TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

GARMIN NAVIII STC SA01830WI AND GI275 STANDBY INSTRUMENT (IF INSTALLED) UPDATES ICA Supplement

MODEL NO: 182

SUPPLEMENT NO: ICA-182-34-80001 Revision A SUPPLEMENT DATE: Aug 18/2021

PURPOSE OF USE: The ICA Documentation that follows is applicable to all airplanes with the Garmin NAVIII STC SA01830WI and the GI 275 Standby Attitude and Direction Indicator (If Installed). If you do not have the GI 275 Standby ADI installed, the Model 182 Maintenance Manual Pages of this ICA Supplement are not applicable to your airplane.

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

REVISIONS

ICA-182-34-80001 Rev: A Date: Aug 18/2021 ICA Summary Pages 1-8 Manuals Affected Description Title See Appendix B See attached wiring schematics. 23-50-04 Figure XM Auto Mute GDL-69A XM (NAV III) Appendix B: Wiring Diagram 02 pages 1-3 Manual • Adds necessary wiring diagram for the XM Auto Mute feature wire installation to the NAVIII STC updates.

ICA-182-34-80001 Rev: - Date: Jun 1/2021 ICA Summary Pages 1-7 Manuals Affected Description Title

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5-10-01 pages Inspection Time Limits 1-27 5-12-20 pages Inspection Operation 20 1-2 • Added Garmin GI275 Standby Battery Inspections. 10-11-00 pages Storage - Maintenance Practices 201-204 • Added storage description and operation for the Garmin GI275 Standby Battery. 24-30-20 pages GI 275 Standby Battery - Maintenance Practices 201-203 Maintenance Manual 24-61-00 pages Circuit Breaker - Maintenance Practices NOTE: 201-204 These documents are only 24-70-00 pages Electrical Load Analysis - Description and Operation applicable if you have the GI 1-4 275 Standby ADI installed on your airplane. • Added Garmin GI275 Standby Battery Maintenance Practices Section, new figure for the circuit breaker panel, and electrical load information for the GI275 system. 31-10-10 pages Instrument and Control Panels - Maintenance Practices 201-206 • Added GI275 system removal/installation updates. 34-11-00 pages Pitot/Static System - Maintenance Practices Airplanes 201-211 with Garmin G1000) 34-21-20 pages GI 275 Standby Attitude and Direction Indicator - 201-210 Maintenance Practices • Updated description and operation and maintenance practices for the GI275 System. Appendix A: Illustrated See Appendix A See attached parts table. Parts Catalog

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See Appendix B See attached wiring schematics. 24-61-01 Figure Circuit Breaker Panel (Airplanes With NavIII Option) 09 pages 1-4 33-10-01 Figure Instrument Dimming (Airplanes 12701 and On with NavIII 06 pages 1-4 Option) 34-22-01 Figure Garmin Magnetometer w/ NavIII Option Appendix B: Wiring Diagram 01 pages 1-3 Manual 34-22-02 Figure Cable Assembly - GI 275 01 pages 1-3 77-40-01 Figure Engine and Airframe Monitor 07 pages pages 1-5 • Adds necessary wiring diagrams for the NAVIII STC Updates and GI275 Installation Appendix C: Garmin STC See Appendix C See attached Garmin STC SA01830WI ICA document. SA01830WI 190-02128-04 (Revision 4)

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.

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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.

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

5. ICA Incorporation into Applicable Manuals

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

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INTRODUCTION

1. Purpose A. The purpose of this Supplement is to provide the maintenance technician with the information necessary to ensure the correct functionality and performance of the GARMIN NAVIII STC SA01830WI AND GI275 STANDBY INSTRUMENT (IF INSTALLED) UPDATES on the Cessna Model 182 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 23.1529 "Instructions for Continued Airworthiness" associated with this installation. This document is a supplement to the Model 182 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 182 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 182 082416, and 083135 and On 182 (NOTE 1) 081318 and On T182 8232 and On

NOTE 1: This serialization is for the incorporation of the XM Auto Mute Wire. The GI 275 and NAVIII Changes remain effective for Cessna Model 182 Airplanes 082416, 03135 and On.

3. Complete ICA Documents A. The following document(s), in conjunction with this supplement, constitute the Instructions for Continued Airworthiness for the GARMIN NAVIII STC SA01830WI AND GI275 STANDY INSTRUMENT (IF INSTALLED) UPDATES on the Cessna Model 182. All items must be available to the operator at initial delivery. (1) Most current revision of the Model 182 Maintenance Manual (2) Most current revision of the Model 182 Wiring Diagram Manual (3) Appendix A of this document: Model 182 Illustrated Parts Table Supplement (4) Appendix B of this document: Model 182 Wiring Diagram Supplement (5) Appendix C of this document: Garmin STC SA01830WI 190-02128-04 (Revision 4 or greater)

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LIST OF INSTRUCTIONS FOR CONTINUED AIRWORTHINESS

1. Model 182 Maintenance Manual

NOTE: The Model 182 Maintenance Manual documents included in this ICA Supplement are only applicable if you have the GI 275 Standby ADI Installed on your airplane. A. Chapter 5 - Time Limits/Maintenance Checks (1) ATA 5-10-01 - Inspection Time Limits (2) ATA 5-12-20 - Inspection Operation 20 B. Chapter 10 - Parking and Mooring (1) ATA 10-11-00 - Storage - Maintenance Practices C. Chapter 24 - Electrical Power (1) ATA 24-30-20 - GI 275 Standby Battery - Maintenance Practices (2) ATA 24-61-00 - Circuit Breaker - Maintenance Practices (3) ATA 24-70-00 - Electrical Load Analysis - Description and Operation D. Chapter 31 - Indicating/Recording Systems (1) ATA 31-10-10 - Instrument and Control Panels - Maintenance Practices (Airplanes with Garmin G1000) E. Chapter 34 - Navigation (1) ATA 34-11-00 - Pitot/Static System - Maintenance Practices (2) ATA 34-21-20 - GI 275 Standby Attitude and Direction Indicator - Maintenance Practices

2. Model 182 Wiring Diagram Manual - Appendix B A. Chapter 23 - Communications (1) ATA 23-50-01, Figure 02 - XM Auto Mute GDL-69A XM (NAVIII), Airplanes (182) 81318 & ON and Airplanes (T182) 8232 & ON B. Chapter 24 - Electrical Power (1) ATA 24-61-01, Figure 09 - Circuit Breaker Panel w/NAV III, Airplanes (182) 83135 & ON C. Chapter 33 - Lights (1) ATA 33-10-01, Figure 06 - Instrument Dimming w/NAV III, Airplanes (182) 83135 & ON with NAV III Option D. Chapter 34 - Navigation (1) ATA 34-22-01, Figure 01 - Garmin Magnetometer w/NAV III, Airplanes (182) 83135 & ON (2) ATA 34-22-02, Figure 01 - Cable ASSY - GI275 STBY, Airplanes (182) 83135 & ON with NAV III Option E. Chapter 77 - Engine Indicating (1) ATA 77-40-01, Figure 07 - Engine/Airframe Monitor w/NAV III, Airplanes (182) 83135 & ON

3. Garmin Supplement Maintenance Manual - Appendix C A. Garmin STC SA01830WI (1) 190-02128-04 - Garmin G1000 NXi Supplemental Maintenance Manual for Textron Aviation Inc. NAV III Aircraft

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INSPECTION PROGRAM AND AIRWORTHINESS LIMITATIONS

1. Continuous Inspection Program A. This ICA Supplement makes the following addition to the current inspection program: (1) Adds inspection for the Standby Battery Capacity Check.

2. Airworthiness Limitations A. Cessna Aircraft Company Model 182 Maintenance Manual, Chapter 4, Airworthiness Limitations, contains the system and airframe limitations for the Model 182.

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.

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INSPECTION TIME LIMITS

1. Inspection Items

REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 050001 Inspect aircraft records to verify W 05-12-23 All Jul 1/12 that all SID Inspections have been complied with as scheduled. Revised 110000 Interior Placards, Exterior Placards, B 05-12-01 ALL Mar 1/05 Decals, Markings and Identification Plates - Inspect for security of installation and legibility. Refer to Chapter 11, Placards and Markings - Inspection/Check. Deleted 112101 Mar 1/04 Deleted 113101 Mar 1/04 212001 Ventilation System - Inspect clamps, D 05-12-05 211 hoses, and valves for condition and security. Revised 212002 Primary Flight Display (PFD) , W 05-12-23 220, 225 Mar 1/05 Multi-Function Display (MFD) Fan, Deck Skin Fan, and Remote Avionics Cooling Fan - Operational Check. Refer to Chatper 21, Avionics Cooling - Maintenance Practices. 214001 Cold and Hot Air Hoses - Check B 05-12-02 120 condition, routing, and security. Revised 214002 Heater Components, Inlets, and B 05-12-01 211 Dec 1/98 Outlets - Inspect all lines, ducts, clamps, seals, and for condition, restriction, and security. Revised 214003 Cabin Heat and Ventilation Controls - B 05-12-01 211 Jun 1/00 Check freedom of movement through full travel. Check friction locks for proper operation. Revised 221001 Autopilot Rigging - Refer to Autopilot - O 05-12-16 610 Apr 1/20 Maintenance Practices. Revised 221002 Autopilot Servo Capstan Assemblies. O 05-12-16 610 Dec 1/98 Check slip-clutch torque settings. Refer to Autopilot - Maintenance Practices. Revised 221003 Autopilot Servo Actuators. Inspect for O 05-12-16 610 Dec 1/98 evidence of corrosion and or buildup of dirt or other particulate matter which may interfere with servo operation. Refer to Autopilot - Maintenance Practices.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION 231001 Communication Antennas and Cables C 05-12-03 210 - Inspect for security of attachment, connection, and condition. 235001 Microphones, Headsets, and Jacks - C 05-12-01 211 Inspect for cleanliness, security, and evidence of damage. Revised 235002 Microphone Push-To-Talk Switch B 05-12-01 222, 223 Aug 4/03 - Clean the pilot's and copilot's microphone switches. Refer to Chapter 23, Communication - Maintenance Practices. Revised 242001 Lycoming Engine, and A 05-12-01 120 Oct 1/15 Mounting Bracket - Check condition and security. Check alternator belts for condition and proper adjustment. Check tension. Revised 242002 Lycoming Engine, Alternator Electrical A 05-12-01 120 Oct 1/15 Connections - Check condition and security. Check for cracks on the shank of terminals connected to alternator BAT and GND connection posts. Make sure the terminals are not bent or under mechanical stress caused by the routing of the attached wire. Make sure the field wire connector on 95 amp. Alternators is secure and firmly latched. Revised 243001 Main Battery - Examine the general B 05-12-02 310 Jan 2/06 condition and security. Complete a check of the level of electrolyte. Refer to Chapter 12, Battery - Servicing. Revised 243002 Main Battery Box and Cables - Clean B 05-12-02 310 Jan 2/06 and remove any corrosion. Examine the cables for routing, support, and security of the connections. 243003 General Airplane and System Wiring C 05-12-01 210 - Inspect for proper routing, chafing, broken or loose terminals, general condition, broken or inadequate clamps, and sharp bends in wiring. 243004 External Power Receptacle and C 05-12-02 120 Power Cables - Inspect for condition and security. 243005 Avionics Standby Battery - Complete S 05-12-20 220 the Standby Battery Capacity Test. Refer to Chapter 24, Standby Battery - Maintenance Practices.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION 243006 Garmin GI 275 Standby Battery (If S 05-12-20 225 Installed) - Complete the Garmin GI 275 Standby Battery Run Down Test. Refer to Chapter 24, Garmin GI 275 Standby Battery - Maintenance Practices. 246001 Switch and Circuit Breaker Panel, C 05-12-01 222 Terminal Blocks, and Junction Boxes - Inspect wiring and terminals for condition and security. Revised 246002 Power Junction Box - Check operation B 05-12-01 222 Jun 1/00 and condition. Check availability and condition of spare fuse (if applicable). Revised 246003 Alternator Control Unit - Complete J 05-12-11 222 Jul 3/06 the Over- Protection Circuit Test. Refer to Chapter 24, Alternator Control Unit. Revised 246101 Essential and Crossfeed Bus Diodes - S 05-12-20 224 Mar 1/05 Check for proper operation. Complete the Essential and Crossfeed Bus Diode Inspection. Refer to Chapter 24, Essential and Crossfeed Bus Diodes - Maintenance Practices. Revised 251001 Seats - Examine the seats to make B 05-12-01 211 Jul 3/06 sure they are serviceable and installed correctly. Make sure the seat stops and adjustment mechanism operate correctly. Examine the seat recline control and attaching hardware to make sure the hardware and lock are not damaged and are correctly installed. Lubricate the threads of the Seat Handle Assembly with MIL-PRF-81322 general purpose grease. 251002 Seat Tracks and Stops - Inspect seat B 05-12-02 230 tracks for condition and security of installation. Check seat track stops for damage and correct location. Inspect seat rails for cracks. 251101 Restraint System, front and rear - B 05-12-01 211 Check belts for thinning, fraying, cutting, broken stitches, or ultra-violet deterioration. Check system hardware for security of installation.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 251102 AMSAFE Aviation Inflatable Restraint S 05-12-20 211 Mar 1/09 (AAIR) - Examine the restraint for dirt, frayed edges, unserviceable stitching, loose connections, and other wear. Refer to Chapter 25, Inflatable Restraint System - Maintenance Practices, and do the Inflatable Restraint Inspection and the AMSAFE Aviation Inflatable Restraint (AAIR) System Adjustment/Test. 252201 Upholstery, Headliner, Trim, and D 05-12-05 211 Carpeting - Check condition and security. Revised 256001 Emergency Locator Transmitter - B 05-12-01 310 Mar 1/04 Inspect for security of attachment and check operation by verifying transmitter output. Check cumulative time and useful life of batteries in accordance with 14 CFR Part 91.207. 262001 Portable Hand Fire Extinguisher - B 05-12-01 230 Inspect for proper operating pressure, condition, security of installation, and servicing date. Revised 262002 Cockpit Mounted Fire Extinguisher - P 05-12-17 211 Apr 1/20 Weigh bottle. Bottle must be serviced by qualified individual if the weight of the extinguishing agent is not within the values listed on the servicing placard of the bottle. Revised 262003 Cockpit Mounted Fire Extinguishers R 05-12-19 211 Apr 1/20 - Perform hydrostatic test. The hydrostatic test shall be at twelve-year intervals based on initial servicing or date of last hydrostatic test. Revised 262004 Cockpit Mounted Fire Extinguishers Q 05-12-18 211 Apr 1/20 - Empty, inspect for damage, and recharge. 271001 Aileron Controls - Check freedom B 05-12-01 520, 620 of movement and proper operation through full travel. Revised 271002 Ailerons and Cables - Check operation C 05-12-03 210, 510, Jul 1/12 and security of stops. Check cables 520, 610, for tension, routing, fraying, corrosion, 620 and turnbuckle safety. Check travel if cable tension requires adjustment or if stops are damaged. Check fairleads and rub strips for condition.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION 271003 Aileron Structure, Control Rods, B 05-12-01 520, 620 Hinges, Balance Weights, Bellcranks, Linkage, Bolts, Pulleys, and Pulley Brackets - Check condition, operation, and security of attachment. 271004 Ailerons and Hinges - Check B 05-12-01 520, 620 condition, security, and operation 271005 Control Wheel Lock - Check general C 05-12-01 222 condition and operation. Revised 271006 Control Linkage - Inspect pulleys, C 05-12-01 222, 223 Dec 1/98 cables, bearings, and turnbuckles for condition and security. Revised 271007 Aileron. 1. Check aileron travel and AX 05-12-50 210, 510, Jul 1/12 cable tension. 2. Check aileron cable 520, 610, system, control cables and pulleys, 620 in accordance with the flight cable inspection procedures in Section 5-20-01, Expanded Maintenance, Control Cables. 272001 Rudder - Check internal surfaces for C 05-12-03 340 corrosion, condition of fasteners, and balance weight attachment. Revised 272002 Rudder - Inspect the rudder skins for B 05-12-01 340 Jun 1/00 cracks and loose rivets, rudder hinges for condition, cracks and security; hinge bolts, hinge bearings, hinge attach fittings, and bonding jumper for evidence of damage and wear, failed fasteners, and security. Inspect balance weight for looseness and the supporting structure for damage. Revised 272003 Rudder, Tips, Hinges, Stops, Clips B 05-12-01 340 Dec 1/98 and Cable Attachment - Check condition, security, and operation. 272004 Rudder Pedals and Linkage - Check C 05-12-01 230 for general condition, proper rigging, and operation. Check for security of attachment. Revised 272005 Rudder Control - Check freedom B 05-12-01 340 Dec 1/98 of movement and proper operation through full travel. Check rudder stops for damage and security. Revised 272006 Inspect rudder pedal torque tube AK 05-12-37 210, 211 Jul 1/12 and cable attachment arms. Refer to 5-14-01, Supplemental Inspection Document 27-20-01, for inspection procedure.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 272007 Rudder structure. Make sure you AB 05-12-28 340 Jul 1/12 inspect these areas: 1. Skin. 2. Forward and aft spars at hinge locations. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 272008 Rudder. 1. Check rudder travel and AX 05-12-50 210, 310, Jul 1/12 cable tension. 2. Check rudder cable 340 system, control cables and pulleys, in accordance with the flight cable inspection procedures in Section 5-20-01, Expanded Maintenance, Control Cables. Added 272010 Rudder Control System - Inspect B 05-12-01 340 Sep 1/16 pulleys, cables, sprockets, bearings, and turnbuckles for condition, security, and operation. Check cables for tension, routing, fraying, corrosion, and turnbuckle safety. Revised 273001 Elevator Control - Check freedom B 05-12-01 222, 223 Dec 1/98 of movement and proper operation through full travel. Revised 273002 Elevator Control System - Inspect B 05-12-01 222, 223 Jun 1/00 pulleys, cables, sprockets, bearings, chains, and turnbuckles for condition, security, and operation. Check cables for tension, routing, fraying, corrosion, and turnbuckle safety Revised 273003 Elevator, Hinges, Stops, and Cable B 05-12-01 320, 330 Dec 1/98 Attachment - Check condition, security, and operation. Revised 273004 Elevator Downspring - Check B 05-12-01 310 Dec 1/98 structure, bolts, linkage, bell crank, and push-pull tube for condition, operation, and security. Check cables for tension, routing, fraying, corrosion, and turnbuckle safety. Check travels if cables require tension adjustment or if stops are damaged. Revised 273005 Elevator. 1. Check elevator travel AX 05-12-50 210, 310, Jul 1/12 and cable tension. 2. Check elevator 320, 330 cable system, control cables and pulleys, in accordance with the flight cable inspection procedures in Section 5-20-01, Expanded Maintenance, Control Cables.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION 273101 Elevator Trim System - Check cables, B 05-12-01 224, 240, push-pull rods, bellcranks, pulleys, 310 turnbuckles, fairleads, rub strips, etc. for proper routing, condition, and security. Revised 273102 Elevator Trim Control and Indicator C 05-12-01 224, 240, Jun 1/00 - Check freedom of movement and 310 proper operation through full travel. Check pulleys, cables, sprockets, bearings, chains, and turnbuckles for condition and security. Check electric trim controls for operation as applicable. Check cables for tension, routing, fraying, corrosion, and turnbuckle safety 273103 Elevator Trim Tab and Hinges - Check B 05-12-01 224 condition, security, and operation. Revised 273104 Elevator Trim Tab Actuator - Examine B 05-12-01 320 Jul 3/06 the free play limits. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices, Trim Tab Free Play Inspection. If the free play is more than the permitted limits, lubricate the actuator and examine the free play limits again. If the free play is still more than the permitted limits, replace the actuator. Deleted 273105 Dec 1/98 273106 Elevator Trim Tab Stop Blocks - C 05-12-01 240 Inspect for damage and security. Revised 273107 Elevator Trim Tab Actuator - Remove, Z 05-12-26 320 Jul 3/06 clean, examine, and lubricate the actuator. Refer to Chapter 27, Elevator Trim Control - Maintenance Practices. Revised 273108 Elevator trim system. 1. Inspect AF 05-12-32 320, 330 Jul 1/12 elevator trim brackets and actuator support brackets. 2. Inspect pulleys, attaching structure and fasteners. Refer to Section 5-14-02, Supplemental Inspection Document 27-30-01, for inspection procedures.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 273109 Elevator Trim. 1. Check elevator trim AX 05-12-50 210, 310, Jul 1/12 travel and cable tension. 2. Check 320, 330 elevator trim cable system, control cables and pulleys, in accordance with the flight cable inspection procedures in Section 5-20-01, Expanded Maintenance, Control Cables. Revised 273110 Elevator trim system. Make sure AB 05-12-28 320, 330 Jul 1/12 you inspect these areas: 1. Elevator trim brackets. 2. Actuator support brackets and bearings. 3. Pulleys and attaching structure. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information). NOTE: Do not apply LPS-3 Heavy Duty Rust Inhibitor on hinge bearing. Revised 275001 Flaps - Check tracks, rollers, and B 05-12-01 510, 610 Dec 1/98 control rods for security of attachment. Check rod end bearings for corrosion. Check operation. 275002 Wing Flap Control - Check operation C 05-12-01 221 through full travel and observe Flap Position indicator for proper indication. 275003 Flap Structure, Linkage, Bellcranks, C 05-12-03 510, 610 Pulleys, and Pulley Brackets - Check for condition, operation and security. 275004 Flaps and Cables - Check cables C 05-12-03 510, 610 for proper tension, routing, fraying, corrosion, and turnbuckle safety. Check travel if cable tension requires adjustment. Revised 275005 Flap Motor, Actuator, and Limit C 05-12-03 610 Dec 1/98 Switches - Check wiring and terminals for condition and security. Check actuator for condition and security. Revised 275006 Flap Actuator Threads - Clean and B 05-12-01 610 Dec 1/98 lubricate. Refer to Chapter 12-21-03. Revised 275007 Flaps. 1. Check flap travel cable AX 05-12-50 210, 510, Jul 1/12 tension and travel time. 2. Check 610 flap cable system, control cables and pulleys, in accordance with the flight cable inspection procedures in Section 5-20-01, Expanded Maintenance, Control Cables.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION 282001 Fuel System - Inspect plumbing B 05-12-01 510, 610 and components for mounting and security. Revised 282002 Vent Lines and Vent Valves B 05-12-01 510, 610 Dec 1/98 - Check vents for obstruction and proper positioning. Check valves for operation. Revised 282003 Fuel Selector Valve - Check controls B 05-12-01 224 Jun 1/00 for detent in each position, security of attachment, and for proper placarding. Revised 282004 Integral Fuel Bays - Check for B 05-12-01 510, 610 Dec 1/98 evidence of leakage and condition of fuel caps, adapters, and placards. Using quick drains, ensure no contamination exists. Check quick drains for proper shut off. Deleted 282005 Aug 4/03 282006 Fuel Selector - Using quick drain, B 05-12-01 224 ensure no contamination exists. 282007 Fuel Strainer, Drain Valve, and B 05-12-01 510, 610 Controls - Check freedom of movement, security, and proper operation. Disassemble, flush, and clean screen and bowl. Deleted 282008 Mar 1/09 Revised 282009 Integral Fuel Bays - Drain the I 05-12-10 510, 610 Jan 2/06 fuel (Refer to Chapter 12, Fuel - Servicing) and purge tanks (Refer to the Single Engine Structural Repair Manual, 1996 and On). Complete an inspection of the tank interior and outlet screens and remove any foreign object debris. Complete an inspection of the tank interior surfaces for sealant deterioration and corrosion (especially in the areas). Revised 282010 Auxiliary (Electric) - B 05-12-02 120 Jun 1/00 Check pump and fittings for condition, operation, security. Revised 284001 Fuel Quantity Indication System Z 05-12-26 220, 510, Jul 1/10 Check (Airplanes without Garmin 610 G1000) - Examine for damage and correct installation. Complete a Fuel Quantity Calibration and Check. Refer to Chapter 28, Fuel Quantity Indication System - Adjustment/Test.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 284002 Fuel Quantity Indication System Z 05-12-26 220, 510, Jul 1/10 Check (Airplanes with Garmin G1000) 610 - Examine for damage and correct installation. Complete a Fuel Quantity System Check. Refer to Chapter 28, Fuel Quantity Indication System - Adjustment/Test. 311001 Instruments - Check general condition B 05-12-01 220 and markings for legibility. Deleted 311002 Mar 1/05 311003 Instrument Lines, Fittings, Ducting, C 05-12-01 220 and Instrument Panel Wiring - Check for proper routing, support, and security of attachment. Revised 321001 Main Landing Gear Wheel Fairings B 05-12-02 721,722 Mar 1/09 and Brake Fairings - Check for cracks, dents, condition of paint, and correct scraper clearance. Revised 321002 Main Gear Spring Assemblies - B 05-12-02 721, 722 Jul 1/12 Examine for cracks, dents, corrosion, condition of paint or other damage. Examine for chips, scratches, or other damage that lets corrosion get to the steel spring. Examine the axles for condition and security. 321003 Main Landing Gear Attachment B 05-12-02 721, 722 Structure - Check for damage, cracks, loose rivets, bolts and nuts and security of attachment. Revised 321004 This inspection is for mild/moderate AO 05-12-41 721, 722 Jul 1/12 corrosion environment. Inspect main landing gear tubular spring for rust or damage to finish. Refer to Section 5-14-03, Supplemental Inspection Document 32-13-01, for inspection procedure. Revised 321005 This interval is for severe corrosion AS 05-12-45 721, 722 Jul 1/12 environment. Inspect main landing gear tubular spring for rust or damage to finish. Refer to Section 5-14-03, Supplemental Inspection Document 32-13-01, for inspection procedure. Revised 321006 Inspect main landing gear fittings AI 05-12-35 210, 721, Jul 1/12 and attachment of the fittings to the 722 bulkheads. Refer to Section 5-14-04, Supplemental Inspection Document 32-13-02, for inspection procedure.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION 322001 Nose Gear - Inspect torque links, B 05-12-02 720 steering rods, and boots for condition and security of attachment. Check strut for evidence of leakage and proper extension. Check strut barrel for corrosion, pitting, and cleanliness. Check shimmy damper and/or bungees for operation, leakage, and attach points for wear and security. 322002 Nose Landing Gear Wheel Fairings - B 05-12-02 720 Check for cracks, dents, and condition of paint. 322003 Nose Gear Fork - Inspect for cracks, C 05-12-04 720 general condition, and security of attachment. 322004 Nose Gear Attachment Structure - B 05-12-02 720 Inspect for cracks, corrosion, or other damage and security of attachment. Revised 322005 Inspect nose landing gear torque AJ 05-12-36 720 Jul 1/12 links, bolts, bushings and nose landing gear fork. Refer to Section 5-14-05, Supplemental Inspection Document 32-20-01, for inspection procedure. Revised 322006 Nose gear trunnion, steering AC 05-12-29 720 Jul 1/12 assembly, torque link assembly, nose gear fork and axle. Make sure you inspect these areas: 1. Nose gear trunnion surface. 2. Steering collar and steering collar attach bolt. 3. Torque link, torque link attach pin and attach bolt. 4. Nose gear fork. 5. Nose gear axle. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 322007 Nose gear trunnion, torque link AC 05-12-29 720 Jul 1/12 assembly and nose gear fork. Make sure you inspect these areas: 1. Nose gear trunnion upper and lower inner surface and bearing. 2. Torque link bolt and attach pin inner bore surface. 3. Nose gear fork lug inner bore surface. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 322008 Nose landing gear outer barrel AC 05-12-29 720 Jul 1/12 assembly. Make sure you inspect these areas: 1. Outer barrel assembly. 2. Upper strut end and lower collar assembly. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information). NOTE: do not apply LPS-3 Heavy-Duty Rust Inhibitor to the sliding surfaces of the oleo strut. 324001 Brakes - Test toe brakes and parking B 05-12-02 230 brake for proper operation. Revised 324002 Brakes, Master Cylinders, and B 05-12-02 224, 230 Dec 1/98 Parking Brake - Check master cylinders and parking brake mechanism for condition and security. Check fluid level and test operation of toe and parking brake. Refer to Chapter 12-13-00 for servicing instructions. 324003 Brake Lines, Wheel Cylinders, Hoses, D 05-12-05 721, 722 Clamps, and Fittings - Check for leaks, condition, and security and hoses for bulges and deterioration. Check brake lines and hoses for proper routing and support. 324004 Tires - Check tread wear and general B 05-12-02 720, 721, condition. Check for proper inflation. 722 324005 Wheels, Brake Discs, and Linings B 05-12-02 721, 722 - Inspect for wear, cracks, warps, dents, or other damage. Check wheel through-bolts and nuts for looseness. Revised 324006 Wheel Bearings - Clean, inspect and B 05-12-04 720, 721, Dec 1/98 lube. 722 Revised 324007 Main landing gear axle assembly. AC 05-12-29 721, 722 Jul 1/12 Make sure you inspect these areas: 1. Main gear axle and attach bolts. 2. Wheel halves. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). NOTE: Do not apply LPS-3 Heavy-Duty Rust Inhibitor to the bearing. NOTE: Coordinate with tire change.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 324101 Nose gear axle assembly. Make sure AE 05-12-31 720 Jul 1/12 you inspect these areas: 1. Nose gear axle and attach bolt. 2. Wheel halves. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). NOTE: Disassemble the nose gear strut to get access. NOTE: Do not apply LPS-3 Heavy-Duty Rust Inhibitor to the sliding surfaces of the oleo strut. NOTE: Coordinate with tire change. 325001 Nose Gear Steering Mechanism - C 05-12-04 720 Check for wear, security, and proper rigging. 331001 Instrument and Cabin Lights - Check B 05-12-01 220, 211, operation, condition of lens, and 221 security of attachment. 334001 Navigation, Beacon, Strobe, and B 05-12-01 340, 520, Landing Lights - Check operation, 620 condition of lens, and security of attachment. Added Oct 334201 LED Landing, Taxi and Recognition B 05-12-01 520, 620 1/15 Lights - Check for condition of the lenses and security of attachment. Complete the LED Landing, Taxi and Recognition Light System Test. Refer to Chapter 33, Landing/Taxi Lights - Maintenance Practices (LED). Refer to Pilots Operating Handbook Kinds Of Operations Equipment List for minimum number of LED's that are required to be operational. 341101 Static System - Inspect for security of C 05-12-03 210 installation, cleanliness, and evidence of damage. Revised 341102 Pitot and Static System - Examine in J 05-12-11 220 Jul 3/06 accordance with 14 CFR Part 91.411. Revised 341103 182 and T182, Pitot Tube and Stall A 05-12-01 510 Oct 1/15 Warning Vane - Check for condition and obstructions and verify operation of anti-ice heat. Added 341801 Complete the Safe Flight SCc AOA P 05-12-17 610 Sep 1/16 System Ground Functional Test. 342101 Magnetic Compass - Inspect for C 05-12-01 225 security of installation, cleanliness, and evidence of damage.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 342102 Magnetic Compass - Calibrate. M 05-12-14 220 Dec 1/98 Revised 345001 Instrument Panel Mounted Avionics C 05-12-01 225 Dec 1/98 Units (Including Audio Panel, VHF Nav/Com(s), ADF, GPS, Transponder, Compass System, Multi-function Display, and Primary Flight Display) and Remote Mounted Avionics Components. Inspect for deterioration, cracks, and security of instrument panel mounts. Inspect for security of electrical connections, condition, and security of wire routing. 345002 Avionics Operating Controls - Inspect C 05-12-01 225 for security and proper operation of controls and switches and ensure that all digital segments will illuminate properly. 345003 Navigation Indicators, Controls, and C 05-12-01 220, 225 Components - Inspect for condition and security. 345004 Navigation Antennas and Cables - C 05-12-01 310 Inspect for security of attachment, connection, and condition. Revised 351001 Oxygen System (if applicable) - C 05-12-01 211 Nov 1/00 Inspect masks, hoses, lines, and fittings for condition, routing, and support. Test operation and check for leaks. Revised 351002 Oxygen (if applicable) T 05-12-21 211 Nov 1/00 - Inspect for condition, check hydrostatic test date and perform hydrostatic test, if due. 371001 Vacuum System - Inspect for condition B 05-12-02 120 and security. 371002 Vacuum Pumps - Check for condition B 05-12-02 120 and security. Check vacuum system breather line for obstructions, condition, and security. 371003 Vacuum System Hoses - Inspect for B 05-12-02 120 hardness, deterioration, looseness, or collapsed hoses. Revised 371004 Gyro Filter - Inspect for damage, B 05-12-02 120 Dec 1/98 deterioration and contamination. Clean or replace if required. Deleted 371005 Aug 4/03

