PC045, PC315, PC093, PC141, PC142, PC143, PC144, PF136, PI029, PI031, PI080, PI081, PI082, PI083, J1, JC034, JC041, JC045, JC141, JC142, JC144, JC143, JC148, JC149, JC320, JC902, SI027, UC320) 229AR Autothrottle (UI001), Wire Bundles, Grounds (GICB02, GICB04, GICS08, GICS06), Nosewheel Steering Control Cables, Pitch Disconnect Cable, Junction Modules (XI002, XI004), Electrical Connectors (JF149, JF150, PI081, PI080, PF094, PF315, PF137, JF138, JF136, JF137, PI034, PI035, PI036, PI038, PF138, PF141), Elevator Input Flight Data Recorder Sensor (UC043) 229BC Pitch Disconnect Installation, UV Light (FI029), Aft Pedestal Maintenance Disconnect (JI300), Electrical Connector (PC910), Left Forward Pedestal Light Emitting Diode (Led) Panel (FI021) 229BL Control Lock Installation, Control Lock Level Proximity Switch (SC014), Emergency Brake Installation, Wire Bundles, Left Aft Pedestal Light Emitting Diode (LED) Panel (FI025), MFD-GTC DIM Switch (RI005), Electrical Connectors (PC012, PC148, PC149, PF096, PF149, PF150, PF907, PF908, PI047, PI048, PI059, PI062, PI077, PI087, PI089, PI091, PI121, JC903, JI087, JI089, JI091, JI300), ENG Bleed Switch/Light (SI059), Cabin Dump Switch/Light (SI077), Cockpit Temp Rotary Switch (SI081), PRESS Source Switch/Light (SI062), Left Aft Pedestal Light Emitting Diode (LED) Panel (FI025), Engine Run/Stop Switch/Light (SI047), Aileron Trim Switch (SI072), Engine Starter Switch/Light (SI048), Pitch/Roll Disconnect Proximity Switch (SF016) 229BR Right Aft Pedestal Light Emitting Diode (LED) Panel (FI028), Handle Assembly (UF017), Pitch Disconnect Cable, Electrical Connectors (PC903, PF013, PF096, PF099, PF149, PF150, PF909, PF911, PF912, PI034, PI035, PI042, PI050, PI051, PI060, PI061, PI063, PI064, PI065, PI078, PI080, PI083, PI090, PI092, JF013, JI090, JI092), APU Bleed Switch/Light (SI060), Aileron Control Lock Proximity Switch (SF019), Press Source Switch/Light (SI064) Bleed Isolate Switch/Light (SI063), ECS Rotary Switch (SI080), Flow Switch/Light (SI065), Engine Bleed Switch (SI061), Cabin Temp Rotary Switch (SI082), Fuel Transfer Rotary Switch (SI033), Press Mode Switch/Light (SI078), Flap Handle Light Emitting Diode (LED) Panel (FI024), Engine Starter Switch/Light (SI050), Engine RUN/STOP Switch/Light (SI051),FLAP RESET Switch/Light (SI042), Event Marker Pushbutton Switch (SI069), HYDRAULICS PUMP switch (SI101 System A, SI102 System B), Fuel Boost Pump Switch/Light (SI034 Right, SI035 Left) PTCU Rotary Switch (SI044), Quadrant Light Emitting Diode (LED) Panel (FI023), Center Pedestal Light Emitting Diode (LED) Panel (FI026), APU START Rotary Switch (SI056)

6-40-00 Page 3 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Nose Wheel Well Access Panels Figure 1 (Sheet 1)

6-40-00 Page 4 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Cockpit Floorboard Access Panels Figure 2 (Sheet 1)

6-40-00 Page 5 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Cockpit Side Console/Center Pedestal Access Panels Figure 3 (Sheet 1)

6-40-00 Page 6 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 3. Cockpit Side Console/Center Pedestal Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 3) 235AL Cockpit Air Duct Installation, Oxygen Tubes, Nosewheel Steering Control Cables, Wire Bundles, Junction Modules (XC001, XC002, XC003, XC004, XC008), Electrical Connectors (JB301, JB001, PC151, JB005, JB007, JB003, JC021, PC021, JC140), Grounds (GCCB01, GCSS07), Angle-of-Attack (AOA) Sensor (UC015), Coaxial Cable Connectors (PB803A, PB815A, PB403B, PB601B, PB602B, PB804A, PB816A, PB604A) 235BL Nosewheel Steering Installation, USB Outlet, Cabin Altitude Module Assembly (UC115), Cockpit Air Duct Installation, Wire Bundles, Total Air Temperature (TAT) Probe (TC303), Ground Shunts (RC001, RC003, RC004, RC005), Forward Emergency Lighting Fuse Box (UC901), Pilot Oxygen Mask Microphone Jack (JC516), Grounds (GCSS05, GCDS13, GCDS25, GCDS05, GCSS07), Splices (AC006, AC068), Relay Box and Relays (KC110, KC113, KC115, KC117, KC118, KC119, KC120, KC125, KC126, KC128), Cockpit Side Console Printed Circuit Board (PCB) Enclosure and PCB's (NC101, NC102, NC103, NC104, NC105, NC106, NC107, NC108, NC109, NC111), Electrical Connectors (JC115, JC137, JC135, PC166, PC116, PC513, PC316, PC110, PC113, PC115, PC117, PC118, PC119, PC006, PC120, PC125, PC126, JC152, PC152, PC019, JC132, JC134, JC136, PC127, PC128, PC129, PC525, JC316, PC303, PC132, PC134, PC135, PC136, PC137, J0006, PC168, JC168, JC513, JXM515, JC111, JC109, JC108, JC107, JC106, JC105, JC104, JC103, JC102, JC101, JC2053), Shunts (BC003, BC005, BC001, BC007) 235CL Nosewheel Steering Installation, Pilot Oxygen Mask Installation, Microphone/Interphone Push to Talk (PTT) Switch (SC501), Wire Bundles 235DL Circuit Breaker Panel, Circuit Breaker LED Panel (FI017), Microphone Jack LED Panel (FI015), USB Outlet, AC Outlet (UC2017), Windshield Anti-Ice Wiring, Wiring Bundles, Diode (DC2011), Bus Bar (BZ109), Electrical Connectors (PC993, PC973, PC991, PC971, PC995, PC975, JC029, JC028, PC523, PC915, PC028, PC029, PC990, PC028, PC029, JC029, JC523, J0001, JC971, JC973, JC975, JC991, JC993, JC995, PXM926, JXM514, JXM513, JXM500, JXM512, JC2090, JC2121), Circuit Breakers (HC055, HC056, HC057, HC062, HC063, HC064) 236AR Cockpit Air Duct Installation, Wire Bundles, Bulkhead Connector (JB002, JB004, JB006, JB300, JB600), Ground (GFCB02, GFSS10), Junction Module (XF001, XF002, XF003, XF004, XF008), Electrical Connector (PF151, JF032, PF032, JF139, JF140), Angle-of-Attack (AOA) Sensor (UF015)

6-40-00 Page 7 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 3. Cockpit Side Console/Center Pedestal Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 3) 236BR Cockpit Air Duct Installation, USB Outlet, Wire Bundles, Shunts (RF001, RF003, RF004, RF005), Grounds (GFSS06, GFDS02, GFCS26), Splices (AF056, AF057), TAT Probe (TF304), Cabin Altitude Module Assembly (UF116), Relay Box and Relays (KF110, KF111, KF114, KF115, KF117, KF117, KF118, KF119, KF120, KF121, KF123, KF125, KF126, KF127, KF128, KF129), Garmin GTS 8000 Traffic Collision Avoidance System (TCAS II) Processor (UF804), Forward Emergency Battery Pack (UF903), Electrical Connectors (JF116, JF132, JF133, JF516, PF516, PF510, PF317, PF110, PF111, PF114, PF115, PF116, PF117, PF118, PF160, JF160, PF903, PF119, JF134, JF135, PF120, PF121, PF123, PF125, PF126, PF127, PF128, PF129, PF804, PF808, PF806, JF2053, PF304, PF132, PF133, PF134, PF135, PF512, JF512, JF317, JF510, PF810, PF812, PF814, PF816, PF818, PF820, PF822, PF824, JXM516, JF211, JF209, JF208, JF207, JF206, JF205, JF203, JF202), Cockpit Side Console PCB Enclosure and PCB's (NF211, NF209, NF208, NF207, NF206, NF205, NF203, NF202, NF201), Shunts (BF002, BF004, BF006) 236CR Copilot Oxygen Mask Installation, Microphone/Interphone PTT Switch (SF501) 236DR Circuit Breaker Panel, Shunt (RF006), Splices (AF001, AF002), USB Outlet, Microphone Jack LED Panel (FI014), Windshield Anti-Ice Wiring, Wiring Bundles, Grounds (GFSS12, GFDS66, GFCS14, GFDS28), Bus Bar (BZ106), Circuit Breakers (HF055, HF056, HF057, HF061, HF062, HF063), Electrical Connectors (PF972, PF974, PR994, PF992, PF976, PF995, PF996, PF508, PF905, JF2121, PF990, JF508, JF972, JF974, JF976, JF992, JF994, JF995, JF996, PXM926, JXM514, JXM513, JXM500, JXM512, JI018)

Table 4. Cabin Floorboard Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 4) 141AC Cabin Aileron Control Cables, Aileron Forward Sector, Pulleys, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable, Air Duct, Wire Bundles 141AL Wire Bundles, Cabin Elevator Control Cables, Grounds (GCDS23, GCDS45, GCDS27), Splices (AC001, AC002, AC009, AC010, AC011, AC012) 141BC Air Duct, Wire Bundles, Cabin Aileron Control Cables, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable 141BL Wire Bundles, Cabin Elevator Control Cables 141CC Air Duct, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable, Air Duct, Wire Bundles, Drain Valve Assembly, Water Distribution System Hoses, Marker Beacon Coaxial Cables (PC604B, PC603B), Wire Bundles, Cabin Aileron Control Cables, Traffic Collision Avoidance System (TCAS II) Coaxial Cables (PC820B, PC822B, PC824B, PC826B), Electrical Connectors (JC604, JC603, JF2070, JC820, JC822, JC824, JC826) 142AR Wire Bundles, Cabin Elevator Control Cables, Grounds (GFDS24, GFDS18, GFDS26), Splices (AF005, AF006, AF007, AF008, AF010, AF011)

6-40-00 Page 8 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 4. Cabin Floorboard Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 4) 142BR Wire Bundles, Cabin Elevator Control Cables 142CR Wire Bundles, Cabin Elevator Control Cables 153AC Air Duct, Grounds (GCDS35, GFDS38), Wire Bundles, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable, Cabin Aileron Control Cables, Water Distribution System Hoses, Splices (AF2005, AF2007), Adapter (JY502), Jack (PY502B) 153AL Cabin Elevator Control Cables 153BC Air Duct, Electrical Wiring, Water Distribution System Hoses, Cabin Aileron Control Cables, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable, Drag Fitting, Splices (AF2003, AF2004) 153BL Wire Bundles, Cabin Elevator Control Cables, Electrical Connectors (JY001, JY071) 154AR Wire Bundles, Cabin Elevator Control Cables, Splices (AF2006, AF2008) 154BR Electrical Connectors (JY072, JY016, JY074), Cabin Elevator Control Cables 163AC Air Duct, Water Distribution System Hoses, Cabin Aileron Control Cables, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable 163AL Wire Bundles, Cabin Elevator Control Cables 163BL Wire Bundles, Cabin Elevator Control Cables 164AR Wire Bundles, Cabin Elevator Control Cables 164BR Wire Bundles, Cabin Elevator Control Cables 175AC Air Duct, Water Distribution System Hoses, Cabin Aileron Control Cables, Pulleys, Emergency Gear Release Cable, Emergency/Parking Brake Control Cable, Grounds (GFDS20, GFCS16, GFDS34) 175AL Wire Bundles, Cabin Elevator Control Cables 175BC Wire Bundles, Grounds (GFCS24, GFDS36), Electrical Connectors (JF021, PF021) 176AR Wire Bundles, Electrical Connectors (PF312, PF610, JF610), Cabin Elevator Control Cables

Table 5. Baggage Compartment Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 5) 281ABC Wire Bundles, Grounds (GFCS08, GFDS32, GCCS05, GCDS29, GCCS43, GCDS47) 281AC Recirculation Air Shutoff Valve (VC107), Electrical Connectors (PC167, PA605B, PA606B), Ground (GCCS03) 281AL Airplane Structure

6-40-00 Page 9 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Cabin Floorboard Access Panels Figure 4 (Sheet 1)

6-40-00 Page 10 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Baggage Compartment Access Panels Figure 5 (Sheet 1)

6-40-00 Page 11 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Baggage Compartment Access Panels Figure 5 (Sheet 2)

6-40-00 Page 12 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Baggage Compartment Access Panels Figure 5 (Sheet 3)

6-40-00 Page 13 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 5. Baggage Compartment Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 5) 281ATC Aft Baggage Compartment Smoke Detector (UC101), Baggage Compartment Light Emitting Diode (LED) Cargo Light (FC902 Forward and FC901 Aft), Collins ADF-4000 Automatic Direction Finder Antenna (YC608 ADF1), Electrical Connectors (PC101, PC608, PC907, PC909), Grounds (GCDS11, GCDS21, GCDS33, GFCS40) 281BC Aft Emergency Battery Pack (UC018 Left, UF917 Right), Aft Emergency Lighting Inertia Switch (SC021 Left, SF021 Right), Aft Emergency Lighting Fuse Box (UC902), Oil Level Signal Conditioner (OLSC) (UC081), Media Server (UF2004) Router (UF2007), Input/Output Concentrator (UF2060), Electrical Connectors (JA001, JA002, JA003, JA004, JA005, JA006, JA011, JA015, JA016, JA017, JA018, JA019, JA021, JA024, JA026, JA027, JA028, JA033, JA034, JA036, JF2004, JF2007, JF2012, JF2060, JF2071, JF2072, PC008, PC017, PC068, PC097, PF066, PF2032, PF2033, PF2061, PF2075, PF2079, PF2085, PF2127), Grounds (GCDS31, GCDS37), Splices (AC066, AC067, AC119, AC120, AF901, AF902) 281BL Airplane Structure 281CL Forward Baggage Door Proximity Switch (SC016), Electrical Connectors (PC905, PC016, J0007) 281DL Forward Baggage Door Proximity Switch (SC016), Baggage Door Momentary Switch (SC903) 281EL Airplane Structure 281FL Forward Baggage Door Proximity Switch (SC016), Baggage Door Momentary Switch (SC903) 281GL Airplane Structure 281HL Airplane Structure 281JL Airplane Structure 281KL Airplane Structure 281LL (Electrical Connectors (JA013, JA023, JA901, PC501) Splices (AC2006) 281ML Aft Baggage Door Proximity Switch (SC017), Electrical Connectors (JA007, JA013, JA025, JA023, JA029), PTCU Vent Valve (VC105) 282AR Airplane Structure 282BR Baggage Compartment Smoke Detector (UF101), Electrical Connectors (PF101, PF610, PC610) 282CR APU Electronic Control Unit (ECU) (UF902), Electrical Connectors (JF165, JF071, JF072, JY076, JY078, JY080, JY082, PF071, PF072, PF165, PF904, PF305A, PF305B, PF305C, PF902A, PF902B, PF902C), Grounds (GFCS20, GFCS22, GFCS42, GFCS44, GFDS40, GFDS42), Lower Electronic Control Unit (ECU) (UF305)

6-40-00 Page 14 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 5. Baggage Compartment Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 5) 282DR Airplane Structure 282ER Ares II Recorder (UC103), Outflow Valve, Pressure Relief Valve, Pressure Controller, Baggage Compartment Printed Circuit Board (PCB) Enclosure, Cabin/PA Speaker Amplifier (UF130, UF2016), Concentrator (UF2024), Upper Rudder Electronic Control Unit (ECU) (UF306), Printed Circuit Board (NF404, NF408, NF409, NF410, NF411, NF421, NF422, NF423, NF424, NF425), AC Controller (UF2071), Electrical Connectors (JA008, JA010, JA014, JA020, JA022, JA030, JA032, JA071, JC036, JC037, JC2045, JF039, JF080, JF090, JF166, JF300, JF303, JF318, JF319, JF320, JF321, JF322, JF404, JF408, JF409, JF410, JF411, JF421, JF422, JF423, JF424, JF425, JF504, JF2024, JF2038, JF2040, JF2055, JF2027, JF2036, JF2037, JF2039, JF2128, PA071, PC100, PC036, PC037, PC507A, PC507B, PC507C, PF039, PF80, PF090, PF091, PF092, PF166, PF301, PF302, PF303, PF305A, PF305B, PF305C, PF306A, PF306B, PF306C, PF310, PF311, PF318, PF319, PF320, PF321, PF322, PF504, PF509 (NOTE 2), PF609 (NOTE 1), PF925, PF929, PF2001, PF2005, PF2025, PF2027, PF2036, PF2037, PF2038, PF2040, PF2055, PF220A, PF2149), Grounds (GFSS16, GFSS20, GFSS14, GFDS44, GFDS58, GFCS52, GFDS64, GFCS06, GFCS50, GFC04, GFD07, GFSS08, GFSS22, GFCS58, GFDS56, GFDS54, GFDS46, GFDS48, GFD08, GFC05, GFDS50) 282FR Full Authority Digital Engine Control (FADEC) Switch (SC023), Quick Access Recorder (QAR)/Qar Memory Card (UF300), Media Share Port (UK501) (NOTE 1), PC Data Port (UK502) (NOTE 1), Circuit Breakers (HC202, HW2001, HW2002, HW2003, HW2004, HW2005, HW2006, HW2007, HW2008, HW2009, HW2010, HW2011, HW2012, HW2013, HW2014, HW2015, HW2016, HW2017, HW2018, HW2019, HW2020, HW2021, HW2022, HW2024, HW2025, HW2026, HW2030, HW2031, HW2032, HW2036, HW2037, HW2038, HW2039, HW2040, HW2042, HW2043, HW2044, HW2045, HW2046, HW2047, HW2048, HW2049, HW2050), Relay Box and Relays (KF2000, KF2001, KF2002, KF2003, KF2004, KF2005, KF2006), Electrical Connectors (JF080, JF2005, JF2001, JF2117, JF2119), Shunts (BW2001, BW2002, BW2003, BW2004, BW2005, BW2006, BW2007, BW2008, BW2009, BW2010, BW2011, BW2012, BW2013)

NOTE 1: Airplanes -0017 and On.

NOTE 2: Airplanes -0001 thru -0016.