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 371006 Vacuum Manifold Check Valve V 05-12-22 120 Jan 2/06 - Complete a check for proper operation. (Only airplanes with dual vacuum pumps and Airborne manifolds. Refer to the Airborne Air & Fuel Products Service Letter Number 39A or latest revision, and in accordance with SB02-37-04.) Refer to Chapter 37, Vacuum System - Maintenance Practices for the removal and installation of the check valve. Revised 371007 Do an inspection of the wear indicator Y 05-12-25 120 Jan 2/06 ports on the vacuum pumps described in Tempest Service Letter 004. 521001 Doors - Inspect general condition. B 05-12-01 210 Check latches, hinges, and seals for condition, operation, and security of attachment. Revised 521002 Passenger/Crew door retention AD 05-12-30 210 Jul 1/12 system. Make sure you inspect these areas: 1. Bell cranks. 2. Pushrods. 3. Handle. 4. Pin retention. 5. Pins. 6. Lockplates and guides. 7. Hinges. 8. Internal door framing. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Note: Remove interior panels for access. 531001 Fuselage Surface - Inspect for skin B 05-12-01 210 damage, loose rivets, condition of paint, and check pitot-static ports and drain holes for obstruction. Inspect covers and fairings for security. 531002 Firewall Structure - Inspect for C 05-12-02 120 wrinkles, damage, cracks, sheared rivets, etc. Check cowl shock mounts for condition and security. 531003 Internal Fuselage Structure - Inspect C 05-12-01 211 bulkheads, doorposts, stringers, doublers, and skins for corrosion, cracks, buckles, and loose rivets, bolts and nuts.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 531004 This interval is for mild/moderate AP 05-12-42 210 Jul 1/12 corrosion environment. Inspect the carry-thru spar area, door post bulkhead attach fittings and spar channel. Refer to Section 5-14-06, Supplemental Inspection Document 53-11-01, for inspection procedure. Revised 531005 This interval is for severe corrosion AT 05-12-46 210 Jul 1/12 environment. Inspect the carry-thru spar area, door post bulkhead attach fittings and spar channel. Refer to Section 5-14-06, Supplemental Inspection Document 53-11-01, for inspection procedure. Revised 531006 This interval is for mild/moderate AV 05-12-48 210 Jul 1/12 corrosion environment. Inspect forward doorpost and surrounding structure. Refer to Section 5-14-07, Supplemental Inspection Document 53-12-01, for inspection procedure. Revised 531007 This interval is for severe AW 05-12-49 210 Jul 1/12 corrosion environment. Inspect forward doorpost and surrounding structure. Refer to Section 5-14-07, Supplemental Inspection Document 53-12-01, for inspection procedure. Revised 531008 Inspect firewall structure. Refer AG 05-12-33 210 Jul 1/12 to Section 5-14-08, Supplemental Inspection Document 53-12-02, for inspection procedure. Revised 531009 This interval is for mild/moderate AP 05-12-42 210, 211 Jul 1/12 corrosion environment. Inspect the cabin interior skin panels, frames and stringers. Refer to Section 5-14-09, Supplemental Inspection Document 53-30-01, for inspection procedure. Revised 531010 This interval is for severe corrosion AU 05-12-47 210, 211 Jul 1/12 environment. Inspect the cabin interior skin panels, frames and stringers. Refer to Section 5-14-09, Supplemental Inspection Document 53-30-01, for inspection procedure. Revised 531011 This interval is for mild/moderate AN 05-12-40 210 Jul 1/12 corrosion environment. Inspect seat rails for corrosion. Refer to Section 5-14-10, Supplemental Inspection Document 53-47-01, for inspection procedure.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 531012 This interval is for severe corrosion AR 05-12-44 210, 211 Jul 1/12 environment. Inspect seat rails for corrosion. Refer to Section 5-14-10, Supplemental Inspection Document 53-47-01, for inspection procedure. Revised 531013 Fuselage lower internal structure AE 05-12-31 210, 211 Jul 1/12 beneath the floor panels. Make sure you inspect these areas: 1. Cabin structure under floorboards. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 531014 Fuselage internal structure in upper AE 05-12-31 210 Jul 1/12 fuselage. Make sure you inspect these areas: 1. Cabin bulkhead corners. 2. Fuselage skin. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 531015 Areas of the cabin structure. Make AE 05-12-31 210 Jul 1/12 sure you inspect these areas: 1. Firewall. 2. Firewall attachments. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 531016 Areas of the cabin structure for the AD 05-12-30 210 Jul 1/12 passenger/crew door. Make sure you inspect these areas: 1. Door frames. 2. Door hinges. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 531017 Areas of the cabin structure. Make AE 05-12-31 210 Jul 1/12 sure you inspect these areas: 1. Cabin door forward and aft frames. 2. Window frames with emphasis at stringers and channel assemblies from aft of door frame to aft bulkhead. 3. Seat attachment structure. 4. Aft Cabin Bulkhead. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 551001 Horizontal Stabilizer and Tailcone B 05-12-01 320, 330 Dec 1/98 structure - Inspect bulkheads, spars, ribs, and skins, for cracks, wrinkles, loose rivets, corrosion, or other damage. Inspect horizontal stabilizer attach bolts for looseness. Retorque as necessary. Check security of inspection covers, fairings, and tips. Revised 551002 Horizontal Stabilizer and Tips - B 05-12-01 320, 330 Dec 1/98 Inspect externally for skin damage and condition of paint. Revised 551003 Inspect horizontal stabilizer and AK 05-12-37 320, 330 Jul 1/12 elevator, including spars, ribs, hinge bolts, hinge bearings, attach fittings and torque tube. Refer to Section 5-14-11, Supplemental Inspection Document 55-10-01, for inspection procedures. Revised 551004 Rudder attachments. Make sure AB 05-12-28 340 Jul 1/12 you inspect these areas: 1. Hinge brackets. 2. Hinge bolts. 3. Hinge bearings. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information). NOTE: Do not apply LPS-3 Heavy Duty Rust Inhibitor on hinge bearing. Revised 551005 Horizontal stabilizer structure. Make AE 05-12-31 320, 330 Jul 1/12 sure you inspect these areas: 1. Stabilizer attachment to the tailcone bulkhead. 2. Front and rear spars. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 553001 Vertical Stabilizer Fin - Inspect B 05-12-01 340 Dec 1/98 bulkheads, spars, ribs, and skins for cracks, wrinkles, loose rivets, corrosion, or other damage. Inspect vertical stabilizer attach bolts for looseness. Retorque as necessary. Check security of inspection covers, fairings, and tip. Revised 553002 Vertical Stabilizer Fin and Tailcone - B 05-12-01 340 Dec 1/98 Inspect externally for skin damage and condition of paint.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 553003 Inspect vertical stabilizer and AK 05-12-37 310, 340 Jul 1/12 rudder, including spars, ribs, hinge bolts, hinge bearings and attach fittings. Refer to Section 5-14-12, Supplemental Inspection Document 55-30-01, for inspection procedure. Revised 553004 Vertical stabilizer structure. Make AE 05-12-31 310, 340 Jul 1/12 sure you inspect these areas: 1. Forward spar attachment to tailcone bulkhead. 2. Aft spar attachment to lower stabilizer spar. 3. Front and rear spars. 4. Rear spar rudder hinges. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). 561001 Windows and Windshield - Inspect B 05-12-01 210 general condition. Check latches, hinges, and seals for condition, operation, and security of attachment. 571001 Wing Surfaces and Tips - Inspect B 05-12-01 510, 520, for skin damage, loose rivets, and 610, 620 condition of paint. 571002 Wing Struts and Strut Fairings - B 05-12-01 510, 610 Check for dents, cracks, loose screws and rivets, and condition of paint. 571003 Wing Access Plates - Check for C 05-12-03 510, 520, damage and security of installation. 610, 620 571004 Wing Spar and Wing Strut Fittings C 05-12-03 510, 520, - Check for evidence of wear. 610, 620 Check attach bolts for indications of looseness and retorque as required. 571005 Wing Structure - Inspect spars, C 05-12-03 510, 520, ribs, skins, and stringers for cracks, 610, 620 wrinkles, loose rivets, corrosion, or other damage. Revised 571006 This interval is for typical usage AV 05-12-48 510, 610 Jul 1/12 environment. 1. Inspect inboard wing structure for damage and working rivets. 2. Inspect flap actuator support structure. Refer to Section 5-14-13, Supplemental Inspection Document 57-11-01, for inspection procedure.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 571007 This interval is for severe usage AW 05-12-49 510, 610 Jul 1/12 environment. 1. Inspect inboard wing structure for damage and working rivets. 2. Inspect flap actuator support structure. Refer to Section 5-14-13, Supplemental Inspection Document 57-11-01, for inspection procedure. Revised 571008 This interval is for mild/moderate AP 05-12-42 510, 520, Jul 1/12 corrosion environment. Inspect wing 610, 620 for corrosion and missing or loose fasteners. Refer to Section 5-14-14, Supplemental Inspection Document 57-11-02, for inspection procedure. Revised 571009 This interval is for severe corrosion AU 05-12-47 510, 520, Jul 1/12 environment. Inspect wing for 610, 620 corrosion and missing or loose fasteners. Refer to Section 5-14-14, Supplemental Inspection Document 57-11-02, for inspection procedure. Revised 571010 This interval is for mild/moderate AP 05-12-42 510, 610 Jul 1/12 corrosion environment. Inspect wing splice joint at strut attach. Refer to Section 5-14-15, Supplemental Inspection Document 57-11-03, for inspection procedure. Revised 571011 This interval is for severe usage AU 05-12-47 510, 610 Jul 1/12 environment. Inspect wing splice joint at strut attach. Refer to Section 5-14-15, Supplemental Inspection Document 57-11-03, for inspection procedure. Revised 571012 This interval is for mild/moderate AM 05-12-39 510, 610 Jul 1/12 corrosion environment. Inspect wing root rib. Refer to Section 5-14-16, Supplemental Inspection Document 57-12-01, for inspection procedure. Revised 571013 This interval is for severe corrosion AQ 05-12-43 510, 610 Jul 1/12 environment. Inspect wing root rib. Refer to Section 5-14-16, Supplemental Inspection Document 57-12-01, for inspection procedure. Revised 571014 This interval is for typical usage AV 05-12-48 510, 610 Jul 1/12 environment. Inspect wing strut and strut tube. Refer to Section 5-14-17, Supplemental Inspection Document 57-40-01, for inspection procedure.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 571015 This interval is for severe usage AW 05-12-49 510, 610 Jul 1/12 environment. Inspect wing strut and strut tube. Refer to Section 5-14-17, Supplemental Inspection Document 57-40-01, for inspection procedure. Revised 571016 Inspect aileron hinges, hinge bolts, AH 05-12-34 520, 620 Jul 1/12 hinge bearings and hinge and pushrod attach fittings. Refer to Section 5-14-18, Supplemental Inspection Document 57-51-01, for inspection procedure. Revised 571017 This interval is for mild/moderate AO 05-12-41 510, 610 Jul 1/12 corrosion environment. Inspect flap tracks for corrosion. Refer to Section 5-14-19, Supplemental Inspection Document 57-53-01, for inspection procedure. Revised 571018 This interval is for severe corrosion AS 05-12-45 510, 610 Jul 1/12 environment. Inspect flap tracks for corrosion. Refer to Section 5-14-19, Supplemental Inspection Document 57-53-01, for inspection procedure. Revised 571019 Wing structure internal. Make sure AA 05-12-27 510, 520, Jul 1/12 you inspect these areas: 1. Main spar 610, 620 upper and lower carry-thru fittings. 2. Main spar upper and lower caps. 3. Main spar web. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 571020 Wing structure internal. Make sure AE 05-12-31 510, 520, Jul 1/12 you inspect these areas: 1. Wing 610, 620 front spar and lower spar caps. 2. Upper and lower wing attach spar fittings. 3. Wing lower skins. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised 571021 Wing structure external. Make sure AE 05-12-31 510, 520, Jul 1/12 you inspect these areas: 1. Skin 610, 620 with emphasis at skin overlaps and under access panels. 2. Rear spar upper and lower caps. 3. Rear spar web. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 571022 Aileron attachments. Make sure AB 05-12-28 520, 620 Jul 1/12 you inspect these areas: 1. Aileron hinges. 2. Hinge bolts. 3. Hinge bearings. 4. Hinge and pushrod support structure. NOTE: Corrosion Prevention and Control Inspection Item (baseline interval, refer to Section 5-30-00 for additional inspection information). NOTE: Do not apply LPS-3 Heavy Duty Rust Inhibitor on hinge bearing. Revised 611001 McCauley , - Check A 05-12-01 110 Oct 1/15 general condition and attachment. Revised 611002 McCauley Propeller, Spinner and B 05-12-02 110 Oct 1/15 Spinner Bulkhead - Remove spinner, wash, and inspect for cracks and fractures. Revised 611003 McCauley Propeller, Blades - Inspect A 05-12-01 110 Oct 1/15 for cracks, dents, nicks, scratches, erosion, corrosion, or other damage. Revised 611004 McCauley Propeller, Hub - Check C 05-12-02 110 Oct 1/15 general condition. Revised 611005 McCauley Propeller, Mounting - A 05-12-01 110 Oct 1/15 Check for security of installation. Revised 611006 McCauley Propeller, Mounting Bolts C 05-12-02 110 Oct 1/15 - Inspect mounting bolts and safety wire for signs of looseness. Retorque mounting bolts as required. Revised 611007 McCauley Propeller, Heat Slip Rings, A 05-12-01 110 Oct 1/15 Brushes, and Boots - Inspect for condition, and security. Perform operational check. Revised 612001 McCauley Propeller, Governor and A 05-12-01 110 Oct 1/15 Control - Inspect for oil and grease leaks. If leakage is evident, refer to McCauley Service Manual. Revised 612002 McCauley Propeller, Governor and C 05-12-02 110 Oct 1/15 Control - Check for security and operation of controls. Maximum linear freeplay is 0.050 inch. Deleted 612003 Oct 1/15

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 710001 Lycoming Engine, (if A 05-12-01 120 Oct 1/15 applicable) - Inspect turbocharger mounting brackets, ducting, linkage, and attaching parts for general condition, leakage or damage, and security of attachment. Check waste gate, actuator, controller, oil and vent lines, overboost relief valve, and compressor housing for leakage, apparent damage, security of attachment, and evidence of wear. Check waste gate return spring for condition and security. Revised 710002 Lycoming Engine, Turbocharger C 05-12-02 120 Oct 1/15 (if applicable) - Examine the turbocharger for burned areas, bulges, or cracks. Use a flashlight and mirror in the tailpipe to examine the turbine for coking, carbonization, oil deposits, and turbine impellers for damage. Revised 711001 Lycoming Engine, Cowling and Cowl A 05-12-01 120 Oct 1/15 Flaps - Inspect for cracks, dents, other damage and security of cowl fasteners. Check cowl flaps for condition, security, and operation. Check cowl flap controls for freedom of movement through full travel. 712001 Engine Shock Mounts, Engine Mount C 05-12-02 120 Structure, and Ground Straps - Check condition, security, and alignment. Revised 712002 Inspect tubular engine mount. Refer AL 05-12-38 120 Jul 1/12 to Section 5-14-20, Supplemental Inspection Document 71-20-01, for inspection procedure. Revised 712003 Engine support structure. Make sure AA 05-12-27 120 Jul 1/12 you inspect these areas: 1. Engine truss. Pay particular attention in the vicinity of the welds. NOTE: Corrosion Prevention and Control Program Inspection item (refer to Section 5-30-00 for additional inspection information). Revised 716001 Lycoming Engine, Alternate Induction A 05-12-01 120 Oct 1/15 Air System - Check for obstructions, operation, and security.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 716002 Lycoming Engine, Induction System - A 05-12-01 120 Sep 1/16 Remove the duct that is between the filter box and the induction air elbow, refer to Chapter 71, Air Induction System - Maintenance Practices. Make sure the duct support wire is correctly placed, there are no loose, or broken cords and the fabric is not torn. Install an operable duct and make sure there is 0.25 inch (6.35 mm) of wire and cord under the clamps that attach the duct to the filter box and elbow. Make sure the clamps, tubes, and duct is correctly installed and make sure there are no leaks. Revised 716003 Induction Airbox, Valves, Doors, B 05-12-02 120 Jun 1/00 and Controls - Remove and inspect hinges, doors, seals, and attaching parts for wear and security. Check operation. Revised 716004 Lycoming Engine, Induction Air Filter A 05-12-01 120 Oct 1/15 - Remove and clean. Inspect for damage and service. Added Oct 716005 Lycoming Engine, Induction System A 05-12-01 120 1/15 - Make sure the duct support wire (if applicable) is secured correctly. Refer to Chapter 71, Air Induction System - Maintenance Practices. Revised 720000 Lycoming Engine, Fuel line (Stainless X 05-12-24 120 Oct 1/15 steel tube assembly) and support clamp inspection and installation. Refer to Lycoming Service Bulletin Number 342E or later version. Revised 722001 Lycoming Engine - Inspect engine A 05-12-01 120 Oct 1/15 for evidence of oil and fuel leaks. Wash engine and check for security of accessories. Revised 722002 Lycoming Engine, , Oil B 05-12-02 120 Oct 1/15 Sump, and Accessory Section - Inspect for cracks and evidence of oil leakage. Check bolts and nuts for looseness and retorque as necessary. Check crankcase breather lines for obstructions, security, and general condition.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 722003 Lycoming Engine, Hoses, Metal A 05-12-01 120 Oct 1/15 Lines, and Fittings - Inspect for signs of oil and fuel leaks. Check for abrasions, chafing, security, proper routing and support and for evidence of deterioration. Revised 723001 Lycoming Engine, Cylinders, Rocker B 05-12-02 120 Oct 1/15 Box Covers, and Pushrod Housings - Check for fin damage, cracks, oil leakage, security of attachment, and general condition. 723002 Engine Metal Lines, Hoses, Clamps, C 05-12-02 120 and Fittings - Check for leaks, condition, and security. Check for proper routing and support. Revised 723003 Lycoming Engine, Engine Baffles and A 05-12-01 120 Oct 1/15 Seals - Check condition and security of attachment. Revised 723004 Lycoming Engine, Cylinder B 05-12-02 120 Oct 1/15 Compression - Complete a differential compression test. If there is weak cylinder compression, refer to Chapter 71, Engine - Troubleshooting, for further procedures. Revised 730001 Lycoming Engine, Engine-Driven B 05-12-02 120 Oct 1/15 Fuel Pump - Check for evidence of leakage, security of attachment, and general condition. Revised 730002 Lycoming Engine, B 05-12-02 120 Oct 1/15 System - Check system for security and condition. Clean fuel inlet screen, check and clean injection nozzles and screens (if evidence of contamination is found), and lubricate air shaft. Revised 730003 Lycoming Engine, Idle and Mixture - B 05-12-02 120 Oct 1/15 Run the airplane engine to determine satisfactory performance. If required, adjust the idle rpm and fuel mixture. Refer to Chapter 73, Fuel Injection Systems - Maintenance Practices. Revised 741001 Lycoming Engine, - B 05-12-02 120 Oct 1/15 Examine the external condition and for correct installation and condition of the electrical leads. Complete a check of the engine timing (external timing). Refer to Chapter 74, - Maintenance Practices.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 741002 Lycoming Engine, Magnetos - Clean, H 05-12-09 120 Oct 1/15 examine, and adjust as necessary. Do the 500-hour inspection in accordance with the Slick 4300/6300 Series Maintenance and Overhaul Manual. Revised 742001 Lycoming Engine, Ignition Harness B 05-12-02 120 Oct 1/15 and Insulators - Check for proper routing, deterioration, and condition of terminals. Revised 742002 Lycoming Engine, Spark Plugs - B 05-12-02 120 Oct 1/15 Remove, clean, analyze, test, gap, and rotate top plugs to bottom and bottom plugs to top. Revised 743001 Lycoming Engine, Ignition Switch B 05-12-02 120 Oct 1/15 and Electrical Harness - Inspect for damage, condition, and security. Revised 743002 Lycoming Engine, Inspect and N 05-12-15 224 Oct 1/15 lubricate ACS brand ignition switch. Refer to Chapter 74, Ignition System - Maintenance Practices. Revised 761001 Lycoming Engine Controls and B 05-12-01 120, 225 Oct 1/15 Linkage - Examine the general condition and freedom of movement through the full range. Complete a check for the proper travel, security of attachment, and for evidence of wear. Complete a check of the friction lock and vernier adjustment for proper operation. Complete a check to make sure the throttle, fuel mixture, and propeller governor arms operate through their full arc of travel. The maximum linear freeplay is 0.050 inch. Revised 781001 Lycoming Engine, A 05-12-01 120 Oct 1/15 - Inspect for cracks and security. Special check in area of heat exchanger. Refer to Chapter 78, Exhaust system - Maintenance Practices. Revised 781002 Lycoming Engine, Exhaust System A 05-12-01 120 Oct 1/15 (turbocharged engine) - Inspect couplings, seals, clamps, and expansion joints for cracks. Special check in area of heat exchanger. Refer to Chapter 78, Exhaust System - Maintenance Practices. Note: This inspection is specifically required for German (LBA) certification.

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REVISION ITEM CODE TASK INTERVAL ZONE STATUS NUMBER OPERATION Revised 791001 Lycoming Engine - Drain engine oil A 05-12-01 120 Oct 1/15 sump and oil cooler. Check for metal particles or foreign material in filter, on sump drain plug, and on engine suction screen. Refer to Textron Lycoming Service Bulletin # 480C or latest revision. Replace filter, and refill with recommended grade aviation oil. Revised 792001 Lycoming Engine, Oil Cooler - Check A 05-12-01 120 Oct 1/15 for obstructions, leaks, and security of attachment. Revised 801001 and Electrical Connections B 05-12-02 120 Jun 1/00 - Check security and condition of starter, electrical connection, and cable. Revised 801002 Lycoming Engine, Bendix Drive A 05-12-01 120 Oct 1/15 Starter Assembly - Clean and lubricate starter drive assembly.

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INSPECTION OPERATION 20

Date: ______Registration Number: ______Serial Number: ______Total Time: ______

1. Description A. Operation 20 gives a list of item(s), which are completed every 1 year. B. Inspection items are given in the order of the zone in which the inspection is to be completed. A general description of the inspection required and the Item Code Number for cross-reference to section 5-10-01 are shown. Frequently, the tasks define more specifically the scope and extent ofeach required inspection. These tasks are printed in the individual chapters of this manual. C. The right portion of each page gives space for the mechanic's and inspector's initials and remarks. A copy of these pages can be used as a checklist when these inspections are completed.

2. General Inspection Criteria A. During each of the specified inspection tasks in this section, more general inspections of the adjacent areas must be done while access is available. These general inspections are used to find apparent conditions which can need more maintenance. B. If a component or system is changed after a required task has been completed, then that specified task must be done again to make sure it is correct before the system or component is returned to service. C. Do a preflight inspection after these inspections are completed to make sure all the required items are correctly serviced. Refer to the Pilot's Operating Handbook and FAA Approved Airplane Flight Manual.

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ITEM CODE TASK ZONE MECH INSP REMARKS NUMBER 243005 Avionics Standby Battery - Complete the Standby 220 Battery Capacity Test. Refer to Chapter 24, Standby Battery - Maintenance Practices. 243006 Garmin GI 275 Standby Battery (If Installed) - 225 Complete the Garmin GI 275 Standby Battery Run Down Test. Refer to Chapter 24, Garmin GI 275 Standby Battery - Maintenance Practices. 246101 Essential and Crossfeed Bus Diodes - Check 224 for proper operation. Complete the Essential and Crossfeed Bus Diode Inspection. Refer to Chapter 24, Essential and Crossfeed Bus Diodes - Maintenance Practices. 251102 AMSAFE Aviation Inflatable Restraint (AAIR) 211 - Examine the restraint for dirt, frayed edges, unserviceable stitching, loose connections, and other wear. Refer to Chapter 25, Inflatable Restraint System - Maintenance Practices, and do the Inflatable Restraint Inspection and the AMSAFE Aviation Inflatable Restraint (AAIR) System Adjustment/Test. *** End of Operation 20 Inspection Items ***

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STORAGE - MAINTENANCE PRACTICES

1. General A. This section provides maintenance instructions and inspection criteria for airplanes in flyable, temporary and indefinite storage. Refer to the Lycoming Service Letter L180B (or latest revision). (1) Flyable storage is defined as a maximum of 30 days of nonoperational status and/or thefirst25 hours of intermittent engine operation. (2) Temporary storage is defined as a maximum of 90 days of nonoperational status. (3) Indefinite storage is defined as more than 90 days of nonoperational status.

2. Flyable Storage A. Flyable storage is a maximum of 30 days storage with no engine operation and/or the first 25 hours of intermittent engine operation. B. Engine temperature and length of operation time are very important in the control of corrosion. The desired flight time for air cooled engines is at least one continuous hour at oil temperatures of165 degrees F (74 degrees C) to 200 degrees F (93 degrees C) at intervals not to exceed 30 days. The one hour does not include taxi, take-off, and landing time. C. The aircraft temperature gages must operate correctly. D. The cooling air baffles must be in good condition and fitted properly. E. The oil cooler system must be of the proper size for the engine and airframe. Oil coolers that are not the correct size can cause an engine to operate at too high or low a temperature. Low temperatures are as dangerous as high temperatures because of build-up of water and acids. F. Pulling the propeller through by hand is not recommended when the airplane has not operated for approximately a week . Pulling the propeller through by hand before you start the engine or to minimize corrosion can cause damage. When the propeller is pulled through by hand, the rings can remove oil from the cylinder walls. The load made by the valve train removes oil from the cam and followers. After two or three times of pulling the propeller through by hand without engine starts, the cylinders, cam, and followers are left without the correct quantity of oil film. Engine starts without the correct lubrication can cause the engine parts to score, which can cause damage to the engine. G. The pitot tube, static air vents, air vents, openings in the engine cowl, and other openings must have protective covers installed to prevent entry of foreign object debris.

3. Temporary Storage

NOTE: The airplane is constructed of corrosion resistant, epoxy primed aluminum, which will last indefinitely under normal conditions, if kept clean. The alloys are subject to oxidation. The first indication of corrosion on unpainted surfaces is in the form of white deposits orspots. Corrosion on painted surfaces shows up as the paint being discolored or blistered. Storage in a dry hangar is necessary for good preservation and must be procured if possible. A. Temporary Storage of the Airplane (1) The tiedown rings must be used as electrical ground points for all ground wires during the refuel procedures. (2) Fill the fuel tanks with the correct grade of gasoline.

WARNING: During all fueling procedures, fire fighting equipment must be available. In case of an accidental disconnect of a ground wire. Two ground wires must be used from different points on the airplane which are attached to separate ground stakes . Make sure to ground the fuel nozzle the airplane.

(3) Clean and wax the airplane thoroughly. (4) Clean all oil or grease from the tires.

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(5) Apply a tire preservative to the tires. (6) Cover the tires to protect against grease and oil. (7) Block up the fuselage to relieve the pressure on the tires or rotate the wheels every 30 days.

NOTE: This aids to change supporting points and prevent flat spotting on the tires.

(8) Lubricate all airframe items and cover all openings which allow moisture and/or dust to enter. (9) Charge the avionics standby battery and the Garmin GI 275 Standby Battery (If Installed).

NOTE: For maximum battery life, the avionics standby battery and Garmin GI 275 Standby Battery (if installed) must be kept partially charged with the aircraft main battery and external power.

(a) Connect external power to the airplane. (b) Put the MASTER switch in the ON position. (c) Allow the avionics standby battery and the Garmin GI 275 Standby Battery (if installed) to charge for 1 hour. (d) Put the MASTER switch in the OFF position. (e) Disconnect external power from the airplane. (10) Turn battery and store in a cool, dry place. Service the battery periodically and charge as required. (11) Every 90 days, install a fully charged main aircraft battery and charge the avionics standby battery and the Garmin GI 275 Standby Battery (if installed). Use the battery charge procedure in this document. (12) Disconnect the leads. (13) Remove the upper and lower spark plugs from each cylinder. (14) Use a portable pressure sprayer to spray a preservative oil in the upper spark plug hole of each cylinder (the must be in a down position). Rotate the as each pair of cylinders is sprayed. (15) Rotate the crankshaft so that no piston is at a top position. (16) If the airplane is to be stored outside, set the two bladed propeller in a horizontal position to provide maximum clearance for passing airplanes. (17) Spray each cylinder without moving the crankshaft to cover all interior surfaces of the cylinder above the piston. (18) Install the spark plugs and attach the spark plug leads. (19) Spray two ounces of the preservative oil into the engine interior through the oil filler tube. (20) Seal all engine openings exposed to the atmosphere using suitable plugs. Attach a red streamer at each point that a plug is installed.

CAUTION: The pitot tube, static source vents, air vent openings in the engine cowling and other similar openings must have protective covers installed to prevent entry of foreign material.

(21) If the airplane is to be stored outside, tie it down using the procedures outlined in Chapter 10, Mooring - Maintenance Practices. (22) Attach a warning placard to the propeller to identify that the propeller must not be moved while the engine is in storage.

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4. Indefinite Storage A. Put the airplane in indefinite storage.

NOTE: Periodic inspections must be performed to make sure of the integrity of preservation methods. Refer to Chapter 10, Inspection During Indefinite Storage.

(1) Operate the engine for the oil temperature to reach the normal operating temperature.

NOTE: Normal operating temperature is within the green arc of the oil temperature gage. The engine oil must be drained while the engine is still warm.

(2) Shut off the engine and remove the lower cowling to drain the engine oil. Refer to Chapter 71, Cowling - Maintenance Practices. (3) Lift the nose of the airplane slightly to aid in the removal of sludge in the engine oil sump.

WARNING: Avoid skin contact with engine oil. Any engine oil that inadvertently gets on the skin should be immediately removed.

(4) Remove and discard the wire from the drain plug. (5) Remove the drain plug and let the oil drain into an applicable container. (6) Install plug in sump when all oil is drained.

CAUTION: The corrosion preventive mixture is harmful to paint and shall be wiped from painted surfaces immediately.

(7) Fill oil sump to normal capacity with thoroughly mixed corrosion preventative oil. Refer to Chapter 10, Parking, Mooring, Storage and Return to Service - General. (8) Remove the top spark plugs. (9) Slowly turn the propeller with the crankcase full of oil, through two revolutions. (10) Allow the engine to stand for ten minutes, then turn the propeller back and forth through 90 degrees for twelve cycles. (11) Drain the preservative oil. (12) Use MIL-C-6529 oil Type 1, to spray the exhaust port and valve of each cylinder. The piston must be approximately 1/4 turn before top center of the exhaust . (13) Use an airless spray gun to spray two ounces of MIL-C-6529 oil, Type 1, into each cylinder through the spark plug hole. (14) For all spraying, the spray nozzle temperature must be maintained between 200°F (93.33°C) and 220°F (104.44°C). (15) Install dehydrator plugs in the upper spark plug holes. Make sure the dehydrator plugs are blue in color when installed. (16) Cover spark plug lead terminals with shipping plugs or other suitable covers. (17) Set the throttle in the full open position. (18) Place a bag of desiccant in the induction air and seal the opening with moisture resistant paper and tape. (19) Place a bag of desiccant in the exhaust tailpipe and seal openings with moisture resistant tape. (20) Seal the cold air inlet to the heater muff with moisture resistant tape. (21) Seal the engine breather tube by inserting a plug in the breather hose and clamping it in place. (22) Seal all other engine openings exposed to the atmosphere. Use applicable plugs or non-hydroscopic tape. (23) Attach a red streamer to each location where plugs or tapes are installed. Attach the red streamers outside the sealed area with tape or to the inside of the sealed area with safety wire to prevent wicking of moisture into the sealed area.

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CAUTION: The corrosion preventive mixture is harmful to paint and must be wiped from painted surfaces immediately.

(24) Drain corrosion preventative mixture from engine sump. (25) Install and safety the drain plug with wire. Refer to Chapter 20, Safetying - Maintenance Practices . (26) Install the lower cowling. Refer to Chapter 71, Cowling - Maintenance Practices. (27) Attach a warning placard on the throttle control knob to identify that the engine contains no lubricating oil. (28) Placard the propeller to the effect that it must not be moved while the engine is in storage.

NOTE: As an alternate method of indefinite storage, the airplane may be serviced according to the temporary storage procedures. Run up at the maximum intervals of 90 days, and then service again according to the procedures in temporary storage.

5. Inspection During Flyable Storage A. There are no inspection requirements for airplanes in flyable storage.

6. Inspection During Temporary Storage A. Airplanes in temporary storage must use the following procedure to complete an inspection. (1) Inspect the airframe for corrosion every 30 days. (2) Remove the dust collections as frequently as possible. (3) Clean and wax airplane as necessary. (4) Every 30 days do a minimum of one cylinder inspection for interior corrosion.

NOTE: Do not move the crankshaft during an inspection of the interior of cylinder.

7. Inspection During Indefinite Storage A. Airplanes in indefinite storage must use the following procedure to complete an inspection. (1) Inspect cylinder Protex plugs every seven days. Change Protex plugs if their color indicates an unsafe condition. (2) If Protex plugs have changed color in one half of the cylinders, all desiccant material in the engine must be replaced with new material. (3) Inspect the interior of one cylinder for corrosion through the spark plug hole and remove at least one rocker box cover and inspect the valve mechanism.

CAUTION: The corrosion preventive mixture is harmful to paint and shall be wiped from painted surfaces immediately.

(4) Spray cylinder interiors with corrosion preventative mixture every six months and replace the desiccant and Protex plugs.

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GARMIN GI 275 STANDBY BATTERY - MAINTENANCE PRACTICES

1. Description and Operation A. Description (1) This section gives the maintenance procedures and checks for the GI 275 Standby Battery. (2) The GI 275 Standby Battery is a rechargeable lithium-ion battery pack that is installed inside the Garmin GI 275 Attitude and Direction Indicator (ADI). The battery is encased in a metal compartment in the GI 275 Standby ADI unit, and held in place by a cover plate and screws. B. Operation (1) In the event of loss of aircraft power, the GI 275 Standby ADI will switch to the internal GI 275 Standby Battery for instrument operations. The battery provides 60 minutes of power to the instrument. The battery charges off the crossfeed electrical bus during normal aircraft operation.

2. Garmin GI 275 Standby Battery Removal/Installation A. Removal (1) Put the MASTER and AVIONICS switches in the OFF position. (2) Remove the screws that secure the GI 275 Standby ADI to the center instrument panel. (3) Carefully push the GI 275 Standby ADI away from the center instrument panel and toward the bottom of the main instrument panel to gain access to the top of the GI 275 unit. (4) Remove the screws that secure the battery cover plate to the top of the GI 275 Standby ADI. (5) Remove the battery cover plate from the instrument. (6) Remove the battery from the battery compartment. B. Installation (1) Put the battery in its place inside the battery compartment. (2) Put the battery cover plate in its place on the instrument. (3) Install the screws to secure the battery cover plate to the GI 275 Standby ADI. (4) Carefully put the GI 275 Standby ADI in its place on the center instrument panel. (5) Install the screws that secure the GI 275 to the center instrument panel. (6) If the GI 275 Standby Battery was replaced with a new one, allow the battery to fully charge. Then, do the Garmin GI 275 Standby Battery Rundown Test in this document.

3. Garmin GI 275 Standby Battery Rundown Test

NOTE: The Battery Rundown Test is required during the initial installation of a new GI 275 Standby ADI unit or GI 275 Standby Battery on the airplane. The Battery Rundown Test is not required if you reload the software on an existing GI 275 Standby ADI unit.

NOTE: This test must be completed if you reload the full configuration on the GI 275 Standby ADI unit. A. Do the GI 275 Standby Battery Rundown Test.

NOTE: The GI 275 Standby ADI is a touch screen instrument.

(1) Power on the GI 275 Standby ADI in configuration mode. (a) Push and hold down the inner encoder knob on the GI 275 Standby ADI instrument. (b) Put the MASTER switch in the ON position. (c) Release the inner encoder knob when the configuration mode splash screen displays on the GI 275 Standby ADI. (d) Touch ACCEPT on the configuration mode splash screen when prompted.

NOTE: If you do not acknowledge the configuration mode splash screen within 60 seconds, the unit will restart in normal mode.

(2) Scroll through the menu options and touch the CALIBRATION/TEST option. (3) Touch the BACKUP BATTERY TEST option.

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Figure 201 (Sheet 1)

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(4) Do the Before Test Checklist. (a) Touch the BEFORE TEST CHECKLIST option. (b) Make sure the current date is selected under the CHECKLIST page. (c) Make sure the BATTERY STATE is fully charged. (d) Touch ENTER TODAY'S DATE option and make sure today's date is filled in. (e) Touch FULLY CHARGE BATTERY option and make sure a green checkmark is present. (f) Touch the BACK option. (5) Touch the START TEST option. (6) Pull the STBY ADI circuit breaker on the circuit breaker panel when the GI 275 Standby ADI prompts you to SWITCH AIRCRAFT BATTERY MASTER TO OFF. (7) Allow the GI 275 Standby ADI unit to run the battery test until complete. (a) Make sure the battery runs the GI 275 Standby ADI for at least 60 minutes. (b) The test can take up to 150 minutes with a new battery. (c) The GI 275 Standby ADI will automatically record the results of the test to memory when the standby battery runs out of power. (8) Push in the STBY ADI circuit breaker on the circuit breaker panel. The GI 275 Standby ADI will start in normal mode. (9) Apply external power to the airplane. (10) Allow the GI 275 Standby Battery to recharge until the battery indication is at least amber. (11) Check the Battery Rundown Test results. (a) Power on the GI 275 Standby ADI in configuration mode. (b) Scroll through the menu and touch the CALIBRATION/TEST option. (c) Touch the BACKUP BATTERY TEST option. (d) Touch the TEST RESULTS option. (e) Make sure the test result is at least 60 minutes or greater. (f) If the test result is less than 60 minutes, repeat the test with a fully charged battery at ambient temperatures of at least 23°C. (g) If the test result still does not meet the 60 minute requirement, replace the battery pack with a new one. Refer to the Garmin GI 275 Standby Battery Removal/Installation in this document. (h) Restart the GI 275 Standby ADI in normal mode. (12) Remove external power from the airplane.

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CIRCUIT BREAKER - MAINTENANCE PRACTICES

1. General A. The circuit breaker panel is on the left lower instrument panel, below the pilot’s control wheel. The circuit breaker panel has electrical circuit breakers, the ignition/magneto switches, the master switch, the avionics master switch, and the light switches. B. The avionics circuit breaker panel is on the bottom of the copilot instrument panel. This panel has one of the following bezels: Standard, Nav I/II, Nav I/II with ADF, Nav I/II with MFD, Nav II with ADF/MFD, Nav II with ADF/IHAS, or Garmin.

2. Circuit Breaker Removal/Installation A. Remove the Circuit Breaker (Refer to Figure 201, Figure 202, or Figure 203).

NOTE: Removal installation of circuit breakers and avionics circuit breakers are typical.

(1) Remove the access/inspection plate (310AR) and disconnect the battery (UC001) cables. Refer to Chapter 6, Access/Inspection Plates - Description and Operation. (2) In the cockpit, remove the screws that attach the circuit breaker panel to the lower instrument panel. (3) Remove the screws that attach the circuit breaker cover to the circuit breaker panel. (4) Remove the circuit breaker cover. (5) Put a label on the applicable circuit breaker wires. (6) Disconnect the applicable circuit breaker wires. (7) Remove the screws and the washers that attach the bus bar to the circuit breakers. (8) Remove the bus bar. (9) Remove the nut that attaches the circuit breaker to the circuit breaker panel. (10) Remove the circuit breaker. B. Install the Circuit Breaker (Refer to Figure 201, Figure 202, or Figure 203).

NOTE: To install or align the circuit breaker cover, it is permitted to add an additional nut between each circuit breaker and circuit breaker panel.

(1) Put the circuit breaker in the circuit breaker panel and attach the circuit breaker with the nut. (2) Attach the bus bar to the circuit breakers with the screws and washers. (3) Remove the labels and connect the wires to the circuit breakers. (4) Install the circuit breaker cover assembly. (a) Put three tie straps between the circuit breakers and the panel. (b) Put the circuit breaker cover assembly over the circuit breakers. (c) The flanges on the cover fit between the circuit breakers and thepanel. (d) The recessed areas in the cover must align with the screw holes in the panel. (e) Put the main power bus wires and the circuit breaker panel assembly wire bundle out of the left side of the cover. (f) Attach the cover with three tie straps. (5) Attach the circuit breaker cover to the circuit breaker panel with the screws. (6) Put the circuit breaker panel on the lower instrument panel and attach with the screws. (7) Connect the battery cables (UC001) and install the access/inspection plate (310AR). Refer to Chapter 6, Access/Inspection Plates - Description and Operation.

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Circuit Breaker Panel Installation Figure 201 (Sheet 1)

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Circuit Breaker Panel Installation Figure 202 (Sheet 1)

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Circuit Breaker Panel Installation Figure 203 (Sheet 1)

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ELECTRICAL LOAD ANALYSIS - DESCRIPTION AND OPERATION

1. General A. The tables give an electrical load analysis of some of the components used on the airplane.

Table 1. Components on all airplanes

Component Draw at 24.0 VDC Draw at 28.0 VDC (Amperes) (Amperes) Landing Light (4596 Lamp) 7.65 8.93 Landing Light (4591 Lamp) 3.06 3.57 Landing Light (35 Watt HID) 1.65 1.41 Taxi Light (4587 Lamp) 7.65 8.93 Taxi Light (4626 Lamp) 4.59 5.36 Taxi Light (35 Watt HID) 1.65 1.41 Navigation Lights 2.65 3.10 Navigation Lights (LED) 0.90 0.90 Standby Indicator Light - Compass 0.01 0.02 (LED) Wing Anti-collision Lights (average 1.98 1.70 value) (Qty. 2) Beacon Light (peak value) 1.07 1.25 Beacon Light (LED) (peak value) 0.225 0.225 Under Wing Courtesy Lights (Qty. 2) 0.98 1.14 Pilot Overhead Light (1864 Lamp) 0.14 0.16 Pilot Overhead Light (LED Lamp) 0.02 0.02 Copilot Overhead Light (1864 Lamp) 0.14 0.16 Copilot Overhead Light (LED Lamp) 0.02 0.02 Passenger Overhead Light (1864 0.14 0.16 Lamp) Passenger Overhead Light (LED 0.02 0.02 Lamp) Map Light 0.08 0.09 Instrument Light (2 and 3 inch round) 0.02 0.02 (Each) Oxygen Control/Gauge Light 0.02 0.02 Pedestal Lights (Qty. 2) 0.08 0.10 Flap Motor 2.06 2.40 Fuel Pump 2.74 3.20 Pitot Heat 3.33 3.89 Stall Warning Heat 1.46 1.70

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Table 1. Components on all airplanes (continued) Component Draw at 24.0 VDC Draw at 28.0 VDC (Amperes) (Amperes) Stall Warning Horn 0.40 0.35 Prop Heat 13.3 15.5 12V Cabin Power Converter (Peak 6.33 5.42 10A out) Hourmeter 0.01 0.02 Battery Relay Coil 0.29 0.33 Start Relay Coil 0.85 N/A Alternator Relay Coil 0.29 0.33 Alternator Field and ACU Power 1.63 1.90 (Maximum) ACU Bus Sense 0.02 0.02 Start Motor 100 N/A Stormscope (WX-500) 0.93 0.80 ADF Receiver (KR 87) 0.60 0.52

Table 2. Components used only on airplanes that do not have Garmin G1000 installation.