Table 6. Fuselage Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 6) 133AC Airplane Structure, Nosewheel Steering Hydraulic Lines 143AC Coaxial Cable Connectors (PY602, PY601), Hydraulic Lines 151AC Forward Grey Drain Heater (UY151), Forward System Drain Heater (UY152), Traffic Collision Avoidance System (TCAS II) Lower Antenna (YF801), Electrical Connectors (PC603A, PC604A, PC820A, PC822A, PC824A, PC826A, PY801, PY803, PY805, PY807), Splices (AY211, AY212, AY217, AY218) 151BC VHF Comm 2 Antenna (YY500), Electrical Connector (PY500)

6-40-00 Page 15 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 6. Fuselage Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 6) 151CC Single-Point Refueling/Defueling Manifold, Single-Point Refueling/Defueling Adapter Valve, Fuel Level Control Unit (FLCU #2) (UY048), Fairing Ground Recognition/Anticollision Light (FY007), Landing Light (FY001 Left, FY002 Right), Fuel Management Door, Single-Point Refueling/Defueling Door, Wing Inspection Light (FY003 Left, FY004 Right), Electrical Connectors (JY925, PY002, PY005, PY007, PY010, PY011, PY021, PY071, PY072, PY0752, PY140, PY141, PY901, PY903, PY925,), Ground (GYDS03, GYDS05, GYDS06), Splices (AY901, AY902, AY903, AY904) 161AC Fuel Level Control Unit (FLCU #1) (UY003), Drain Mast Assembly (UY150), Fuel Quantity Gauging Computer (FQGC) (UY004), Aircell ATG Antenna (YY591) (NOTE 1), Gogo Dual Directional Antenna (YY592) (NOTE 2), Electrical Connectors (JC050, JL037, JR036, JR050, PR036, PR050, PL050, PL0378, PY010, PY011, PY020, PY022, PY074, PY140, PY141, PY150, PY590, PY592), Ground (GCYS03), Relay (KY102) (NOTE 3) 161AL Ground (GYDS09), Relay (KY101) (NOTE 3) 161BL Airplane Structure, Fuel Drain Valve, Fuel Boost Pump Cartridge (ML001), Electrical Connector (JL018), Skid Rail, Poppet Drain Valve 162AR Forward Drain Mast Heater (UY150), Single-Point Refueling/Defueling Manifold, Single-Point Refueling/Defueling Shutoff Valve (VL003 Left, VR002 Right), Electrical Connectors (PL013, PR012, PY074, PY150), Grounds (GYCS02, GYCS04, GYCS11, GYDS10, GYDS12, GYDS27) 162BR Airplane Structure, Fuel Drain Valve, Skid Rail, Poppet Drain Valve, Fuel Boost Pump Cartridge (MR001), Electrical Connector (JR027) 171AL Radio Antenna (YY807), Fuel Drain Valve, Heat Exchanger, Emergency/Parking Brake Control Cable, Skid Rail, Inboard Spoiler Accumulator, Aft Fairing Leak Detection Sensing Element (TY007) Electrical Connectors (JL019, PY817, PY245, PY257), Fuel Recirculation Pump Cartridge (ML002) 171BL Electrical Connector (PY013, PY049, PY065, PY179, PY311), Flap Power Drive Unit (MY001), Fuel Pressure Switch (SY005), Ground Spoiler Manifold (VY301), Motive Flow Check Valve, Left Electric Motor Operated (ELMO) Valve (VY017), Transfer Valve (VY001), Main Landing Gear Door Closed Sensor (UY025), Main Landing Gear Door Open Sensor (UT023), Main Landing Gear Door Uplock Sensor (UY022), Main Landing Gear Uplock Assembly, Hydraulic Fluid Heat Exchanger, Aft Fairing Leak Detection Sensing Element (TY007), Flexshaft, Emergency Gear Release Cable, Inboard Spoiler Manifold (PY311), Main Landing Gear Uplock Sensor (UY021) Hydraulic Reservoir Return Check Valve (System A), Grounds (GYDS01, GYSD07, GYCS29, GYDS15, GYSS05, GYSS23), Scavenge Valve (VY029), Splices ( AY017, AY018, AY015, AY016, AY021, AY022, AY013, AY014) 172AR Right Radio Altimeter Antenna (YY808), Inboard Spoiler Accumulator, Fuel Drain Valve, Hydraulic Fluid Heat Exchanger, Skid Rail, Aft Fairing Leak Detection Sensing Element (TY008), Electrical Connectors (JR018, PY235, PY247, PY818), Fuel Recirculation Pump Cartridge (MR002)

6-40-00 Page 16 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 6. Fuselage Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 6) 172BR Electrical Connector (PY048, PY066, PY069, PY180, PY312), Fuel Pressure Switch (SY006), Main Landing Gear Door Open Sensor (UY015), Main Landing Gear Uplock Sensor (UY017) Hydraulic Fluid Heat Exchanger, Main Landing Gear Uplock Assembly, Emergency Gear Release Cable, Main Landing Gear Door Closed Sensor (UY019), Hydraulic Reservoir Return Check Valve, Main Landing Gear Door Uplock Sensor (UY016), Flap Power Drive Unit (MY001), Flexshaft, Motive Flow Check Valve, Aft Fairing Leak Detection Sensing Element (TY008), Ground Spoiler Manifold (VY302), APU Fuel Low-Pressure Valve (VY019), Right ELMO Valve (VY018), Hydraulic Reservoir Return Check Valve (System B), Grounds (GYDS04, GYDS32, GYDS30, GYCS06, GYS08), Scavenge Valve (VY030), Splices (AY001, AY002, AY003, AY004, AY005, AY006, AY009, AY010) 261AL Electrical Connectors (PY201, PY203), Left Forward Fairing Leak Detection Sensing Element (TY001), Left Mid Fairing Leak Detection Sensing Element (TY003), Left Wing Inspection Light (FY003), Ground (GYCS35) 261BL Left Wing Anti-Ice Overtemperature Switch (TL004), Forward Fairing Leak Detection Sensing Element, Left Inboard Wing Leading Edge 261CL Mid Fairing Leak Detection Sensing Element, Tube, Mid Fairing Leak Detection Sensing Element (TY003) 262AR Electrical Connectors (PY200, PY202), Right Forward Fairing Leak Detection Sensing Element (TY002) Right Mid Fairing Leak Detection Sensing Element (TY004), Right Wing Inspection Light (FY004), Ground (GYCS02, GYCS26, GYCS36) 262BR Right Wing Anti-Ice Overtemperature Switch (TR004), Forward Fairing Leak Detection Sensing Element, Right Inboard Wing Leading Edge 262CR Electrical Connector (PY204), Right Mid Fairing Leak Detection Sensing Element (TY004), Overwing Emergency Exit Light (FY006), Electrical Connector (JY056) 271AL Water Fill Heater (UY143), Drain Line Heater (UY145), Cabin Aileron Control Cable, Grey Drain Heater (UY147), Hydraulic Spoiler Accumulator Manifold (VY305, VY307), Wing Anti-Ice Pressure Transducer UY033), Main Landing Gear Shuttle Valve, Splices (AY202, AY203, AY206, AY214, AY208, AY209), Bleed Air 272AR Cabin Aileron Control Cable, Hydraulic Spoiler Accumulator Manifold (VY308), Wing Anti-Ice Pressure Transducer (UY034), Accelerometer (UF312), Main Landing Gear Shuttle Valve, Waste Tube, Electrical Connecor (PY018, PY234, PY328, PY330) 311AL Hydraulic Lines, Tailcone Access Door Proximity Switch (SY004) 312AR Airplane Structure 313AL Drain Line Heater (UY144), Grey Drain Heater (UY146), Water Fill Heater (UY142), Landing Gear Control Manifold (VY003), Shutoff Valve (VY026), Pressure Sensor, Brake Control Valve (VY024, VY022), Battery Door, Electrical Connectors (JY003, JY009, JY005, PY027, PY028, PY031, PY041, PY045, PY047, PY048), Splices (AY201, AY213, AY204, AY205, AY207, AY215), Grounds (GYCS19, GYCS15)

6-40-00 Page 17 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuselage Access Panels Figure 6 (Sheet 1)

6-40-00 Page 18 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuselage Access Panels Figure 6 (Sheet 2)

6-40-00 Page 19 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 6. Fuselage Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 6) 314AR Hydraulic Reservoir (UY010 System A, UY030 System B), Splices (AT112, AY113, AT111, AY116, AY117, AY118), Electrical Connectors (JY012, JY018, JY010, JY130, PY082, PY078 PY258), Waste Tube, Battery Door, Hydraulic Sight Glass Door, Grounds (GYCS18, GYCS20) 314BR Airplane Structure, Electrical Connector (PY262) 315AC Aft Fairing IPS Leak Detection Sensing Element, Drain Mast Assembly (UY148), Heated Cuff (UY149), Wing Anti-Ice Check Valve, Electrical Connector (PY148), Electrical Splices (AY210, AY216), Aircell ATG Antenna (YY587) (NOTE 1), Gogo Dual Directional Antenna (YY593) (NOTE 2) 315AL Wing Anti-Ice Crossflow Valve (VY008), Left Wing Anti-Ice Pressure Transducer (UY033), Pressure Sensor, Hydraulic System Accumulator (System A), Aft Fairing Leak Detection Sensing Element (TY006) Spoiler Isolation Valve (VY303), Hydraulic Reservoir Relief Cable, Hydraulic Priority Valve, Power Transfer and Conversion Unit (PTU) (UY009), Landing Gear Control Manifold (VY003), Landing Gear Return Filter Assembly, Landing Gear Return Filter Element, Hydraulic Pressure Sensor (UY045 System A, UY047 System B), Brake Shuttle Valve, Brake Control Valve (VY022, VY024), Parking Brake Valve, Parking Brake Accumulator Brake System Pressure Sensor (UY045 System A, UY047 System B), Hydraulic Fuse, Parking Brake Accumulator Pressure Sensor (VY028 System A, VY027 System B), VHF Comm 3 Antenna (YY501), Main Landing Gear Auxiliary Extend Manifold, Electrical Connectors (PY045, PY047, PY315, PY059, PY060, PY151, PY121, JY151, JY121, PY063, JY923, PY173, PY177, PY148, PY027, PY028, PY023, PY019, PY235, PY247, PY402), Grounds (GYDS25, GYDS36, GYDS33, GYSC01) 315BC External Power Receptacle (JY002), External Power Circuit Breaker (HY002), DME Antenna 2 (YY809), Waste Tank Assembly, Vacuum Generator (UY101), Remote Demister (UY114), Waste Tank Vent Tube (UY115), Tailcone Access Door Proximity Switch (SY004), Vacuum Generator Vent Tubes (UY112, UY111, UY113), Ground Power Door, Electrical Connectors (PT821, PT819, PT424, PY809)