Component Draw at 24 VDC Draw at 28 VDC (Amperes) (Amperes) Glareshield Light (Fluorescent) 0.86 1.00 Glareshield Light (LED) 0.17 0.20 Radio Lights 0.17 0.20 (All annunciations 0.35 0.30 on) Avionics Fan 0.43 0.50 Engine and Fuel Gauges 0.38 0.45 Audio Panel (KMA-26) (Maximum) 1.50 1.29 Audio Panel (KMA-28) (Maximum) 1.50 1.29 MFD (KMD-550) 0.93 0.80 GPS (KLN 89/89B) 1.45 1.25 GPS (KLN 94) 1.40 1.20 Transponder (KT 73) (Maximum) 1.07 1.25 Transponder (KT 76) (Maximum) 0.60 0.70 Altitude Encoder (SSD120) 0.20 0.23 HSI (KCS 55A) (Maximum) 1.46 1.25 #1 Nav/Comm (KX 155A) (Receive) 0.80 0.69

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Table 2. Components used only on airplanes that do not have Garmin G1000 installation. (continued) Component Draw at 24 VDC Draw at 28 VDC (Amperes) (Amperes) #1 Nav/Comm (KX 155A) (Transmit) 6.00 6.00 (Maximum) #2 Nav/Comm (KX 165A) (Receive) 0.80 0.69 #2 Nav/Comm (KX 165A) (Transmit) 6.00 6.00 (Maximum) Autopilot Computer (KAP 140) 0.58 0.50 Pitch Servo & Clutch (KAP 140) 0.58 0.50 Pitch Trim Servo & Clutch (KAP 140) 0.58 0.50 Roll Servo & Clutch (KAP 140) 0.53 0.45 Turn Coordinator (Blind) (KAP 140) 0.27 0.33

Table 3. Components used only on airplanes that have Garmin G1000 installation.

Component Draw at 24 VDC Draw at 28 VDC (Amperes) (Amperes) Circuit Breaker Panel Light (LED) 0.06 0.07 Switch Panel Light (LED) 0.07 0.08 Avionics Panel Lights (MFD, PFD, 0.17 0.20 A/P) Throttle/Flap Panel Light (LED) 0.07 0.08 Standby Battery Main Volt Sense 0.001 0.001 Standby Battery Controller 0.007 0.008 Standby Battery Test 2.00 N/A Main Bus Voltage Sense 0.001 0.001 Essential Bus Voltage Sense 0.001 0.001 Deck Skin Fan 0.28 0.33 PFD Fan 0.08 0.09 MFD Fan 0.08 0.09 #1 Comm (GIA 63) (Receive) 0.22 0.19 #1 Comm (GIA 63) (Transmit) 4.96 4.16 (VSWR 3) #2 Comm (GIA 63) (Receive) 0.22 0.19 #2 Comm (GIA 63) (Transmit) 4.96 4.16 (VSWR 3) #1 Nav (GIA 63) 0.94 0.80 #2 Nav (GIA 63) 0.94 0.80 PFD (GDU 1040) 1.46 1.25 MFD (GDU 1040) 1.46 1.25

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Table 3. Components used only on airplanes that have Garmin G1000 installation. (continued) Component Draw at 24 VDC Draw at 28 VDC (Amperes) (Amperes) AHRS (GRS 77) 0.29 0.25 Air Data Computer (GDC 74) 0.25 0.21 Engine/Airframe Unit (GEA 71) 0.20 0.17 Transponder (GTX 33) 1.17 1.00 Audio Panel (GMA 1347) 1.58 1.36 FIS (GDL-69A) 0.42 0.36 TAS (KTA 870) 1.34 1.15 Autopilot Computer (KAP 140) 0.58 0.50 Pitch Servo & Clutch (KAP 140) 0.58 0.50 Pitch Trim Servo & Clutch (KAP 140) 0.58 0.50 Roll Servo & Clutch (KAP 140) 0.53 0.45 Blind Turn Coordinator (KAP 140) 0.27 0.33 Pitch Servo & Clutch (GFC 700) 1.00 0.86 Pitch Trim Servo & Clutch (GFC 700) 1.13 0.96 Roll Servo & Clutch (GFC 700) 1.46 1.25 CAN Bus Fuel Level Sensors 0.10 0.09 Landing Light ( LED) (Qty. 2) 3.00 3.00 Taxi Light (LED) (Qty. 2) 1.00 1.00 Recognition Light (LED) (Qty. 2) 1.50 1.50 GI 275 Standby Flight Display 1.17 1.00

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INSTRUMENT AND CONTROL PANELS - MAINTENANCE PRACTICES Airplanes with Garmin G1000

1. General A. This section covers the removal and installation for the center panel, switch panel, flap/enviro panel, throttle/flap panel, throttle quadrant, and instrument panel.

2. Center Panel Removal/Installation A. Remove the Center Panel (Refer to Figure 201). (1) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position. (2) Disengage the STDBY IND-LTS circuit breaker. (3) Remove the screws that attach the center panel to the instrument panel. (4) Carefully pull out the center panel as necessary to get access behind the panel. (5) Install tags for identification on the electrical connectors and hoses and disconnect themfrom the instruments. B. Install the Center Panel (Refer to Figure 201). (1) Connect the electrical connectors and hoses to the applicable instruments. (2) Remove the tags from the electrical connectors and hoses. (3) Carefully put the center panel in the instrument panel. (4) Install the screws that attach the center panel. (5) Engage the STDBY IND LTS circuit breaker.

3. Switch Panel Removal/Installation A. Remove the Switch Panel (Refer to Figure 201). (1) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position. (2) Remove the screws that attach the switch panel to the instrument panel. (3) Carefully pull the switch panel out from the instrument panel to get access behind the panel. (4) Disconnect the electrical connections from the switches. (5) If you are not replacing the switch panel, disconnect the airplane wiring bundle electrical connector (PI039) from the LED panel electrical connector. B. Install the Switch Panel (Refer to Figure 201). (1) If the LED panel is not removed from the switch panel, connect the airplane wiring bundle electrical connector (PI039) to the LED panel electrical connector. (2) Connect the electrical connections to the switches. (3) Put the switch panel in the instrument panel. (4) Attach the switch panel with the screws.

4. Throttle/Flap Panel A. Throttle/Flap Panel Removal (Refer to Figure 201). (1) Disconnect the negative cable from airplane battery. Refer to Chapter 24, Battery - Maintenance Practices. (2) Make sure the MASTER ALT/BAT and AVIONICS switches are in the off position. (3) Remove the screws that attach the throttle/flap panel to the instrument panel. (4) Carefully pull the throttle/flap panel out from the instrument panel to get access behind thepanel. (5) Disconnect the electrical connections from the switches. (6) If you are not replacing the throttle/flap panel, disconnect the airplane wiring bundle electrical connector from the LED panel electrical connector. B. Throttle/Flap Panel Installation (Refer to Figure 201). (1) If the LED panel is not removed from the throttle/flap panel, connect the airplane wiring bundle electrical connector from the LED panel electrical connector. (2) Connect the electrical connections to the switches. (3) Put the throttle/flap panel in the instrument panel. (4) Attach the throttle/flap panel with the screws. (5) Connect the negative battery cable. Refer to Chapter 24, Battery - Maintenance Practices.

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Instrument and Control Panel Installation Figure 201 (Sheet 1)

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Instrument and Control Panel Installation Figure 201 (Sheet 2)

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5. Instrument Panel Removal/Installation A. Remove the Instrument Panel (Refer to Figure 201). (1) Disconnect electrical power to the airplane. (a) Make sure the AVIONICS switch is in the off position. (b) Disengage the two PFD circuit breakers, the MFD, STDBY BATT, STDBY IND-LTS AUDIO circuit breakers. (2) Remove the center panel. Refer to Center Panel - Removal/Installation. (3) Remove the switch panel. Refer to Switch Panel - Removal/Installation. (4) Remove the throttle/flap panel. Refer to Throttle/Flap Panel - Removal/Installation. (5) Remove the Audio Panel. Refer to Audio Panel - Maintenance Practices. (6) If installed, remove the Right Hand Switch and Circuit Breaker Panel. Refer to Right Hand Switch and Circuit Breaker Panel Removal/Installation. (7) Remove the screws that attach the control column collars to the instrument panel. (8) Remove the hourmeter to the instrument panel. (a) Remove the screws for the hourmeter. (b) Pull the hourmeter out and disconnect the connector. (9) Remove the Control Display Units (CDU). (a) Disengage the quick release fasteners. (b) Carefully pull the CDU away from the instrument panel and disconnect the electrical connector. (10) Remove the screws from the instrument panel.

NOTE: The ELT switch can only be removed from the back of the instrument panel.

(11) Disconnect and remove the ELT switch from the instrument panel. (12) Remove the instrument panel. B. Install the Instrument Panel (Refer to Figure 201). (1) Set the instrument panel in position. (2) Install the ELT switch and connect the electrical connector. (3) Install the instrument panel screws. (a) Make sure to put the electrical connector for the hourmeter through the panel hole for the hourmeter installation. (4) Connect the electrical connector to the hourmeter. (5) Install the hourmeter. (6) Attach the collar for the control column to the instrument panel. (7) Set the throttle/flap panel in position and connect the electrical connections to the switches. (8) Install the throttle/flap panel to the instrument panel with the screws. (9) Set the switch panel in position and connect the electrical connections to the switches. (10) Install the switch panel to the instrument panel with the screws. (11) Set the center panel in position and connect the electrical connectors and vacuum hoses to the instruments. (12) Install the center panel to the instrument panel with the screws. (13) Set the Control Unit Displays (CDU's) in position and connect the electrical connector. (14) Install the CDU's with the quick release fasteners to the instrument panel. (15) Engage the two PFD circuit breakers, the MFD, STDBY BATT, STDBY IND-LTS AUDIO circuit breakers.

6. Right Hand Switch and Circuit Breaker Panel Removal/Installation A. Remove the Right Hand Switch and Circuit Breaker Panel (Refer to Figure 202). (1) Disconnect the main battery. Refer to Chapter 24, Battery - Maintenance Practices. (2) Make sure the MASTER and AVIONICS switches are in the off position. (3) Remove the screws that attach the right hand switch and circuit breaker panel to the instrument panel. (4) Carefully pull the right hand switch and circuit breaker panel out from the instrument panel to get access behind the panel.

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Right Hand Switch and Circuit Breaker Panel Installation Figure 202 (Sheet 1)

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(5) Disconnect the electrical connector (PI039/JI039) from the right hand switch and circuit breaker panel. (6) Disconnect the electrical connector (JI049) from the BUS 3 switch (SI037). (7) If you are not replacing the right switch and circuit breaker panel, disconnect the LED panel electrical connector (PI050) from the airplane wiring bundle electrical connector. (8) Remove the right hand switch and circuit breaker panel from the airplane. B. Install the Right Hand Switch and Circuit Breaker Panel (Refer to Figure 201). (1) Connect the electrical connector (JI049) to the BUS 3 switch (SI037). (2) Connect the electrical connector (PI039/JI039) to the right hand switch and circuit breaker panel. (3) If the LED is not removed from the right switch and circuit breaker panel, connect the LED panel electrical connector (PI050) from the airplane wiring bundle electrical connector. (4) Put the right hand switch and circuit breaker panel in the instrument panel. (5) Attach the right hand switch and circuit breaker panel to the instrument panel with the screws. (6) Connect the main battery. Refer to Chapter 24, Battery - Maintenance Practices. (7) Do a check of the system(s) using BUS 3 power. Refer to applicable sections of this maintenance manual.

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PITOT AND STATIC SYSTEMS - MAINTENANCE PRACTICES

1. General A. The pitot system supplies ram air pressure to the airspeed indicator or the GI 275 Standby Attitude and Direction Indicator (if installed) from an “L” shaped heated pitot tube. It is found in the left wing at approximately WS 62.00. The heating element in the pitot tube is controlled by the PITOT HEAT/OFF switch on the circuit panel assembly. B. The static system provides atmospheric pressure for the autopilot, blind encoder (on airplanes without Garmin G1000), airspeed indicator, altimeter, and vertical speed indicator or GI 275 Standby Attitude and Direction Indicator (If installed) through tubing connected to the left and right static ports. (1) A static line sump assembly is installed at each static port which collects condensation from the ambient air in the static system. An alternate static source from the cockpit is available for use when the external static source is not serviceable. This alternate source is controlled with the alternate static source valve and is selected by pulling the ALT STATIC AIR PULL ON alternate static source knob on the stationary panel assembly. An opening in the side of the alternate static source valve body is used to get static pressure data from the cockpit area. Refer to the Pilot’s Operating Handbook for flight operation with the alternate static source. Refer to Figure 201 for pitot/static system schematic.

NOTE: For airplanes with the optional KAP-140 Two Axis Autopilot but without the Garmin G1000, an additional static tube is connected to the autopilot from a tee fitting from the blind encoder. C. Correct maintenance of the pitot and static system is necessary for correct operation of the altimeter, vertical speed and airspeed indicators, and, if installed, the autopilot. Leaks, moisture, and blockage can affect readings of the instruments. Under instrument flight conditions, these instrument errors can be unsafe. Cleanliness and security are the principal rules for system maintenance. The pitot tube and static ports must be kept clean with no blockage. D. For additional information and maintenance requirements of the blind encoder, refer to the introduction of the List of Manufacturers Technical Publications.

2. Pitot Tube Removal/Installation A. Pitot Tube Removal (Refer to Figure 202). (1) Set the ALT/BAT MASTER switch to the off position. (2) Make sure the PITOT HEAT switch is set to the OFF position. (3) Get access to the pitot tube assembly in the left wing. (4) Remove the screws that attach the pitot tube assembly to the wing structure. (5) Disconnect the ram air tube from the pitot tube assembly. (6) Disconnect the electrical wires for the pitot tube heater. B. Pitot Tube Assembly Installation (Refer to Figure 202).

CAUTION: Never blow through the pitot lines toward the instruments, as damage will occur to the instruments.

NOTE: For correct operation, keep the pitot tube assembly clean and all system components free of obstruction and leaks.

(1) Set the pitot tube assembly in position and connect the ram air tube to the pitot tube assembly. (2) Connect the electrical wires to the pitot tube heater. (3) Attach the pitot tube assembly to the wing structure with the screws. (4) Set the ALT/BAT MASTER switch to the ON position. (5) If necessary, set the PITOT HEAT switch to the HEAT position. (6) Do a leak check. Refer to the Pitot System Inspection and Leakage Test.

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Pitot/Static System Schematic Figure 201 (Sheet 1)

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Pitot/Static System Schematic Figure 201 (Sheet 2)

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Pitot/Static System Schematic Figure 201 (Sheet 3)

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Pitot/Static System Schematic Figure 201 (Sheet 4)

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Pitot/Static Systems Installation Figure 202 (Sheet 1)

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Pitot/Static Systems Installation Figure 202 (Sheet 2)

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3. Sump Assembly Removal/Installation

NOTE: The removal and installation is typical for the left and right sump assembly. A. Sump Assembly Removal (Refer to Figure 202). (1) Get access to the sump assembly at FS 7.94. (2) Loosen the nut that connects the static tube to the sump assembly nipple. (3) Turn the sump assembly and remove the sump assembly from the elbow. B. ump Assembly Installation (Refer to Figure 202).

NOTE: Apply Teflon® tape (U000912) as necessary where plastic and metal connections interface.

(1) Attach the sump assembly to the elbow. (2) Connect the static tube to the sump assembly nipple with the nut. (3) Do a leak check. Refer to the Static Pressure System Inspection and Leakage Test.

4. Alternate Static Source Valve Removal/Installation A. Alternate Static Source Valve Removal (Refer to Figure 202). (1) Loosen the nuts behind the stationary control panel that connect the two static tubes to the alternate static source valve. Disconnect the static tubes from the alternate static source valve. (2) Remove the screws that attach the alternate static source valve to the stationary control panel. B. Alternate Static Source Valve Installation (Refer to Figure 202). (1) Set the alternate static source valve behind the stationary control panel and attach the static tubes with the nuts. (2) Attach the alternate static source valve to the stationary control panel with the screws. (3) Make sure that the vent hole is not blocked. (4) Do a leak check. Refer to the Static Pressure System Inspection and Leakage Test.

5. Blind Encoder Removal/Installation (On airplanes without Garmin G1000) A. Blind Encoder Removal (Refer to Figure 202).

NOTE: The blind encoder is behind the stationary instrument panel on the right forward fuselage at WL 0.00, between FS 7.94 and FS 17.00.

(1) Set the ALT/BAT MASTER switch to the off position. (2) Disconnect the static tube from the blind encoder. (3) Disconnect the electrical connector from the blind encoder. (4) Loosen the knurl nut attaching the blind encoder in the mounting tray and remove the blind encoder. B. Blind Encoder Installation (Refer to Figure 202). (1) Put the blind encoder in the mounting tray and attach it with the knurl nut. (2) Connect the static tube to the blind encoder. (3) Connect the electrical connector to the blind encoder. (4) Set the ALT/BAT MASTER switch to the ON position. (5) Do a leak check. Refer to the Static Pressure System Inspection and Leakage Test.

6. Vertical Speed Indicator Removal/Installation A. Vertical Speed Indicator (VSI) Removal (Refer to Figure 203). (1) Set the ALT/BAT MASTER switch to the off position. (2) Remove the center pilot's panel to get access to the back of the VSI. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices. (3) Disconnect the static tube and the vertical speed connector from the VSI. (4) Remove the screws that attach the VSI to the center pilot's panel.

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Pitot and Static System Indicator Installation Figure 203 (Sheet 1)

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B. Vertical Speed Indicator (VSI) Installation (Refer to Figure 203). (1) Install the VSI behind the center pilot's panel and attach it with the screws. (2) Connect the static tube and the vertical speed connector to the VSI. (3) Install the center pilot's panel. Refer to Chapter 31, Instrument and Control Panels - Maintenance Practices. (4) Set the ALT/BAT MASTER switch to the ON position. (5) Do a leak check. Refer to the Static Pressure System Inspection and Leakage Test.

7. Altimeter Removal/Installation A. Altimeter Indicator Removal (Refer to Figure 203). (1) Make sure that the MASTER and AVIONICS switches are in the OFF position. (2) Remove the screws that hold the altimeter to the panel. (3) Carefully pull the panel out to get access to the back of the altimeter. (4) Disconnect the static tubes from the tee on the altimeter indicator. (5) Remove the screws that attach the altimeter to the panel. (6) Remove the altimeter from the airplane. B. Altimeter Indicator Installation (Refer to Figure 203). (1) Install the altimeter to the panel with the screws. (2) Connect the static tubes to the altimeter. (3) Install the panel to the structure with screws. (4) Do a leak check. Refer to Static Pressure System Inspection and Leakage Test.

8. Airspeed Indicator Removal/Installation A. Airspeed Indicator Removal (Refer to Figure 203). (1) Make sure that the MASTER and AVIONICS switches are in the off position. (2) Remove the screws that hold the airspeed indicator to the panel. (3) Disconnect the pitot tube from the airspeed indicator. (4) Disconnect the static tube from the airspeed indicator. (5) Disconnect the electrical connector (JI009) from the airspeed indicator. (6) Remove the screws that attach the airspeed indicator to the panel (7) Remove the airspeed indicator from the airplane. B. Airspeed Indicator Installation (Refer to Figure 203). (1) Install the airspeed indicator to the panel with the screws. (2) Connect the pitot tube to the airspeed indicator. (3) Connect the static tubes to the airspeed indicator. (4) Connect the electrical connector (JI009) to the airspeed indicator. (5) Install the panel to the structure with the screws. (6) Do a leak check. Refer to Static Pressure System Leak Test/Inspection.

9. Static Pressure System Leak Test/Inspection A. Do a leak test and do an inspection. (1) Make sure that there are no restrictions or moisture in the static system. (2) Make sure there are no alterations or deformations of the airframe surface in the area around the static ports.

NOTE: Airframe surface damage affects the relationship between air pressure in the static pressure system and true ambient air pressure for any flight configuration.

(3) Make a seal to one static source port with pressure sensitive tape. The seal must be air tight. (4) Make sure that the valve to the alternate source for the static pressure is closed. (5) Attach a source of suction to the remaining static pressure port. (6) Slowly apply suction until the altimeter indicates a 1000 foot increase in altitude.

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CAUTION: When you apply or release suction, do not exceed the range of the vertical speed indicator or the airspeed indicator.

(7) Stop the suction to maintain a closed system for one minute. Leakage must not exceed 100 feet of altitude loss as indicated on the altimeter. (8) If the rate of the leak is within tolerance, slowly release the suction source and remove the tape from the static port. (9) If the rate of the leak exceeds the maximum permitted, tighten all the connections first and then do the leak test again. If the rate of the leak still exceeds the maximum permitted, do as follows. (a) Disconnect the static pressure lines from the airspeed indicator and the vertical speed indicator. (b) Attach the lines together with permitted fittings. The altimeter must be the only instrument connected into the static pressure system. (c) Do a leak test to check if the static pressure system or the bypassed instruments are the cause of a leak. (10) If the instruments are the cause of the leak, they must be replaced or repaired by an applicable repair station. If the static pressure system is at fault, use the procedure that follows to find the leak. (a) Attach a source of positive pressure to the static source entrance.

CAUTION: Do not apply positive pressure with the airspeed indicator or vertical speed indicator connected to the static pressure system.

(b) Slowly apply positive pressure until the altimeter shows a 500-foot decrease in altitude. (c) Maintain the altimeter indication while checking for leaks. Apply LEAK-TEC or a solution of mild soap and water to the line connections and the static source flange. Watch for bubbles to find the leaks. (d) Tighten the connections that have leaks. Parts that have damage must be repaired or replaced. (e) Connect the airspeed and the vertical speed indicators into the static pressure system. (11) Do the leak test again.

10. Pitot System Leak Test/Inspection A. Do a leak test and do an inspection. (1) Apply a piece of tape over the small hole in the lower aft end of the pitot tube. (2) Attach a piece of rubber or plastic tube over the end of the pitot tube. (3) Close the opposite end of the plastic tube and slowly roll up the tube. (4) Pressurize the pitot system to a minimum airspeed indication of 120 knots with the pitot tube drain hole blocked. (5) Maintain the pressure. (6) After one minute, the leak must not be more than 1 knot after the pressure source has been isolated from the pitot system.

CAUTION: Unroll the tubing slowly or damage will occur to the instrument or the air data computer.

(7) Slowly unroll the tubing to reduce the pressure gradually before you remove it. (8) Remove the tape from the small hole at the aft end of the pitot tube. (9) If the test reveals a leak in the system, check all the connections for tightness.

34-11-00 Page 211 © TEXTRON AVIATION INC. Jun 1/2021 ICA-182-34-80001 Form 2261 Rev 1 CESSNA® MODEL 182 (SERIES 1997 AND ON) MAINTENANCE MANUAL

GI 275 STANDBY ATTITUDE AND DIRECTION INDICATOR - MAINTENANCE PRACTICES

1. Description and Operation A. Description (1) This section gives the maintenance procedures, troubleshooting, and operational checks for the Garmin GI 275 Standby Attitude and Direction Indicator (ADI). If installed, this unit can be found on airplanes with the Garmin G1000 avionics suite. (2) The Garmin GI 275 Standby ADI is a self-contained, situational awareness unit that combines the functions of an altimeter, horizon gyro, and airspeed indicator into a single instrument. The GI 275 keeps the function of independent standby instruments and interfaces with the Garmin G1000 avionics system via an ARINC 429 data busing system. The unit is installed on the instrument center panel and has internal Air Data and Attitude Heading Reference (ADAHRS) sensors that collect flight data outside of the existing Attitude Heading Reference System (AHRS). The existing pitot-static system connects to the GI 275 ADI via two ports on the back of the unit. (3) The GI 275 Standby ADI unit is configured using a software that is loaded through a USBport and a configuration module that stores configuration data related to the specific airplane. The GI 275 USB port used to load the software is captured in the wire bundle connected to the GI 275 plug behind the instrument panel. The airplane-specific configuration module is located on the ship-side of the GI 275 electrical connector. (4) Power is supplied to the GI 275 Standby ADI unit through an electrical connector that connects to the back of the ADI unit. Power is routed through the STBY ADI circuit breaker on the circuit breaker panel. The GI 275 has an internal lithium-ion battery pack that supplies power for a minimum of 60 minutes in the event of a power loss. For more information on the GI 275 standby battery, refer to GI 275 Standby Battery - Maintenance Practices. B. Operation (1) The Garmin GI 275 Standby ADI gives the pilot standby altitude, airspeed, and attitude data. This data is collected outside of the airplane's existing ADAHRS unit via the GI 275 ADI's internal ADAHRS sensors and separate pitot-static connections, although the primary ADAHRS and GI 275 ADAHRS share common pitot and static ports. The information is converted into digital information, which is then displayed on the GI 275 ADI screen. (2) The GI 275 uses an encoder knob or touchscreen for instrument navigation inputs. This touchscreen display is configured so that attitude, airspeed, and altitude are always visibleon the top half of the screen when you navigate through the ADI menus. Under normal conditions, pilot input is not necessary except to manually set the barometric pressure in the event of aircraft power loss or loss of the G1000 avionics system. When available, the barometric pressure will automatically sync with the Garmin G1000 data. The encoder knobs navigation inputs are as follows: the outer knob is used for page navigation and inner knob can be used to adjust slider menus or as an 'Enter' key when you press down on it. (3) Instrument display brightness is controlled through the existing standby dimmer potentiometer on the instrument panel. An internal photocell provides an automatic dimming function in the event of a lighting bus loss of power.

2. GI 275 Standby ADI Removal/Installation A. Remove the GI 275 Standby ADI (Refer to Figure 201). (1) Put the MASTER and AVIONICS switches in the OFF position. (2) Remove the center instrument panel screws. (3) Carefully pull out the center panel as necessary to gain access behind the panel. (4) Disconnect the pitot and static tubes and electrical connectors from the back of the GI 275 Standby ADI. (5) Remove the screws that hold the GI 275 Standby ADI to the instrument panel. (6) Remove the GI 275 Standby ADI from the airplane. B. Install the GI 275 Standby ADI (Refer to Figure 201). (1) Put the GI 275 ADI in its place on the center instrument panel. (2) Install the screws that hold the GI 275 ADI to the instrument panel. (3) Reconnect the pitot and static tubes and electrical connectors to the back of the GI 275 ADI.

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(4) Carefully put the center panel in its place on the airplane. (5) Install the center instrument panel screws. (6) Do the GI 275 Software Load and Configuration Verification in this document. (7) If you replaced the GI 275 Standby ADI with a new unit, do the tests that follow: (a) Do the GI 275 Standby ADI AHRS Calibration in this document. (b) Do the GI 275 Standby Battery Rundown Test in Chapter 24, GI 275 Standby Battery - Maintenance Practices. (8) Do a check of the system for leaks. Refer to the Static System Leak Test in Chapter 34, Pitot/ Static System - Maintenance Practices.

3. GI 275 Standby ADI Software and Configuration Installation

NOTE: The GI 275 Standby ADI is a touch screen instrument.

NOTE: The GI 275 can take up to 30 seconds after boot up in configuration mode or insertion of the Garmin USB drive before files are visible. A. Do the GI 275 Standby ADI Software load procedure. (1) Power on the GI 275 Standby ADI in configuration mode. (a) Push and hold down the inner encoder knob on the GI 275 Standby ADI instrument. (b) Put the MASTER switch in the ON position. (c) Release the inner encoder knob when the configuration mode splash screen displays on the GI 275 Standby ADI. (d) Touch ACCEPT on the configuration mode splash screen when prompted.

NOTE: If you do not acknowledge the configuration mode splash screen within 60 seconds the unit will restart in normal mode.

(2) Get access to the GI 275 wire bundle behind the instrument panel. (3) Insert the Garmin GI 275 USB drive into the USB port contained in the GI 275 wire bundle. (4) Touch the SW/CONFIG option. (5) Touch the LOADER CARD option. (6) Touch the SELECT ALL option on the top right side of the screen. (7) Touch the UPDATE PACKAGES option. (8) Touch the BEGIN UPDATE option. The software will begin to load into the GI 275 Standby ADI unit. A progress bar will appear at the top of the screen. It will take about 4 minutes to load the software. (9) Once the software load is complete, touch the RESTART NOW option. (10) If you need to reload the configuration, continue to the GI 275 Standby ADI Configuration installation procedure. (11) If you are complete with your software maintenance, do the GI 275 Software Load and Configuration Verification procedure. (12) Put the MASTER switch in the OFF position. (13) Disconnect the Garmin GI 275 USB drive from the USB port behind the instrument panel. (14) Install access panels as necessary. B. Do the GI 275 Standby ADI Configuration load procedure. (1) If you have not reloaded the software, prepare the GI 275 Standby ADI for a new configuration load. If you have reloaded the software, go to the next step. (a) Get access to the GI 275 wire bundle behind the instrument panel. (b) Insert the Garmin GI 275 USB drive into the USB port contained in the GI 275 wire bundle. (c) Push and hold down the inner encoder knob on the GI 275 Standby ADI instrument. (d) Put the MASTER switch in the ON position. (e) Release the inner encoder knob when the configuration mode splash screen displays on the GI 275 Standby ADI. (f) Touch ACCEPT on the configuration mode splash screen when prompted.

NOTE: If you do not acknowledge the configuration mode splash screen within 60 seconds the unit will restart in normal mode.

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Pitot and Static System Indicator Installation Figure 201 (Sheet 1)

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(2) In the configuration menu, touch the SW/CONFIG option. (3) Touch CONFIG OPTIONS. (4) Touch the IMPORT CONFIGURATION option. (5) Touch the SELECT FILES option. (6) Select the GI_CNFG_182T001.gca file and touch SELECT CONFIGURATION. This will take you to the IMPORT CONFIG page. (7) Touch SELECT ALL at the top of IMPORT CONFIG page. (8) Touch the BACK arrow on the left hand side of the screen. (9) Touch IMPORT CONFIG and touch START. A progress bar will appear as the file copies. This will take about one minute. (10) Once the configuration is complete, touch RESTART NOW. The unit will restart in configuration mode. (11) If you installed a new GI 275 Standby ADI, do the GI 275 AHRS Calibration in this document. If you did not install a new GI 275 on the airplane, go to the next step. (12) Do the GI 275 Standby Battery Rundown Test. Refer to Chapter 24, GI 275 Standby Battery - Maintenance Practices. (13) Restart the unit in normal mode. (a) Navigate to RESTART OPTIONS with the arrows on the right hand side of the screen. (b) Touch RESTART ALL TO NORMAL. (c) Make sure there are no Red X's on the screen. (14) Put the MASTER switch in the OFF position. (15) Disconnect the Garmin GI 275 USB drive from the USB port behind the instrument panel. C. Do the Software Load and Configuration Verification procedure. (1) Connect external power to the airplane. (2) Power on the GI 275 Standby ADI in configuration mode. (a) Push and hold down the inner encoder knob on the GI 275 Standby ADI instrument. (b) Put the MASTER switch in the ON position. (c) Release the inner encoder knob when the configuration mode splash screen displays on the GI 275 Standby ADI. (d) Touch ACCEPT on the configuration mode splash screen when prompted.

NOTE: If you do not acknowledge the configuration mode splash screen within 60 seconds the unit will restart in normal mode.

(3) Navigate to the SW/CONFIG option and touch it to select. (4) Touch CONFIG OPTIONS. (5) Touch the SUMMARY option. (6) Touch the VIEW SUMMARY option. (7) Touch the GI 1 option. (8) Verify that the software versions match as shown:

Software Version Main SW Version 2.20 Wifi SW Version 2.20 Exp Software Version 2.20 (9) Touch the BACK option. (10) Verify the configuration loaded in the GI 275 matches the configuration called out in Figure202. (11) Put the MASTER switch in the OFF position. (12) Disconnect external power from the airplane.

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4. GI 275 Standby ADI AHRS Calibration

NOTE: The AHRS Calibration is only required during the initial installation of a new GI 275 Standby ADI unit on the airplane. The AHRS calibration is not required if you reload the software or the configuration on an existing GI 275 Standby ADI unit. A. Do the GI 275 Standby ADI AHRS calibration.

NOTE: The GI 275 Standby ADI is a touch screen instrument.

(1) Level the airplane to a flight attitude. Refer to Chapter 8, Leveling - Maintenance Practices. (2) Connect external power to the airplane. (3) Power on the GI 275 Standby ADI in configuration mode. (a) Push and hold down the inner encoder knob on the GI 275 Standby ADI instrument. (b) Put the MASTER switch in the ON position. (c) Release the inner encoder knob when the configuration mode splash screen displays on the GI 275 Standby ADI. (d) Touch ACCEPT on the configuration mode splash screen when prompted.

NOTE: If you do not acknowledge the configuration mode splash screen within 60 seconds the unit will restart in normal mode.

(4) Once in configuration mode, scroll through the options and touch the CALIBRATION/TEST option. (5) Touch the CALIBRATE PITCH/ROLL option. (6) Touch the ATTITUDE/HEADING option. (7) Make sure that AHRS 2 is selected. (8) Touch ENTER on the right hand side of the screen. (9) Touch START. A 30 second countdown will appear as the unit calibrates. (10) Touch DONE once the calibration is complete. (11) Make sure the values displayed are approximately -1.20 pitch and 0.0 roll. (12) Touch the BACK option twice to return to the configuration menu. (13) Scroll through the menu options and touch RESTART OPTIONS. (14) Touch the RESTART ALL TO NORMAL. (15) Make sure the unit restarts into normal mode and there are no red X's present on the screen. (16) Put the MASTER switch in the OFF procedure. (17) Disconnect external power to the airplane.

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Pitot and Static System Indicator Installation Figure 202 (Sheet 1)

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Pitot and Static System Indicator Installation Figure 202 (Sheet 2)

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Pitot and Static System Indicator Installation Figure 202 (Sheet 3)

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Pitot and Static System Indicator Installation Figure 202 (Sheet 4)

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Pitot and Static System Indicator Installation Figure 202 (Sheet 5)

34-21-20 Page 210 © TEXTRON AVIATION INC. Jun 1/2021 ICA-182-34-80001 Form 2261 Rev 1 TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

SUPPLEMENT NO: ICA-182-34-80001 Revision A APPENDIX A: ILLUSTRATED PARTS CATALOG

Nomenclature Part Number QTY GMU44B Magnetometer 011-04201-00 1 - Cover Plate 1222022-1 1 - Cover Plate Screws MS35214-23 3 - Flux Detector Bracket 0522649-3 1 - Magnetometer Rack 125-00437-00 1 - Magnetometer Rack Screws MS24693-BB26 3 - Installation Label 9754008-24 1 Circuit Breaker Panel Assembly 0718018-28 1 GI275 Standby Avionics 3930499-1 1

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

SUPPLEMENT NO: ICA-182-34-80001 Revision A APPENDIX B: WIRING DIAGRAM MANUAL

© TEXTRON AVIATION INC. Form 2261 Rev 1 CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

23-50-04

XM AUTO MUTE GDL-69A XM (NAV III) AIRPLANES (182) 81318 & ON AND AIRPLANES (T182) 8232 & ON

Figure 02 Page 1 23-50-04Aug 18/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL NOTES: 1. ALL WIRE 22AWG UNLESS OTHERWISE NOTED.

2 PART OF GARMIN CONNECTOR KIT 011-01000-01 3 PART OF GARMIN CONNECTOR KIT 011-00997-01

3 DATA LINK PI533 (P691)

2 PT311 INT AVN #2 (2P604)

AUDIO 64 29 ANNUNCIATE 6 SUPPRESION 4

XM AUTOMUTE182

3927149_1

XM AUTO MUTE GDL-69A XM (NAV III) Figure 02. (Sheet 1) Figure 02 Page 2 23-50-04 Aug 18/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

XM AUTO MUTE GDL-69A XM (NAV III)

AIRPLANES (182) 81318 & ON AND AIRPLANES (T182) 8232 & ON

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

PI533 M39029/58-360 CONTACT PIN 0TRC3 (182) 81318 & ON 01 (T182) 8232 & ON PT311 M39029/58-360 CONTACT PIN 0TRC3 (182) 81318 & ON 01 (T182) 8232 & ON

Figure 02 Page 3 23-50-04 Aug 18/2021 ©TEXTRON AVIATION INC. This Page Intentionally Left Blank. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

24-61-01

CIRCUIT BREAKER PANEL W/NAVIII AIRPLANES (182) 83135 & ON

Figure 09 Page 1 24-61-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL HI016 ELECT BUS 1 PC025 JC025 CB / SWITCH PANEL DISC 21 HI025 2HI025-1PC025(20) 1 FUEL PUMP 5 NOTES: 21 1. ALL WIRE 22AWG, UNLESS OTHERWISE NOTED. HI026 2HI026-2PC025(18) 2 BEACON LIGHT 5 (REF SWITCH PANEL - NAV III OPTION) 2 CAP AND STOW WIRE WHEN OPTION IS NOT INSTALLED. 21 HI065 2HI065-3PC025(20) 3 REFER TO 24-40-01 LANDING LIGHT 5 3 INSTALL PROTECTIVE TUBING OVER DIODE AS SHOWN: 21 HI023 2HI023-4PC025(14) 4 AVIONICS 1 15 15 1N6391 HI015 1 CABIN LTS/PWR 5 2 21 PC024 JC024 HI007 ELECT CB PNL DISC FLAPS 10 HI021 CROSSFEED BUS 2HI015-1PC024(20) 1 (REF CABIN EQPMT PWR INTERFACE) REFER TO 24-50-01 REFER TO 24-20-01 SHRINK SLEEVE 3 2HI015-2PC024 2 (REF INTERIOR LIGHTS) REFER TO 33-11-02 (M23053/5 REF) (REF ALTERNATOR SYSTEM) (10) HI016-2DI001(14) 12 DI001 2HI007-3PC024(16) 3 (REF WING FLAPS) REFER TO 27-50-01 QTY 2 2DI007-HI016(14) 21 HI010 2HI010-15PC025 4 USE HIGH CURRENT CONTACTS (REF S3373-X). ALT. FIELD 5 HI014 2HI022-4PC024 4 (REF ENGINE/AIRFRAME MONITOR - NAV III) REFER TO 77-40-01 ELECT BUS 2 21 5 ROUTE ALL WIRES REFER TO 24-20-01 HI022 2HI022-14PC025(20) CLEAR OF RI010 WARNING 5 HI067 5 (REF DIMMING) REFER TO 33-10-01 RESISTOR BY AT (REF ALTERNATOR SYSTEM) (10) HI014-2DI002(14) STBY ADI 12 6 (REF ENGINE/AIRFRAME MONITOR - NAV III) LEAST 0.5 INCH. 2DI006-HI014(14) REFER TO 77-40-01 3 21 2HI067-24PC023 7 (REF ENGINE/AIRFRAME MONITOR - NAV III) RESISTOR MAY GET 21 DI002 5 HI003 2HI003-8PC024 8 (REF DIMMING) HOT. PANEL LIGHTS 5 REFER TO 33-10-01 2HI003-9PC024 9 (REF DIMMING) 21 6 FIS CIRCUIT BRKR. HI024 WAS OPTIONAL PRIOR AVIONICS 2 15 PC025 JC025 TO 18281664 & ON, HI066 21 CB / SWITCH PANEL DISC T18208470 & 0N. WIRE RECOG TAXI LIGHT 5 2HI045-12PC023 WAS 2HI024-5PC025(14) 5 "CAP AND STOW" 21 HI029 2HI066-6PC025(20) 6 WHEN OPTION NOT NAV. LIGHT 5 2HI029-7PC025(20) 7 INSTALLED. 21 HI031 2HI031-8PC025(20) 8 STROBE LIGHTS 5 7 DME/ADF CIRCUIT 14 (REF SWITCH PANEL - NAV III OPTION) REFER TO 24-40-01 BREAKER WAS ADF 21 HI032 2HI032-9PC025(18) 9 PRIOR TO 18281741 PITOT HEAT 10 10 & ON, T18208480 & ON. 4 8 TERMINATE WIRES 2HI034-11PC025(14) 11 USING 52927 12 TERMINALS. HI020 13 9 FIS AND STORM ESSENTIAL BUS CIRCUIT BREAKERS PC023 JC023 WERE STANDARD FROM 12 DI006 3 AVN CB PNL DISC 18282281 THRU 18282368, HI034 21 T18209024 THRU T18209100 STANDBY BATT 20 2HI022-22PC023 22 (REF ELT) REFER TO 25-60-01 AND MADE OPTIONAL AT 21 18282369 & ON, T18209101 & ON, HI035 2HI035-5PC024 24 (GI 275 STBY) REFER TO 34-22-02 STNDBY IND LTS 5 -7 &-8 WIRE ASSYS REMAIN UNCHANGED. 21 HI036 2HI036-1PC023 1 (REF PRIMARY FLT. DISPLAY) REFER TO 23-20-01 PFD 5 10 VENDOR SUPPLIED 2HI037-2PC023(18) 2 (REF AIR DATA / AHRS) REFER TO 31-60-01 WIRES TO BE CUT, 1 HI037 2HI037-3PC023(18) 3 (REF AIR DATA / AHRS) REFER TO 34-21-01 NOT TO EXCEED 2 ADC/AHRS 10 2 INCHES IN LENGTH. 2HI038-6PC024(16) 1 HI038 2HI038-4PC023(16) 4 (REF NAV 1) REFER TO 34-61-01 NAV 1/ENG 15 2 21 HI039 2HI039-5PC023(20) 5 (REF COMM 1) REFER TO 34-60-01 COMM 1 5 12 DI007 3 HI018 AVN BUS 1 HI018-12PC025(14) 2HI040-7PC024(16) 1 HI040 2HI040-6PC023(16) 6 (REF NAV 1) REFER TO 34-60-01 NAV 1/ENG 15 2 2HI041-7PC023(18) 7 (REF AIR DATA / AHRS) 1 REFER TO 34-21-01 HI041 2HI041-8PC023(18) 8 (REF AIR DATA / AHRS) ADC/AHRS 10 2 21 HI042 2HI042-9PC023 9 (REF PRIMARY FLT. DISPLAY) REFER TO 31-60-01 PFD 5 2 9 STORM SCOPE 2HI043-10PC023 10 (REF STORMSCOPE) REFER TO 34-40-01 (OPTION) 2 TAS 2HI044-11PC023 11 (REF TRAFFIC OPTION) REFER TO 34-40-02 (OPTION) 2 9 FIS 2HI045-12PC023 12 (REF WEATHER OPTION) REFER TO 34-40-01 (OPTION) 2 7 DME/ADF 2HI046-13PC023 13 (REF ADF OPTION) REFER TO 34-50-03 (OPTION) 10 HI073 10 (VEND)(16) 21 (VEND)(16) 2HI073-23PC023(20) 23 (REF AOA - SAFE FLIGHT) HI019 5 AVN BUS 2 AOA HI019-13PC025(14) 2HI047-14PC023 14 (REF AUTO PILOT) REFER TO 22-10-04 1 HI047 2HI047-15PC023 15 (REF AUTO PILOT) REFER TO 34-53-01 AUTO PILOT 5 2 2HI047-16PC023 16 (REF AUTO PILOT) REFER TO 23-50-01 21 HI048 2HI048-17PC023 17 (REF TRANSPONDER) REFER TO 34-53-01 XPDR 5 21 HI049 2HI049-18PC023 18 (REF AUDIO PANEL) REFER TO 23-50-01 AUDIO 5 21 HI050 2HI050-19PC023(20) 19 (REF COMM 2) REFER TO 34-60-01 COMM 2 5 21 HI051 2HI051-20PC023 20 (REF NAV 2) REFER TO 34-60-01 NAV 2 5 0770519Q14 21 HI052 2HI052-21PC023 21 (REF MULTI FUNCTION FLT. DISPLAY) REFER TO 34-20-03 MFD 5

CIRCUIT BREAKER PANEL W/NAVIII Figure 09. (Sheet 1) Figure 09 Page 2 24-61-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

CIRCUIT BREAKER PANEL W/NAVIII

AIRPLANES (182) 83135 & ON

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

DI001 1N6391 DIODE (ZONE 224) (182) 83135 & ON 01 DI002 1N6391 DIODE (ZONE 224) (182) 83135 & ON 01 DI006 1N6391 DIODE (182) 83135 & ON 01 DI007 1N6391 DIODE (182) 83135 & ON 01 HI003 S1360-5L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI007 S1360-10L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI010 S1360-5L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI015 S1360-5L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI022 S1360-5L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI023 S1360-15L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI024 S1360-15L CIRCUIT BREAKER (ZONE 224) (182) 83135 & ON 01 HI025 S1360-5L CIRCUIT BREAKER (182) 83135 & ON 01 HI026 S1360-5L CIRCUIT BREAKER (182) 83135 & ON 01 HI029 S1360-5L CIRCUIT BREAKER (182) 83135 & ON 01 HI031 S1360-5L CIRCUIT BREAKER (182) 83135 & ON 01 HI032 S1360-10L CIRCUIT BREAKER (182) 83135 & ON 01 HI034 S2899L20.0 CIRCUIT BREAKER (182) 83135 & ON 01 HI035 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI036 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI037 S2899L10.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI038 S2899L15.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI039 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI040 S2899L15.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI041 S2899L10.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI042 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI047 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI048 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI049 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI050 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI051 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI052 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI065 S1360-5L CIRCUIT BREAKER - LANDING LIGHT (182) 83135 & ON 01 HI066 S1360-5L CIRCUIT BREAKER - RECOGNITION TAXI LIGHT (182) 83135 & ON 01 HI067 S2899L5.0 CIRCUIT BREAKER 82647 (182) 83135 & ON 01 HI073 ATM-5 FUSE 71400 (182) 83135 & ON 01 JC023 S2350-10 CONNECTOR (182) 83135 & ON 01 S2353-4 . CONTACT AR S2353-5 . CONTACT AR S2353-7 . CONTACT AR JC024 S2350-4 CONNECTOR - ELECTRICAL CIRCUIT BREAKER PANEL (182) 83135 & ON 01 DISCONNECT (ZONE 220) S2353-4 . CONTACT 01 S2353-5 . CONTACT 01 JC025 S2350-3 CONNECTOR (182) 83135 & ON 01 S2353-4 . CONTACT 01 S2353-5 . CONTACT 06 S2353-6 . CONTACT 05 S3373-1 . CONTACT 01

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CIRCUIT BREAKER PANEL W/NAVIII

AIRPLANES (182) 83135 & ON

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

PC023 S2349-5 CONNECTOR (182) 83135 & ON 01 S2099-3 . CONTACT 06 S2099-4 . CONTACT 00779 17 PC024 S2349-3 CONNECTOR - ELECTRICAL CIRCUIT BREAKER PANEL (182) 83135 & ON 01 DISCONNECT (ZONE 220) S2099-3 . CONTACT 01 S2099-4 . CONTACT 00779 01 PC025 S2349-1 CONNECTOR 00779 (182) 83135 & ON 01 S2099-13 . CONTACT 06 S2099-3 . CONTACT 02 S2099-4 . CONTACT 00779 05 S3373-2 . CONTACT 02

Figure 09 Page 4 24-61-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

33-10-01

INSTRUMENT DIMMING W/NAV III AIRPLANES (182) 83135 & ON WITH NAV III OPTION

Figure 06 Page 1 33-10-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL NOTES: 1. ALL WIRE 22AWG, UNLESS OTHERWISE NOTED JC024 PC024 2 WIRES SUPPLIED WITH COMPASS. LOCATE SPLICES UNDER UPPER WINDSHIELD TRIM. ELECT CB PNL DISC 3 CONNECTOR AND PINS PART OF LIGHT INSTL. 5PI045-5JC024 5 (REF CIRCUIT BREAKER & 4 COVER RESISTOR AND RESISTOR LEADS WITH 1PI045-8JC024 8 SWITCH PANEL - NAV 3 OPTION) HEAT SHRINK TUBING. 9 J1 PI045 REFER TO 24-61-01 5 ASSEMBLE REGULATOR, BRACKET, SOCKET AND POTENTIOMETER AS SHOW. SECURE SOCKET TO DIMMING MODULE DISC PC031 JC031 REGULATOR WITH TIE STRAP. 5 ELECT/AVN DISC NUT (QI001) 1 WASHER (2)(QI001) 2 2PI045-1PC031 1 REFER TO 23-50-02 SCREW (QI001) 4 RI006 RI008 PI029 SOCKET JC005 PC005 AVIONICS SW / CB PNL QI001 REGULATOR DIMMING DIMMING RI001 POTENTIOMETER DIMMING CONTROL DISC POTENTIOMETER POTENTIOMETER BRACKET (QI001) 3 3PI045-1JC005 1 3 3 CW=BRIGHTER CW=BRIGHTER 6 WIRE AND CONNECTOR SUPPLIED WITH LIGHT ASSY. 1 2 1 2 7 REF DES UI015 WAS UI010 AND UI016 WAS UI012 PRIOR TO T18208480 & ON, 18281741 & ON. 8 REF DES UI017 WAS UI009 AND UI018 WAS UI011 PRIOR RI011 TO T18208481 & ON, 18281742 & ON. 7 1 2 PI041 QI002 9 UI014 LED LIGHTED THROTTLE/FLAP PANEL INSTALLED IN 8 LED PANEL LIGHT AIRCRAFT STARTING T18208481 & ON, 18281742 & ON. 9 REGULATOR 11 REF DES UI024 WAS UI017 AND UI025 WAS UI018 PRIOR 1 ADJ (REF DIMMING CONTROL MODULE) TO T18209024 & ON, 18282281 & ON 2 OUT REFER TO 33-10-04 9JC024-5JC005 5 3 IN *** REFER TO 91-10-01 FOR GROUND INFORMATION 6 6PI045-2JC005 2 RI007 RI009 PEDESTAL STANDBY INDICATORS DIMMING DIMMING POTENTIOMETER POTENTIOMETER 9 9PI045-6JC005 6 3 3 CW=BRIGHTER CW=BRIGHTER 1 2 1 2

AGI001-4JC005 4

1 2 BGI001-3JC005 3 GI001 RI012

B A 7 7PI045-NNGI001 NN (W/O PROP DE-ICE) 11 UI024 8 N (WITH PROP DE-ICE) FC001 D PI039 J1 UI025 REFER TO 33-11-04 C LED SWITCH PNL DISC LED LIGHTED COMPASS (REF OXYGEN LIGHTING SWITCH PANEL LIGHT 2 T182 ONLY) 1 2 (VEND)(BLK) 2FC001-4PI045 1 (VEND)(RED) 2 (VEND)(BLK) (VEND)(BLK) 1FC001-NGI001 PC051 JC051 (REF OXYGEN LIGHTING ELECT/AVN DISC REFER TO T182 ONLY) 34-22-02 UI015 (W/O PROP DE-ICE) 2 (REF GI 275 STBY) REFER TO 33-11-04 (WITH PROP DE-ICE) 1 (REF GI 275 STBY) UI016 FC014 REFER TO PI040 J1 LED LIGHTED PEDESTAL J1 PC038 34-22-02 LED C/B PNL DISC CIRCUIT BREAKER PANEL FUEL SELECT PEDESTAL FUEL LIGHT SELECT LIGHT DISC DIMMER CONTROL WBA 2 (VEND)(BLK) 6 1JC038-8PI045 EFFECTIVE: 1 (VEND)(RED) (VEND)(RED) 1 1JC038-1PI047 (VEND)(BLK) 2 2JC038-DGI001 082046 & ON WITH NAV 3 OPTION 3 2JC038-2PI047 AND 008232 & ON WITH NAV 3 OPTION

FC015 PEDESTAL J1 PC039 (VEND)(BLK) TRIM PEDESTAL TRIM (VEND)(RED) LIGHT LIGHT DISC 6 UI014 LED LIGHTED (VEND)(RED) 1 1PC039-9JC024 P1 J1 LED THROTTLE/FLAP PNL DISC THROTTLE/FLAP PANEL (VEND)(BLK) 2 2PC039-DGI001 1 (VEND)(RED) 2 (VEND)(BLK)

UI021 LED LIGHTED J1 PI047 CONSOLE COVER PANEL LED CONSOLE COVER PNL DISC

(VEND)(BLK) 2 (VEND)(RED) 1 0770557U7 3

INSTRUMENT DIMMING W/NAV III Figure 06. (Sheet 1) Figure 06 Page 2 33-10-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

INSTRUMENT DIMMING W/NAV III

AIRPLANES (182) 83135 & ON WITH NAV III OPTION

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

FC001 LIGHT - COMPASS (ZONE 211) RF FC014 LIGHT - PEDESTAL FUEL SELECT RF FC015 LIGHT - PEDESTAL TRIM RF GI001 200838-2 GROUND BLOCK (ZONE 211) 00779 (182) 83135 & ON 01 S2099-13 . CONTACT 02 S2099-3 . CONTACT AR S2099-4 . CONTACT 00779 AR J1 S2035-1 CONNECTOR - POWER JUNCTION BOX DISCONNECT (182) 83135 & ON 01 S1635-1 . PIN 49367 AR JC005 S1641-9 CONNECTOR - DIMMING CONTROL (ZONE 210) (182) 83135 & ON 01 S1636-1 . ELECTRICAL SOCKET 01 S1636-2 . SOCKET 01 JC024 S2350-4 CONNECTOR - ELECTRICAL CIRCUIT BREAKER PANEL (182) 83135 & ON 01 DISCONNECT (ZONE 220) S2353-4 . CONTACT 01 S2353-5 . CONTACT 01 JC031 S2350-4 CONNECTOR - ELECTRICAL/AVIONIC DISCONNECT (182) 83135 & ON 01 S2353-5 . CONTACT AR JC051 S2350-2 CONNECTOR (182) 83135 & ON 01 S2351-2 . BACKSHELL 00779 01 S2353-5 . PIN 02 P1 S1640-9 CONNECTOR - DIMMING MODULE (182) 83135 & ON 01 S1635-1 . CONTACT 49367 09 PC005 S1640-9 CONNECTOR - DIMMING CONTROL MODULE DISCONNECT (ZONE (182) 83135 & ON 01 210) S1635-1 . CONTACT 49367 AR S1635-2 . CONTACT (182) 80945 & ON AR S2099-4 . CONTACT 00779 PC024 S2349-3 CONNECTOR - ELECTRICAL CIRCUIT BREAKER PANEL (182) 83135 & ON 01 DISCONNECT (ZONE 220) S2099-3 . CONTACT 01 S2099-4 . CONTACT 00779 01 PC031 S2349-3 CONNECTOR - ELECTRICAL/AVIONIC DISCONNECT (ZONE 220) (182) 83135 & ON 01 S2099-2 . CONTACT - ALT FOR S2099-4 01 S2099-4 . CONTACT 00779 01 PC038 S1638-1 CONNECTOR - PEDESTAL FUEL SELECT LIGHT (182) 83135 & ON 01 S1636-1 . SOCKET AR PC039 S2035-2 CONNECTOR - PEDESTAL TRIM LIGHT (182) 83135 & ON 01 S1636-1 . SOCKET AR PC051 S2349-2 PLUG (182) 83135 & ON 01 S2099-4 . CONTACT 00779 02 PI039 S1636-2 SOCKET (ZONE 220) (182) 83135 & ON 01 PI040 S2035-2 CONNECTOR - LED CIRCUIT BREAKER PANEL DISCONNECT (ZONE (182) 83135 & ON 01 220) S1636-2 . CONTACT 01 PI041 08-50-0114 TERMINAL - LED PANEL LIGHT REGULATOR (ZONE 220) 27264 (182) 83135 & ON 01 10-17-2032 . CONTACT 27264 01 PI045 S2349-3 CONNECTOR - DIMMING MODULE DISCONNECT (ZONE 210) (182) 83135 & ON 01 S2099-4 . CONTACT 00779 AR

Figure 06 Page 3 33-10-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

INSTRUMENT DIMMING W/NAV III

AIRPLANES (182) 83135 & ON WITH NAV III OPTION

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

PI047 S1638-1 CONNECTOR (182) 83135 & ON 01 S1636-1 . SOCKET AR QI002 REGULATOR VOLTAGE - ADJUSTABLE RF RI006 S1904-5 RESISTOR - AVIONICS DIMMING (ZONE 220) (182) 83135 & ON 01 RI007 S1904-5 RESISTOR - PEDESTAL DIMMING (ZONE 220) (182) 83135 & ON 01 RI008 S1904-5 RESISTOR - SWITCH/CIRCUIT BREAKER PANEL DIMMING (ZONE (182) 83135 & ON 01 220) RI009 S1904-5 RESISTOR - STANDBY INDICATORS DIMMING (ZONE 220) (182) 83135 & ON 01 RI011 CCF-553740F RESISTOR 91637 (182) 83135 & ON 01 RI012 CCF-552611F RESISTOR 91637 (182) 83135 & ON 01 UI014 SWITCH PANEL - LED LIGHTED RF UI015 SWITCH PANEL - LED LIGHTED RF UI016 SWITCH PANEL - LED LIGHTED RF UI021 CONSOLE COVER - LED PANEL RF UI024 SWITCH PANEL - LED LIGHTED RF UI025 SWITCH PANEL - LED LIGHTED RF

Figure 06 Page 4 33-10-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

34-22-01

GARMIN MAGNETOMETER W/NAV III AIRPLANES (182) 83135 & ON

Figure 01 Page 1 34-22-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

NOTES: 1. ALL WIRES 22 GA UNLESS OTHERWISE NOTED. 2. THE FOLLOWING SPECS ARE PART OF THIS DRAWING: CSAM012 SHIELDED CABLE INSTALLATION. CES2716 WIRE TERMINATIONS.

PL302 JM300

1 4 (WHT) 1 GMU44 2 (BLU) 2 WING MAGNETOMETER 3 ROOT 8 (WHT) 4 DISC 9 (BLU) 5 6 (ORN) 6 3 7

1 C/A - MAGNETOMETER

PL303 JM300

1 3 (WHT) 1 GMU44B 2 (BLU) 2 WING MAGNETOMETER 3 ROOT 5 (WHT) 4 DISC 6 (BLU) 5 4 (ORN) 6 7

2 C/A - MAGNETOMETER

3925109C1

GARMIN MAGNETOMETER W/NAV III Figure 01. (Sheet 1) Figure 01 Page 2 34-22-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

GARMIN MAGNETOMETER W/NAV III

AIRPLANES (182) 83135 & ON

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

JM300 206434-1 CONNECTOR - FLUX TRANSMITTER (ZONE 510) 00779 (182) 83135 & ON 01

206062-3 . BACKSHELL 00779 AR 5-66506-9 . PIN CONTACT 01

PL303 GMU44 CONNECTOR KIT 0TRC3 (182) 83135 & ON RF

Figure 01 Page 3 34-22-01 Jun 1/2021 ©TEXTRON AVIATION INC. This Page Intentionally Left Blank. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

34-22-02

CABLE ASSY - GI275 STBY AIRPLANES (182) 83135 & ON WITH NAV III OPTION

Figure 01 Page 1 34-22-02 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

NOTES: 1. ALL WIRES 22 AWG UNLESS OTHERWISE NOTED. 2 GROUND SHIELDS TO THE BACKSHELL OF THE CONNECTOR USING THE GARMIN SUPPLIED GROUNDING LUGS ON THE CONNECTOR. SHIELD WIRES SHOULD BE NO LONGER THAN 3". REFER TO GARMIN DOCUMENT 190-00313-09 FOR SHIELD BLOCK INSTALLATION INSTRUCTIONS. 3 USE 922204 CABLE 4. THE FOLLOWING SPECS ARE PART OF THIS DRAWING: CSAM012 SHIELDED CABLE INSTALLATION. CES2716 WIRE TERMINATIONS. 5 CONFIGURATION MODULE IS MOUNTED INSIDE OF THE BACKSHELL 1 C/A GI275 - ADAPTER NAV III OF CONNECTOR PI337. 6 PART OF GARMIN CONNECTOR KIT 011-01000-00 (REF). 7 PART OF GARMIN CONNECTOR KIT 011-03109-00 (REF). 8PART OF GARMIN CONNECTOR KIT 011-04809-00 (REF) P/N 325-00238-02. SHORTEN PIGTAIL TO ABOUT 12" AND SECURE USB PORT IN GI275 WIRE BUNDLE BEHIND INSTRUMENT PANEL. THE USB CONNECTOR IS FOR MAINTENANCE PURPOSES ONLY AND MUST BE CAPPED AND STOWED PRIOR 2 TO RETURING THE AIRCRAFT TO SERVICE GI 275 JC051 PC051 PI337 ELECT/AVN DISC

LIGHTING HI 22 1 AIRCRAFT GND 41 AIRCRAFT GND 61 2 LIGHTING LO 42 JC023 PC023 2 C/A GI275 - MAIN NAV III AVN CB PNL DISC A/C POWER 2 3 24 A/C POWER 1 2 5

CONFIG MOD PWR 21 (RED) 4 6 CONFIG GND 1 (BLK) 1 CONFIG 2 330-00185-78 CONN CONFIG DATA 40 (YEL) 3 MODULE CONFIG CLOCK 60 (WHT) 2 3 PI338 JI338 3 PT304 INT AVN #1 INSTR PNL DISC (1P603) ETHERNET OUT 1A 46 (ORN/WHT) 1 (ORN/WHT) 38 ETH 3 IN A ETHERNET OUT 1B 47 (BLU/WHT) 2 (BLU/WHT) 78 ETH 3 IN B ETHERNET IN 1A 65 (--ORN--) 3 (--ORN--) 66 ETH 3 OUT A ETHERNET IN 1B 66 (--BLU--) 4 (--BLU--) 68 ETH 3 OUT B

A429 IN 2A 72 (WHT) 5 (WHT) 75 A429 OUT 3A A429 IN 2B 14 (BLU) 6 (BLU) 74 A429 OUT 3B A429 IN 3A 53 (WHT) 7 (WHT) 73 A429 OUT 2A A429 IN 3B 34 (BLU) 8 (BLU) 72 A429 OUT 2B 9

2 PT321 7 330-00776-78 CONN A429 IN 1A 52 (WHT) 10 (WHT) 27 A429 OUT 1A A429 IN 1B 33 (BLU) 11 (BLU) 7 A429 OUT 1B 8 12

USB DATA HI 58 (GRN) USB DATA LO 39 (WHT) USB A USB VBUS POWER 78 (RED) FEMALE USB GND 59 (BLK)

3925125_1

CABLE ASSY - GI275 STBY Figure 01. (Sheet 1) Figure 01 Page 2 34-22-02 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

CABLE ASSY - GI275 STBY

AIRPLANES (182) 83135 & ON WITH NAV III OPTION

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

JC023 S2350-10 CONNECTOR (182) 83135 & ON 01 S2353-4 . CONTACT AR S2353-5 . CONTACT AR S2353-7 . CONTACT AR JC051 S2350-2 CONNECTOR (182) 83135 & ON 01 S2351-2 . BACKSHELL 00779 01 S2353-5 . PIN 02 JI338 LMD-4003-S CONNECTOR 49367 (182) 83135 & ON 01 LMD-4122-96LD . CONTACT 49367 01 LMS-01T-TL . SPLICE CONNECTOR 49367 01 PC023 S2349-5 CONNECTOR (182) 83135 & ON 01 S2099-3 . CONTACT 06 S2099-4 . CONTACT 00779 17 PC051 S2349-2 PLUG (182) 83135 & ON 01 S2099-4 . CONTACT 00779 02 PI337 011-04809-00 GI 275 CONNECTOR KIT 0TRC3 (182) 83135 & ON 01 PI338 LMD-4003-P CONNECTOR 49367 (182) 83135 & ON 01 LMD-4022-36LJ . PIN 49367 01 PT304 CONNECTOR RF PT321 011-00979-20 CONFIGURATION MODULE KIT 0TRC3 (182) 83135 & ON 01 336-00044-00 . #18 PIN HI-DENSE DSUB 0TRC3 02 011-01855-04 . BACKSHELL 0TRC3 01 330-00776-78 . CONNECTOR 0TRC3 01 M39029/58-360 . CONTACT PIN 0TRC3 01

Figure 01 Page 3 34-22-02 Jun 1/2021 ©TEXTRON AVIATION INC. This Page Intentionally Left Blank. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

77-40-01

ENGINE/AIRFRAME MONITOR W/NAV III AIRPLANES (182) 83135 & ON

Figure 07 Page 1 77-40-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL PC031 JC031 (P701) ELECT/AVN DISC NOTES: GEA71 PI037 1. ALL WIRE 22AWG, UNLESS OTHERWISE NOTED. ENGINE/AIRFRAME REFER TO 33-10-01 (REF DIMMING) 1 (REF AUDIO) 2 WIRE AND CONNECTOR SUPPLIED WITH SENSOR. (REF NAVIGATION 6 UI008 (P701) REFER TO 33-11-01 & MAP LIGHTS) 9 REFER TO 23-50-02 GEA71 3 CONFIGURATION MODULE AND THERMOCOUPLE ASSY ARE LOCATED IN THE CONNECTOR BACKSHELL. RS 485 1 A 5 5PI037-2PC031(WHT) 2 ENGINE/AIRFRAME PI037 4 GROUND STUD LOCATED ON LH MAGNETO CASE LABLED AS "GND". RS 485 1 B 6 6PI037-3PC031(BLU) 3 4 (REF AIR DATA UI008 5 & AHRS) OIL PRESSURE REFER TO 34-10-01 JN004 RS 485 2 A 7 7PI037-7PC031(WHT) 7 TRANSDUCER RS 485 2 B 8 8PI037-8PC031(BLU) 8 5 5 UI006 CONFIG MODULE GROUND 1 (BLK)(VEND) 1 UI001 +5V TRANSDUCER POWER 15 15PI037-BJN004(20) B INPUT 5V CONFIG MODULE POWER 21 (RED)(VEND) 4 CONFIGURATION OIL PRESSURE ANALOG IN 2 HI 24 24PI037-CJN004(20) C OUTPUT CONFIG MODULE DATA 40 (YEL)(VEND) 3 MODULE OIL PRESSURE ANALOG IN 2 LO 25 25PI037-AJN004(20) A GND CONFIG MODULE CLOCK 60 (WHT)(VEND) 2 3 TRANSDUCER LO (GND) 12

THERMOCOUPLE REF HI 68 (YEL)(VEND) TI001 UN004 COVER - TERMINAL BOARD 3 OIL TEMP SENSOR THERMOCOUPLE REF LO 69 (RED)(VEND) THERMOCOUPLE ASSY TERMINAL BOARD OIL TEMP ANALOG IN 1 HI 22 22PI037-1UN004(20) 1 OUTPUT 8 JN011 PN011 UN014 OIL TEMP ANALOG IN 1 LO 23 23PI037-GN004(20) #1 EGT SENSOR DISC #1 EGT 2 SENSOR 4 UN011 #1 EGT TEMP ANALOG IN 7 HI 48 48PI037-+JN011(YEL)(24) + (VEND) JN009 PN009 FUEL FLOW #1 EGT TEMP ANALOG IN 7 LO 49 (RED) 49PI037--JN011(RED)(24) - (VEND) GN004 FUEL FLOW TRANSDUCER DISC TRANDUCER 5 +12V TRANDUCER POWER 16 16PI037-CJN009(20) C RED (VEND) INPUT +12V SHRINK SLEVING COVER 8 5 JN012 PN012 UN015 FUEL FLOW DIGITAL IN 1 2 2PI037-BJN009(20) B WHT (VEND) OUPUT #2 EGT SENSOR DISC #2 EGT TRANSDUCER LO (GND) 13 13PI037-AJN009(20) A BLK (VEND) GND 2 SENSOR #2 EGT TEMP ANALOG IN 8 HI 50 50PI037-+JN012(YEL)(24) + (VEND) #2 EGT TEMP ANALOG IN 8 LO 51 (RED) 51PI037--JN012(RED)(24) - (VEND) COVER WALL BETWEEN R1 & R2 5 TIE STRAP (4) 8 5 JN013 PN013 UN016 UN031 #3 EGT SENSOR DISC #3 EGT PN028 JN028 2 SENSOR TACHOMETER SENSOR DISC SENSOR #3 EGT TEMP ANALOG IN 9 HI 52 52PI037-+JN013(YEL)(24) + (VEND) 9 7 5 13 #3 EGT TEMP ANALOG IN 9 LO 53 (RED) 53PI037--JN013(RED)(24) - (VEND) +10V TRANSDUCER POWER 14 14PI037-2PN028(WHT) 2 WHT (VEND) INPUT +10V TACHOMETER DIGITAL IN 2 3 3PI037-3PN028(BLU) 3 BLU (VEND) OUTPUT 5 D1 R1 R2

TRANSDUCER LO (GND) 11 11PI037-1PN028(ORN) 1 ORN (VEND) GND R3 8 D2 5 JN014 PN014 UN017 #4 EGT SENSOR DISC #4 EGT 5 2 SENSOR #4 EGT TEMP ANALOG IN 10 HI 54 54PI037-+JN014(YEL)(24) + (VEND) 10 8 6 24 #4 EGT TEMP ANALOG IN 10 LO 55 (RED) 55PI037--JN014(RED)(24) - (VEND) REFER TO 30-30-01 5 PC024 JC024 ELECT CB PNL DISC (REF HEATED PITOT TUBE 8 EI003 5 JN015 PN015 UN018 & HEATED STALL WARNING) HOURMETER #5 EGT SENSOR DISC #5 EGT TERMINAL BOARD FRONT LAYOUT (REF CIRCUIT 4 (REF MAGNETO SYSTEM) 2 SENSOR (COVERS NOT SHOWN) BREAKER & 4JC024-(+)EI003 (+) #5 EGT TEMP ANALOG IN 11 HI 56 56PI037-+JN015(YEL)(24) (VEND) + SWITCH PANEL - 6 (16) REFER TO 74-10-01 GND #5 EGT TEMP ANALOG IN 11 LO 57 (RED) 57PI037--JN015(RED)(24) (VEND) - NAV 3 OPTION) 7 5 REFER TO 24-61-01 8 POWER 2 (AVN BUS 1) 37 37PI037-7JC024(16) GI001 5 JN016 PN016 UN019 HEAT SHRINK SLEVING #6 EGT SENSOR DISC #6 EGT POWER 1 (ESSENTIAL BUS) 35 35PI037-6JC024(16) OIL PRESSURE 2 SENSOR POWER GROUND 20 20PI037-KGI001 K JN005 SWITCH 1 3 #6 EGT TEMP ANALOG IN 12 HI 58 58PI037-+JN016(YEL)(24) + (VEND) VOLTS-ESSNTL BUS ANALOG IN 5 HI 46 46PI037-6JC024(16) R SN001 7 9 #6 EGT TEMP ANALOG IN 12 LO 59 (RED) 59PI037--JN016(RED)(24) (VEND) VOLTS-ESSNTL BUS ANALOG IN 5 LO 47 J 5 - 47PI037-RGI001 NO VOLTS-MAIN BUS ANALOG IN 4 LO 45 GNDEI003-AJN005(20) A 5 C 20PSI VOLTS-MAIN BUS ANALOG IN 4 HI 44 44PI037-4JC024 JGI001-BJN005(20) B 8 NC 5 JN017 PN017 UN020 "LOW OIL PRESS" DISCRETE IN 3 76 76PI037-CJN005(20) C #1 CHT SENSOR DISC #1 CHT 2 SENSOR (P702) (16)(SPIDER A) #1 CHT TEMP ANALOG IN 1 HI 26 26PI037-+JN017(YEL)(24) (VEND) + GEA71 (16)(SPIDER B) 10 #1 CHT TEMP ANALOG IN 1 LO 27 (RED) 27PI037--JN017(RED)(24) (VEND) 2 4 6 8 - ENGINE/AIRFRAME 5 5 UI008 PI038 8 5 JN018 PN018 UN021 GF011 #2 CHT SENSOR DISC #2 CHT PB018 J1 2 SENSOR J-BOX DISC TERMINAL BOARD REAR LAYOUT #2 CHT TEMP ANALOG IN 2 HI 28 28PI037-+JN018(YEL)(24) + (VEND) REFER TO 24-20-01 (COVERS NOT SHOWN) #2 CHT TEMP ANALOG IN 2 LO 29 (RED) 29PI037--JN018(RED)(24) (VEND) "LOW VOLTS" RED DISCRETE IN 1A 60 60PI038-APB018(20) A - (REF ALTERNATOR ANALOG/CURRENT MON IN 1A HI 44 44PI038-FPB018(20) F 5 SYSTEM) 5 WIRE SHIELD TERMINATIONS, CONNECTOR BACKSHELL GROUNDING AND THERMOCOUPLE GROUNDING ANALOG/CURRENT MON IN 1A LO 45 45PI038-GPB018(20) G 8 SHALL BE ACCOMPLISHED BY USING GARMIN BACKSHELL GROUND WIRE HARNESS ("SPIDER"). 5 JN019 PN019 UN022 (MAIN BATTERY CURRENT) #3 CHT SENSOR DISC #3 CHT 7 ASSEMBLE 0770582-3 FUEL QTY SIGNAL CONDITIONER 2 SENSOR JC026 PC026 SWITCH PNL DISC (REF DES UL004 & UR004) IN BUNDLE AS SHOWN: #3 CHT TEMP ANALOG IN 3 HI 30 30PI037-+JN019(YEL)(24) (VEND) PC034 MANIFOLD + 8 INSTALL H610033 NYLON TUBE BETWEEN THERMOCOUPLE WIRE AND CONNECTOR CLAMP AS SHOWN. #3 CHT TEMP ANALOG IN 3 LO 31 (RED) 31PI037--JN019(RED)(24) - (VEND) PRESSURE ANALOG/CURRENT MON IN 2A HI 46 46PI038-11JC026 11 (REF CB & SW PNL TRANSDUCER FLOAT THERMOCOUPLE SHIELD UNDER NYLON TUBE. 5 ANALOG/CURRENT MON IN 2A LO 47 47PI038-16JC026 16 - NAV 3 OPTION) APPLY LOC-TITE 232 TO ALL SIX SCREWS ON THE THERMOCOUPLE CONNECTOR AND CLAMP. 8 (STANDBY BATTERY CURRENT) REFER TO 24-61-01 UN006 5 JN020 PN020 UN023 #4 CHT SENSOR DISC #4 CHT 9 APPLY U074805, CONTACT ENHANCER, TO THE INSIDE SURFACE OF THE SOCKETS USING A SMALL BRUSH. +5V TRANSDUCER POWER 15 15PI038-BPC034 B INPUT 5V 2 SENSOR NO EFFECTIVITY REQUIRED. ANALOG IN 1A HI 52 52PI038-CPC034 C OUTPUT #4 CHT TEMP ANALOG IN 4 HI 33 33PI037-+JN020(YEL)(24) (VEND) CONNECTOR + ANALOG IN 1A LO 53 53PI038-APC034 A GND CLAMP #4 CHT TEMP ANALOG IN 4 LO 34 (RED) 34PI037--JN020(RED)(24) (VEND) - TRANSDUCER LO (GND) 12 H610033 TUBE THERMOCOUPLE WIRE 5 8 5 JN021 PN021 UN024 #5 CHT SENSOR DICS #5 CHT 2 SENSOR #5 CHT TEMP ANALOG IN 5 HI 36 36PI037-+JN021(YEL)(24) + (VEND) #5 CHT TEMP ANALOG IN 5 LO 38 (RED) 38PI037--JN021(RED)(24) - (VEND) 5 2.0 8 5 JN022 PN022 UN025 *** REFER TO 91-10-01 FOR GROUND INFORMATION #6 CHT SENSOR DISC #6 CHT 2 SENSOR #6 CHT TEMP ANALOG IN 6 HI 17 17PI037-+JN022(YEL)(24) + (VEND) #6 CHT TEMP ANALOG IN 6 LO 18 (RED) 18PI037--JN022(RED)(24) - (VEND) 5 5 0770582M8

ENGINE/AIRFRAME MONITOR W/NAV III Figure 07. (Sheet 1) Figure 07 Page 2 77-40-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