6-40-00 Page 20 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 6. Fuselage Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 6) 315BL Parking Brake Accumulator, Aft Fairing Leak Detection Sensing Element (TY006) Hydraulic System Accumulator (System A), Hydraulic Reservoir Volume Indicator (EY001 System A, EY003 System B), Main Landing Gear Inboard Door, Hydraulic Reservoir Relief Cable, Spoiler Isolation Valve (VY309), Hydraulic Reservoir Servicing Coupling, Hydraulic Reservoir Servicing Check Valve, Hydraulic Shutoff Valve (VY011, System A), PTU (UY009), Electrical Connectors (PY235, PY247) 316AR Aft Fairing Leak Detection Sensing Element (TY005), Parking Brake Accumulator, Emergency/Parking Brake Control Cable, Parking Brake Accumulator Pressure Sensor (VY028 System A, VY027 System B), Right Wing Anti-Ice Pressure Transducer (UY034), Pressure Sensor, Engine-Driven Hydraulic Pump Discharge Filter Element, Engine-Driven Hydraulic Pump Case Drain Filter Element, Hydraulic Sight Glass Door, Isolation Valve (VY006), Thermal Relief Valve, Hydraulic Inspection Door, Hydraulic System Accumulator (System B), Hydraulic Reservoir (UY010 System A, UY030 System B), Main Landing Gear Inboard Door, Hydraulic Reservoir Relief Cable, Waste Tube, Rinse Nipple Valve, Hydraulic Reservoir Ecology Bottle, Parking Brake Valve, Hydraulic System Filter Manifold (UY012 System A, UY014 System B), Hydraulic System Return Filter Element, Hydraulic Temperature Transducer (TY014 System A, TY016 System B), Splices (AY111, AY112, AY113), Electrical Connectors (PY023, PY019, PY236, PY248, PY080, PY076, PY126, PY122, PY124, PY128, PY008, PY004, PY082), Grounds (GYCS22, GYCS24, GYDS38), 316BR Aft Fairing Leak Detection Sensing Element (TY005), Parking Brake Accumulator, Cabin Elevator Control Cable, Engine-Driven Hydraulic Pump Discharge Filter Element, Engine-Driven Hydraulic Pump Case Drain Filter Element, Hydraulic System Accumulator (System B), Hydraulic Reservoir (UY010 System A, UY030 System B), Hydraulic Reservoir Relief Cable, Hydraulic System Filter Manifold (UY012 System A, UY014 System B), Hydraulic System Return Filter Element, Hydraulic Shutoff Valve (VY012, System B), Landing Gear Accumulator, Emergency/Pakring Brake Control Cable, Parking Brake Valve, Parking Brake Accumulator Check Valve, Waste Tube, Drain Valve, Rinse Nipple Valve, Indicator Status Light (FY101), Drain Valve Heater (UY019), Drain Tube Assembly (UY110), Rinse Tube, Waste Tank Door, Electrical Connectors (PY236, PY248, PY154, PY156, PY152, PY158, PY109, PY117, PY175, PY112, PY064, PY108, PY109), Grounds (GYDS13, GYDS16)

NOTE 1: Airplanes -0001 thru -0016.

NOTE 2: Airplanes -0017 and On.

NOTE 3: Airplanes -0043 and On.

Table 7. Pylon Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 7) 413AB Left Pylon Work Light (FT003), Electrical Connectors (JD048, PT921, JD043), Manifold Air Turbine Start (ATS) Leak Detection Sensing Element (TT023), Air Turbine Starter Supply Line, DC Generator Line 413AL Airplane Structure 413AT Airplane Structure, Upper Center Pylon Seal, Assembly

6-40-00 Page 21 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 7. Pylon Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 7) 413BB Fuel System Disconnect, Engine Fire Extinguisher Lines, Yoke Assembly 413BT Airplane Structure 413CB Electrical Connectors (JD001, JD044, JD045, PT011, PT013, PT015), Pylon High-Pressure Pressure-Regulating Shutoff Valve (VT011), Pylon Bleed Air Pressure-Regulating Shutoff Valve (VT013), Pylon Skin Temperature RTD Sensors (TT001, TT003, TT005), Pylon Leak Detection Sensing Element (TT007), Pylon Temperature Control Valve (VT015), Pylon Precooler Heat Exchanger, Thermal Detector, Service Air Tube, Pylon Bleed Air Check Valve, Yoke Assembly 413DB Left Logo Light (FT001), Electrical Connector (PT005), Hydraulic System Disconnect, Hydraulic Lines 414AB Right Pylon Work Light (FT004), Electrical Connectors (JE043, PT920), Leak Detection Sensing Element (TT020) 414AR Airplane Structure, Electrical Connector (JE045) 414AT Airplane Structure 414BB Fuel System Disconnect, Engine Fire Extinguisher Lines 414BT Airplane Structure 414CB Electrical Connectors (JE002, JE047, JE044, PT012, PT014, PT016), Right Pylon Temperature Control Valve (VT016), Right Pylon Bleed Air Pressure-Regulating Shutoff Valve (VT014), Right Pylon High-Pressure Pressure-Regulating Shutoff Valve (VT012), Right Pylon Leak Detection Sensing Element (TT008), Right Pylon Skin Temperature RTD Sensors (TT002, TT004, TT006), Pylon Precooler Heat Exchanger, Thermal Detector, Service Air Tube, Pylon Bleed Air Check Valve 414DB Right Logo Light (FT002), Electrical Connector (PT004), Thrust Reverser Hydraulic System Disconnect 417AZ Airplane Structure, Engine Mount Bolts 417BZ Airplane Structure, Engine Mount Bolts 418AZ Airplane Structure, Engine Mount Bolts 418BZ Airplane Structure, Engine Mount Bolts

Table 8. Nacelle and Thrust Reverser Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 8) 411AB Air Turbine Starter 411AL Door Hook 411AR Door Hook 411AT Engine Control Unit 411ATC T2 Sensor 411BB Hydraulic Valves, Hydraulic Tubes, Wire Harness 411BL Deploy Switch 411BR Deploy Switch

6-40-00 Page 22 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Pylon Access Panels Figure 7 (Sheet 1)

6-40-00 Page 23 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Pylon Access Panels Figure 7 (Sheet 2)

6-40-00 Page 24 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Pylon Access Panels Figure 7 (Sheet 3)

6-40-00 Page 25 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Nacelle and Thrust Reverser Access Panels Figure 8 (Sheet 1)

6-40-00 Page 26 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Nacelle and Thrust Reverser Access Panels Figure 8 (Sheet 2)

6-40-00 Page 27 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Nacelle and Thrust Reverser Access Panels Figure 8 (Sheet 3)

6-40-00 Page 28 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Nacelle and Thrust Reverser Access Panels Figure 8 (Sheet 4)

6-40-00 Page 29 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 8. Nacelle and Thrust Reverser Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 8) 411BT Engine Control Unit 411BTC Monopole 411CB Door Actuator 411CL Door Pivot Bolt 411CR Door Pivot Bolt 411CT Hydraulic Valves, Hydraulic Tubes, Wire Harness 411DB Door Actuator 411DL Door Pivot Bolt 411DR Door Pivot Bolt 411DT Door Actuator 411ET Door Actuator 412AB Air Turbine Starter 412AL Door Hook 412AR Door Hook 412AT Engine Control Unit 412ATC T2 Sensor 412BB Hydraulic Valves, Hydraulic Tubes, Wire Harness 412BL Deploy Switch 412BR Deploy Switch 412BT Engine Control Unit 412BTC Monopole 412CB Door Actuator 412CL Door Pivot Bolt 412CR Door Pivot Bolt 412CT Hydraulic Valves, Hydraulic Tubes, Wire Harness 412DB Door Actuator 412DL Door Pivot Bolt 412DR Door Pivot Bolt 412DT Door Actuator 412ET Door Actuator

6-40-00 Page 30 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 9. Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 9) 341AC Coaxial Cable Connectors (PV505, PV506, PV1055, PV1058), Electrical Connectors (PV503, PV504), Honeywell KAC-1052 Antenna Coupler (UV501 HF 1, UV502 HF 2) 341BC Tailcone - Vertical Stabilizer Disconnect, HF Antenna Tube Assembly, Electrical Connectors (PT501), Coaxial Cable Connector (PT503A) 342AL Electrical Wiring 342AR Electrical Wiring 342BL Electrical Wiring, Elevator Control Cables 342BR Electrical Wiring 342CL Electrical Wiring 342CR Electrical Wiring 342DL Electrical Wiring, Tailcone - Vertical Stabilizer Disconnect, Empennage Elevator Control Cables, Pulley, Electrical Connectors (JV011, JV007, JV009) 342DR Electrical Wiring, Tailcone - Vertical Stabilizer Disconnect, Empennage Elevator Control Cables, Pulley, Electrical Connector (JV010) 342EL Electrical Wiring 342ER Tailcone - Vertical Stabilizer Disconnect, Lower Rudder Power Control Unit (PCU) (UV008), Hydraulic Lines, Empennage Elevator Control Cables, Electrical Connectors (PV009, PV010, PV013, PV015, PV011, PV007) 342FL Tailcone - Vertical Stabilizer Disconnect, Hydraulic Lines, Empennage Elevator Control Cables, Electrical Connectors (PV007, PV009, PV011, PV015, PV017), Upper Rudder PCU (UV007) 342FR Electrical Wiring, Rudder Surface Position Sensor (UV005 Upper, UV006 Lower), Rudder PCU (UV007 Upper, UV008 Lower), Rudder Hinge 342GL Rudder Surface Position Sensor (UV005 Upper, UV006 Lower), Rudder PCU (UV007 Upper, UV008 Lower), Rudder Hinge, Electrical Connectors (PV021, PV022), Hydraulic Tubes 342GR Electrical Wiring 342HL Lower Rudder PCU (UV008), Electrical Connectors (PV014, PV018, PV020) 342HR Upper Rudder PCU (UV007), Wing Aileron Control Cable, Electrical Connector (PV007, PV011, PV016), Rudder Surface Position Sensor (UV005 Upper, UV006 Lower), Rudder Assembly 342JL Electrical Wiring 342JR Electrical Wiring, Empennage Elevator Control Cables 342KL Electrical Wiring, Empennage Elevator Control Cables 342KR VOR Navigational Antenna (YV601), VOR Navigational Antenna Coupler, Horizontal Stabilizer Trim Actuator Condenser, Empennage Elevator Control Cables, Electrical Wiring, Coaxial Cable Connectors (PV601, PV602)

6-40-00 Page 31 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 9. Vertical Stabilizer Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 9) 342LL Ground (GVDS01), Horizontal Stabilizer Trim Actuator (HSTA) Controller (UV009), HSTA Filter (UV010), HSTA (UV003), Electrical Wiring, Electrical Connectors (PV025, PV027) 342LR Ground (GVDS02), HSTA (UV003), HSTA Filter (UV010), HSTA Controller (UV011), Electrical Wiring, Electrical Connectors (PV026, PV028, PV032, JV038, PV025) 342ML Aft Elevator Sector, Elevator Linkage, Cabin Elevator Control Cable, Empennage Elevator Control Cable, Elevator Assembly 342MR Electrical Wiring, Empennage Elevator Control Cables 342NL Aft Elevator Sector, Elevator Linkage, Elevator Bias Spring, Cabin Elevator Control Cable, Empennage Elevator Control Cable, Aft Elevator Control Pushrod 342NR Aft Elevator Sector, Elevator Linkage, Cabin Elevator Control Cable, Empennage Elevator Control Cable, Elevator Assembly 342PL Left HSTA Position Sensor (UV001), Elevator Bias Spring, Elevator Bias Link, Aft Elevator Control Pushrod, Elevator Idler, Elevator Linkage, Electrical Connector (PV033) 342PR Aft Elevator Sector, Elevator Linkage, Elevator Bias Spring, Cabin Elevator Control Cable, Empennage Elevator Control Cable, Aft Elevator Control Pushrod 342QR Right HSTA Position Sensor (UV002), Elevator Bias Spring, Elevator Bias Link, Elevator Idler, Elevator Linkage, Electrical Connector (PV034), Aft Elevator Control Pushrod 344AB Elevator Linkage, Aft Elevator Control Pushrod, Elevator Surface Position Sensor (UV301), Elevator Assembly, Electrical Connector (PV301, PV302) 344AC HSTA (UV003), Scissor Link Assembly 344AL Airplane Structure, Elevator Bias Link 344AR Airplane Structure, Elevator Bias Link 344AT Bullet Fairing Disconnect, Left Elevator Surface Position Sensor (UV301), Right Elevator Surface Position Sensor (UV302), Electrical Connectors (JV012, PH005, PV032, PV301, PV302) 344BT Bullet Fairing Disconnect, Tail Position/Anticollision Light (FV008), Empennage Ground Recognition/Anticollision Light (FV007), Electrical Connectors (PV012, PV023, PV024)

Table 10. Fuel Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 10) 161AB Scavenge Ejector Pump, Inboard Vent Float Valve, Wiring, Fuel Tubes 161BB Flapper Check Valve, Canted Flapper Check Valve, Fuel Probe (UL001), Wiring, Fuel Tubes 161CB Flapper Check Valve, Canted Flapper Check Valve, Fuel Probe (UL002), Fuel Boost Pump Canister, Electrical Connectors (JL018, PL031), Check Valve, Low-Level Fuel Sensing Units (#1 SL002 and #2 SL003), Wiring, Fuel Tubes

6-40-00 Page 32 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 10. Fuel Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 10) 161DB Canted Flapper Check Valve, Fuel Boost Pump Canister, Electrical Connector (JL018), Fuel Tubes, Fuel Hopper 162AB Scavenge Ejector Pump, Inboard Vent Float Valve, Single-Point Refueling/Defueling Manifold, Fuel Tubes, Wiring 162BB Flapper Check Valve, Canted Flapper Check Valve, Fuel Probe (UR001), Wiring, Fuel Tubes 162CB Flapper Check Valve, Canted Flapper Check Valve, Fuel Probe (UR002), Fuel Boost Pump Canister, Electrical Connector (JR027), Fuel Tubes, Fuel Hopper, Low-Level Fuel Sensing Units (#1 SR002 and #2 SR003) 162DB Canted Flapper Check Valve, Fuel Boost Pump Canister, Electrical Connector (JR027), Fuel Tubes, Fuel Hopper 171AB Hydraulic Fluid Heat Exchanger (System A), Canted Flapper Check Valves, Check Valve, Fuel Tubes, Wiring 171BB Hydraulic Fluid Heat Exchanger (System A), Scavenge Ejector Pump, Transfer Valve (VY001) Electrical Connector (PY013), Fuel Probe (UL003), Transfer Valve (VY001), Motive Flow Check Valve, Fuel Tubes, Wiring 172AB Hydraulic Fluid Heat Exchanger (System B), Canted Flapper Check Valve, Check Valve, Fuel Tubes, Wiring 172BB Hydraulic Fluid Heat Exchanger (System B), Scavenge Ejector Pump, Fuel Tube, Wiring, Fuel Probe (UR003), Motive Flow Check Valve, APU Fuel Low-Pressure Valve (VY019) 512AB Wiring, Fuel Tubes, Fuel Temperature Sensor, Scavenge Ejector Pump, Flapper Check Valve, Thermometer (NOTE 1) 512BB Fuel Probe, Wiring, Fuel Tubes, Flapper Check Valve, Fuel Temperature Sensor 521AB Fuel Tubes, Flapper Check Valve, Fuel Probe, Wiring 521BB Fuel Probe, Fuel Tubes, Wiring 521CB Fuel Tubes, Wiring 521DB Fuel Tubes, Wiring 521EB Flapper Check Valve, Vent Flapper Valve, Fuel Probe, Fuel Tubes, Wiring 521FB Flapper Check Valve, Fuel Tubes, Wiring 531AB Fuel Tubes, Fuel Probe, Wiring 531BB Fuel Tubes, Wiring 531CB Flapper Check Valve, Fuel Tube, Fuel Probe, Wiring 531DB Flapper Check Valve, Wiring, Fuel Tube 531EB Positive/Negative Relief Fuel Valve, Vortex Generator (Left), Fuel Probe, Wiring, Fuel Tube, Overwing Fuel Filter 531FB Vortex Generator (Left), Wiring, Fuel Probe, Fuel Tube 541AB Vortex Generator (Left), Wiring, Fuel Tube

6-40-00 Page 33 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Vertical Stabilizer Access Panels Figure 9 (Sheet 1)

6-40-00 Page 34 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Vertical Stabilizer Access Panels Figure 9 (Sheet 2)

6-40-00 Page 35 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuel Access Panels Figure 10 (Sheet 1)

6-40-00 Page 36 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuel Access Panels Figure 10 (Sheet 2)

6-40-00 Page 37 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuel Access Panels Figure 10 (Sheet 3)

6-40-00 Page 38 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuel Access Panels Figure 10 (Sheet 4)

6-40-00 Page 39 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Fuel Access Panels Figure 10 (Sheet 5)

6-40-00 Page 40 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 10. Fuel Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 10) 541BB Vortex Generator (Left), Vent Flapper Valve, Wiring, Outboard Vent Float Valve, Flame Arrestor 541CB Fuel Tubes, Level Sensor, Vent Flapper Valve, Outboard Vent Float Valve, High-Level Fuel Sensing Unit (SL001) 541DB Vortex Generator (Left), MAG-3000 Magnetometer (UL001), Electrical Connector (JL310), Bonding Jumper 612AB Aft Fuel Temperature Sensor, Forward Fuel Temperature Sensor (NOTE 2), Flapper Check Valve, Scavenge Ejector Pump, Thermometer (NOTE 1) 612BB Vent Flapper Valve, Fuel Probe, Aft Fuel Temperature Sensor, Forward Fuel Temperature Sensor (NOTE 2), Wiring 621AB Flapper Check Valve, Fuel Probe, Fuel Tube 621BB Fuel Probe, Fuel Tube 621CB Fuel Tube 621DB Fuel Tube 621EB Flapper Check Valve, Fuel Probe, Fuel Tube, Vent Flapper Valve 621FB Flapper Check Valve, Fuel Tube 631AB Fuel Probe, Fuel Tube 631BB Fuel Tube 631CB Fuel Probe, Fuel Tube, Flapper Check Valve 631DB Flapper Check Valve, Fuel Tube 631EB Vortex Generator (Right), Positive/Negative Relief Fuel Valve, Fuel Probe 631FB Vortex Generator (Right), Fuel Probe 641AB Vortex Generator (Right), Fuel Tube 641BB Vortex Generator (Right), Vent Flapper Valve, Outboard Vent Float Valve 641CB Vent Flapper Valve, Outboard Vent Float Valve, High-Level Fuel Sensing Unit (SR001) 641DB Vortex Generator (Right)

NOTE 1: Airplanes -0001 thru -0042.

NOTE 2: Airplanes -0043 and On.