ENGINE/AIRFRAME MONITOR W/NAV III

AIRPLANES (182) 83135 & ON

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

EI003 INDICATOR - HOURMETER (182) 83135 & ON RF GF011 GROUND (ZONE 210) RF GI001 200838-2 GROUND BLOCK (ZONE 211) 00779 (182) 83135 & ON 01

S2099-13 . CONTACT 02 S2099-3 . CONTACT AR S2099-4 . CONTACT 00779 AR GN004 GROUND (ZONE 211) (182) 83135 & ON RF J1 S2035-1 CONNECTOR - POWER JUNCTION BOX DISCONNECT (182) 83135 & ON 01

S1635-1 . PIN 49367 AR JC024 S2350-4 CONNECTOR - ELECTRICAL CIRCUIT BREAKER PANEL (182) 83135 & ON 01 DISCONNECT (ZONE 220) S2353-4 . CONTACT 01 S2353-5 . CONTACT 01 JC026 S2350-3 CONNECTOR - SWITCH PANEL DISCONNECT (ZONE 220) (182) 83135 & ON 01

S2353-4 . CONTACT AR S2353-5 . CONTACT AR S2353-6 . CONTACT AR S3373-1 . CONTACT AR JC031 S2350-4 CONNECTOR - ELECTRICAL/AVIONIC DISCONNECT (182) 83135 & ON 01

S2353-5 . CONTACT AR JN004 S2800-277 CONNECTOR KIT - OIL PRESSURE TRANSDUCER (ZONE 120) (182) 83135 & ON 01

JN005 S2800-276 CONNECTOR KIT - OIL PRESSURE SWITCH (ZONE 120) (182) 83135 & ON 01

JN009 S2800-340 CONNECTOR (182) 83135 & ON 01

JN011 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN012 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN013 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN014 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN015 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN016 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN017 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN018 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN019 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN020 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

Figure 07 Page 3 77-40-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

ENGINE/AIRFRAME MONITOR W/NAV III

AIRPLANES (182) 83135 & ON

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

JN021 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN022 NMP-K-F CONNECTOR 29907 (182) 83135 & ON 01

JN028 CONNECTOR RF PB018 S2800-274 CONNECTOR - POWER JUNCTION BOX (ZONE 121) 01

PC024 S2349-3 CONNECTOR - ELECTRICAL CIRCUIT BREAKER PANEL 01 DISCONNECT (ZONE 220) S2099-3 . CONTACT 01 S2099-4 . CONTACT 00779 01 PC026 S2349-1 CONNECTOR - SWITCH PANEL DISCONNECT 00779 (182) 83135 & ON 01

S2099-13 . CONTACT 02 S2099-3 . CONTACT 02 S2099-4 . CONTACT 00779 09 S3373-2 . CONTACT 02 PC031 S2349-3 CONNECTOR - ELECTRICAL/AVIONIC DISCONNECT (ZONE 220) 00779 (182) 83135 & ON 01

S2099-2 . CONTACT - ALT FOR S2099-4 01 S2099-4 . CONTACT 01 PC034 S2800-277 CONNECTOR KIT 00779 (182) 83135 & ON 01

PI037 CONNECTOR RF PI038 CONNECTOR RF PN009 CONNECTOR - FUEL FLOW DISCONNECT RF PN011 CONNECTOR RF PN012 CONNECTOR RF PN013 CONNECTOR RF PN014 CONNECTOR RF PN015 CONNECTOR RF PN016 CONNECTOR RF PN017 CONNECTOR RF PN018 CONNECTOR RF PN019 CONNECTOR RF PN020 CONNECTOR RF PN021 CONNECTOR RF PN022 CONNECTOR RF PN028 826886-7 CONNECTOR 00779 (182) 83135 & ON 01

S2099-4 . CONTACT 00779 03 SN001 SWITCH - OIL PRESSURE (ZONE 120) (182) 83135 & ON RF TI001 011-00981-00 THERMOCOUPLE 0TRC3 (182) 83135 & ON 01

UI001 MODULE KIT - CONFIGURATION (182) 83135 & ON RF UI006 TRANSDUCER - OIL PRESSURE (ZONE 120) (182) 83135 & ON RF UI008 COMPUTER - ENGINE/AIRFRAME MONITOR (182) 83135 & ON RF UN004 SENSOR - OIL TEMPERATURE (ZONE 120) (182) 83135 & ON RF UN006 TRANSDUCER - PRESSURE (182) 83135 & ON RF UN011 TRANSDUCER (182) 83135 & ON RF

Figure 07 Page 4 77-40-01 Jun 1/2021 ©TEXTRON AVIATION INC. CESSNA® MODEL 182 (SERIES 1997 AND ON) WIRING DIAGRAM MANUAL

ENGINE/AIRFRAME MONITOR W/NAV III

AIRPLANES (182) 83135 & ON

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

UN014 PROBE - 1 EGT RF UN015 PROBE - CYLINDER HEAD 2 EGT RF UN016 PROBE - CYLINDER HEAD 3 EGT RF UN017 PROBE - CYLINDER HEAD 4 EGT RF UN018 PROBE - CYLINDER HEAD 5 EGT RF UN019 PROBE - CYLINDER HEAD 6 EGT RF UN020 PROBE - CYLINDER HEAD 1 CHT RF UN021 PROBE - CYLINDER HEAD 2 CHT RF UN022 PROBE - CYLINDER HEAD 3 CHT RF UN023 PROBE - CYLINDER HEAD 4 CHT RF UN024 PROBE - CYLINDER HEAD 5 CHT RF UN025 PROBE - CYLINDER HEAD 6 CHT RF UN031 SENSOR - TACHOMETER RF

Figure 07 Page 5 77-40-01 Jun 1/2021 ©TEXTRON AVIATION INC. TEXTRON AVIATION INC. AIRCRAFT DIVISION WICHITA, KANSAS 67277

SUPPLEMENT NO: ICA-182-34-80001 Revision A APPENDIX C: GARMIN SUPPLEMENTAL MAINTENANCE MANUAL

© TEXTRON AVIATION INC. Form 2261 Rev 1 Supplemental Maintenance Manual

Textron Aviation Inc. NAV III Aircraft

Includes Instructions for Continued Airworthiness for STC SA01830WI

190-02128-04 2018 Revision 4

© Copyright 2017-2018 Garmin Ltd. or its subsidiaries All Rights Reserved

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

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Garmin AT, Inc. 2345 Turner Rd., SE Salem, OR 97302 USA Telephone: 503.581.8101

RECORD OF REVISIONS

Revision Date Description Updated Loader Card Creation Instructions 2 02/02/2017 (Section 3.2.2) and Traffic System Test Procedures (Section 7.13 and 8.8) 3 07/28/2017 Added pitot static drain check (Section 7.7.3) 4 08/31/2018 Updated for Phase 2 hardware/software

DOCUMENT PAGINATION

Section Pagination Table of Contents i – vi Section 1 1-1 – 1-6 Section 2 2-1 – 2-8 Section 3 3-1 – 3-44 Section 4 4-1– 4-11 Section 5 5-1 – 5-33 Section 6 6-1 – 6-10 Section 7 7-1– 7-50 Section 8 8-1 – 8-6 Section 9 9-1 - 9-10 Appendix A A-1 G1000 System Maintenance Manual Page i Textron Nav III Series Revision 4 190-02128-04

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

This document may contain information which is subject to the Export Administration Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual.

WARNING

This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.

CAUTION

The GDU lens is coated with a special anti-reflective coating that is very sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI- REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective coatings.

IMPORTANT

All G1000 screen shots used in this document are current at the time of publication. Screen shots are intended to provide visual reference only. All information depicted in screen shots, including software file names, versions and part numbers, is subject to change and may not be up to date.

G1000 System Maintenance Manual Page ii Textron Nav III Series Revision 4 190-02128-04

TABLE OF CONTENTS PARAGRAPH PAGE 1. INTRODUCTION ...... 1-1 1.1 Content, Scope, Purpose ...... 1-1 1.2 Organization ...... 1-2 1.3 Definitions/Abbreviations ...... 1-3 1.4 Units of Measure ...... 1-4 1.5 Publications...... 1-4 1.6 Revision and Distribution ...... 1-6 2. SYSTEM DESCRIPTION ...... 2-1 2.1 Equipment Descriptions ...... 2-1 2.2 G1000 Optional Interfaces ...... 2-6 2.3 Electrical Power Distribution ...... 2-6 2.4 Pitot/Static System ...... 2-6 2.5 GDU 1054B and GDU 1050 Displays ...... 2-6 2.6 Softkeys ...... 2-6 2.7 FMS Knob ...... 2-6 2.8 G1000 Normal Mode ...... 2-7 2.9 Reversionary Mode ...... 2-8 3. SOFTWARE AND CONFIGURATION ...... 3-1 3.1 Configuration Mode Overview ...... 3-1 G1000 System Software Information ...... 3-6 3.2 Configuration Mode ...... 3-14 3.3 G1000 Hardware/Software Compatibility Check ...... 3-14 3.4 Equipment Verification (Third Party/Optional Equipment Documentation) ...... 3-14 3.5 G1000 Software/Configuration Procedure ...... 3-16 3.6 System Software and Configuration Load ...... 3-17 3.7 Feature Enablement ...... 3-33 3.8 Aircraft Registration Number Entry and Flight ID Configuration ...... 3-37 3.9 Configuration Manager ...... 3-39 3.10 Splash Screen Loading ...... 3-39 3.11 Database Loading ...... 3-40 3.12 Configuration of Navigation Map for Traffic System ...... 3-42 3.13 Clearing Default User Settings ...... 3-42 3.14 Interface Confirmation ...... 3-43 4. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ...... 4-1 4.1 Airworthiness Limitations ...... 4-1 4.2 Servicing Information ...... 4-2 4.3 Maintenance Intervals ...... 4-4 4.4 Electrical Bonding Test ...... 4-5 4.5 GSU 75 Earth Magnetic Field Updates ...... 4-7 4.6 G1000 Redundant Connection Check ...... 4-7 4.7 GSM 86 Spring Cartridge Torque Check ...... 4-9 5. TROUBLESHOOTING ...... 5-1 5.1 System Annunciations ...... 5-2 5.2 G1000 Alerting System ...... 5-12 5.3 Synthetic Vision and Pathways Troubleshooting ...... 5-13 5.4 Backup Communications Path Checks ...... 5-14 5.5 GDU 105X Troubleshooting ...... 5-15 5.6 GDU 105X Alerts ...... 5-17 5.7 GTX Troubleshooting ...... 5-21 5.8 GDL69A SXM Troubleshooting (if installed) ...... 5-22 G1000 Supplemental Maintenance Manual Page iii Textron Nav III Series Revision 4 190-02128-04

5.9 GEA 71B Troubleshooting (if installed) ...... 5-22 5.10 GIA 64W Troubleshooting (if installed) ...... 5-22 5.11 GMA 1360 Troubleshooting (if installed) ...... 5-22 5.12 GSR 56 Troubleshooting ...... 5-22 5.13 GSU 75 and GMU 44 Troubleshooting ...... 5-23 5.14 GSU 75 Troubleshooting ...... 5-27 5.15 Software/Configuration Troubleshooting ...... 5-28 5.16 Backshell/Backplate Connectors ...... 5-30 6. EQUIPMENT REMOVAL & INSTALLATION ...... 6-1 6.1 GDU 1054B/1050 ...... 6-2 6.2 GTX 335R/GTRX 345R Transponder (if installed) ...... 6-2 6.3 GSU 75 ADAHRS (if installed) ...... 6-2 6.4 GDL 69A SXM (if installed) ...... 6-3 6.5 Configuration Modules ...... 6-3 6.6 GMA 1360 Audio Panel (if installed) ...... 6-7 6.7 GIA 64W Integrated Avionics Unit (if installed) ...... 6-7 6.8 GSR 56 Satellite Transceiver (if installed) ...... 6-7 6.9 Iridium Antenna (if installed) ...... 6-8 6.10 GEA 71B Engine/Airframe Unit (if installed) ...... 6-8 6.11 FS 510 Wifi/Bluetooth Data Link (if installed) ...... 6-9 6.12 GSA 81 Servo Actuator (if installed) ...... 6-9 6.13 GSM 86 Servo Gearbox (if installed) ...... 6-10 7. GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING ...... 7-1 7.1 GDU 1054B/1050 PFD & MFD ...... 7-1 7.2 GMA 1347 or GMA 1360 Audio Panel ...... 7-4 7.3 GIA 63W or GIA 64W Integrated Avionics Unit ...... 7-8 7.4 GEA 71 or GEA 71B Engine/Airframe Unit ...... 7-17 7.5 GTX 335R, GTX 345R, or GTX 33 Transponder ...... 7-21 7.6 GSU 75 ADAHRS (if installed) ...... 7-24 7.7 GDC 74A Air Data ...... 7-26 7.8 GRS 77 and GMU 44 Magnetometer (if installed) ...... 7-30 7.9 GMU 44 Magnetometer ...... 7-32 7.10 GSU/GRS/GMU Calibration Procedures ...... 7-33 7.11 GDL 69A or GDL 69A SXM Data Link (if installed) ...... 7-42 7.12 GSA 81 Servos (if installed) ...... 7-44 7.13 Garmin Traffic Systems (GTS 800) (if installed) ...... 7-46 7.14 GSR 56 ...... 7-49 8. SUBSYSTEM FUNCTIONAL CHECKS ...... 8-1 8.1 Stormscope Functional Check (if installed) ...... 8-1 8.2 TAWS Functional Check ...... 8-1 8.3 FliteCharts Functional Check ...... 8-1 8.4 ChartView Functional Check ...... 8-2 8.5 SafeTaxi Functional Check ...... 8-3 8.6 DME Functional Check ...... 8-4 8.7 ADF Functional Check ...... 8-4 8.8 GTS Traffic System Functional Check ...... 8-4 8.9 Search and Rescue Functional Check (if installed) ...... 8-6 9. G1000 SYSTEM RETURN TO SERVICE PROCEDURE ...... 9-1 9.1 Display Test ...... 9-1 9.2 Display Failure Test ...... 9-4 9.3 Reversion Mode Check ...... 9-5 9.4 GPS Signal Acquisition ...... 9-6 9.5 GPS Failure Test ...... 9-7

G1000 Supplemental Maintenance Manual Page iv Textron Nav III Series Revision 4 190-02128-04

9.6 GIA Failure Test ...... 9-8 9.7 GEA Functional Check ...... 9-9 9.8 G1000 Backup Path Test ...... 9-10 9.9 GFC 700 Autopilot Clutch Overpower Check ...... 9-10 9.10 Maintenance Records ...... 9-10

LIST OF ILLUSTRATIONS FIGURE PAGE Figure 2-1, Flight Stream 510 ...... 2-1 Figure 2-2, GTX 345R/GTX 335R Transponder ...... 2-2 Figure 2-3, GSU-75 ADAHRS with Connector and Mounting Tray ...... 2-3 Figure 2-4, GDL 69A SXM Datalink ...... 2-4 Figure 2-20, GSA 81 Servo Actuator, GSM 86 Servo Gearbox ...... 2-4 Figure 2-3, GMA 1360 Audio Panel ...... 2-5 Figure 2-7, GIA 64W unit ...... 2-5 Figure 2-8, GEA 71B unit ...... 2-5 Figure 2-5, G1000 Softkeys ...... 2-6 Figure 2-6, Normal Mode ...... 2-7 Figure 2-7, Automatic Reversion with MFD failure ...... 2-8 Figure 3-1, SET>ACTV Diagram ...... 3-2 Figure 3-2, Loss of Communication ...... 3-3 Figure 3-3, Configuration Status ...... 3-3 Figure 3-4, Data Transmission Indicators ...... 3-3 Figure 3-5, GSU Configuration Settings Storage ...... 3-13 Figure 3-6, Garmin Unit S/N Location ...... 3-15 Figure 3-7, Software/Configuration Overview ...... 3-16 Figure 3-8, Airframe Group Selection ...... 3-18 Figure 3-9, Airframe Change Confirmation ...... 3-19 Figure 3-10, MFD Aux - Database Page DB Transfer ...... 3-41 Figure 3-11, Stormscope Configuration Page ...... 3-43 Figure 3-12, Stormscope Configuration ...... 3-43 Figure 4-3, GFC Status Page ...... 4-9 Figure 5-1, Aux – System Status Page ...... 5-1 Figure 5-2, System Annunciations ...... 5-2 Figure 5-3, Alerts & Annunciations ...... 5-12 Figure 5-4, Alerts Softkey Annunciation ...... 5-12 Figure 5-5, Magnetometer Interference Test ...... 5-25 Figure 5-6, GTX 335R/345R Looking at Front of Connector (P3251) ...... 5-30 Figure 5-7, GTX 345R (Only) Looking at Front of Connector (P3252)...... 5-30 Figure 5-8, GDU 1054B/1050 Backshell Connector (P10401) ...... 5-31 Figure 5-9, GSU 75 Connector View from Front (P751) ...... 5-31 Figure 5-10, GDL 69A SXM Backplate Connector (P69A1) ...... 5-31 Figure 5-11, GIA 64W Backplate Connectors ...... 5-32 Figure 5-12, GEA 71B Backplate Connectors ...... 5-32 Figure 5-13, GMA 1360 Backplate Connectors ...... 5-33 Figure 5-14, GSR 56 Mating Connector ...... 5-33 Figure 6-1, Configuration Module Installation ...... 6-4 Figure 6-2, GSU 75 Configuration Module Installation ...... 6-5 Figure 6-1, Servo Gear ...... 6-9 Figure 7-1, G1000 Normal Mode Check ...... 7-3 Figure 7-2, Aux – GPS Status Page (MFD) ...... 7-14 Figure 7-3, Normal Engine Instrument Markings (MFD) ...... 7-20

G1000 Supplemental Maintenance Manual Page v Textron Nav III Series Revision 4 190-02128-04

Figure 7-4, Aircraft Registration ...... 7-23 Figure 7-5, GRS/GMU Calibration, Pitch/Roll Offset ...... 7-35 Figure 7-6, GRS/GMU Calibration, Engine Run-Up ...... 7-39 Figure 7-7, Normal Mode AHRS Check ...... 7-41 Figure 8-1, Traffic Map ...... 8-4 Figure 9-1, MFD Power Up Page ...... 9-1 Figure 9-2, PFD Power-up System Annunciations ...... 9-2 Figure 9-3, PFD Normal Operation ...... 9-3 Figure 9-4, GDU Reversionary Mode ...... 9-5 Figure 9-5, AUX-GPS Status Page ...... 9-6

LIST OF TABLES TABLE ...... PAGE Table 1-1, Required Documents ...... 1-4 Table 1-2, Reference Publications ...... 1-6 Table 4-1, Maintenance Intervals ...... 4-4 Table 4-2, GSM 86 Allowable Torque Values (Automated Test) ...... 4-10 Table 4-3, GSM 86 Allowable Torque Values (Fixture Test) ...... 4-11 Table 5-1, SVS Troubleshooting ...... 5-13 Table 5-2, SVS-Related Alert Messages ...... 5-14 Table 5-3, Magnetometer Interference Test Sequence ...... 5-26 Table 6-1, Configuration Module Kit – 011-00979-00 ...... 6-4 Table 6-2, GSU 75 Configuration Module Kit – 011-00979-20 ...... 6-5 Table 7-1, Altitude Test Points ...... 7-28 Table 7-2, Airspeed Test Points ...... 7-29 Table 7-3, Vertical Speed Table ...... 7-29 Table 7-4, Required GRS/GMU Calibrations ...... 7-34

G1000 Supplemental Maintenance Manual Page vi Textron Nav III Series Revision 4 190-02128-04

1. INTRODUCTION 1.1 Content, Scope, Purpose This document provides Instructions for Continued Airworthiness (ICA) for the NXi configuration of the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control System (AFCS) as installed in the Textron Aviation Inc., NAV III series of aircraft, under STC SA01830WI. This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and 14 CFR Part 23 Appendix G. Information in this document is required to maintain the continued airworthiness of the G1000 and GFC700. Throughout this document, the GFC 700 autopilot system is included in the G1000NXi system description and is identified separately only when needed. References to “NAV III” throughout this document include 172R, 172S, 182T, T182T, 206H, and T206H models. Items in this document that are aircraft model(s) specific will identify the model(s) instead of “NAV III”. This document is a supplement to the existing G1000 Nav III Line Maintenance Manual, Garmin part number 190-00352-00. Except where noted, refer to the G1000 Nav III Line Maintenance Manual for servicing instructions.

Applicability This document applies to all Textron Aviation Inc. NAV III aircraft equipped with the G1000NXi system. All G1000NXi NAV III airplanes are configured per General Arrangement drawing 005- 00620-22 Rev 1 or subsequent. Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft operator to include the maintenance information provided by this document in the operator’s Aircraft Maintenance Manual.

Identifying an STC Configuration The General Arrangement drawing lists the G1000 System Software Version numbers approved for this STC. IMPORTANT! If the technician is unsure of an aircraft’s STC configuration, perform the following: After acknowledgement of the splash screen, use the FMS knob to go to the Aux – System Status page on the MFD. In the AIRFRAME section (upper right corner,) the display shows the current G1000NXi airframe configuration and system software version number. The airframe configuration is shown in the Airframe field and the system software version number is shown in the following format: ‘SYS SOFTWARE VERSION XXXX.XX’. It correlates to the software image used to load the software to the system:

EXAMPLE: System Software Version ’2501.00’ = Software Image P/N 006-B2501-00

G1000 Supplemental Maintenance Manual Page 1-1 Textron Nav III Series Revision 4 190-02128-04

1.2 Organization The following outline briefly describes the organization of this manual: Section 2: System Description Provides a description of the type design change associated with installing the G1000 update in the Cessna Nav III Series. Section 3: Software and Configuration Provides software and configuration loading instructions for a complete system software load. Section 4: Instructions for Continued Airworthiness Provides maintenance instructions for continued airworthiness of the G1000 system. Section 5: Troubleshooting Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000 system. Section 6: Equipment Removal & Replacement Gives instructions for the removal and replacement of G1000 equipment. Section 7: Garmin G1000 LRU Replacement/Configuration & Testing Gives instructions for loading software, configuring, and testing of G1000 equipment. Section 8: Subsystem Functional Checks Gives instructions for testing G1000 subsystems. Section 9: G1000 System Return to Service Procedure Specifies return-to-service procedures to be performed upon completion of maintenance of the G1000 system.

G1000 Supplemental Maintenance Manual Page 1-2 Textron Nav III Series Revision 4 190-02128-04

1.3 Definitions/Abbreviations ADAHRS: Air Data and Attitude Heading Reference System ADC: Air Data Computer ADF: Automatic Direction Finder ADS-B: Automatic Dependent Surveillance – Broadcast ADTS: Air Data Test Set AFCS: Automatic Flight Control System AFM: Airplane Flight Manual AFMS: Airplane Flight Manual Supplement AHRS: Attitude Heading Reference System AML: Approved Model List CDU: Control Display Unit CFR: Code of Federal Regulations DME: Distance Measuring Equipment EIS: Engine Indication System FIS-B: Flight Information Services – Broadcast FS: Flight StreamTM GPS: Global Positioning System HSDB: High-Speed Data Bus (Ethernet) ICS: Inter-Com System LRU: Line Replaceable Unit MFD: Multi-Function Display MMC: Multi-Media Card OAT: Outside Air Temperature PFD: Primary Flight Display STC: Supplemental Type Certificate TAWS: Terrain Awareness & Warning System TIS-B: Traffic Information Services – Broadcast VHF: Very High Frequency

G1000 Supplemental Maintenance Manual Page 1-3 Textron Nav III Series Revision 4 190-02128-04

1.4 Units of Measure Unless otherwise stated, all units of measure are English units. 1.5 Publications The following documents are required by this maintenance manual to perform maintenance. It is the responsibility of the owner / operator to ensure latest versions of these documents are used during operation, servicing or maintenance of the airplane. Table 1-1, Required Documents Part Number Garmin Document

005-00620-21 Master Drawing List, G1000 Avionics Updates, Part 23 AML STC

005-00620-22 General Arrangement, G1000 Textron NAV III 005-00620-24 Forward Avionics Install, G1000 Update 172R/172S 005-00620-25 Forward Avionics Install, G1000 Update, 182T/T182T 005-00620-26 Forward Avionics Install G1000 Update, 206H/T206H 005-00620-27 Remote Avionics Install, G1000 Update, 172R/172S 005-00620-28 Remote Avionics Install, G1000 Update, 182T/T182T 005-00620-29 Remote Avionics Install, G1000 Update, 206H/T206H 005-00620-31 Wiring Diagram, GDU 105X PFD/MFD, Textron Models 172, 182, 206 005-00620-32 Wiring Diagram, GSU 75 ADAHRS, Textron Models 172, 182, 206 005-00620-33 Wiring Diagram, GTX3X5 Transponder, Textron Models 172, 182, 206 005-00620-34 Wire Harness Install/Routing, Textron Model 172R/172S 005-00620-35 Wire Harness Install/Routing, Textron Model 182T/T182T 005-00620-36 Wire Harness Install/Routing, Textron Model 206H/T206H 005-00620-38 Pitot/Static Plumbing Mod, Textron Model 182T/T182T 005-00620-39 Pitot/Static Plumbing Mod, Textron Model 206H/T206H 005-00620-AQ Pitch and Trim Servo Installs, Textron 172, GFC 700 Update 005-00620-AR Roll Servo Install, Textron 172, GFC 700 Update 005-00620-AY Wiring Diagram, Cessna 172 E-AFCS 005-00620-B5 Servo Install, GFC700 Update, Textron 182 005-00620-B6 Servo Install, GFC700 Update, Textron 206 005-00620-B7 GSR 56 Install, G1000 Update, Textron 172 005-00620-B8 GSR 56 Install, G1000 Update, Textron 182 005-00620-B9 GSR 56 Install, G1000 Update, Textron 206 005-00620-BA Wiring Diagram, E-AFCS, Textron 182/206 005-00620-BB Wiring Diagram, GMA1360 Audio Panel, Textron NAV III 005-00620-BR Wiring Diagram, GSR 56 Iridium, Textron NAV III

G1000 Supplemental Maintenance Manual Page 1-4 Textron Nav III Series Revision 4 190-02128-04

Part Number Textron Aviation Documents C172RMM Model 172R/172S Maintenance Manual C182SMM Model 182S/182T/T182T Maintenance Manual C206HMM Model 206H/T206H Maintenance Manual SESR Single Engine Structural Repair Manual – 172, 182, 206 Series

G1000 Supplemental Maintenance Manual Page 1-5 Textron Nav III Series Revision 4 190-02128-04

The following publications are recommended to be on hand during the performance of maintenance activities. Table 1-2, Reference Publications Part Number Garmin Document Airplane Flight Manual Supplement, G1000 NXi Integrated Avionics System and GFC 700 190-02128-02 AFCS In Textron NAV III Series of aircraft 190-02178-00 G1000 Cockpit Reference Guide for Cessna NAV III 190-00355-04 GDL 69 Series SiriusXM Satellite Radio Activation Instructions 190-00352-00 G1000 NAV III Line Maintenance Manual

Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealer Resource Center’ section of the Garmin web site; refer to Section 1.6 for details.

1.6 Revision and Distribution This document is required for maintaining the continued airworthiness of the aircraft. When this document is revised, every page will be revised to indicate current revision level. Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center website. Owner/operators may obtain the latest revision of this document from the https://fly.garmin.com/ Support page, or by contacting a Garmin dealer, contacting Garmin Product Support at 913- 397-8200, toll free 866-739-5687, or using around the world contact information on https://fly.garmin.com/. A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant.

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2. SYSTEM DESCRIPTION 2.1 Equipment Descriptions For description of equipment and functions not listed here, refer to the G1000 Nav III Line Maintenance Manual, Garmin part number 190-00352-00. GDU 1054B OR GDU 1050 PFD & MFD Two Garmin GDU 1054B or GDU 1050 displays are installed in the Nav III instrument panel. The GDU 1054B displays are standard equipment on all Nav III models, while the GDU 1050 displays are installed on Model 172 aircraft that are not equipped with the Garmin GFC700 autopilot. The GDU 1054B or GDU 1050 displays are 10.4 inch LCD displays with 1024 x 768 resolution. The GDU 1054B or GDU 1050 units communicate with each other and the GIA 63W units through a high-speed data bus (HSDB) Ethernet connection. The PFD receives primary electrical power from the Essential Bus and secondary electrical power from Avionics Bus No. 1. The MFD receives electrical power from Avionics Bus No. 2. The displays will power-up immediately with external or aircraft power or battery operation. All displays are installed in the panel using ¼-turn fasteners.

Flight Stream 510 The Flight Stream™ 510 (FS 510) is a Wi-Fi/Bluetooth capable multi-media card (MMC) installed the bottom SD slot of the MFD. It sends position, velocity, time, attitude, heading, FIS- B, TIS-B traffic, Sirius XM audio control, Sirius XM weather data, and flight plan transfer to mobile devices via Bluetooth. The FS 510 can also interface with a mobile device via Wi-Fi pairing for the purposes of updating databases used by the GDU(s). Bluetooth and Wi-Fi are mutually exclusive with only one interface functional at a time. Connecting via Wi-Fi requires a pilot-configurable Wi-Fi Protected Access WPA2 security password. By updating databases wirelessly, new databases may be transferred to the G1000 system without taking the data card out of the aircraft.

Figure 2-1, Flight Stream 510

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Transponder The Garmin GTX 33, GTX 345R, or GTX 335R transponders communicate with the GIA 63Ws through RS-232 digital interface. The GTX 345R also communicates with the G1000 Avionics through an HSDB interface connected to the PFD. When installed, the GTX 345R communicates and controls the GTS Processor through the HSDB interface for all TAS operations. The GTX 345R mixes and coordinates the TAS targets with TIS-B targets to provide one coordinated traffic display to the crew. The transponder units are mounted in the tail section of the aircraft. Power is provided to the GTX from the Avionics Bus #2. The GTX transponder interfaces with a transponder antenna mounted to the bottom of the fuselage.

Figure 2-2, GTX 345R/GTX 335R Transponder

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GSU 75 ADAHRS The GSU 75 ADAHRS is a combined Air Data and AHRS system. The unit is mounted in the tail avionics area. It contains advanced tilt sensors, accelerometers, rate sensors, static pressure sensors, and pitot pressure sensors. The GSU 75 receive GPS data from the GIA 63Ws, and magnetic heading from the GMU 44 Magnetometer. The GSU receives primary electrical power from the Essential Bus and a secondary power supply from Avionics Bus 1. The GSU provides electrical power to the onside GMU 44 Magnetometer and the GTP 59 OAT probe. The GSU connects to the existing pitot/static ports. Each GSU 75 provides the following information via ARINC 429 busses to both GIAs, the PFD and the MFD.  Aircraft altitude and airspeed  Aircraft vertical speed, Mach and outside air temperature  Aircraft heading, pitch and roll  Aircraft yaw, pitch and roll rates  Aircraft body-axis accelerations  Rates of change of heading, pitch and roll  Aircraft accelerations expressed in a local level frame of reference

Figure 2-3, GSU-75 ADAHRS with Connector and Mounting Tray

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GDL 69A SXM Datalink The GDL 69A SXM provides SiriusXM Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A SXM is mounted behind the instrument panel in the 182 and 206 models and in the aft avionics area for 172 models. Power to the GDL 69A SXM is received from the Avionics No. 1 bus. The GDL 69A SXM sends weather data through the HSDB bus to the MFD, where the data link interface is controlled. Audio is sent directly to the GMA Audio Panel.

Figure 2-4, GDL 69A SXM Datalink

GSA 81 Servo Actuator and GSM 86 Servo Gearbox The Garmin GSA 81 Servo Actuators are electromechanical units that provides the autopilot control for pitch, roll and pitch trim. The GSM 86 Servo Gearboxes are attached to a mount bracket and are responsible for transferring the output torque of the GSA 81 servo actuators to the mechanical flight control surface linkage.

Figure 2-5, GSA 81 Servo Actuator, GSM 86 Servo Gearbox The installation of these units supports Electronic Stability Protection (ESP) and Under Speed Protection (USP) features. ESP works to assist the pilot in maintaining the aircraft in a stable flight condition. When autopilot is not engaged, ESP helps avoid inadvertent flight attitudes and provide airspeed protection while the pilot is hand-flying the aircraft. The USP feature will correct for slow airspeeds while the autopilot is engaged. USP will lower the nose of the aircraft to maintain an airspeed that prevents the aircraft from stalling.

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GMA 1360 Audio Panel The GMA 1360 audio panel integrates NAV/COM digital audio, intercom system and marker beacon controls. Manual display reversion mode (red DISPLAY BACKUP button) for the PFD and MFD is controlled by the GMA.

Figure 2-6, GMA 1360 Audio Panel

GIA 64W Integrated Avionics Unit The GIA 64W functions as the main communication hub to the G1000 system linking LRUs with the PFD and MFD displays. The GIA 64W contains the GPS/WAAS receiver, VHF COM/NAV receivers, and system integration microprocessors.

Figure 2-7, GIA 64W unit GEA 71B Engine Airframe Unit The GEA 71B Engine/Airframe unit receives and processes signals from engine sensors. Communication interface is to the GIA via RS-485.

Figure 2-8, GEA 71B unit

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2.2 G1000 Optional Interfaces There are no new optional interfaces approved as part of this STC. Refer to the G1000 Nav III Line Maintenance Manual for optional interfaces.

2.3 Electrical Power Distribution The electrical power distribution has not changed as a result of this STC. Refer to the G1000 Nav III Line Maintenance Manual for power distribution.

2.4 Pitot/Static System The layout of the pitot/static system has not changed as a result of this STC, except that the plumbing has been rerouted from the instrument panel area to the tail avionics area for 182 and 206 models.

2.5 GDU 1054B and GDU 1050 Displays The location and function of the controls on the GDU 1054B or GDU 1050 displays are unchanged from those described for the GDU 1040 or GDU 1044B in the G1000 Nav III Line Maintenance Manual.

2.6 Softkeys Some pages have commands or selections that are activated by the GDU 1054B or GDU 1050 softkeys. If a softkey is associated with a command, that command will be displayed directly above the key. A grayed-out softkey shows a command that is unavailable. A softkey that is highlighted (green bar) shows the current active selection.

Figure 2-9, G1000 Softkeys

2.7 FMS Knob The FMS knob is the primary control for the G1000 system. To cycle through different configuration screens: To change page groups: Rotate the large FMS knob. To change pages in a group: Rotate the small FMS knob. To activate the cursor for a page, press the small FMS knob directly in, as one would push a regular button. To cycle the cursor through different data fields, rotate the large FMS knob. To change the contents of a highlighted data field, rotate the small FMS knob. This action either brings up an options menu for the particular field, or in some cases allows the operator to enter data for the field. To confirm a selection, press the ENT key.

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To cancel a selection, press the small FMS knob in again, deactivating the cursor. The CLR key may also be used to cancel a selection or deactivate the cursor. 2.8 G1000 Normal Mode To start the G1000 system in Normal Mode: 1. With a ground power unit connected to the external power receptacle, turn ON the BAT (battery) switch. The following G1000 equipment is powered on:  PFD display  GSU 75 ADAHRS  GIA #1 (NAV and COM)  GEA Engine/Airframe Unit 2. Turn ON the AVIONICS BUS 1 and AVIONICS BUS 2 switches. The following G1000 equipment is powered on:  PFD (secondary power)  MFD  GSU 75 ADAHRS (secondary power)  GIA #1 (NAV) (secondary power)  GEA Engine/Airframe Unit (secondary power)  GTS 800 Traffic System (if installed)  GTX Mode S/ADS-B Transponder  GIA #2 (NAV and COM)  GMA Audio Panel  GSA Servos  GSR 56 Satellite Transceiver The G1000 system is now powered in the normal mode. In the normal operating mode, data fields that are invalid have large red X’s through them. A valid field does not display a red X. Allow the displays to initialize for approximately one minute for the red X’s to be removed. The PFD and MFD will function as specified in the G1000 Cockpit Reference Guide when the system has been correctly installed and configured.

Figure 2-10, Normal Mode

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2.9 Reversionary Mode Reversionary mode allows for display of information related to safe flight in the event of a display communication or hardware failure. The PFD automatically goes into reversionary mode when communication to the MFD is lost. Manual reversionary mode allows the operator to force the PFD and MFD into reversionary mode by pressing the large red button labeled ‘DISPLAY BACKUP’ on the GMA audio panel. NOTE When the ‘DISPLAY BACKUP’ button is pushed to exit reversionary mode, there is a 5-second delay until the display returns to normal mode. If the ‘DISPLAY BACKUP’ button is pushed again during this 5-second delay, the display will reset the five second delay timer.

Figure 2-11, Automatic Reversion with MFD failure

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3. Software and Configuration 3.1 Configuration Mode Overview Throughout this document, references are made to the PFD and/or MFD being in configuration mode. The configuration mode exists to provide the avionics technician with a means of configuring, checking, and calibrating various G1000 sub-systems. Troubleshooting and diagnostics information can also be viewed in this mode. To start the G1000 system in configuration mode, follow these steps: 1. Apply power to the G1000 system by applying aircraft EXT power, selecting the BAT MASTER and AVIONICS BUS 1 and AVIONICS BUS 2 switches to ON. 2. Pull the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 3. Press and hold the ENT key on the MFD while applying power using the MFD circuit breaker. 4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the MFD. 5. Press and hold the ENT key on the PFD while applying power using the PFD (ESS BUS) circuit breaker. 6. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the PFD. CAUTION: Configuration Mode contains certain pages and settings that are critical to aircraft operation and safety. These pages are protected and cannot be modified, unless the technician is properly authorized and equipped. However, most protected pages are viewable to allow system awareness for troubleshooting. NOTES If the specific procedure requires an SD card to be in the top slot of the PFD/MFD, this card must be inserted prior to applying power to the PFD/MFD. Any time a card is inserted, the power to the PFD/MFD must be cycled. For a complete description and breakdown of each Configuration Mode page, refer to the G1000 System Maintenance Manual listed in Table 1-2.