6-40-00 Page 41 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 11. Wing Trailing Edge Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 11) 513AB Hydraulic Tube, Flexshaft, Inboard Flap Actuator, Main Landing Gear Inboard Electrical Harness, Main Landing Gear Door Aft Seal, Main Landing Gear 513AT Main Landing Gear Inboard Electrical Harness 513BB Inboard Spoiler Panel (Left), Inboard Flap Actuator, Flexshaft, Inboard Spoiler Position Sensor, Inboard Spoiler Actuator, Outboard Spoiler Accumulator, Ground Spoiler Actuator, Ground Spoiler Sensor 513CB Hydraulic Tubes, Hydraulic Accumulator, Pulleys, Wing Aileron Control Cable, Outboard Spoiler Accumulator, Ground Spoiler Actuator 513DB Inboard Spoiler Panel (Left), Wing Aileron Cable, Hydraulic Tubes, Flexshaft, Spoiler Manifold 513EB Roll Spoiler Manifold (VL302), Hydraulic Tubes, Flexshaft, Wiring, Wing Aileron Cable, Flexshaft, 532AB Middle Spoiler Panel (Left), Middle Spoiler Hardware, Outboard Flap Actuator, Flexshaft, Left Middle Roll Spoiler Actuator (UL304), Hydraulic Tubes, Control Cables, Bonding Jumper, Electrical Connector (JL304) 532AT Aileron Panel (Left), Pushrod, Pulleys, Wing Aileron Control Cable, Bellcrank, Aileron Sector Pushrod, Wiring 532BB Middle Spoiler Panel (Left), Outboard Spoiler Panel (Left), Outboard Spoiler Position Sensor, Wiring, Outboard Hydraulic Actuator, Hydraulic Tubes, Left Outboard Roll Spoiler Actuator (UL405) Roll Spoiler Manifold (VL303), Flap Brake, Flap Actuator, Outboard Middle Spoiler Position Sensor, Control Cables, Outboard Spoiler Hardware, Electrical Connector (JXM305) 532CB Outboard Spoiler Panel (Left), Pulley, Wing Aileron Control Cable, Wiring, Bellcrank, Pushrod, Fairleads 542AB Aileron Panel (Left), Aileron Trim Actuator (UR020), Pushrod, Wiring, Pushrod, Bellcrank, Bonding Jumper, Pushrods 613AB Flexshaft, Wiring, Hydraulic Tubes, Flap Actuator, Main Landing Gear Inboard Electrical Harness, Main Landing Gear Door Aft Seal 613AT Main Landing Gear Inboard Electrical Harness 613BB Inboard Spoiler Panel (Right), Flexshaft, Outboard Spoiler Accumulator, Ground Spoiler Actuator, Ground Spoiler Sensor (UR306), 613CB Outboard Spoiler Accumulator, Wing Aileron Control Cable, Ground Spoiler Actuator, Hydraulic Tubes 613DB Inboard Spoiler Panel (Right), Flexshaft, Hydraulic Tubes, Wing Aileron Control Cable 613EB Flexshaft, Roll Spoiler Manifold (VR302) 632AB Middle Spoiler Panel (Right), Flexshaft, Roll Middle Spoiler Actuator (UR304), Inboard Hydraulic Accumulator, Hydraulic Tubes, Control Cables, Roll Spoiler Position Sensor (UR307), Electrical Connector (JR304) 632AT Aileron Panel (Right)

6-40-00 Page 42 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 11. Wing Trailing Edge Access Panels (continued) Panel Equipment Inside the Access Panel (Refer to Figure 11) 632BB Middle Spoiler Panel (Right), Outboard Spoiler Panel (Right), Flap Brake (UR014), Roll Spoiler Actuator (UR305) Roll Spoiler Position Sensor (UR308), Roll Spoiler Manifold (VR303), Electrical Connector (JXM305) 632CB Outboard Spoiler Panel (Right), Wing Aileron Control Cable 642AB Aileron Panel (Right), Aileron Trim Actuator (UR020), Aileron Panel

Table 12. Wing Leading Edge Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 12) 511AL Inboard Wing Anti-Ice Temperature Sensor 511BL Inboard Wing Leading Edge (Left), Center Wing Leading Edge (Left) 511CL Center Wing Leading Edge (Left), Outboard Wing Leading Edge (Left) 511DL Outboard Wing Anti-Ice Temperature Sensor 611AR Inboard Wing Anti-Ice Temperature Sensor 611BR Inboard Wing Leading Edge (Right), Center Wing Leading Edge (Right) 611CR Center Wing Leading Edge (Right), Outboard Wing Leading Edge (Right) 611DR Outboard Wing Anti-Ice Temperature Sensor

Table 13. Horizontal Stabilizer Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 13) 351AL Energy Storage Bank 351BL Structure 352AR Energy Storage Bank 352BR Structure

Table 14. Stinger Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 14) 331AC Rudder Standby Pump (UT080), Isolation Control Valves (UT061, UT062), Electrical Connectors (JT099, PT075, PT076, PT077, PT078, PT091, PT092, PT093, PT094, PT095, PT096), Hydraulic Lines 331AL Structure 331AR Electrical Connector (JT086), Hydraulic Lines 331BL Bleed Air, Electrical Connectors (PT071, PT089)

6-40-00 Page 43 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Wing Trailing Edge Access Panels Figure 11 (Sheet 1)

6-40-00 Page 44 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Wing Trailing Edge Access Panels Figure 11 (Sheet 2)

6-40-00 Page 45 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Wing Leading Edge Access Panels Figure 12 (Sheet 1)

6-40-00 Page 46 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Horizontal Stabilizer Access Panels Figure 13 (Sheet 1)

6-40-00 Page 47 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Stinger Access Panels Figure 14 (Sheet 1)

6-40-00 Page 48 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Stinger Access Panels Figure 14 (Sheet 2)

6-40-00 Page 49 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 14. Stinger Access Panels (continued) 331BR Structure 331CL (APU) Power Plant, APU Generator Cooling Duct, APU Mount, APU Fire Detector Assembly (UT079), APU Drain Tube, APU Fuel Hose Assembly, APU Exhaust Nozzle, Electrical Connectors (PT090, PT071, PT089, PT079) 331CR Auxiliary Power Unit (APU) Power Plant, APU Mount, APU Inlet Seal, APU Drain Tube, APU QAD Mount

Table 15. Main Landing Gear Wheel Well Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 15) 721AL Main Landing Gear Trunnion Bolts, Grounds (GYCS21, GYCS23), Main Landing Gear Inboard Door Actuator, Main Landing Gear Actuator (UY027) 722AR Main Landing Gear Trunnion Bolts, Main Landing Gear Inboard Door Actuator, Main Landing Gear Actuator (UY028), Grounds (GYCS14, GYCS16)

6-40-00 Page 50 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Main Landing Gear Wheel Well Access Panels Figure 15 (Sheet 1)

6-40-00 Page 51 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Table 16. Winglet Access Panels

Panel Equipment Inside the Access Panel (Refer to Figure 16) 551AB Wire Bundle 551BB Aileron Position Sensor (UL021), Electrical Connector (PL007, PL009), Bonding Jumper 651AB Wire Bundle 651BB Aileron Position Sensor (UR022), Electrical Connector (JR006, JR008, PR006, PR008, PR010)

6-40-00 Page 52 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Winglet Access Panels Figure 16 (Sheet 1)

6-40-00 Page 53 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

PITOT-STATIC SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a general description and the operation of the pitot-static system. The line replaceable units (LRU)'s in the pitot-static system are the pitot probe, optional EASA pitot probe, static port, Garmin GDC 7400 (ADC), and total air temperature (TAT) probe. B. Refer to Figure 1 for a general view of the pitot-static system. C. Refer to Figure 2 for the pitot-static system block diagram.

2. Description A. Pitot Probe (1) Three pitot probes are installed on the airplane. Two of the pitot probes, pilot's and copilot's, are symmetrically installed on the nose of the airplane. The third is the standby pitot probe and is installed on the right side of the airplane, behind the copilot's side window. (2) The pilot's pitot tube is connected to the left ADC and the copilot's pitot tube is connected to the right ADC. The pitot tubes are connected to the ADC's by hoses and tube assemblies. The standby pitot tube is connected to the standby ADC with a tube. For more data about the standby pitot probe, refer to Chapter 34, Standby Instrument System - Description and Operation. (3) Each of the pitot probes is isolated and installed to supply total pressure input. This helps to decrease the possibility of a full pitot failure because of a bird strike. Each pitot probe is electrically heated to prevent an ice buildup in the inlet port. Openings in the pitot probes let foreign debris and moisture drain from the system to keep the risk of incorrect pressures to a minimum. B. EASA Pitot Probe (1) Three EASA pitot probes are installed on the airplane as an option for airplanes -0036 and On. Two of the EASA pitot probes, pilot's and copilot's, are symmetrically installed on the nose of the airplane. The third is the EASA standby pitot probe and is installed on the right side of the airplane, behind the copilot's side window. (2) The pilot's EASA pitot probe is connected to the left ADC and the copilot's EASA pitot probe is connected to the right ADC. The pitot probes are connected to the ADC's by hoses and tube assemblies. The EASA standby pitot probe is connected to the standby ADC with a tube. For more data about the EASA standby pitot probe, refer to Chapter 34, Standby Instrument System - Description and Operation. (3) Each of the EASA pitot probes is isolated and installed to supply total pressure input. This helps to decrease the possibility of a full pitot failure because of a bird strike. Each EASA pitot probe is electrically heated to prevent an ice buildup in the inlet port. Openings in the EASA pitot probes let foreign debris and moisture drain from the system to keep the risk of incorrect pressures to a minimum. C. Static Port (1) Six static ports are installed on the airplane and are installed symmetrically in sets of three on the lower side of the fuselage below the pilot’s and the copilot’s side windows. (2) Each system (pilot's, copilot's, and standby) is isolated and uses two of the static ports (one on each side of the airplane). This helps to average out differences in the static pressure between the left and the right sides of the airplane. (3) The left static port and the right static port for the pilot's static system are connected to the left ADC by hoses and tubes. The left static port and the right static port for the copilot's static system are connected to the right ADC by hoses and tubes. The left static port and the right static port for the standby static system are connected to the standby ADC by tubes. For more data about the standby static port, refer to Chapter 34, Standby Instrument System - Description and Operation. (4) The static ports have small holes that are flush with the airplane skin. Each static port directs atmospheric pressure from ambient air outside of the airplane through the holes, tubes, and hoses to one of ADC's. Each static port is electrically heated to prevent ice buildup.

34-10-00 Page 1 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Pitot-Static System Figure 1 (Sheet 1)

34-10-00 Page 2 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Pitot-Static System Block Diagram Figure 2 (Sheet 1)

34-10-00 Page 3 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

D. Garmin GDC 7400 Air Data Computer (ADC) (1) There are two ADC's that are installed on the forward side of the forward pressure bulkhead. An electrical connector, static hose, and pitot hose connect at the rear of each ADC. (2) The standby pitot-static system ADC is also installed in the airplane. For more data about the standby ADC, refer to Chapter 34, Standby Instrument System - Description and Operation. (3) Each ADC converts the pressures from a pitot probe and static ports into a raw electrical signal. This signal is used to display pressure data about the airplane's speed and altitude on each of the Garmin GDU 1400W Primary Flight Displays (PFD's) and the standby display. E. Total Air Temperature (TAT) Probe (1) There are two TAT probes symmetrically installed on the side of the fuselage below the pilot’s and the copilot’s side windows. (2) The left TAT probe supplies temperature data to the left ADC. The right TAT probe supplies supplies temperature data to the right ADC. (3) Both probes are electrically heated to prevent ice buildup.

3. Operation A. Pitot-Static System (1) The pitot-static system supplies altitude and airspeed indications to the flight crew. It also supplies a reference pressure source for the cabin differential pressure (ΔP) digital display on the multifunction display (MFD). The pitot-static system has three redundant/isolated systems: the pilot, copilot, and standby pitot-static systems. This redundancy prevents confusion because of possibly dangerous or incorrect data caused by failures in one system. For more data about the standby pitot-static system, refer to Chapter 34, Standby Instrument System - Description and Operation. (2) Each pitot-static system has one pitot probe and two static ports which supply total and static air pressure to a Garmin GDC 7400 Air Data Computer (ADC). The ADC changes each air pressure into electrical signals that are sent to the Garmin G5000 Integrated System. This data and air temperature supplied by the TAT probes are used to calculate airplane airspeed and altitude. This data shows on the PFD's. (a) The pitot probes supply total pressure data to the ADC that is used to calculate the airplane velocity through the air. (b) The static ports supply static pressure data to the ADC that is used to calculate the airplane altitude above average sea level and the vertical speed (rate of change of altitude). (c) The TAT probes supply outside air temperature to the ADC that is used to calculate correction factors for airspeed, altitude, and vertical speed and to calculate engine performance factors. (3) The pitot tubes and static ports are installed at low points in the system. Any moisture collected in the pitot-static system will automatically drain when the airplane is not in flight. (4) The pitot-static system has an electrically heated for the pitot probes, static ports, and TAT probe. For more data about the air data anti-icing system, refer to Chapter 30, Air Data Anti-Icing System - Description and Operation. B. Garmin GDC 7400 Air Data Computer (ADC) (1) The ADC measures airplane static and impact pressure data from pressure transducers and raw air temperature from the TAT probes. The ADC uses the raw data to calculate pressure altitude, vertical speed, airspeed values, air temperature data, and density altitude. (2) The ADC supplies the data that follows in ARINC 429 format to the Garmin G5000 Integrated Avionics System: • Air Temperature (total air temperature, outside/static air temperature) • Static pressure, impact pressure, and total pressure • Density Altitude • Indicated Airspeed • Mach Number • Pressure altitude • True Airspeed • Vertical Speed.

34-10-00 Page 4 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

EASA PITOT PROBE - REMOVAL/INSTALLATION

1. General A. This section gives the removal and installation procedures for the optional EASA pitot probe (TN001 left, TN002 right). For a general description of the EASA pitot probe, refer to Chapter 34, Pitot-Static System - Description and Operation.

NOTE: The EASA pitot probe is installed as an option on airplanes -0036 and On.

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 • Protective Cover. B. Special Consumables • None. C. Reference Material • Chapter 6, Nose Wheel Well Access Panel - Removal/Installation • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 30, Air Data Anti-Icing System - Adjustment/Test • Chapter 34, Pitot-Static System - Inspection/Check • Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure and High- Temperature Sealing - Maintenance Practices • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices.

3. Setup A. Prepare the Airplane for the EASA Pitot Probe 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 L PITOT HEAT Left Circuit Breaker Panel R PITOT HEAT Right Circuit Breaker Panel (3) Remove nose wheel well access panel 213AZ left, 214AZ right to get access to the EASA pitot probe (TN001 left, TN002 right). Refer to Chapter 6, Nose Wheel Well Access Panel - Removal/ Installation.

4. EASA Pitot Probe Removal A. Remove the EASA Pitot Probe (Refer to Figure 401).

NOTE: The removal of the left and right EASA pitot probes is typical.

(1) Disconnect the electrical connector (P0020 left, P0020 right) from the EASA pitot probe (TN001 left, TN002 right). (2) Disconnect the pitot tube assembly from the EASA pitot probe. (3) Put protective covers on the open ports. (4) Remove the screws that attach the EASA pitot probe to the pitot doubler.

34-10-07 Page 401 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

EASA Pitot Probe Installation Figure 401 (Sheet 1)

34-10-07 Page 402 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

(5) Remove the EASA pitot probe. (6) If necessary, clean the sealant from the EASA pitot probe and the pitot doubler. Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure and High-Temperature Sealing - Maintenance Practices.

5. EASA Pitot Probe Installation A. Install the EASA Pitot Probe (Refer to Figure 401).

NOTE: The installation of the left and right EASA pitot probes is typical.

(1) Put the EASA pitot probe (TN001 left, TN002 right) in its position at the pitot doubler. (2) Install the screws that attach the EASA pitot probe to the pitot doubler. (3) Do an electrical bond check (Type I) between the EASA pitot probe and the fuselage skin. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices. (4) Remove the protective covers from the open ports. (5) Connect the pitot tube assembly to the EASA pitot probe. (6) Connect the electrical connector (P0020 left, P0020 right) to the EASA pitot probe. (7) Apply a fillet seal (Type V, Class B) on the inboard side between the EASA pitot probe and the pitot doubler. Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure and High-Temperature Sealing - Maintenance Practices.

6. EASA Pitot Probe Post-Maintenance Checks A. Do the EASA Pitot Probe Post-Maintenance Checks. (1) Engage the circuit breakers given in Table 401. (2) Do the Pitot-Static Leak Test. Refer to Chapter 34, Pitot-Static System - Inspection/Check. (3) Do the PITOT/STATIC ICE PROTECTION Switch/Light Operational Check. Refer to Chapter 30, Air Data Anti-Icing System - Adjustment/Test.

7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Install nose wheel well access panel 213AZ left, 214AZ right. Refer to Chapter 6, Nose Wheel Well Access Panel - Removal/Installation.

34-10-07 Page 403 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

STANDBY INSTRUMENT SYSTEM - DESCRIPTION AND OPERATION

1. General A. This section gives a description and the operation of the standby instrument system. The line replaceable units (LRU)'s in the standby instrument system are the standby pitot probe, optional EASA standby pitot probe, standby static port, L-3 Communications GH-3900 Secondary Flight Display (SFD), detachable configuration module (DCM), MAG-3000 magnetometer, standby battery, and L-3 Communications ADC-4000 Standby Air Data Computer (ADC). B. Refer to Figure 1 for a general view of the standby instrument system.

2. Description A. Standby Pitot Probe (1) The standby pitot probe is installed on the fuselage on the right side of the airplane, behind the refreshment center. A tube connects to the rear side of the standby pitot probe. The standby pitot probe is installed to supply total pressure input to the standby ADC. (2) The pitot probe is electrically heated to prevent an ice buildup in the inlet port. B. EASA Standby Pitot Probe (1) The EASA standby pitot probe is installed as an option on airplanes -0036 and On. It is installed on the fuselage on the right side of the airplane, behind the refreshment center. A hose connects to the rear side of the standby pitot probe. The standby pitot probe is installed to supply total pressure input to the standby ADC. (2) The pitot probe is electrically heated to prevent an ice buildup in the inlet port. C. Standby Static Port (1) There is a left and a right standby static port installed on the airplane on the lower side of the fuselage below the pilot’s and the copilot’s side windows. The static ports supply static pressure to the standby ADC. (2) The static ports have small holes that are flush with the fuselage skin. Each static port directs atmospheric pressure from ambient air outside of the airplane through the holes and the tubes to the standby ADC. The tubes from the left and the right static ports are connected into a single tube, which is then connected to the standby ADC. This configuration helps to average out any differences in static pressure between the left and the right sides of the airplane. (3) Each static port is electrically heated to prevent ice buildup. D. L-3 Communications GH-3900 Secondary Flight Display (SFD) (1) The SFD is installed in the instrument panel in the cockpit, above the Garmin GDU 1450W multifunction display (MFD). (2) The SFD has two controls on its face, a adjustment knob and a menu button. The adjustment knob is used to enter data in the selected menus. The menu button is used to select or adjust the SFD Menu functions. (3) The SFD unit is a stand-alone unit that has inertial sensors that give attitude data on an active matrix color liquid crystal display (AMLCD) screen. Also, it shows: • Altitude and airspeed data received from the standby air data computer (ADC) through an ARINC 429 data bus • Magnetic heading data received from the MAG-3000 Magnetometer through an RS-422 data bus and the internal inertial sensors • Navigational data received from the Garmin G5000 Integrated Avionics System through an RS-422 data bus. (4) Electrical power to the SFD is supplied by the airplane electrical system. If the airplane electrical power is not available, the standby battery in the nose compartment will supply the electrical power. E. Detachable Configuration Module (DCM) (1) The DCM is attached to the wiring harness at the rear of the SFD. (2) DCM configuration options control what information is shown to the airplane flight crew and how that information appears. DCM configuration also includes SSEC performance curves for standby air data.