SET>ACTV Configuration Throughout the configuration mode pages, there are SET and ACTIVE columns for input/output settings and other parameters. SET: Refers to a setting or group of settings that reside in PFD Internal Memory and/or the Master Configuration Module. ACTIVE: Refers to an ‘active’ setting or parameter currently being used by the LRU. LRUs store the ‘active’ settings within internal memory. Data can be manually copied from one column to the other (and consequently from PFD memory to the LRU memory and vice-versa) by using the following two softkeys, when available:  SET>ACTV (read ‘Set to Active’) softkey: Allows the installer to send the information in the SET column (data stored in the master config module) to the ACTV column (data used by LRU).

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 ACTV>SET (read ‘Active to Set’) softkey: Causes the LRUs current settings to be copied to the master configuration module as SET items. CAUTION: The ACTV>SET softkey must be used with caution! If an improperly configured unit is installed, this softkey causes the wrong configuration to replace the correct aircraft configuration.

In the first example shown in Figure 3-1 the SET columns do not match the ACTIVE columns. The inequality between SET and ACTIVE indicates a configuration mismatch. By pressing the SET>ACTV softkey, this copies the SET column to the LRU unit’s configuration memory. The settings then become the ACTIVE settings for the LRU being configured.

Figure 3-1, SET>ACTV Diagram

When troubleshooting the system, technicians can look for inequalities between SET and ACTIVE columns. Certain problems can be resolved simply by pressing the SET>ACTV softkey, which reloads settings to the specific LRU from the PFD. (Note that this can also be accomplished by reloading the configuration files for the LRU. Section 7 describes this process for each LRU).

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A blank active column, as shown in Figure 3-2, represents loss of communication between the display and the particular unit. See Section 5 for more details on troubleshooting.

Figure 3-2, Loss of Communication

Configuration Prompts When configuration settings are changed, the technician receives on-screen prompts and/or confirmations such as those shown in Figure 3-3.

Figure 3-3, Configuration Status

Data Transmission Indicators Several configuration screens utilize an indicator light system to show discrete (ON/OFF) data and/or hardware component status. Unless otherwise noted, the following applies to all such status indicators:  Green Checkmark: Expected data is successfully received and is ON. A green check could also indicate that the parameter/component is working correctly.  Red X: Expected data is not received. A red X could also indicate that a parameter/component is invalid.  White N/A: Expected data is OFF, or no data is expected.

Figure 3-4, Data Transmission Indicators

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Configuration Mode Navigation Using the FMS knob as described in Section 2.7, a user can navigate through different pages and page groups in the Configuration Mode. For complete description and breakdown of each page, refer to the G1000 System Maintenance Manual listed in Table 1-2. Pages below will be shown only for the units/options installed on the aircraft. System Page Group 1. System Status 7. Transaction Log 13. System Setup 2. Time Configuration 8. Aircraft Configuration 14. Manifest Configuration 3. Lighting Configuration 9. Diagnostics Terminal 15. Log Utilities 4. System Audio 10. OEM Diagnostics 16. Configuration Manager 5. System Upload 11. System Configuration 6. LRU Replacement 12. System Data Path Configuration GDU Page Group 1. Serial Configuration 6. Diagnostics 11. Airframe Configuration 2. CDU Status Page 7. Ethernet Test 12. TAWS Configuration 3. Key Test 8. Video Test 13. SurfaceWatch Configuration 4. FS 510 Test 9. Alert Configuration 14. Connext Connections 5. CDU Calibration 10. DAT Configuration GIA Page Group (for GIA 63W only) 1. Serial Configuration 3. GIA I/O Configuration 5. GIA Status Page 2. GIA RS-485 Configuration 4. GIA COM Setup Page 6. GIA CAN Configuration GIA 64x Page Group (for GIA 64W only) 1. ARINC Configuration 5. GFC Status 9. IO Configuration 2. CAN Configuration 6. COM Status 10. NAV Status 3. COM Calibration 7. GFC Configuration 11. Serial Configuration 4. COM Configuration 8. GIA Status GEA Page Group (for GEA 71 only) 1. 2. GEA Status Page 3. GEA Configuration GEA 71x Page Group (for GEA 71B only) 1. Engine Configuration 4. Digital In 7. GEA Status 2. Analog In 5. Discrete In 8. XVDT In 3. Annunciate Out 6. Excitation 9. XVDT Out GTX Page Group (for GTX 33 only) 1. Serial Configuration 2. Transponder Configuration GTX 3X5 Page Group 1. Transponder Airframe Config 2. Transponder Wiring Config 3. Transponder Diagnostics GTX 3X5 Page Group (for GTX 335R, GTX 345R only) 1. Transponder Airframe Config 2. Transponder Diagnostics 3. Transponder Wiring Config GRS Page Group 1. Inputs Configuration 3. GRS Flight Data Log 4. GRS 79 Flight Log Download 2. GRS / GMU Calibration G1000 Supplemental Maintenance Manual Page 3-4 Textron Nav III Series Revision 4 190-02128-04

ADC Page Group 1. ADC Configuration GFC Page Group 1. GFC Configuration 2. GFC Status GMA Page Group (for GMA 1347 only) 1. GMA Configuration GMA x36x Page Group (for GMA 1360 only) 1. GMA Discrete In 5. GMA Misc 9. GMA Status 2. GMA Discrete Out 6. GMA Noise 10. GMA Volume 3. GMA Fast Volume 7. GMA Options Configuration 4. GMA Marker 8. GMA Squelch GDL Page Group 1. GDL 69 Configuration 2. GSR 56 Configuration GTS Page Group 1. GTS Configuration OTHER Page Group 1. Stormscope CAL Page Group 1. Fuel Tank Calibration 3. HSCM Calibration 2. Flaps & Trim Calibration 4. DAT Calibration

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G1000 System Software Information NOTE The following sections provide a detailed description of loading all G1000 software and configuration files, which may be excessive for individual LRU removal and replacement. If removing and replacing individual LRUs, refer to Section 6 of this manual for the necessary steps.

G1000 Software Image All software and configuration files were certified by Garmin and are considered part of FAA- approved Type Design data. Approved software and hardware definitions for each STC Configuration are defined on the appropriate General Arrangement drawing listed in Table 1-1. G1000 software and configuration files are controlled via the approved software image part number listed on the General Arrangement drawing listed in Table 1-1. This software image is loaded into the G1000 using a software loader card. The installer shall create this software loader card by downloading the approved software image in accordance with Section 3.1.6. NOTE Only SanDisk brand SD cards are recommended for use with the G1000 system. Other brand cards have not been tested by Garmin.

IMPORTANT! To satisfy the G1000/GFC700 STC requirements for the Nav III aircraft, it is critical that the technician install correct software image part number when servicing the G1000 system.

Approved software image part numbers are defined on the appropriate General Arrangement drawing (see Table 1-1).

CAUTION: Be cautious when using software loader cards during maintenance. The G1000 system immediately initializes the card upon power-up. On-screen prompts must be given careful attention in order to avoid potential loss of data. Always read through procedures given in this manual before attempting to use the software loader cards.

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Loader Card Creation The software image is an executable self-extracting file which builds the correct file structure onto an SD card for use loading software to the G1000 System. To obtain the current file follow the procedures outlined below.

NOTE

In order to create a Textron Nav III system loader card, the installer completing these procedures must be an authorized Garmin Service Center to gain access to the necessary data via the Garmin website.

1. Go to www.garmin.com and click on the Dealer Resource Center link in the lower portion of the home page. Enter your Garmin Dealer username and password.

2. Select Support button then select Software Downloads.

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3. In the Product Search tab, type Cessna in the Product Name or Part Number box, then select the appropriate system and then press the Search button. 4. A screen similar to the one shown below will appear. The numbers shown are for example only.

5. Click on the Select Action button for the appropriate software image part number as shown on the Garmin General Arrangement drawing 005-00620-22 and choose Download to save the software file to the local hard drive.

6. After the file is downloaded, close the web browser. 7. Insert a blank (empty) SD card in the card reader. The loader card program will delete all files on the SD card before loading G1000 system software files on it if the card is not blank. 8. Double-click the .exe file that was downloaded onto the local hard drive. The following window will pop-up on the screen. Click Yes to continue.

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9. Follow the on screen prompts to continue.

10. Check the “I accept the terms of the License Agreement” checkbox.

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11. Select the SD card reader drive and click Next>.

12. Follow the on screen prompts to continue.

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13. The program will make the SD loader card and prompt you when it’s done.

14. Once successfully completed, the following window will display. Click Finish to close the program. The SD card can then be removed from the computer and is ready for use in the aircraft.

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Software Files Software files are defined by part number and version number on the General Arrangement drawing. Each G1000 system LRU reports the software version it currently contains to the user in two places.  Normal System Mode: The Aux – System Status page lists each LRU and the reported software version.  Configuration Mode: The System Status page (System page group) reports more detailed LRU information, including software version, part number, and LRU status. Software files are loaded to LRUs from the PFD System Upload page in configuration mode.

Configuration File Descriptions There are configuration files for baseline settings and various options. Configuration files contain preset selections for input/output channels, aircraft-specific settings, and LRU-specific settings.

IMPORTANT! Certain software and configuration files are REQUIRED to be re-loaded during maintenance that involves removal and replacement of G1000 equipment. Refer to Section 7 for re-configuration requirements for each individual G1000 LRU. Pay special attention to the selection of option files for the units to assure a complete load.

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Configuration File Storage The storage of G1000 system configuration files is unchanged from that depicted in the G1000 Nav III Line Maintenance Manual, except as noted in Figure 3-5 for the GSU 75. The GSU 75 ADAHRS air data configuration file is loaded directly to GSU 75 internal memory. A copy of the file is stored in the GSU 75 configuration module. The GSU also stores AHRS calibration data acquired during the post installation checkout, which is characteristic to the specific installation. A copy of this calibration data is stored in the GSU configuration module. While performing maintenance on this unit, re-calibration may be required. See Section 7.10 for more information on re-calibration criteria.

Figure 3-5, GSU Configuration Settings Storage

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3.2 Configuration Mode Throughout this document, references are made to the PFD and/or MFD being in configuration mode. To start the G1000 system in configuration mode, follow these steps: 1. With the G1000 system off, open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Connect external power to the aircraft and energize the aircraft and avionics electrical busses. 3. Press and hold the ENT key on the MFD and close the MFD circuit breaker. 4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the MFD. 5. Press and hold the ENT key on the PFD and close the PFD (ESS BUS) and PFD (AVN BUS 1) circuit breaker. 6. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the PFD.

3.3 G1000 Hardware/Software Compatibility Check Before installing software, the technician must first ensure that hardware part numbers are compatible with the G1000 system software image that is to be used. The General Arrangement drawing shows all available combinations of hardware and software part numbers. A G1000 system loader card is required to install software and configuration settings to a newly installed G1000 system. The part number of the software image used to create the loader card is directly associated with the combination of software file part numbers and version levels that are defined on the General Arrangement drawing. Should software part numbers or versions change, a new software image part number is issued.

IMPORTANT

After verifying hardware/loader card compatibility, record the software image part number and all LRU hardware part numbers in the appropriate aircraft records before proceeding.

NOTE

Throughout the next section of this document, screen shots and examples are used to illustrate the software and configuration loading process. These screen shots are provided as reference only. Always refer to the General Arrangement drawing for the correct software file names, versions and part numbers.

3.4 Equipment Verification (Third Party/Optional Equipment Documentation) It is extremely important to know exactly what equipment the aircraft is equipped with before loading any files. Loading the incorrect files could lead to longer down time and unplanned removal of equipment.  Garmin optional equipment (i.e. GDC 74 ADC, GRS 77 AHRS or GSU 75 ADAHRS, GTX 33 or GTX 3X5 transponder, etc.). Section 3.4.1 helps find which units are installed without a physical inspection.

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 Third party avionics equipment interfaced to G1000 (ADF, DME, non-Garmin traffic systems, WX-500, etc.). To determine if the third party equipment is installed, check the circuit breaker panel for circuit breakers for the units, and check for G1000 controls for the third party devices. Determining Installed Garmin Units Use the table in Appendix A to determine what the unit part number is based on the unit’s serial number reported on the MFD Aux - System Status page in Normal mode or PFD System Status page in Config mode. The table lists the units that have different loader card option files so the installer can choose the correct file without requiring the unit to be physically inspected.

Figure 3-6, Garmin Unit S/N Location

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3.5 G1000 Software/Configuration Procedure This section summarizes the procedures required to load software and configuration files to the G1000. It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft. In sections of this manual where software is required to be reloaded, these sections will make reference back to this section for instructions. The technician should use proper judgment regarding the context of maintenance required while following this section. The following diagram depicts an overview of the software/configuration sequence for the G1000 system. This applies mostly to a new G1000 system software installation by Service Bulletin and is for informative purposes only.

Figure 3-7, Software/Configuration Overview

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3.6 System Software and Configuration Load System Power Up Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. DO NOT RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A BATTERY CHARGER AS AN EXTERNAL POWER SOURCE DUE TO ELECTRICAL NOISE IT MAY INJECT IN THE G1000 SYSTEM. Power loss during a software upgrade may cause a LRU to become corrupted and unresponsive requiring replacement. Remove power only when told to do so in the procedure.

MFD & PFD Software Load 1. Open the MFD, PFD (ESS BUS) and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS510 cards from bottom slots of PFD and MFD if present. 3. Insert the software loader card into the MFD top card slot. 4. Turn on Avionics/electrical busses. 5. Press and hold the ENT key on the MFD. 6. Close the MFD circuit breaker. 7. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, release the ENT key, then press the YES softkey.

8. After the new GDU software is loaded to the MFD, a “DO YOU WANT TO UPDATE THE SPLASH SCREEN?” prompt may appear. If it does, press the NO softkey. The splash screen will be loaded later in this procedure.

9. When complete, the MFD starts in configuration mode displaying the “System Status” page. 10. Open MFD circuit breaker, remove the loader card from the MFD and insert it into the PFD top card slot. 11. Repeat Steps 5 through 9 for the PFD. When complete, leave the PFD on with the loader card remaining in the top card slot. 12. Start the MFD in configuration mode by pressing and holding the ENT key when closing the circuit breaker. Release the key when the words “INITIALIZING SYSTEM” appear on the screen.

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Baseline Software and Configuration Load

IMPORTANT If the aircraft being modified has incorporated any modifications beyond factory configuration that effect engine or airspeed limitations, your configuration may not be supported at this time. It is the responsibility of the installer to ensure compatibility with existing modifications. Do not allow power to be removed from the system when loading software. Remove power only when instructed by the following procedures. Unless instructed otherwise, all displays should be in the same mode (configuration or normal). Follow the order of software and configuration loading, do not skip or rearrange steps. Do not operate or turn off MFD while loading software and configuration files unless specifically instructed to do so. A failed or cancelled load may result. If an incorrect configuration file is loaded at any time during this procedure, STOP and start the configuration load over.

1. Ensure all avionics circuit breakers are closed and the G1000 system is fully powered. 2. On the PFD, go to the SYSTEM UPLOAD page using the small FMS knob. 3. Push in the PFD FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to activate the drop-down menu. Rotate the small FMS knob to highlight the applicable airframe from the selections shown in Figure 3-8 in the drop-down menu and press the ENT key to select it.

Figure 3-8, Airframe Group Selection

4. If an airframe type was selected that does not match the previously configured airframe type, a popup similar to the one shown in Figure 3-9 will appear. Select “NO” by pressing the “NO” softkey at the bottom of the screen. Return to the previous step and select the correct airframe type in the Airframe Group selection.

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Figure 3-9, Airframe Change Confirmation

5. Once the appropriate airframe option is selected, the cursor moves to the ITEM window. Rotate the small FMS knob to activate the drop-down menu. Highlight “Cessna XXX – Baseline Configuration” (where XXX is the airframe type selected above) and press the ENT key to select it. The PRODUCT field will then populate. NOTES The PRODUCT window displays information regarding each G1000 LRU. The LRU column depicts the reported software version of the LRU (may be blank if PFD cannot communicate with the unit yet until after config files are loaded). The CARD VERS column shows the LRU software version stored on the Loader Card. The SOFTWARE column may or may not have all boxes checked automatically. For the initial software load in the system all software boxes should be checked to load all files. This is done by pressing the CHK ALL softkey when instructed below. The CONFIGURATION column defaults to having all unit configuration boxes checked. The hardware serial number is used to determine appropriate software for the GIA COM, GIA NAV, GMU 44, and GSA 8X units. Until the system configuration loads sufficiently to access and read these units, they may show a “INV” invalid status under the LRU VERS and CARD VERS columns with up to two line items per item (representing different hardware configurations). After the configuration files are loaded, the units will update and remove the “INV” status and will load automatically. 6. Press the CHK All softkey. 7. Press the Load softkey. 8. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” or White “N/A” in all Configuration and Software columns.  “Upload Complete………….COMPLETE” in the summary box. 9. Press the ENT key to acknowledge the prompt that appears in the pop-up box..

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GSU 75 Software/Configuration Loading (if installed) Follow this procedure to configure the GSU 75 ADAHRS. Move the cursor to the Item window and rotate FMS inner knob to display drop down menu. Highlight “Baseline Option – GSU75 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” or White “N/A” in all Configuration and Software columns.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

GTX 335 Transponder Software/Configuration Loading (if installed) Follow this procedure to configure the GTX 335 transponder in the aircraft. Do not follow the procedures in this section if a GTX 335 is not installed in the aircraft. Move the cursor to the Item window and rotate FMS inner knob to display drop down menu. Highlight “Baseline Option – GTX 335 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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GTX 345 without GTS 800 Transponder Software/Configuration Loading (if installed) Follow this procedure to configure the GTX 345 transponder in the aircraft in aircraft without a GTS 800. Do not follow the procedures in this section if a GTX 345 is not installed in the aircraft or if the GTX 345 is installed with a GTS 800. Move the cursor to the Item window and rotate FMS inner knob to display drop down menu. Highlight “Baseline Option – GTX 345 Installation, without GTS 800” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

GTX 345 with GTS 800 Transponder Software/Configuration Loading (if installed) Follow this procedure to configure the GTX 345 transponder in the aircraft in those aircraft that have a GTX 345 and a GTS 800 installed Do not follow the procedures in this section if a GTX 345 is not installed in the aircraft or if there is a GTX 345 installed without a GTS 800 installed. Move the cursor to the Item window and rotate FMS inner knob to display drop down menu. Highlight “Baseline Option – GTX 345 Installation, with GTS 800” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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GDL 69A SXM Software/Configuration Loading (if installed) Follow this procedure to configure the GDL 69A SXM Receiver. Do not follow the procedures in this section if a GDL69A SXM unit is not installed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Baseline Option – GDL 69A SXM Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

GMA 1360 Software/Configuration Loading Follow this procedure to configure the GMA 1360 Audio panel. 1. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Baseline Option – GMA 1360 Installation” and press the ENT key to select it. 2. Press the CHK All softkey. 3. Press the Load softkey. 4. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. 5. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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Enhanced GFC 700 Software/Configuration Loading (if installed) Follow this procedure to configure the GFC 700 Enhanced Autopilot. Do not follow the procedures in this section if the aircraft is not equipped with GFC 700. 1. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – GFC 700 E-AFCS Installation” and press the ENT key to select it. 2. Press the CHK All softkey. 3. Press the Load softkey. 4. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

GFC 700 Software/Configuration Loading (if installed) Follow this procedure to configure the GFC 700 Autopilot. Do not follow the procedures in this section if the aircraft is not equipped with GFC 700. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – GFC 700 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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Flight Stream 510 Configuration Loading (if installed) Follow this procedure to configure the system to use the FS 510 WiFI/Bluetooth datalink. Do not follow the procedures in this section if the aircraft is not equipped with a FS 510. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – Enable FS510” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

CAN Bus Fuel Level Sensors (if installed) Follow this procedure to configure the system to use CAN Bus Fuel Level Sensors. Do not follow the procedures in this section if the aircraft is not equipped with CAN Bus Fuel Level Sensors. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – CAN BUS FUEL LEVEL SENSORS” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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GSR 56 loading (if installed) Follow this procedure to load the GSR 56 satellite phone/text/weather datalink transceiver. Do not follow the procedures in this section if the aircraft is not equipped with a GSR 56. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – GSR 56 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. 6. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

GTS 800 without GTX 345 Software/Configuration Loading (if installed) Follow this procedure to configure the GTS 800 Traffic System. Do not follow the procedures in this section if the aircraft is not equipped with GTS 800 or if it is equipped with a GTS 800 and a GTX 345.

NOTE Configuration of the GTS Processor will require entering the aircraft registration number into the unit using Section 3.8, “Aircraft Registration Number Entry”. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – GTS 800 Installation, without GTX 345” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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GTS 800 with GTX 345 Software/Configuration Loading (if installed) Follow this procedure to configure the GTS 800 Traffic System. Do not follow the procedures in this section if the aircraft is not equipped with GTS 800 or if it is equipped with a GTS 800 and without a GTX 345.

NOTE Configuration of the GTS Processor will require entering the aircraft registration number into the unit using Section 3.8, “Aircraft Registration Number Entry”. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – GTS 800 Installation, with GTX 345” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

WX500 Configuration Loading (if installed) Follow this procedure to configure the system to utilize the WX 500. Do not follow the procedures in this section if the aircraft is not equipped with WX500. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – WX500 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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KN63 DME Configuration Loading (if installed) Follow this procedure to configure the system to use the KN 63 DME. Do not follow the procedures in this section if the aircraft is not equipped with a KN 63. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – KN63 DME Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

KR87 ADF Configuration Loading (if installed) Follow this procedure to configure the system to use the KR 87 ADF. Do not follow the procedures in this section if the aircraft is not equipped with a KR 87. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – KR87 ADF Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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GRS 77 and GDC 74 Software/Configuration Loading (if installed) Follow this procedure to configure the system for GRS 77 and GDC 74. Do not follow the procedures in this section if the aircraft is not equipped with the GRS 77 and GDC 74. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Baseline Option – Legacy – GRS77 and GDC74 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

GTX 33 ES Software/Configuration Loading (if installed) Follow this procedure to configure the system to use a GTX 33 ES Transponder. Do not follow the procedures in this section if the aircraft is not equipped with a GTX 33 ES. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Baseline Option – Legacy – GTX 33 ES Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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GDL 69 Software/Configuration Loading (if installed) Follow this procedure to configure the GDL 69 Receiver. Do not follow the procedures in this section if a GDL69 unit is not installed or if a GDL 69A SXM unit is installed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Baseline Option – Legacy – GDL 69 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

Disable CO Guardian Configuration Loading (if CO Guardian not installed) Follow this procedure to disable the CO Guardian (if a CO Guardian is not installed). Do not follow the procedures in this section if the aircraft is equipped with a CO Guardian. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – Disable CO Guardian Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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KTA 870 Configuration Loading (if installed) Follow this procedure to configure the system to use a KTA 870 Traffic System. Do not follow the procedures in this section if the aircraft is not equipped with a KTA 870. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – KTA870 TAS Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

KAP 140 Configuration Loading (if installed) Follow this procedure to configure the system to use a KAP 140 Autopilot. Do not follow the procedures in this section if the aircraft is not equipped with a KAP 140. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – KAP 140 Installation” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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Pre BP 2007 CI 2480-400 Antenna Configuration Loading (if installed) Follow this procedure to configure the system to use a CI 2480-400 Antenna (Pre BP 2007 aircraft). Do not follow the procedures in this section if the aircraft is not a Pre-BP 2007 Aircraft with CI 2480-400 Antenna installed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – Pre BP 2007 Comant CI 2480-400 Antenna Configuration” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

BP 2007 CI 2580-410 Antenna Configuration Loading (if installed) Follow this procedure to configure the system to use a CI 2580-410 Antenna (BP 2007 aircraft). Do not follow the procedures in this section if the aircraft is not a BP 2007 Aircraft with CI 2580- 410 Antenna installed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – BP 2007 Comant CI 2580-410 Antenna Configuration” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

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Initialize Fuel Cal Data (Only for CAN Bus Fuel sensors before fuel cal) Follow this procedure to initialize fuel cal data. This section is only for aircraft with CAN Bus Fuel Sensor and only before the fuel calibration is completed. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – INITIALIZE FUEL CAL DATA (only for CAN Bus sensors before fuel cal)” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

Delete CAN Fuel Sensor Fuel Calibration (if installed) Follow this procedure to delete the CAN Bus Fuel Sensor Fuel Calibration. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “Option – Delete CAN Fuel Sensor Fuel Calibration” and press the ENT key to select it. Press the CHK All softkey. Press the Load softkey. Monitor the loading progress and verify the software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Save Configuration 1. Press the UPDT CFG softkey at the bottom of the SYSTEM UPLOAD page. 2. Press the ENT key to select YES in the pop-up window to start the update. 3. When the config module update is done, press the ENT key to select OK in the pop-up window to close it. 4. Open PFD circuit breakers, remove the software loader card.

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3.7 Feature Enablement This section describes how to unlock or enable optional features. The installer will only load the sections for the features they require. For installing all feature enablement cards, the PFD and the MFD must be in configuration mode. The G1000 has various features that require the use of unlock/enable cards to activate the feature. Throughout this document these cards are generically referred to as ‘enablement cards’. In some cases, the actual label on the physical card may say ‘unlock’. If uncertain what SD Card to use, the technician must verify the card part number on the General Arrangement drawing prior to use to assure the correct feature is unlocked.

ChartView Feature Enablement Follow this procedure to activate Jeppesen ChartView. Enabling this feature, allows the pilot to switch between Garmin FliteCharts and Jeppesen ChartView products.

NOTES The required ChartView databases are subscription-based and need to be procured by the installing agency from the Garmin or Jeppesen website. The ChartView database is not present in a new display.

Insert the ChartView Enablement card in the top slot of the PFD and power on the PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10 On the PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “Configuration Files” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “Enable ChartView” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open the PFD circuit breakers and remove the ChartView enablement card.

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Synthetic Vision System Enablement Follow this procedure to enable the Synthetic Vision feature. Insert the SVS Enablement card in the top slot of the PFD and power on the PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10. On the PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “Configuration Files” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “Enable SVS Single PFD” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open the PFD circuit breakers and remove SVS enablement card.

SurfaceWatch Enablement Follow this procedure to enable the SurfaceWatch feature. Insert the SurfaceWatch Enablement card in the top slot of the PFD and power on the PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10. On PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “Enable_SurfaceWatch” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “SurfaceWatch Feature Enable” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open PFD circuit breaker and remove the SurfaceWatch enablement card.

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TAWS-B Enablement Follow this procedure to enable the TAWS-B feature.

Insert the TAWS-B Enablement card in the top slot of the PFD, power on the PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10. On the PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “Configuration Files” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “Enable TAWS” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open the PFD circuit breaker and remove TAWS-B enablement card.

Enhanced Search and Rescue Enablement Follow this procedure to enable the Enhanced Search and Rescue (SAR) feature.

Insert the Enhanced SAR Enablement card in the top slot of the PFD, power on PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10. On the PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “Enhanced SAR” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “Enhanced Search and Rescue” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open the PFD circuit breaker and remove Enhanced SAR enablement card.

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Search and Rescue Enablement (not required if enhanced SAR is enabled) Follow this procedure to enable the Search and Rescue (SAR) feature.

Insert the SAR Enablement card in the top slot of the PFD, power on PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10. On the PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “Configuration Files” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “Enable SAR” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open the PFD circuit breaker and remove the SAR enablement card. Enhanced AFCS Enablement Follow this procedure to enable the Enhanced AFCS feature.

Insert the Enhanced AFCS Enablement card in the top slot of the PFD, power on PFD in configuration mode. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.7. On the PFD, select the “System Upload” page using the small FMS knob. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS knob to highlight “Enhanced AFCS” and press the ENT key to select it. In the ITEM window, rotate the small FMS knob to highlight “Enable Enhanced AFCS” and press the ENT key to select it. Press the Load softkey. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration column for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. Press the ENT key to acknowledge the prompt that appears in the pop-up box. Open the PFD circuit breaker and remove the Enhanced AFCS enablement card.

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3.8 Aircraft Registration Number Entry and Flight ID Configuration NOTE Steps to complete the aircraft registration entry and Flight ID configuration are dependent on transponder equipment installed. Choose the appropriate procedure from Section 3.8.1 or 3.8.2 to complete the aircraft registration entry.

Aircraft Equipped with GTX 33 Aircraft Registration Number Entry Place the PFD in configuration mode, if not already there. Select the AIRCRAFT CONFIGURATION page on the PFD. Activate the cursor to select the” AIRCRAFT REGISTRATION” field and enter the aircraft’s tail number. If the ICAO Address field does not auto-fill, rotate the large FMS knob to select the “ICAO ADDRESS” and enter the aircraft’s 24 bit ICAO address. If applicable, rotate the large FMS knob to select the “ICAO REGION” field and select the appropriate ICAO region. If applicable, rotate the large FMS knob to select the “DOMAIN IDENTIFIER” field and enter the number. Press the ENT key to save. Otherwise, leave blank. Rotate the large FMS knob to select the “VFR CODE” field and enter the desired code that will become active when the VFR key on the GDU is pressed. Press the SET GTX1 softkey and acknowledge the PFD prompt by pressing the ENT key. Press the SET GTS softkey (if present) and acknowledge the PFD prompt by pressing the ENT key. After completing transponder configuration, deactivate the cursor.

Flight ID Configuration 1. Select the GTX Group and the TRANSPONDER CONFIGURATION page on the PFD. 2. Activate the cursor and select the “FLIGHT ID TYPE” field. 3. Rotate the small FMS knob to activate the drop-down menu. 4. Select “PFD ENTRY” and press the ENT key. 5. After completing transponder configuration, deactivate the cursor.

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Aircraft Equipped with GTX 335 or GTX 345 Aircraft Registration Number Entry Insert the software loader card into the top slot of the PFD. Place the PFD in configuration mode. Press the NO softkey (number 11 softkey) to acknowledge the following prompt.

Rotate the small FMS knob, select the AIRCRAFT CONFIGURATION page on PFD. Activate the cursor to select the “AIRCRAFT REGISTRATION” field and enter the aircraft’s tail number. If the ICAO Address field does not auto-fill, rotate the large FMS knob to select the “ICAO ADDRESS” and enter the aircraft’s 24 bit ICAO address. If applicable, rotate the large FMS knob to select the “ICAO REGION” field and select the appropriate ICAO region. If applicable, rotate the large FMS knob to select the “DOMAIN IDENTIFIER” field and enter the number. Press the ENT key to save. Otherwise, leave blank Rotate the large FMS knob to select the “VFR CODE” field and enter the desired code that will become active when the VFR key on the GDU is pressed. Press the SET GTS softkey (if present) and acknowledge the prompt by pressing the ENT key. Deactivate the cursor. Rotate large FMS knob to select “GTX 3X5.” Rotate the small FMS knob to select “Transponder Airframe Configuration” page. Verify the GTX1 box at the top of the page is green and the tail number, ICAO address, IATA Airline Designator, and VFR code that were entered previously are correct.

Flight ID Configuration 1. Select the GTX 3X5 Group and the Transponder Airframe Config page on the PFD. 2. Activate the cursor and select the “Allow Flight ID Entry” field. 3. Rotate the small FMS knob to activate the drop-down menu. 4. Select “PFD ENTRY” and press the ENT key. 5. Scroll Down to highlight “SET > ACTIVE” and press the ENT key. 6. After completing transponder configuration, deactivate the cursor.

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3.9 Configuration Manager NOTE All items listed in the Configuration Manager will display “Valid” in the Status column, with the exception of the GSR 56 (if installed). The GSR 56 will display “Status not supported” in the Status column. Rotate the large FMS knob to select “SYSTEM”. Rotate the small FMS knob to select Configuration Manager page on PFD. Press the softkey labelled CNFM CFG on PFD. Press the ENT key on PFD to select OK when prompted to confirm configuration as expected configuration. Verify the fleet, aircraft expected and actual configuration IDs match. If they do not match, repeat steps 2-4. If they match, continue to next step. Open MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers.

3.10 Splash Screen Loading When all software and configuration has been loaded, the splash screens must be loaded to the display units (PFD and MFD). Insert the software loader card in the upper slot of the MFD. Cloe MFD circuit breaker. When prompted to update system files, press the NO softkey. When prompted to update splash screen files, press the YES softkey. When the SYSTEM STATUS configuration page appears, Open the MFD circuit breaker. Remove the loader card from the MFD and insert it into the upper slot of the PFD. Close PFD (ESS BUS) circuit breaker. When prompted to update system files, press the NO softkey. When prompted to update splash screen files, press the YES softkey. When the SYSTEM STAUTS configuration page appears, Open PFD (ESS BUS) circuit breaker.

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3.11 Database Loading Follow this procedure to load the databases. Obtain the following databases from fly.garmin.com and install on a blank 16GB or larger card or by obtaining Garmin SD Card p/n 010-00474-50. Databases with an asterisk are not included on the p/n 010-00474-50 SD card. When obtaining the databases from fly.garmin.com and using SD cards smaller than 16GB, you may need to use multiple cards (or reuse one) to load all the databases into the G1000 system. a. Terrain (Worldwide, 4.9 Arc Second, TBD2 format) b. Obstacle (US/Canada/Europe, OBD2 format) c. AOPA Airport Directory (US) d. AC-U-KWIK Airport Directory* e. SafeTaxi (US, North America*, Canada*, Europe*, Full Coverage*) f. Basemap (Worldwide) g. Garmin FliteCharts (US, Canada*, Europe*) h. Jeppesen ChartView* i. IFR/VFR Charts (US) j. Navigation* With the displays off, insert the SD card into the MFD bottom slot. Apply power to the PFD and the MFD. On the MFD, database verification messages may appear. If so, follow the on-screen instructions to continue. Go to the MFD Aux - Databases page to monitor the automatic database update progress. The new databases will show “Syncing” to the Standby column. After the databases are synchronized, the system will verify them for use by showing “Verifying” in the Standby column. After the databases are verified, a cyan double arrow symbol will appear between the Standby and Active columns to show which databases will be transferred to Active use on the next power cycle or restart.

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Figure 3-10, MFD Aux - Database Page DB Transfer

When all database updates are complete, the Database Update field at the top of the screen will say, “Restart avionics to activate selected standby databases.” If the engine is not running, a Restart softkey appears at the bottom of the MFD. Press Restart to cycle power on the displays. If the Restart softkey is not present, turn OFF PFD and MFD. Remove the database update card from the top slot of the MFD. Turn ON the displays. The displays may state they are verifying databases at power-up. If so, follow the on- screen instructions to continue. Go to the MFD Aux - Databases page and verify the uploaded databases transferred from the Standby column to the Active column. If any did not transfer, follow these steps to initiate a manual transfer - a. Push the FMS knob on the MFD controller to turn on the cursor. b. Turn the FMS knob to highlight the database to transfer to the Active column. c. Press the ENT key on the MFD and a cyan double arrow will appear between the Standby and Active columns. d. Restart the displays. e. Go to the MFD Aux - Databases page and confirm the databases transferred. G1000 Supplemental Maintenance Manual Page 3-41 Textron Nav III Series Revision 4 190-02128-04

3.12 Configuration of Navigation Map for Traffic System With the MFD in normal mode, use the FMS knob to select the Navigation Map page then press the Map Opt softkey, the press the Traffic Softkey and ensure that the bar under the Traffic softkey turns green. Press the MENU button on the MFD, then select “Map Settings” with the FMS knob, then press ENT. Verify the flashing cursor highlights the GROUP field. Turn the small FMS knob to select Traffic and press ENT on the MFD. If not already selected, use the MFD FMS knob to make the following selections:  Traffic – On  Traffic Mode – All Traffic  Traffic Symbols – 250NM  Traffic Labels – On 250NM Return to the Map Page by pressing the FMS knob.

3.13 Clearing Default User Settings Open MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. While holding the CLR button on the PFD, close the PFD (ESS BUS) circuit breaker. When prompted to clear user settings, select the YES softkey. When user settings have been cleared appears on the screen, Open the PFD (ESS BUS) circuit breaker. Wait ten seconds, then while holding the CLR button on the MFD, close the MFD circuit breaker. When prompted to clear user settings, select the YES softkey. When user settings have been cleared appears on the screen, open MFD circuit breaker.

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3.14 Interface Confirmation Lightning Detection System Configuration Load Confirmation Coordinate the StormScope configuration with Section 8.1 “Stormscope Functional Check”.

1. With PFD in configuration mode, use the PFD large FMS knob to select OTHER and the Stormscope configuration page.

Figure 3-11, Stormscope Configuration Page

2. Activate the cursor to highlight the DATA field. Use the small FMS knob to open the drop down menu then select ‘Config’ and press ENT key on the PFD.

Figure 3-12, Stormscope Configuration

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3. Verify that the DATA window shows the following:

Hdg: None: J3-1 Open

J3-2 Open

Hdg Valid Flag N/A

Flag Sense N/A

J3-4 Open

Hdg Value N/A

Inhibit Line Off

Antenna Mount Bottom

J3-3 Open

4. Deactivate the cursor. NOTE The DATA window is only updated once every five seconds.

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4.2 Servicing Information G1000 LRU maintenance is ‘on condition’ only. No component-level overhaul is required for this type design change.

On Condition Servicing ‘On Condition’ replacement and/or servicing should occur when an item exhibits conditions, symptoms, and/or abnormalities defined in Section 5 of this manual. Replacement and/or servicing should be made only after the technician troubleshoots the system to the extent determined necessary by using the guidance in this manual along with common avionics maintenance practices. IMPORTANT! It is impossible to provide guidance for every conceivable failure scenario within the scope of this manual. Every effort has been made to provide comprehensive guidance for possible failures. The information in this document should always be combined with sound aviation maintenance practices and a thorough knowledge of the system. Use sound avionics maintenance practices when working around or on G1000 equipment.

The remainder of this document is organized in the following fashion:  Section 4.3 lists maintenance requirements related to the G1000 system.  Section 6 gives instructions regarding the removal and replacement of physical G1000 equipment and parts.  Section 7 gives configuration and testing instructions to be accomplished if G1000 equipment or parts are removed or replaced.  Section 9 specifies system return-to-service procedures.