34-15-00 Page 1 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Standby Instrument System Figure 1 (Sheet 1)

34-15-00 Page 2 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

Standby Instrument System Figure 1 (Sheet 2)

34-15-00 Page 3 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

(3) The DCM has sufficient memory to record data that is special to the hardware and software configurations for each installation, such as panel angle, navigation interface, airplane heading calibration, and display format including metric display. When the SFD is removed from the airplane, the DCM stays connected to the airplane wiring harness. When the DCM is connected to a new or different SFD, it is not necessary to configure the unit. F. L-3 Communications MAG-3000 Magnetometer (1) The magnetometer is installed in the left wing at FS 549.61 and LBL 370.31. (2) The magnetometer is a three-axis magnetic sensor that converts magnetic field data into a digital format for a stabilized magnetic heading. The magnetic fields around the Earth give magnetic flux lines that can be sensed by the magnetometer and sent to the SFD for directional data. G. Standby Battery (1) The standby battery is found in the nose compartment behind the left nose access door. It is installed in a mounting tray between FS 90.47 and 67.40 at WL 107.57. It supplies emergency electrical power for avionics and lighting during airplane operations. (2) The standby battery is a sealed lead-acid battery that incorporates a charging and fault isolation system. For more data about the standby battery, refer to the manufacturer's component maintenance manual. Refer to the Introduction - Supplier Publication List. H. L-3 Communications ADC-4000 Standby Air Data Computer (ADC) (1) The standby ADC is installed on the right side of the airplane, behind the refreshment center. An electrical connector, pitot hose, and static tube connect to the bottom of the ADC. (2) The ADC calculates pressure altitude, vertical speed, airspeed values, air temperature data, and density altitude from the pressures it receives from the standby pitot probe and standby static port. This data is sent to the SFD.

3. Operation A. Standby Instrument System (1) During flight, ram air pressure goes into the standby pitot probe from the forward movement of the airplane through the air. The force from the ram air pressure in the standby pitot probe pushes the air pressure through the pitot tube assembly to the standby ADC. (2) During flight and on the ground, static air pressure goes into the standby static ports from the atmosphere around the airplane. The static air pressure from each of the two standby static ports is sent through left and right static tube assemblies to the standby ADC. (3) The standby ADC changes the pressure and static data into a digital signal and sends it through an ARINC 429 data bus to the SFD. (4) The SFD gets magnetic heading data from the magnetometer. The magnetic heading data is sent over an RS-422 serial data bus. (5) Push the menu button below the display screen on the SFD to show the menus. (6) Push or turn the adjustment knob to select submenus or set values.

34-15-00 Page 4 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

EASA STANDBY PITOT PROBE - REMOVAL/INSTALLATION

1. General A. This section gives the removal and installation procedures for the optional EASA standby pitot probe (TF005). For a general description of the EASA standby pitot probe, refer to Standby Instrument System - Description and Operation.

NOTE: The EASA standby pitot probe is installed as an option on airplanes -0036 and On.

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 • Protective Cover • Tags. B. Special Consumables • None. C. Reference Material • Chapter 6, Cockpit Side Console/Center Pedestal Access Panel - Removal/Installation • Chapter 24, External Electrical Power - Maintenance Practices • Chapter 30, Air Data Anti-Icing System - Adjustment/Test • Chapter 34, Pitot-Static System - Inspection/Check • Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure and High- Temperature Sealing - Maintenance Practices • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices • Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Splices - Maintenance Practices.

3. Setup A. Prepare the Airplane for the EASA Standby Pitot Probe 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 STBY PITOT HEAT Right Circuit Breaker Panel (3) Remove cockpit side console panel 236DR to get access to the EASA standby pitot probe (TF005). Refer to Chapter 6, Cockpit Side Console/Center Pedestal Access Panel - Removal/ Installation.

4. EASA Standby Pitot Probe Removal A. Remove the EASA Standby Pitot Probe (Refer to Figure 401). (1) Tag and disconnect the electrical wiring from the wiring splices (AF001, AF002). Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Splices - Maintenance Practices. (2) Disconnect the pitot tube assembly from the elbow. (a) Remove the elbow from the EASA standby pitot probe (TF005). (b) Put protective covers on the open ports. (3) Remove the screws that attach the EASA standby pitot probe to the standby pitot plate assembly.

34-15-07 Page 401 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

EASA Standby Pitot Probe Installation Figure 401 (Sheet 1)

34-15-07 Page 402 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 CESSNA® MODEL 700 MAINTENANCE MANUAL

(4) Remove the EASA standby pitot probe. (5) Clean the sealant from the EASA standby pitot probe and the standby pitot plate assembly mating surfaces. Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure and High-Temperature Sealing - Maintenance Practices.

5. EASA Standby Pitot Probe Installation A. Install the EASA Standby Pitot Probe (Refer to Figure 401). (1) Put the EASA standby pitot probe (TF005) in its position at the standby pitot plate assembly. (a) Install the screws that attach the EASA standby pitot probe to the standby pitot plate assembly. (b) Make sure that the standby pitot probe points down 2 degrees. (2) Apply a fillet seal (Type V, Class B) on the inboard side between the EASA standby pitotprobe and the standby pitot plate assembly. Refer to the Citation Standard Practices Manual, Chapter 20, Fuel, Weather, Pressure and High-Temperature Sealing - Maintenance Practices. (3) Do an electrical bond check (Type I) between the EASA standby pitot probe and the fuselage skin. Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Bonding and Grounding - Maintenance Practices. (4) Remove the protective covers from the open ports. (5) Install the elbow to the EASA standby pitot probe. (6) Connect the standby pitot tube assembly to the elbow. (7) Remove the tags and connect the electrical wiring to the wiring splices (AF001, AF002). Refer to the Model 700 Electrical Wiring Interconnect System Manual, Chapter 20, Electrical Splices - Maintenance Practices.

6. EASA Standby Pitot Probe Post-Maintenance Checks A. Do the EASA Standby Pitot Probe Post-Maintenance Checks. (1) Engage the circuit breaker given in Table 401. (2) Do the Pitot-Static Leak Test. Refer to Chapter 34, Pitot-Static System - Inspection/Check. (3) Do the PITOT/STATIC ICE PROTECTION Switch/Light Operational Check. Refer to Chapter 30, Air Data Anti-Icing System - Adjustment/Test.

7. Closeout A. Put the Airplane Back to its Initial Condition. (1) Install cockpit side console panel 236DR. Refer to Chapter 6, Cockpit Side Console/Center Pedestal Access Panel - Removal/Installation.

34-15-07 Page 403 © TEXTRON AVIATION INC. Nov 24/2020 ICA-700-34-00001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

SUPPLEMENT NO: ICA-700-34-00001 APPENDIX A: ILLUSTRATED PARTS CATALOG

Nomenclature Part Number Quantity EASA Pitot Probe 9916312-1 02 Screw (NOTE 1) MS24694-S56 08 Pitot Tube Assembly (NOTE 1) 7414721-19 (LH) 01 7414721-20 (RH) 01 EASA Standby Pitot Probe 9916312-2 01 Screw (NOTE 2) MS24694-S53 04 Pitot Tube Assembly (NOTE 2) 7414721-17 01

NOTE 1: Used to install the EASA Pitot Probe.

NOTE 2: Used to install the EASA Standby Pitot Probe.

© TEXTRON AVIATION INC. Form 2261 Rev 1 Nov 24/2020 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

SUPPLEMENT NO: ICA-700-34-00001 APPENDIX B: WIRING DIAGRAM MANUAL

© TEXTRON AVIATION INC. Form 2261 Rev 1 Nov 24/2020 CESSNA® Model 700 WIRING DIAGRAM MANUAL

30-31-01

EASA PITOT PROBE AIRPLANES 0036 & ON

Figure 01 Page 1 30-31-01 Nov 24/2020 ©TEXTRON AVIATION INC. CESSNA® Model 700 WIRING DIAGRAM MANUAL

NOTES: 2. WIRE IS 22 AWG UNLESS OTHERWISE NOTED.

EASA PITOT PROBE INSTALLATION ASSEMBLY

J1 P0020 TN001 PILOT BCK A0001 PITOT A 16 50912XXS1-14WH REFER TO 30-30-01 HTR A0003 B 16 50912XXS1-14BL REFER TO 30-30-01

EASA PITOT PROBE INSTALLATION ASSEMBLY

J1 P0020 TN002 COPILOT A0001 PITOT A 16 14WH REFER TO 30-30-01 HTR A0003 B 16 14BL REFER TO 30-30-01

8203031-1_1

EASA PITOT PROBE Figure 01. (Sheet 1) Figure 01 Page 2 30-31-01 Nov 24/2020 ©TEXTRON AVIATION INC. CESSNA® Model 700 WIRING DIAGRAM MANUAL

EASA PITOT PROBE

AIRPLANES 0036 & ON

UNITS NOMENCLATURE REF PER DES PART NUMBER 1 2 3 4 5 6 7 EFFECTIVITY ASSY

A0001 M81714/65-12-1 SPLICE 0036 & ON 1 A0003 M81714/65-12-1 SPLICE 0036 & ON 1 J1 CONNECTOR RF P0020 MS3106A10SL4S PLUG 96906 0036 & ON 1 TN001 9916312-1 PITOT PROBE 71379 0036 & ON 1 TN002 9916312-1 PITOT PROBE 71379 0036 & ON 1

Figure 01 Page 3 30-31-01 Nov 24/2020 ©TEXTRON AVIATION INC.