The beginning of Section 6 provides instructions to check the software part number and version of each LRU before removing a unit. Procedures in Section 7 require the same check after LRU replacement and software loading. IMPORTANT! All structural repairs associated with this installation are to be addressed in accordance with the Cessna Structural Repair Manual listed in Table 1-1. NOTE After replacing or servicing electrical components near the GMU 44 magnetometers, the Magnetometer Interference Test (reference Section 5) and Magnetometer Calibration Procedure (reference Section 7) must be performed.

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Required Tools The following tools are needed to perform maintenance tasks on G1000 equipment:  Calibrated Milliohm meter, OR o Agilent 34410A Ammeter or equivalent o Fluke 187 Voltmeter or equivalent o Variable DC Power Supply capable of providing 1 amp current  #2 Non-Magnetic Phillips Screwdriver  3/32” Hex tool  Calibrated digital level (Required for AHRS ‘Procedure A’ Calibration)  Calibrated VHF NAV/COM/ILS ramp tester or equivalent  Calibrated transponder ramp tester or equivalent  Calibrated pitot/static ramp tester  Outdoor line-of-site to GPS satellite signals or GPS indoor repeater  Headset/microphone  Ground Power Unit (Capable of supplying 28 VDC)

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4.3 Maintenance Intervals Table 4-1 shows systems and items, installed by this STC, which must undergo tests or checks at specific intervals. If the interval is shown in flight time as well as calendar months, the first interval reached should be used as the limit. IMPORTANT! The tolerance for inspection times is the same as that stated in 5-10-00 of the Cessna Maintenance Manual applicable to the airframe.

The intention of Garmin is to align this maintenance program as best as possible with the existing Cessna Nav III inspection program. For a complete description of the Cessna inspection program, refer to the Cessna Maintenance Manuals listed in Table 1-1. For equipment not listed here, refer to the G1000 Nav III Line Maintenance Manual.

Table 4-1, Maintenance Intervals Manual Item Description/Procedure Interval Section No.

G1000/GFC 700 Equipment GDU 1054B PFD and MFD (Qty 2) or Removal & Replacement 6.1 On Condition GDU 1050 PFD and MFD (Qty 2 Removal & Replacement 6.2 On Condition GTX 335R or GTX Special Inspection - Perform GTX 335R, 345R Transponder 7.5.4 24 Calendar Months GTX 345R test. Removal & Replacement 6.3 On Condition GSU 75 ADAHRS Magnetic variation database update. 0 On Condition Special Inspection – Perform Air Data Test. 7.7.3 24 Calendar Months GDL 69A SXM Removal & Replacement 6.4 On Condition GMA 1360 Audio Removal & Replacement 6.6 On Condition Panel GEA 71B Removal & Replacement 6.10 On Condition Engine/Airframe Unit GSR 56 Satellite Removal & Replacement 6.8 On Condition Transceiver Iridium Antenna Removal & Replacement 6.9 On Condition GSA 81 Servo Removal & Replacement 6.12 On Condition Actuators GSM 86 Servo Removal & Replacement 6.13 On Condition Gearboxes GSM 86 Servo Verify that the pitch, roll, and pitch trim GSM 1000 flt-hrs or 1 year Gearbox Spring 86 spring cartridge torque values are within 4.7 (annual inspection) Cartridge Torque acceptable limits whichever occurs first Check

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Manual Item Description/Procedure Interval Section No.

Verify PRI and SEC power sources for PFD, GIA 1, and GSU. Verify secondary paths for ADAHRS, engine parameters and GPS data. G1000 Redundant Verify the operation of PFD and MFD 4.6 24 Calendar Months Connection Check Ethernet connections. Verify ARINC connection between GSU 1 and MFD. Verify DISPLAY BACKUP button function. G1000 Accessories Configuration Module Removal & Replacement. 6.5 On Condition Replacement G1000 Lightning Protection Electrical Bonding Perform the electrical bonding resistance 4.4.3 24 Calendar Months Test check of G1000 equipment.

4.4 Electrical Bonding Test The following bonding tests are provided for G1000-equipped Nav III Series aircraft as a requirement beyond what is given in the 172, 182, or 206 Series Maintenance Manual.

Requirements All G1000 equipment must be installed. Gain access for the procedure listed below in Section 4.4.3 as required and in accordance with the Cessna Nav III Series Maintenance Manuals.

Test Equipment A milliohm meter and Kelvin probes are recommended for this test. However, an alternate method may be used to provide equivalent results by using the following procedure and a standard voltmeter, power supply with adjustable current limit, and ammeter. The test set up for this alternate method is described below. All test equipment used for the bond checks must be calibrated.

1. Connect the positive lead of the power supply to airframe ground. Connect/touch the positive lead of the voltmeter to the same point. NOTE Ensure that the voltmeter and power supply probes do not touch, so as not to induce contact resistance. 2. Touch negative lead of power supply to each of the test points listed while performing Step 3. At each required point, configure the power supply to produce 1 amp before measuring voltage. (Use an ammeter to ensure current is within minimum of 1 amp ±100 milliamp at each point). Do not allow the reference current to exceed 1.5 amps for safety.

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3. With the current set to 1A, the voltage reading will be the value of the bonding resistance. Set the voltmeter to measure millivolts and null the reading. Measure the voltage from airframe ground (step 1) to each required test points and record the voltage. (Perform Step 2 at each required point and ensure that minimum of 1 amp ±100 milliamp is present when measuring the voltage.) TIP: When a 1A current is used all the millivolt readings are the same as milliohms, and required no further calculation of bond resistance. If 1 amp reference current cannot be maintained and is higher divide the measured voltage by current to get the resistance value. Alternatively, calculate the percentage increase in current and then reduce the measured voltage reading by the same percentage. Example: If the measured current is 1.2 amps, (20% high from the desired 1 amp current) and the measured voltage is 3.0 millivolts, then the value recorded will be 3 millivolts reduced by 20% which is 2.4 millivolts which is the same as 2.4 milliohms.

Electrical Bonding Procedure Using one of the two measurement methods in Section 4.4.2 record the bonding measurement for the following equipment. Some equipment in the list is optional and may not be installed. Ensure that the PFD unit, and MFD unit test points, no more than 40 mΩ is present. Ensure that at other unit test points, no more than 5 mΩ is present.

Pilot Compartment

 Metal case of PFD: ______mΩ  Metal case of MFD: ______mΩ  GDL 69A body (182 and 206 only): ______mΩ  GEA 71B body: ______mΩ  GMA 1360 body: ______mΩ

Rear Fuselage and Empennage

 GDL 69A body (172 only): ______mΩ  GSU 75 body: ______mΩ  GTX 335R or GTX 345R body: ______mΩ  GIA 64W body: ______mΩ  GSR 56 body: ______mΩ

Rear Fuselage and Wing

 GSA 81 body (pitch): ______mΩ  GSA 81 body (trim): ______mΩ  GSA 81 body (roll): ______mΩ

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4.5 GSU 75 Earth Magnetic Field Updates The GSU 75, utilizes an Earth magnetic field model which is updated once every five years. The update is expected to be available from Garmin every five years, as long as the GSU 75, remain Garmin-supported products. The G1000 system alerts the operator that the magnetic field database is out of date by issuing the message “AHRS SERVICE – AHRS Magnetic-field model needs update”. Garmin will distribute updates as part of the navigation database cycle. If the IGRF model in the update is newer than the model installed, a prompt will appear for each GRS/GSU (Select “OK” to update the IGRF Magnetic Field Model). Use the FM Knob and ENT key to select “OK”.

4.6 G1000 Redundant Connection Check Perform the following steps to verify the following: (A) The primary (PRI) and secondary (SEC) power sources for the PFD, GSU (if installed) or GDC and GRS (if installed). (B) The GSU (if installed) data path to PFD and MFD. Note: Section B is not required if a GSU 75 is not installed. Refer to the Cessna Nav III Line Maintenance Manual for procedures if a GDC 74A and GRS 77 are installed..

(A) PRI and SEC power sources for PFD and GSU (if installed) check 1. Connect a ground power unit to the external power receptacle and turn on the ground power unit. 2. Set the BAT and AVIONICS MASTER PWR switches to ON. 3. With the G1000 system in normal mode, pull the following circuit breakers on the circuit breaker panel:  PFD (ESS BUS)  ADC/AHRS (ESS BUS)  NAV 1/ENG (ESS BUS) 4. Wait at least 5 seconds, then verify the data on the PFD remains valid and the following alert messages are not present:  GIA 1 FAIL (or any related message such as COM1, NAV1, XPDR1, GPS1)  AHRS 1 FAIL  ADC 1 FAIL 5. Close the circuit breakers listed in step 3. 6. Repeat step 4. 7. Pull the following circuit breakers on the circuit breaker panel:  PFD (AVN BUS 1)  ADC/AHRS (AVN BUS 1)  NAV 1/ENG (AVN BUS 1) 8. Wait at least 5 seconds, then repeat step 4. 9. Close the circuit breakers listed in step 7. G1000 Supplemental Maintenance Manual Page 4-7 Textron Nav III Series Revision 4 190-02128-04

(B) AHRS and ADC data path check (when GSU 75 installed) 1. Verify there are no AHRS loss of data messages, such as:  AHRS not receiving any GPS information  AHRS not receiving backup GPS information  AHRS using backup GPS source 2. Place the G1000 system in configuration mode. 3. In the GIA page group, go to the GIA RS-232/ARINC 429 CONFIG page. 4. With GIA1 selected in the SELECT UNIT window, verify the following indicators are green checks:  RS232 Channel 1 (GDC72 #1)  RS232 Channel 6 (GRS79 #1)  ARINC 429 IN 6 (GSU75 #1) (Ref. Section 5.1.1.2.) 5. With GIA2 selected in the SELECT UNIT window, verify the following indicators are green checks:  RS232 Channel 2 (GRS79 #1)  ARINC 429 IN 5 (GSU75 #1) (Ref. Section 5.1.1.2.) 6. In the GDU page group, go to the GIA RS-232/ARINC 429 CONFIG page. 7. With PFD1 selected in the SELECT UNIT window, verify the following indicators are green checks:  ARINC 429 IN1 (GSU75 #1)  ARINC 429 IN2 (GDC72 #1) (Ref. Section 5.1.1.1.) 8. With MFD selected in the SELECT UNIT window, verify the following indicators are green checks:  ARINC 429 IN1 (GSU75 #1)  ARINC 429 IN2 (GDC72 #1) (Ref. Section 5.1.1.1.) 9. Restart the G1000 in normal mode.

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4.7 GSM 86 Spring Cartridge Torque Check Perform the test per Sections 4.71 or 4.7.2. Automated Torque Check Procedure 1. Start the G1000 system in Configuration Mode and go to the GFC Page Group and select the GFC STATUS page using the FMS knob.

Figure 4-1, GFC Status Page

IMPORTANT! It is highly recommended that the following test be performed at temperatures between 50° F and 120° F. 2. Use GIA 1 in the SELECT GIA UNIT field for these tests. Use the FMS knob to select the desired servo (Pitch, Roll, or Pitch Trim) in the SELECT SERVO AXIS field. 3. Verify that the Monitor Board and Control Board PFT status fields show PASSED. 4. Verify that the aircraft control surface to be checked is free to travel throughout its range of motion. 5. Press the Test SVO softkey on the PFD. Follow prompts to begin the test. IMPORTANT! Once the test starts the servo will begin to move the aircraft controls. If the test must be stopped, firmly grasp the aircraft control being moved and press the red AP DISC switch on the aircraft control wheel. If an abnormal disconnect of a servo occurs, reset the AFCS SERVO circuit breaker and repeat the test. 6. The test begins and the selected servo drives the control surface to the control stop.

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7. Upon reaching the control stop, the test initializes and begins a 50 second data collection period, where the servo is commanded to drive at ~2.5 rpm while the servo load cell measures clutch torque. 8. Monitor the CURRENT field and verify the current displayed is greater than zero. 9. After the data is collected and processed, the test displays the results of the first direction on the PFD. 10. The servo immediately begins to drive in the opposite direction toward the opposite control stop. 11. Upon reaching the stop, the test repeats the data collection process and displays the results on the PFD. 12. Firmly grasp the aircraft control under test and push the red AP DISC button to relieve any control tension. Push the ENT key to acknowledge the COMPLETE prompt on the PFD. 13. Record the torque values in Table 4-2 or in the appropriate aircraft maintenance records. 14. Repeat this procedure for each servo axis. 15. Verify the minimum and maximum torque values measured are within the Minimum and Maximum torque values allowed for the given axis, listed in Table 4-2. 16. If the values are outside of the torque values allowed, repeat the test twice in the failed axis. If the tests do not pass, the servo gearbox must be removed from the aircraft and tested per Section 4.7.2.

Table 4-2, GSM 86 Allowable Torque Values (Automated Test) Min Max Min Max Measured Measured Allowed Allowed Torque Torque Torque Torque Axis Direction (in-lb) (in-lb) (in-lb) (in-lb) Model

Left 45 62 172 Roll 53 72 182 Right 62 86 206

Up 39 53 172 Pitch 53 72 182

Down 34 46 206

Up 39 53 172 Pitch 39 53 182 Trim Down 53 72 206

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Fixture Torque Check Procedure This test is an alternative to the automated torque check procedure. The GSM 86 servo gearbox does not have an adjustable slip clutch; however, the torque value can be measured using this procedure.

IMPORTANT! This adjustment requires the use of the Garmin fixture, P/N T10-00110-01. For detailed operating instructions for the fixture, refer to GSA8X / GSM85(A) Installation Manual.

It is highly recommended that the following test be performed at temperatures between 50° F and 120° F.

1. Remove the GSM 86 servo gearbox as per Section 6.13. 2. Place the GSM 86 servo gearbox on the adjustment fixture and secure with the toggle clamps. Install the fixture cable between the capstan under test and the fixture capstan. Remove the slack in the cable using the tension adjustment knob. Tighten the two wingnuts on bottom of fixture while holding the top thumbscrews. 3. Attach a socket to a calibrated torque wrench of appropriate range and place on top of the fixture capstan. Adjust the wrench support fixture so that it contacts the handle in the appropriate location. 4. Connect a 2 Amp, 24 V, DC power supply to the fixture. 5. Place the solenoid switch to "on" and move the direction switch to the clockwise or counter-clockwise position. Allow the spring clutch to rotate at least one revolution in each direction (note: the capstan itself is fixed.) 6. Observe the torque reading for at least two full revolutions in each direction. Ensure the minimum and maximum torque readings are within the tolerance specified. 7. If the minimum and maximum torque values are within the specified range in Table 4-3, the GSM 86 spring cartridge is acceptable. Reinstall the GSM 86 servo gearbox per Section 6.13. 8. If the minimum and maximum torque values are not within the specified range in Table 4-3, the GSM 86 slip clutch cartridge must be replaced.

Table 4-3, GSM 86 Allowable Torque Values (Fixture Test) Model Pitch Trim Pitch Roll 172 32 to 59 in-lb 32 to 59 in-lb 36 to 68 in-lb 182 32 to 59 in-lb 43 to 79 in-lb 43 to 79 in-lb 206 43 to 79 in-lb 27 to 51 in-lb 62 to 86 in-lb

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5. TROUBLESHOOTING This section provides instructions and guidance for G1000 system troubleshooting as installed in the Cessna Nav III Series. IMPORTANT! Sections 6, 7 and 9 provide detailed instructions on equipment removal, replacement, configuration, and return-to-service testing. Anytime a G1000 component or LRU is removed, swapped, or replaced, the technician must follow the procedures given in Sections 6, 7 and 9 to ensure proper operation of the system.

Troubleshoot the G1000 system by first identifying, then isolating the specific failure to the responsible LRU. There are several indications that the G1000 presents to the pilot or technician, showing overall system condition. A course of action should be determined based on the information presented on the display. This section shows possible scenarios likely to be encountered during normal operation and gives troubleshooting guidance to the technician to resolve problems.

Figure 5-1, Aux – System Status Page

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The Aux – System Status page displays the following information for each LRU and sub- function:  Status: A green check is displayed for properly operating LRUs. A red ‘x’ appears when an internal LRU fault is detected and it has taken itself offline, or if the MFD cannot communicate with the LRU.  Serial Number: Each LRU serial number is displayed (functions such as COM and GS are contained within an LRU; therefore, serial numbers are not shown for these).  Current SW Version Loaded. When troubleshooting, first check to ensure that each LRU status is ‘green’ and that the correct software is loaded in each unit. Additional airframe and database information is also displayed on this page.

5.1 System Annunciations If data fields become invalid due to an LRU failure, the PFD/MFD typically annunciates the failure with a large red X, as shown in Figure 5-2.

Figure 5-2, System Annunciations

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Failed Path Messages The following message indicates there is a data path connected to the GDU (PFD or MFD) or the GIA (1 or 2) that has failed. FAILED PATH – A data path has failed. The FAILED PATH message is triggered by a timeout of any one digital channel.

IMPORTANT! Once the FAILED PATH message has been triggered, it will remain on the list of messages until the next power cycle. This latching was implemented so that for intermittent failures, the message would remain at the end of the flight (to alert maintenance crew). Also, this keeps the crew from having to acknowledge message repeatedly in the case of intermittent failures.

To determine which path is causing the FAILED PATH message, start the PFD and MFD in configuration mode. Using the FMS knobs, scroll to the pages listed below. The channels that are checked are listed on these pages in config mode: 1) GDU RS-232 / ARINC 429 CONFIG (PFD and MFD) 2) GIA RS-232 / ARINC 429 CONFIG (GIA1 and GIA2) 3) GIA CAN / RS-485 CONFIGURATION (GIA1 and GIA2)

The box next to each channel indicates the current status of the channel per the below:  Red X = data path is known to be failed  Amber question mark (?) = data path status is unknown  Green checkmark ()= data path is known to be good The applicable data paths can be verified by viewing the following configuration mode pages.

NOTE For paths not listed here, refer to the Cessna G1000 Nav III Line Maintenance Manual.

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GDU ARINC 429 CONFIG Page PFD and MFD ARINC 429

Channel LRU Indicator Status

Green PFD/GSU 75 data path is functioning correctly. PFD/GSU 75 data path is not functioning correctly.  Verify GSU 75 status is “OK” using the Aux – System Status page on the MFD. If it is not, correct condition before proceeding, reference GRS troubleshooting sections.  Load PFD configuration file. GSU 75 #1 Red IN 1  Swap PFD and MFD to confirm if the problem is in the (if installed) original PFD. o Replace original PFD if box turns green after swapping displays.  Check the PFD/GSU 75 interconnect wiring for faults. o Replace the GSU75 if the problem persists. PFD/GSU 75 #1 data path functionally is unknown. Amber Reload PFD configuration file. Green PFD/GSU 75 (ADC) data path is functioning correctly PFD/GSU 75 (ADC) data path is not functioning correctly.  Verify GDC status is “OK” using the Aux – System Status page on the MFD. If it is not, correct condition before proceeding, reference GSU troubleshooting sections. GDC 72 #1  Load PFD and GSU configuration files. Red IN 2 (if GSU 75  Swap PFD and MFD to confirm if the problem is in the installed) original PFD. o Replace original PFD if box turns green after swapping displays.  Check the PFD/GSU 75 interconnect wiring for faults. Replace GSU if problem remains. PFD/GSU 75 (ADC) data path functionality is unknown. Amber Reload PFD configuration file.

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GIA RS-232 / ARINC 429 CONFIG Page GIA1 RS-232

Channel LRU Indicator Status

Green GIA1/GSU 75 (ADC) data path is functioning correctly. GIA1/GSU 75 (ADC) data path is not functioning correctly.  Load GIA1 and GSU configuration files.  Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GDC 72 #1 Red GIA1. CHNL 1 (if GSU 75 Replace original GIA1 if box turns green after is installed) o swapping units.  Check the GIA1/GSU 75 interconnect wiring for faults. Replace GSU 75 if problem remains. GIA1/GSU 75 (ADC) data path functionality is unknown. Amber Reload GIA1 configuration files. Green GIA1/GTX 3X5 data path is functioning correctly. GIA1/GTX 3X5 data path is not functioning correctly.  Load GIA1 and GTX 335 or GTX 345 (as applicable) configuration files.  Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GTX 3x5 #1 GIA1. (if GTX 335 Red CHNL 5 or GTX 345 o Replace original GIA1 if box turns green after installed) swapping units.  Check the GIA1/GTX 3X5 interconnect wiring for faults. Replace GTX 335 or GTX 345 (as applicable) if problem remains. GIA1/GTX 3X5 data path functionality is unknown. Reload Amber GIA1 configuration files.

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GIA1 RS-232 (continued)

Channel LRU Indicator Status

Green GIA1/GSU 75 (AHRS) data path is functioning correctly. GIA1/GSU 75 (AHRS) data path is not functioning correctly.  Load GIA1 configuration files.  Swap GIA1 and GIA2, reconfigure both GIA’s to their GRS 79 #1 new locations to confirm if the problem is in the original Red CHNL 6 (if GSU 75 GIA1. installed) o Replace original GIA1 if box turns green after swapping units.  Check the GIA1/GSU 75 interconnect wiring for faults. o Replace the GSU 75 if the problem persists. GIA1/GSU 75 (AHRS) data path functionality is unknown. Amber Reload GIA1 configuration files.

GIA1 ARINC 429 Channel LRU Indicator Status

GIA1/GSU 75 (ADAHRS) data path is functioning Green correctly.

GIA1/GSU 75 (ADAHRS) data path is not functioning correctly.  Load GIA1 configuration files.  Swap GIA1 and GIA2, reconfigure both GIA’s to their GSU 75 #1 new locations to confirm if the problem is in the original IN 6 (if GSU 75 Red GIA1. is installed) o Replace original GIA1 if box turns green after swapping units.  Check the GIA1/GSU 75 interconnect wiring for faults. o Replace the GSU 72 if the problem persists.

GIA1/GSU 75 (ADAHRS) data path functionality is Amber unknown. Reload GIA1 configuration files.

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GIA2 RS-232

Channel LRU Indicator Status

GIA2/GSU 75 (AHRS) data path is functioning Green correctly. GIA2/GSU 75 (AHRS) data path is not functioning correctly.  Load GIA2 and GSU configuration files.  Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem GRS 79 #1 (if GSU 75 CHNL 2 Red is in the original GIA1. is installed) o Replace original GIA2 if box turns green after swapping units.  Check the GIA1/GSU 75 interconnect wiring for faults. o Replace GSU 75 if problem remains. GIA2/GSU 75 data path functionality is unknown. Amber Reload GIA2 configuration files. Green GIA2/GTX 3X5 data path is functioning correctly. GIA2/GTX 3X5 data path is not functioning correctly.  Load GIA2 and GTX 335 or GTX 345 (as applicable) configuration files.  Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem Red is in the original GIA1. CHNL 5 GTX 3x5 #1 o Replace original GIA2 if box turns green after swapping units.  Check the GIA2/GTX 3X5 interconnect wiring for faults.  Replace GTX 335 or GTX 345 (as applicable) if problem remains. GIA2/GTX 3X5 data path functionality is unknown. Amber Reload GIA2 configuration files.

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GIA2 ARINC 429

Channel LRU Indicator Status

Green GIA2/GSU 75 data path is functioning correctly.

GIA2/GSU 75 data path is not functioning correctly.  Load GIA2 and GSU 75 configuration files.  Swap GIA2 and GIA1, reconfigure both GIA’s to their new locations to confirm if the problem is in the original GSU 75 #1 Red GIA2. IN 5 (if GSU 75 is installed) o Replace original GIA2 if box turns green after swapping units.  Check the GIA2/GSU 75 interconnect wiring for faults. Replace GSU 75 if problem remains.

GIA2/GSU 75 data path functionality is unknown. Reload Amber GIA2 configuration files.

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System Failure Troubleshooting The following table provides basic troubleshooting guidance for LRU failures. Refer to G1000 Wiring Diagram, listed in Table 1-1, as needed to verify interconnects.

NOTE: For troubleshooting of data fields and units not listed here, refer to the Cessna Nav III Line Maintenance Manual.

Associated Invalid Data Field Solution LRU(s)  Check GTX 335R/345R configuration settings for GIA1 and GIA2.  Check GTX 335R/345R and GIA1 interconnect. XPDR FAIL GTX 335R,  Check GTX 335R/345R and GIA2 interconnect. GTX 345R (if installed)  Perform a SET>ACTV configuration reset on the GTX Config page, and verify the aircraft registration is present.  Replace GTX 335R/345R.  If problem persists, replace GIA.

TAS FAIL AIRSPEED FAIL ALTITUDE FAIL VERT SPEED FAIL  Inspect GSU 75 pitot/static plumbing integrity.  Inspect pitot/static ports and associated equipment for faults. GSU 75 (if For TAS failure, also check GTP 59 probe. installed)   Check GSU 75 configuration settings for the PFD, MFD, GIA1, and GIA2.  If problem persists, replace the GSU 75.

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Associate Invalid Data Field Solution d LRU(s)  Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin.  Cycle GSU 75 power to restart initialization.  Ensure GSU 75 connecter is secure and proper wire harness strain relief is provided.  Ensure the GSU 75is fastened down tightly in its mounting ATTITUDE FAIL rack and that the mounting rack is not loose (CAUTION - do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re-leveled and the PITCH/ROLL OFFSET procedure performed).  Ensure GPS has acquired at least four satellites, has a 3D GSU 75 navigation solution, and a DOP of less than 5.0. This is particularly important for an ATTITUDE FAIL that appears (if installed) during ground operation only.  Perform an Engine Run-Up Test to check if engine vibration is causing the GSU 75 to go offline.  Load configuration files to the PFD, MFD, GIA1, and GIA2.  Calibrate the GSU 75 (Pitch/Roll Offset and Magnetometer Calibration).  Replace GSU 75.  If problem persists replace GSU 75 configuration module.  Contact Garmin Aviation Product Support if condition continues after replacing the GSU 75 and config module for additional assistance.

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Associate Invalid Data Field Solution d LRU(s)

 Ensure metal objects (tool boxes, power carts, etc.) are not interfering with the magnetometer and aircraft is not in hangar, near other buildings, parked over metal drainage culverts or on hard surfaces that may contain steel reinforcements  Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin.  Cycle power after moving aircraft away from metal objects to determine if metal objects were the source of the GSU 75 interference. Allow up to five minutes for the heading to HDG FAIL reinitialize. (if installed)  Perform a Magnetometer Interference Test to check for & interference from onboard electrical system components (e.g. NAV lights). Pay particular attention to any new GMU 44 electrical devices that have been installed since the aircraft was new. Correct any discrepancies that do not allow this test to pass before continuing.  Ensure GSU 75 and GMU 44 connectors are secure.  Check the wiring and any inline connectors between the GSU and GMU for faults.  Recalibrate the GMU 44  Load configuration files to the PFD, GIA1, and GIA2  If problem persists replace the GMU 44.  If problem persists, replace the GSU 75.

GSU 75

(if installed)  If this message persists longer than five minutes, perform & AHRS calibration procedures as described in Section 7.10. GMU 44

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5.2 G1000 Alerting System

Figure 5-3, Alerts & Annunciations The G1000 Alert System conveys alerts to the pilot using combinations of the following features:

Alert Window: The Alert window displays alert text messages. Pressing the Alerts softkey displays the Alerts window. Pressing the ALERTS softkey again removes the Alerts window from the display.

Softkey Annunciation: When the G1000 Alerting System issues an alert, the Alerts softkey is used as a flashing annunciation to accompany the alert. During the alert, the Alerts softkey label flashes between white letters on black to black letters on a white. The flashing continues until the alert is acknowledged by a press of the Alerts softkey. The alerts softkey remains black letters on white until the condition causing the alert is corrected, or a new alert triggers the flashing.

Figure 5-4, Alerts Softkey Annunciation

System Failure Annunciations: Typically, a large red X appears in windows when a failure is detected in the LRU providing the information to the window.

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5.3 Synthetic Vision and Pathways Troubleshooting The SVS/Pathways software feature requires the following G1000 sensors/data to be valid:  AHRS  Heading  GPS Position  9 Arc-Second (or less) Terrain Data

In the event that one the above items fails or is unavailable, the SVS/Pathways feature is automatically removed from the PFD. The following table describes possible symptoms associated with the SVS/Pathways feature, and provides corresponding actions for troubleshooting: Table 5-1, SVS Troubleshooting Symptom Recommended Action

“SVT” softkey does not appear on Follow the steps in Section 3.7.2 to reactivate the SVS/Pathways feature. PFD softkey tier.

Verify that terrain database is current on the Aux – Databases page on the MFD.

Verify that the alert messages shown in Table 5-2 are not displayed on the PFD Alerts Window. If so, follow the solutions described in Table 5-2.

3D terrain presentation does not Verify that the G1000 AHRS and heading data are valid on the PFD. Verify appear on PFD. that a valid GPS 3D position solution is being received. Troubleshoot these systems in accordance with Section 5.13 and the Cessna G1000 Nav III Line Maintenance Manual.

If a terrain database update has just been performed, allow the system time to initialize and verify the data. When the databases have been verified, the current database cycle and version are reported on the MFD Aux – System Status and Aux – Databases page.

The following table provides SVS/Pathways specific alert messages which may appear in the Alerts Window on the PFD (press the ALERTS softkey on the PFD to view the Alerts Window):

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Table 5-2, SVS-Related Alert Messages Failure Message Cause Solution Geographical operation limitations are SVS is disabled because the SVS – SVS DISABLED: Out of defined in the AFMS listed in Table 1-1. aircraft exceeded the boundaries available terrain region. of the loaded terrain database. Ensure that operations are within this geographic area.

5.4 Backup Communications Path Checks Overview The G1000 system architecture is designed with redundant communication ports for several LRUs so that critical information can continue to be displayed in the event of an equipment or wiring failure. Of most importance is flight attitude, heading, and air data information. The GSU 75 (if installed) has two separate ARINC 429 data lines which are all capable of sending data to the displays. The GTX 335R or GTX 345R (if installed) have two redundant serial communication paths for the same purpose. See the Cessna Nav III Line Maintenance Manual for a basic G1000 block diagram depicting this architecture. Several other diagrams are shown later in this section for illustrative purposes. When troubleshooting, refer to the G1000 Wiring Diagram listed in Table 1-1.

NOTE Refer to Section 9.8 for procedures on checking the status of each configured G1000 / GFC 700 backup data path.

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Data Path Failures

Failure Message Cause Solutions Determine which data path has failed: See Section 0. A communications data path FAILED PATH – A data path has status is not being received by the Check wiring continuity for the failed failed. G1000. path.

Swap or replace the affected LRU.

5.5 GDU 105X Troubleshooting GDU 105X Symptoms

Symptom Recommended Action

 Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. Display is blank  Cycle power.  If GDU recovers, observe display for yellow text containing error information at the top of the screen. If message indicates software need to be re-loaded, then re-load software. Otherwise, replace the GDU.  Use a bright light to verify LCD is active.  Adjust avionics dimmer control full clockwise.  Manually turn up backlight on the PFD and load configuration files to the GDU. Display resets  Ensure slide lock is fully engaged with the locking tabs on the back of the unit.  If slide lock is not fully engaged, remove connector and verify the locking tabs on the GDU are perpendicular to the connector. If necessary, straighten them before reseating connector.  Ensure GDU is receiving power. If a circuit breaker is tripped, determine source of short before resetting breaker.  Ensure circuit breakers have not failed and power wire connections are secure.  Swap PFD and MFD Display flickers  If problem follows unit, replace the display. Please note the position it failed in (PFD or MFD).  If problem does not follow unit, troubleshoot aircraft wiring for fault.

 DO NOT insert a screwdriver of any length into the card slot.  DO NOT pry against the overlay.  DO NOT force the SD Card out.  Use a small screwdriver in the groove on the side of the exposed end of the card to help pull out the card.  Push the card in further to release the card locking mechanism. SD card is stuck in GDU  Check SD Card for having more than one label. Two or more labels on the card will cause sticking.  Remove all but one label.  Ensure the SD card is from SanDisk. Use of other SD Cards is not recommended.  If card was inserted with the label facing to the right, do not attempt to remove. Return the unit to an authorized repair facility.

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Symptom Recommended Action  Go to the GDU TEST page in configuration mode and verify button, knob, or joystick operates correctly by observing a change in color from red to green in A button/knob/joystick does not the button/knob/joystick icon when the button/knob/joystick is pressed. If a appear to function button is stuck, the button icon will be green without pressing the button as soon as you turn to the GDU TEST page.  If problem is verified, replace GDU.  Allow the system to verify the data in internal memory for approximately five Terrain/Obstacle/SafeTaxi does not minutes after power-up. display  If a database does not activate, reload the problem database.  Reload GDU configuration files.  Swap PFD and MFD to see if problem remains with display. Display will not track dimmer bus  Replace display if condition remains with the same unit.  If condition remains in original position after swapping displays, check GDU dimmer input to verify voltage is present.

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5.6 GDU 105X Alerts Software/Configuration Alerts Failure Message Cause Solution The system has found the PFD SW MISMATCH – GDU software and MFD software versions do not version mismatch. Xtalk is off. match. MANIFEST – PFD 1 software  Load correct software version. mismatch. Communication See Section 3.6.2 for GDU 1050A Halted. The system has detected an Software Loading procedure. incorrect software version loaded MANIFEST – MFD1 software in the specified display. mismatch. Communication Halted.  Check master configuration module connector and wiring for damage inside the GDU connector backshell.  Replace master configuration module wiring and pins.  If problem persists, replace master configuration module. NOTE CNFG MODULE – PFD 1 The PFD master configuration New Terrain/Obstacle databases, configuration module is module has failed. Jeppesen Aviation Database and other inoperative. optional features (i.e. TAWS unlock card) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old Terrain and other databases will no longer work as they will remain locked to the old System ID number.

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Failure Message Cause Solution  Reload the display configuration files from SD Loader Card.  Reload system configuration files by pressing the UPDT CFG MFD1 CONFIG – MFD1 softkey on the Configuration configuration error. Config service Upload Page in the PFD System req’d. Page Group to load configuration files into the configuration module.  If message persists, check PFD config module wiring for faults and replace if necessary.  If issue continues, replace PFD master configuration module. A configuration mismatch has occurred between the display and  If problem persists, replace the the Master Configuration Module. display.

NOTE PFD 1 CONFIG – PFD 1 New Terrain/Obstacle databases, configuration error. Config service Jeppesen Aviation Database and other req’d. optional features (i.e. TAWS unlock card) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old Terrain and other databases will no longer work as they will remain locked to the old System ID number.

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Key Alerts Failure Message Cause Solution  Go to the GDU TEST page in MFD “key” KEYSTK – key is The SYSTEM has determined a configuration mode and verify key stuck. key is stuck on MFD. is stuck (if key is stuck the corresponding indicator will be green).  Exercise suspected stuck key and reset GDU TEST page to see if The system has determined a key indicator remains green without PFD “key” KEYSTK – key is stuck. is stuck on the PFD. pressing the key.  If problem persists replace the display.

Miscellaneous Alerts Failure Message Cause Solution  Ensure a database error has not occurred (identified in the ALERTS window on the PFD).  If a database error has occurred, correct error before A communication error has XTALK ERROR – A flight display proceeding. occurred between the MFD and cross talk error has occurred.  Check display Ethernet PFD. interconnect wiring.  Replace PFD with a known good unit, to verify location of problem:  If problem persists, reinstall original PFD and replace MFD.  If the CLR key was held during a power cycle, disregard message.  Cycle power to PFD: DATA LOST – Pilot stored data Pilot stored data has been lost. lost. Recheck settings.  Ensure CLR key is not stuck on the GDU TEST page.  If problem persists, replace PFD.

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Failure Message Cause Solution

 Ensure the MFD connector is fully seated and locked. MFD SERVICE – needs service. The G1000 has determined MFD  Replace the MFD. Return unit for repair. needs service.  Return faulty unit to an Authorized Repair Facility.

 Ensure the PFD connector is fully seated and locked. PFD SERVICE – needs service. The G1000 has determined the  Replace the PFD. Return unit for repair. PFD needs service.  Return faulty unit to an Authorized Repair Facility.

PFD VOLTAGE – PFD has low The specified PFD supply voltage  Check input voltage to PFD. voltage. Reducing power usage. is low.  If input voltage is ok, replace PFD.

MFD VOLTAGE – MFD has low  Check input voltage to MFD. The MFD supply voltage is low. voltage. Reducing power usage.  If input voltage is ok, replace MFD.

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5.7 GTX Troubleshooting GTX Alerts Failure Message Cause Solutions MANIFEST – GTX software The system has detected an mismatch. Communication incorrect software version loaded  Reload software. halted. in the GTX unit.

 Perform a SET>ACTV configuration reset on the GTX Config page and verify the aircraft registration is present.  If error is still present, reload config files from a loader card.  If problem persists, replace master configuration module, check config module harness for faults and replace if XPDR CONFIG – XPDR The system has detected a necessary. configuration error. Config service configuration mismatch for the NOTE req’d. GTX unit. New Terrain/Obstacle databases, Jeppesen Aviation Database and other optional features (i.e. TAWS unlock card) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old Terrain and other databases will no longer work as they will remain locked to the old System ID number.  Replace GTX unit. XPDR SRVC – XPDR needs The G1000 has detected a failure service. Return unit for repair. in the GTX  Return faulty unit to an Authorized Repair Facility.  Check wiring between GIA’s and GTX. XPDR FAIL – XPDR is The GTX is not responding.  Replace GTX unit. inoperative.  Return faulty unit to an Authorized Repair Facility.  Check wiring between GIA’s and XPDR ADS-B FAIL – XPDR The GTX transponder is not able GPS antenna. unable to transmit ADS-B to transmit ADS-B data. message.  Check wiring between GIA’s and GTX.

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5.8 GDL69A SXM Troubleshooting (if installed) For GDL69A SXM Troubleshooting, refer to the GDL 69A Troubleshooting section in the G1000 Nav III Line Maintenance Manual. 5.9 GEA 71B Troubleshooting (if installed) For GEA 71B Troubleshooting, refer to the GEA 71 section in the G1000 Nav III Line Maintenance Manual. 5.10 GIA 64W Troubleshooting (if installed) For GIA 64W Troubleshooting, refer to the GIA 63W section in the G1000 Nav III Line Maintenance Manual. 5.11 GMA 1360 Troubleshooting (if installed) For GMA 1360 Troubleshooting, refer to the GMA 1347 section in the G1000 Nav III Line Maintenance Manual. 5.12 GSR 56 Troubleshooting

Symptom Recommended Action  Check power wiring and pin out of GSR 56 unit. No communication with GSR 56  Ensure GSR 56 configuration option has been loaded.  Ensure the Iridium antenna has an unobstructed view of satellite constellation. No or low-quality Iridium signal  Check the Iridium antenna cable and connectors.  Verify antenna ground plane is adequate.  Check wiring from GSR 56 to GIA #1. No audio output  Verify subscription with Garmin Connext (reference Section 7.14.1.  Verify signal quality is adequate Unable to make a phone call  Verify communication between GSR 56 and the display/control device  Verify subscription with Garmin Connext (reference Section 7.14.1).

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5.13 GSU 75 and GMU 44 Troubleshooting For troubleshooting of the GRS 77, refer to the G1000 Nav III Line Maintenance Manual AHRS Symptoms

Symptom Recommended Action  Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin.  Ensure GPS has acquired at least four satellites, has a 3D navigation solution, and a DOP of less than 5.0. This is particularly important if this issue appears ADAHRS does not complete during ground operation only. initialization  Calibrate the GSU 75.  Check GSU 75 configuration module wiring for damage.  Check GSU 75 connector for bent pins.  If no damage can be found, replace GSU 75 configuration module.  If problem persists, replace the GSU 75.  Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. (Wi-Fi and Bluetooth may be operational)  Ensure the two mounting jack screws are tight. Finger tight is not sufficient, a screwdriver must be used to verify.  Ensure mounting rack and airframe shelf are secure and all hardware and brackets are present (CAUTION - do not loosen the mounting rack hardware to Attitude appears unstable the airframe shelf or the aircraft will need to be re-leveled and the PITCH/ROLL OFFSET procedure performed).  Ensure the GSU 75 connector is securely fastened and proper strain relief is provided.  Remove the GSU 75 connector and verify there are no bent pins.  Replace the GSU 75.  Contact Garmin for further troubleshooting if required.

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GSU Alerts Failure Message Cause Solutions MANIFEST – GRS software The system has detected an mismatch. Communication incorrect software version loaded  Load correct software version. halted. in the specified GRS unit. The AHRS magnetic field model AHRS SERVICE – AHRS should be updated for the  Load updated AHRS magnetic field magnetic-field model needs specified unit. Appears on ground file. See Section 4.5. update. only. GEO LIMITS – AHRS too far No magnetic compass information  Operate the aircraft only within the north/south, no magnetic available due to being too far limits as specified in the G1000 compass. north or south. AFMS, listed in Table 1-2 The GSU 75 AHRS card is not AHRS TAS – AHRS not receiving receiving airspeed from the  Replace the GSU 75. airspeed. internal air data card  Ensure that a cell phone or a device using cell phone technology is not The GSU 75 is not receiving turned on (even in a monitoring AHRS GPS – AHRS not receiving backup GPS information from GIA state) in the cabin. backup GPS information. 63 #2.  Check GPS status for GIA 1 and 2 on MFD Aux – GPS Status page. If one or both GPS receivers cannot AHRS GPS – AHRS using backup The GSU 75 is using the backup acquire a position lock, see GPS GPS source. GPS data path. troubleshooting section  Troubleshoot GIA1/2 –GSU wiring for faults (ref. Failed Path troubleshooting section).  Replace the GSU 75.  If flying near large radio towers or other sources of possible electromagnetic interference, the MAG VAR WARN – Large condition should correct itself as the Magnetic variance value from magnetic variance. Verify all aircraft leaves the area. GMU 44 is not accurate. course angles.  If problem persists, run magnetic interference check in Section 5.13.4 to check for magnetic interference in the aircraft.

GMU Alerts Failure Message Cause Solutions MANIFEST – GMU software The system has detected an mismatch. Communication incorrect software version loaded Load the correct software version. halted. in the GMU 44.  Check GMU 44/GSU 75 A fault has occurred in the interconnect for faults. HDG FAULT – AHRS magnetometer; heading will be  Replace GMU 44. magnetometer fault has occurred flagged invalid.  If problem persists, replace GSU 75.

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Calibration Procedure E: Magnetometer Interference Test A magnetometer interference test is available for troubleshooting and/or verifying a magnetically ‘clean’ installation of the GMU 44. This test exercises various devices on the aircraft that could potentially affect the magnetic field as measured by the GMU 44. NOTE This test is used to validate that no electronic device or magnetized components produce a magnetic field sufficient to interfere with the operation of the GMU 44 magnetometer. It is highly recommended that this test be performed after installation or maintenance of electrical components on the aircraft and/or for troubleshooting the GMU 44.

Figure 5-5, Magnetometer Interference Test 1. Initiate the AHRS magnetometer interference test procedure by performing the following steps: 2. On the PFD, enter Configuration Mode and go to GRS/GMU Calibration page as shown in Figure 5-5. 3. This page is protected and requires a keystroke password to perform this test. Press the following softkeys in sequence: (as counted from left to right on lower bezel of MFD)  softkey 9  softkey 10  softkey 11  softkey 12 4. Select MAG INTERFERENCE TEST and press the PFD ENT key. 5. Follow the checklist items displayed on the PFD, and press the ENT key as each one is completed or confirmed. G1000 Supplemental Maintenance Manual Page 5-25 Textron Nav III Series Revision 4 190-02128-04

NOTE The 3rd item on the checklist instructs the operator to “prepare a detailed test sequence with precise start and stop times for exercising all electronic devices”. The list of relevant electronic devices is given in Table 5-3. Begin test with flaps retracted, flight controls in a neutral position, all lights selected OFF. Elapsed Time since Start of Test Action (min:secs) 0:00 Test begins 0:10 Navigation lights on 0:20 Navigation lights off 0:30 Landing lights on 0:40 Landing lights off 0:50 Recog/Taxi lights on 1:00 Recog/Taxi lights off 1:10 Strobes on 1:20 Strobes off 1:30 Beacon on 1:40 Beacon off 1:50 Pitot Heat on 2:00 Pitot Heat off 2:10 Aileron full right 2:20 Aileron full left 2:30 Flaps full down 3:00 Flaps full up 3:30 Rudder full left 3:40 Rudder full right 3:50 Elevator full nose UP 4:00 Elevator full nose DN Elevator trim full nose UP 4:10 (manual) Elevator trim full nose DN 4:40 (manual) 5:10 End of test

Table 5-3, Magnetometer Interference Test Sequence 6. When the CALIBRATE field is blinking, press the ENT key to begin the procedure, and have a stopwatch ready to begin recording the elapsed time. NOTE It is important that the “time equals zero” moment corresponds with the moment the PFD first displays the blinking TEST COMPLETE? Message.

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7. The operator should carry out the actions called for in the prepared test sequence.

NOTE It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence. 8. When the operator has completed the actions specified in the test sequence, press the ENTER button to indicate that the process is complete. When this is done, the TEST COMPLETE field stops blinking. 9. The PFD informs the operator if the installation has passed or failed the magnetometer interference test. If the test passes, no further action is required for this test. If the test fails, the installation should be considered unreliable until the source of magnetic interference is identified and remedied. When the magnetometer interference test fails, record the three magnetometer maximum deviation values and their corresponding timestamps. Reference the installation manual for the GSU 75 (190- 01639-00 for acceptable magnetic interference limits. Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem. Contact Garmin for assistance in resolving the problem. NOTE Two common reasons for a failed magnetometer interference test are: 1) new equipment is installed in close proximity to the GMU 44 magnetometer, and 2) an existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair. 10. Press the ENT key on the PFD to conclude this procedure.

5.14 GSU 75 Troubleshooting Air Data Symptoms For GSU 75 Air Data Troubleshooting, refer to the GDC 74A section in the G1000 Nav III Line Maintenance Manual.

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5.15 Software/Configuration Troubleshooting

Problem Solutions MFD or PFD displays do not power up:  Ensure that the criteria listed in Section 5.15.1 are fulfilled for the applicable situation.  Ensure power is present at display backshell connector.  Troubleshoot per the “Blank Display” GDU section. Software file load fails:  Ensure that criteria listed in Section 5.15.1 are fulfilled for the applicable situation.  Ensure that LRU is reporting data on Aux – System Status page (LRU is ‘ONLINE’). Check data path wiring as needed.  Retry software file load or try using a different card. Ensure that the MFD is not touched during the loading process.  Ensure that LRU part number is compatible with software version and Card Loader. Refer to Section 3.1.7.  Replace LRU. Configuration file load fails:  Ensure that the criteria listed in Section 5.15.1 are fulfilled for the applicable situation.  Ensure that LRU is reporting data on the Aux – System Status page (LRU is ‘ONLINE’). Check data path wiring as needed.  Retry configuration file load or try using a different card. Ensure that the MFD is not touched during the loading process.  Ensure that LRU part number is compatible with Card Loader. Refer to Section 3.1.7.  Replace LRU. GIA1 and/or GIA2 to ‘LRU’ data path not working  Ensure that the criteria listed in Section 5.15.1 are fulfilled for the applicable situation.  Ensure GIA1 and GIA2 are configured correctly.  Check wiring, connectors & pins as needed. Software File Mismatch Alert appears in lower right  Ensure that proper software file part number and corner of PFD when started in normal mode: version were loaded to LRU. Refer to Section 5.15.1.  Check and ensure that correct Card Loader was used during load process. Refer to the General Arrangement Drawing.  Reload software to LRU.  With the G1000 system powered on, open the After being in configuration mode, the PFD displays a MFD, PFD (ESS BUS), and PFD (AVN BUS 1) red AFCS annunciation and cycling of the transponder circuit breakers for approximately 30 seconds, then field between valid and invalid states. close the circuit breakers.

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System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation: Desired Operation Criteria for Success Load Software to MFD or PFD Displays  SW Loader Card must be inserted in top slot for each display to be loaded.  ENT keys must be held during power up of display.  Power on only one display at a time during software loading. Load AIRFRAME, SYSTEM, MFD, PFD and  SW Loader Card must be inserted in top slot of MANIFEST configuration files to MFD and PFD PFD.  PFD and MFD must be powered on.  PFD and MFD must have correct software. Load Software/Configuration files to GIAs  SW Loader Card must be inserted in top slot of PFD.  G1000 system must be powered on.  PFD and MFD must have correct software.  PFD and MFD must be successfully configured with AIRFRAME, SYSTEM, MANIFEST, MFD and PFD configuration files. Load Software/Configuration files to:  SW Loader Card must be inserted into PFD top - GMA 1347 / GMA 1360 slot. - GSU 75 (if installed)  G1000 must be powered on. - GDC 74 (if installed)  PFD and MFD must have correct software and configuration settings. - GEA 71 / GEA 71B  GIAs must have correct software. - GRS 77 (software only) (if installed)  GIAs must be successfully configured with GIA1 - GMU 44 (software only) and GIA2 configuration files. - GTX 33 (if installed)  Data path from GIA1 to each LRU must be - GTX 335R or GTX 345R (if installed) operational.

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5.16 Backshell/Backplate Connectors

The following figures depict the backplate connectors as viewed with the LRU removed. For units not shown here, refer to the G1000 Nav III Line Maintenance Manual.

Figure 5-6, GTX 335R/345R Looking at Front of Connector (P3251)

Figure 5-7, GTX 345R (Only) Looking at Front of Connector (P3252)

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Figure 5-8, GDU 1054B/1050 Backshell Connector (P10401)

Figure 5-9, GSU 75 Connector View from Front (P751)

Figure 5-10, GDL 69A SXM Backplate Connector (P69A1)

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COM ANTENNA CONNECTOR COM BOARD CONNECTOR (P601) COOLING PORT

1234567891011121314 15 16 171819 20 21222324 2526 2728 2930 31323334 353637 38394041 424344

MAIN DISCRETE CONNECTOR (P604) MAIN SERIAL CONNECTOR (P603)

GPS ANTENNA CONNECTO

I/O CONNECTOR #2 (P606) I/O CONNECTOR #1 (P605)

12345678 9 1011121314151617181920 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

G/S ANTENNA CONNECTOR VOR/ILS CONNECTOR (P602 NAV ANTENNA CONNECTOR

Figure 5-11, GIA 64W Backplate Connectors

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

Figure 5-12, GEA 71B Backplate Connectors

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Figure 5-13, GMA 1360 Backplate Connectors

15 14 13 12 11 10 9 8 7 6 5 4 3 2 1

30 29 28 27 26 25 24 23 22 21 20 19 18 17 16

44 43 42 41 40 39 38 37 36 35 34 33 32 31

Figure 5-14, GSR 56 Mating Connector

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6. Equipment Removal & Installation This section describes how to remove and replace equipment in the Cessna Nav III Series associated with this STC. After removal and replacement, LRUs must be configured and tested as described in Section 7. CAUTION: When removing and/or replacing any G1000 component, always ensure that aircraft power is off. Unplug any auxiliary power supplies. Before performing maintenance, it is required that the technician verify the LRU software part number and version number matches the software configuration listed in the General Arrangement drawing, listed in Table 1-1. NOTE After installation or maintenance of electrical components near the GMU 44 magnetometers, perform the Calibration Procedure E: Magnetometer Interference Test (reference Section 5) and Procedure B: GSU 75 and GMU 44 magnetic calibration (reference Section 7).

To check an LRU software part number and/or version, follow the procedure defined in Section 3.1.7. If a faulty LRU is not reporting its software version and part number, check aircraft maintenance logs for last software version loaded and verify against the General Arrangement drawing. The Software Manifest page may also be used to check part numbers and versions. The General Arrangement drawing allows alternate part number units to be installed with certain hardware/software combination restrictions. Refer to the applicable “Garmin Equipment/Software List” contained in the General Arrangement drawing for details.

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6.1 GDU 1054B/1050 Removal: 1. Using a 3/32” hex tool, rotate all four ¼-turn fasteners counter-clockwise until they reach their stops. 2. Carefully remove the display from the panel. 3. While supporting the display, disconnect the connector. Reinstallation: 1. Visually inspect the connector and pins for signs of damage. Repair any damage. 2. While supporting the display, connect the connector to the rear of the unit. Verify the connector is fully locked by rocking the connector up and down to verify the connector stays attached to the unit. 3. Carefully insert the display into the panel cutout, ensuring that all 4 ¼-turn fasteners align with the corresponding holes. 4. Seat the display in the panel cutout. Do not use excessive force while inserting the display. 5. Once seated, rotate all four ¼-turn fasteners clockwise to lock the display to the panel. 6. Configure and test the MFD and/or PFD according to Section 7.1.

6.2 GTX 335R/GTRX 345R Transponder (if installed) GTX 335R/GTX 345R Removal: 1. Gain access to the aft avionics compartment in the tail of the aircraft. 2. Insert a 3/32” hex drive tool into the access hole in the front of the unit. 3. Turn hex drive tool counterclockwise until the hex drive tool stops. 4. Pull the unit from the rack using the spring-loaded tab on the front of the unit. GTX 335R/GTX 345R Reinstallation: 1. Visually inspect the connectors in the back of the rack to ensure there are no bent or damaged pins. Repair any damage if found. 2. Insert a 3/32” hex drive tool into the access hole in the front of the unit. 3. Turn hex drive tool counterclockwise until the hex drive tool stops. 4. Slide the unit in the rack until it stops. The unit will appear to stick out of the rack approximately 3/8”. 5. Insert a 3/32” hex drive tool into the access hole in the front of the unit. 6. Push on the left side of the unit and turn hex drive tool clockwise until it stops. Do not apply more than 8 in-lbs of torque on the hex tool to seat the unit. 7. Configure and test the GTX 335R or GTX 345R according to Section 7.5.

6.3 GSU 75 ADAHRS (if installed) GSU 75 Removal: 1. Gain access to the aft avionics compartment in the tail of the aircraft. G1000 Supplemental Maintenance Manual Page 6-2 Textron Nav III Series Revision 4 190-02128-04

2. Disconnect the ADAHRS connector. 3. Disconnect the pitot and static lines. 4. Turn each retention screw counterclockwise until they disconnect from the remote rack. 5. Gently slide the unit from the remote rack. Do NOT loosen the remote rack hardware fastening it to the avionics shelf or the GSU 75 must be re-calibrated per Section 7.10) GSU 75 Installation: 1. Visually inspect the connector to ensure there are no bent or damaged pins. Also inspect the pitot and static fittings for damage. Repair any damage. 2. Place the GSU 75 unit on the remote rack and slide the unit back until the feet are fully engaged with the remote rack. 3. Push down and turn each retention screw clockwise. Torque each retention screw to 15-20 in-lbs. 4. Connect the pitot and static lines. 5. Connect the ADAHRS connector to the unit. 6. Calibrate and test the GSU 75 per Section 7.10.

6.4 GDL 69A SXM (if installed) Removal: 1. For 182 and 206 aircraft, gain access by removing the right side GDU 1054B display unit (see Section 6.1.) 2. For 172 aircraft, gain access to the aft avionics compartment in the tail of the aircraft. 3. Unlock the GDL 69A SXM handle by loosening the Phillips screw on the handle. 4. Pull the handle upward to unlock the GDL 69A. Gently remove the unit from the rack. Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 2. Lift the handle and gently insert the GDL 69A SXM into its rack. The handle should engage the dogleg track. 3. Press down on the GDL 69A SXM handle to lock the unit into the rack. 4. Lock the handle to the GDL 69A SXM body using the Philips screw. Torque the handle screw to 10-14 in-lbs. 5. Configure and test the GDL 69A SXM according to Section 7.11.

6.5 Configuration Modules Configuration Module Removal & Replacement Configuration modules (Reference Figure 6-1 and Table 6-1, Item 1 shown below) are located in the following LRU harness connector backshells: GDU 1054B or GDU 1050 PFD. Additionally, the GSU 75 has different style configuration modules that are located in the connector backshells. Refer to Section 6.5.2 for the GSU 75 configuration module removal and

G1000 Supplemental Maintenance Manual Page 6-3 Textron Nav III Series Revision 4 190-02128-04 replacement instructions. Refer to the Master Drawing List, listed in Table 1-1, for specific installation drawings.

Figure 6-1, Configuration Module Installation

Table 6-1, Configuration Module Kit – 011-00979-00

Garmin Part Item Description Qty Needed Number Configuration Module PCB Board Assembly w/EEPROM & Temp 1 1 012-00605-00 or -02 Sensor 2 Spacer, Config Module 1 213-00043-00 3 Cable, 4-Conductor Harness 1 325-00122-00 4 Pins, #22 AWG (HD) 5 336-00021-00

Removal: 1. Disconnect connector from LRU. 2. Remove 2 screws (8) from cover (7) and remove cover. 3. Unplug connector from configuration module (1). 4. Remove configuration module. Installation: 1. Inspect connector for damaged pins (4). 2. Place configuration module (1) in position. 3. Insert connector into configuration module (1). 4. Assembly of the connector is the reverse of disassembly. 5. Checkout per Section 6.5.3.

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GSU 75 Configuration Module Removal & Replacement

CONFIGURATION MODULE

Figure 6-2, GSU 75 Configuration Module Installation

Table 6-2, GSU 75 Configuration Module Kit – 011-00979-20

Garmin Part Item Description Qty Needed Number

1 Sub-Assy,Potted,Config Mdl,w/EEPROM,Jackscrew 1 011-02179-00 2 Cable, 4-Conductor Harness 1 325-00122-00 3 Pins, #22 AWG (HD) 4 336-00021-00 4 Pan Head Screw 1 211-60232-07

Removal: 1. Disconnect connector from LRU. 2. Remove 2 screws from cover and remove cover. 3. Unplug the connector from the configuration module. 4. Remove 1 screw from configuration module. 5. Remove the configuration module. Installation: 1. Inspect connector for damaged pins. 2. Insert the connector into the configuration module. 3. Place configuration module in position. 4. Install 1 screw attaching the configuration module to the backshell. 5. Assembly of the connector is the reverse of the disassembly. 6. Checkout per Section 6.5.3.

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Configuration Module Checkout If a GSU 75 Configuration Module is replaced: Configuration settings must be reloaded to the GSU 75 per Section 7.6, then proceed to Section 7.7.3. Additionally, GSU 75 and GMU 44 calibration procedures must be performed. Proceed to Section 7.10. If only the Master (PFD) Configuration Module is replaced: NOTE New Terrain/Obstacle databases, Jeppesen Aviation Database and other optional features (i.e. unlock/enablement cards) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old databases and feature enable cards will no longer work as they will remain locked to the old System ID number. 1. Start the G1000 system in configuration mode. 2. Go to the Configuration Upload Page on the PFD. 3. Press the UPDT CFG softkey and press ENT.

If both the PFD and Master Configuration Module are replaced: NOTE New Terrain/Obstacle databases, Jeppesen Aviation Database and other optional features (i.e. unlock/enablement cards) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old databases and feature enable cards will no longer work as they will remain locked to the old System ID number. 1. The entire G1000 system must be re-configured. Insert the correct G1000 software loader card into the PFD. 2. Start the G1000 in configuration mode. Go to the System Upload Page on the PFD. 3. See Section 3.6 for instructions on how to use the System Upload page. Check all configuration files and reload them. 4. After reloading configuration files, examine the G1000 installation for any installed configuration options. Options are listed in Section 3.6. Load optional files as necessary. 5. Continue to Section 9 and conduct the return to service checkout.

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6.6 GMA 1360 Audio Panel (if installed) Removal: 1. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the GMA is unlocked from the rack in the instrument panel. 2. Carefully remove the GMA from its rack. Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 2. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the lock tab stops. 3. Gently insert the GMA into the rack until the locking tab engages the rack. 4. Tighten the hex nut until resistance is felt and the unit stops sliding into the rack. Do not over-tighten the nut. 5. Configure and test the GMA according to Section 7.2.

6.7 GIA 64W Integrated Avionics Unit (if installed) Removal: 1. Gain access to the tail of the aircraft. 2. Unlock the GIA handle by loosening the Phillips screw on the handle. 3. Pull the handle upward to unlock the GIA. Gently remove the unit from the rack. Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 2. Lift the handle and gently insert the GIA into its rack. The handle should engage the dogleg track. 3. Press down on the GIA handle to lock the unit into the rack. 4. Lock the handle to the GIA body using the Philips screw. Torque the handle screw to 10-14 in-lbs. 6. Configure and test the GIA(s) according to Section 7.3

6.8 GSR 56 Satellite Transceiver (if installed) Removal: 1. Gain access to the tail of the aircraft. 2. Unlock the unit from the rack by pulling out on the ratcheting latch mechanism and turning counter-clockwise until the latch mechanism clears the tab on the unit. 3. Slide the unit out of the rack. Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 2. Insert the unit into the installation rack. G1000 Supplemental Maintenance Manual Page 6-7 Textron Nav III Series Revision 4 190-02128-04

CAUTION: Do not use excessive force when inserting the GSR 56 into the rack. This may cause damage to occur to the connectors, unit, and/or unit rack. If heavy resistance is felt during installation, stop! Remove the GSR 56 and identify the source of resistance. 3. Lock the unit into the rack by using the ratcheting latch mechanism. 4. Register with Garmin Connext per Section 7.14.1. 5. No software or configuration loading is required for the GSR 56. Test the GSR 56 according to Section 7.14.2.

6.9 Iridium Antenna (if installed) Removal: 1. Gain access to the antenna coaxial cable connector in the tail. 2. Disconnect the antenna coaxial cable. 3. Remove the antenna mounting screws. 4. Remove antenna. Reinstallation: 1. Install antenna using retained mounting screws. 2. Connect the antenna coaxial cable. 3. Fillet seal around antenna. 4. Proceed to Section 7.14.2 for testing of the GSR 56.

6.10 GEA 71B Engine/Airframe Unit (if installed) Removal: 1. Gain access by removing the MFD (see Section 6.1). 2. Unlock the GEA handle by unscrewing the Phillips screw. 3. Firmly grasp the GEA handle and pull it. This unlocks the unit from the rack. 4. Gently remove the GEA from its rack. Reinstallation: 1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage. 2. Lift the handle and gently insert the GEA into the rack. The handle should engage the dogleg track. 3. Press on the handle to lock the unit into place. 4. Lock the handle to the GEA body using the Philips screw. Torque the handle screw to 10-14 in-lbs. 5. Reinstall the MFD. 6. Configure and test the GEA according to Section 7.4. G1000 Supplemental Maintenance Manual Page 6-8 Textron Nav III Series Revision 4 190-02128-04

6.11 FS 510 Wifi/Bluetooth Data Link (if installed) Removal: 1. FS 510 card is installed in the bottom slot of the MFD. 2. Press the edge of the card and release to remove card. Reinstallation: 1. Insert FS510 card in the bottom slot of the MFD.

6.12 GSA 81 Servo Actuator (if installed) Removal: 1. Gain access to the desired servo(s). 2. Disconnect the servo harness connector. 3. Use a socket or open-wrench to loosen and remove the servo attachment bolts. 4. Carefully remove the servo and place a protective cover on the output gear. 5. Place a protective cover over the GSM 86 servo gearbox. Reinstallation: 1. Inspect the servo output gear for abnormal wear. 2. Using a lint-free cloth, remove excess grease build-up from the servo output gear (see Figure 6-1.) IMPORTANT! It is not necessary to remove all of the grease from the output gear, only the excess grease. DO NOT USE SOLVENTS TO CLEAN THE OUTPUT GEAR!

3. Using a brush or other applicator, apply a thin coat of Aeroshell 33MS (Lithium-complex based) grease to the servo output gear.

Figure 6-3, Servo Gear

4. Carefully place the servo into the servo gearbox, ensuring proper orientation and alignment.

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5. Fasten the servo to the servo gearbox using the existing hardware. Follow the installation instructions provided in the respective servo installation drawing(s) listed in Table 1-1. 6. Inspect the harness connectors and check that no pins are bent or otherwise damaged. Connect the harness and secure it appropriately. 7. Configure and test the GSA according to Section 7.12. 6.13 GSM 86 Servo Gearbox (if installed) Removal: 1. Remove the desired servo(s) per Section 6.12. 2. Disconnect the servo cables from the flight control system. 3. Use a socket or open-wrench to loosen and remove the servo gearbox attachment bolts. 4. Carefully remove the servo gearbox(es). 5. Remove the cable retention pins and top ring and then remove the servo cable from the capstan. Reinstallation: 1. Follow the installation instructions provided in the respective servo installation drawing(s) listed in Table 1-1 to reinstall the servo cable and servo gearbox. 2. If no other maintenance is to be performed, reinstall the servo(s) per Section 6.12.

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7. Garmin G1000 LRU Replacement/Configuration & Testing This section provides procedures to be followed after a piece of G1000 equipment is replaced. At the beginning of each LRU section, instructions are given to guide the technician for various removal/replacement scenarios. These instructions define necessary procedures to be followed for situations where original equipment was reinstalled as well as for situations where new equipment (new serial number) is installed.

NOTE Only SanDisk brand SD cards are recommended for use with the G1000 system. Other brand cards have not been tested for use with the G1000 system.

CAUTION Connect a ground power unit to the aircraft for software loading. DO NOT RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A BATTERY CHARGER AS AN EXTERNAL POWER SOURCE DUE TO ELECTRICAL NOISE IT MAY INJECT IN THE G1000 SYSTEM. DO NOT ALLOW POWER TO BE REMOVED FROM THE SYSTEM WHEN LOADING SOFTWARE! Remove power only when told to do so by the following procedure. Power loss during a software upgrade may cause a LRU to become corrupted and unresponsive requiring replacement. Remove power only when told to do so in the procedure. All displays should be in the same mode (configuration or normal), unless instructed differently. If an incorrect configuration file is loaded at any time in this section, STOP and start the configuration load over using Section 3.6.

7.1 GDU 1054B/1050 PFD & MFD Original Display Reinstalled If the removed display(s) are re-installed in their original positions, no software or configuration loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the PFD/MFD Test procedure, Section 7.1.5. Original Displays Installed in Opposite Locations for Troubleshooting If the PFD and MFD are installed in opposite positions, no software or configuration loading is required. Continue to the PFD/MFD Test procedure, Section 7.1.5. New Repair or Exchange Display(s) Installed If a new, repaired or exchanged GDU is installed, the correct software and configuration files must be loaded to the unit.

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LRU Replacement Procedure PFD 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove SD cards from top and bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics/electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the MFD, scroll to the LRU replacement page. 7. Activate the cursor and select PFD in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 3.6. 17. If there are no red-Xs or system alerts, continue to Section 7.1.5.

Legacy Replacement Procedure PFD (Alternate Method) A full system configuration re-load is required when a new, repaired, or exchanged display is installed using this method. This includes all options and feature enablements. To complete this procedure, continue to Section 3.6.

LRU Replacement Procedure MFD NOTE Anytime the MFD is replaced, all databases must be reloaded.

1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS) circuit breakers. 2. Remove SD cards from top and bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select MFD in the LRU dropdown box. G1000 Supplemental Maintenance Manual Page 7-2 Textron Nav III Series Revision 4 190-02128-04

8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 3.8. 17. Install databases as directed in Section 3.14. 18. After databases are re-loaded, continue to Section 7.1.5.

Legacy Replacement Procedure MFD (Alternate Method) A full system configuration re-load is required when a new, repaired, or exchanged display is installed using this method. This includes all options and feature enablements. To complete this procedure, perform Section 3.6.

PFD/MFD Test 1. Allow displays to initialize for ~1 minute. 2. Check that all COM/NAV display fields are valid in the top corners of the PFD. 3. Check that attitude, heading, altitude, airspeed, vertical speed and OAT fields are valid within 2 minutes of power up on the PFD. 4. Check that the engine instrument fields are valid on the MFD.

Figure 7-1, G1000 Normal Mode Check 5. Push the red DISPLAY BACKUP button on the GMA. Verify that the PFD and MFD displays enter reversion mode. MFD should have valid altitude, airspeed, vertical speed, COMM1, COMM2, NAV1, NAV2 and engine instruments. 6. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify the PFD and MFD return to normal display modes. G1000 Supplemental Maintenance Manual Page 7-3 Textron Nav III Series Revision 4 190-02128-04

7. Select the Map – TAWS Map page on the MFD. 8. Verify that the title at the top of the page reads “Map – TAWS-B”. If TAWS has not been enabled, the title will read “Map – Terrain Proximity” or “Map – Terrain”. 9. Press the MENU button and select “Test TAWS” from the pop-up menu. 10. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over the cockpit speaker. 11. If no other service is to be performed, perform final return-to-service test as specified in Section 9.

7.2 GMA 1347 or GMA 1360 Audio Panel Original GMA 1347 or GMA 1360 Reinstalled No software/configuration loading or testing is required if the removed GMA is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the final return-to-service checks in Section 9. New, Repaired or Exchange GMA 1347 or GMA 1360 Installed If a new, repaired or exchanged GMA is installed, the correct software and configuration files must be loaded to the unit. See Section 7.2.1.

LRU Replacement Procedure GMA 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GMA1 in the LRU dropdown box 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.2.2.

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17. If there are no red-Xs or system alerts, continue to Section 7.2.3. Legacy Replacement Procedure GMA (Alternate Method) To load the GMA complete the following subsections in order as they apply to the aircraft.

Cessna XXX – Baseline Configuration (where XXX is the airframe type) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD. 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the small FMS knob to highlight “0X-XXX” (where 0X is the menu position, and XXX is the airframe type) and press ENT key on the PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Cessna XXX – Baseline Configuration” (where XXX is the airframe type). Press ENT key on the PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GMA. 9. Highlight the software box and press the ENT key. 10. Highlight the Configuration box and press the ENT key. 11. Press “Load” softkey. 12. Monitor load progress. Verify software load completes without errors as indicated by the following: 13. Green “PASS” in the Configuration and Software columns for each item loaded. 14. “Upload Complete………….”COMPLETE” in the summary box. 15. Acknowledge the prompt by pushing the ENT key.

Option – KR87 ADF Installation (For GMA replacement and aircraft equipped with an ADF only) 1. In the ITEM window highlight “Option – KR87 ADF Installation” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GMA and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

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Option – KN63 DME Installation (For GMA replacement and aircraft equipped with a DME only) 1. Scroll the cursor to the ITEM window highlight “Option – KN63 DME Installation” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GMA and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

Configuration Manager Update 1. With the system still in configuration mode, scroll to the Configuration Manager page on the PFD. 2. Press the CNFM CFG softkey. 3. Select ok when prompted to “Confirm configuration as expected configuration” 4. Power cycle the system verify there are no red-Xs or system alerts. 5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 6. If there are no red-Xs or system alerts, continue to Section 7.2.3.

GMA 1347 or GMA 1360 Test Except for marker beacon operation, an in-aircraft checkout may be performed in the aircraft with a known good microphone, headset, and speaker.

Intercom System (ICS) Check 1. Ensure that the MAN SQ key is off (no light). 2. Ensure that PILOT and COPLT ICS ISOLATION are off (no light). 3. Adjust GMA ICS volume to a comfortable level. 4. Plug in a headset at each COCKPIT position. One at a time, plug a headset into each left and right CABIN ICS jack location (if installed) (one headset on right, one headset on left). 5. Verify that there is two-way communications between all jack positions. 6. On GMA select COM1 MIC and AUDIO. 7. Verify an active (green) COM1 frequency is displayed on the PFD. 8. On the GMA, select PA and verify the PA select annunciator is illuminated on GMA. Verify COM1 active frequency is displayed white. G1000 Supplemental Maintenance Manual Page 7-6 Textron Nav III Series Revision 4 190-02128-04

9. Initiate passenger address using pilot’s headset boom mic by keying the pilot’s PTT. Verify the following:  Clear PA audio can be heard over cabin speaker and headsets  PA selected annunciator on GMA flashes ~ once per second during PA address. 10. Repeat Step 8 using hand mic. 11. Initiate passenger address using copilot’s headset boom mic by keying the copilot’s PTT. Verify the following:  Clear PA audio can be heard over cabin speaker and headsets  PA selected annunciator on GMA flashes ~ once per second during PA address.

Transceiver Operational Check Perform a ramp test radio check by exercising the installed transceivers, microphone, microphone key and audio over the headphones and speaker. Verify that communications are clear and PTT operation is correct for each pilot position. 1. On the pilot’s audio panel, select the audio source corresponding to each installed avionics unit (i.e. NAV1, NAV2, COM1, COM2, ADF and DME) and check for audio over the pilot’s headset. 2. Press the SPKR key on pilot’s audio panel and verify that the selected audio is heard over the pilot’s speaker.

Failsafe Operation Check – GMA 1. Turn the GMA off by pulling the AUDIO circuit breaker. This directs all COM 1 phone audio, MIC audio and MIC key to the pilot’s position. 2. Check the failsafe operation by exercising the COM 1 boom mic, hand mic, microphone key and audio over the headphones. All volume control for the COM audio should be through the PFD volume control. Verify proper operation of COM 1 using the failsafe operation. 3. Close the AUDIO circuit breaker to continue testing.

Marker Beacon Test 1. Using a ramp tester, simulate the outer marker, middle marker, and inner marker signals by following the test equipment manufacturer’s instructions. Verify that each marker audio signal is present over the pilot and co-pilot headphones and speaker. 2. Verify that the outer, middle, and inner annunciations appear on PFD when the corresponding signal is applied. Marker beacon annunciations ( , , and ) appear at the upper left corner of the altitude indicator on the PFD. Operate the MKR MUTE key on the GMA and ensure that the audio signal is muted. 3. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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7.3 GIA 63W or GIA 64W Integrated Avionics Unit Original GIA 63W or GIA 64W Reinstalled No software or configuration loading is required if the removed GIA is re-installed in its original position (GIA1 and GIA2 in their original racks). This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the return-to-service checks in Section 9. Original GIA 63W or GIA 64W Swapped for Troubleshooting No software loading is required if the originally installed GIA units are re-installed in opposite positions (GIA1 and GIA2 in opposite unit racks). However, configuration loading is required. See Section 7.3.1. New, Repaired or Exchange GIA 63W or GIA 64W Installed If a new, repaired or exchange GIA is installed, the correct software and configuration files must be loaded to the unit. See Section 7.3.1. LRU Replacement Procedure GIA1 or GIA2 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GIA1 or GIA2, whichever was replaced in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Select Com1 or 2 (as applicable) in the LRU dropdown box. 12. Press the CHK All softkey. 13. Press the Load softkey. 14. Press ENT to acknowledge the process was complete. 15. Select GPS1 or 2 (as applicable) in the LRU dropdown box. 16. Press the CHK All softkey. 17. Press the Load softkey. 18. Press ENT to acknowledge the process was complete. 19. Select Nav1 or 2 (as applicable) in the LRU dropdown box. 20. Press the CHK All softkey. 21. Press the Load softkey. 22. Press ENT to acknowledge the process was complete.

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23. Deactivate the cursor. 24. Scroll to the Configuration Manager page. 25. Press the CNFM CFG softkey. 26. Select ok when prompted to “Confirm configuration as expected configuration” 27. Power cycle the system verify there are no red-Xs or system alerts. 28. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.3.2. 29. If there are no red-Xs or system alerts, continue to Section 7.3.3.

Legacy Replacement Procedure GIA1 or GIA2 (Alternate Method) To load the GIA complete the following subsections in order as they apply to the aircraft.

Cessna XXX – Baseline Configuration (For GIA 1 or GIA 2 replacement) (where XXX is the airframe type) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 5. Activate the cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X-XXX” (where 0X is the menu position, and XXX is the airframe type) and press ENT key on the PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight Cessna XXX – Baseline Configuration (where XXX is the airframe type) Press ENT key on the PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GIA 1 - SYS or GIA 2 - SYS, whichever was replaced. 9. Highlight the software box and press the ENT key to check the box. 10. Highlight the Configuration box and press the ENT key to check the box. 11. Use the large FMS knob to scroll to GIA 1 – GEA PIN MAPPING or GIA 2 – GEA PIN MAPPING, whichever was replaced. 12. Highlight the Configuration box and press the ENT key to check the box. 13. Use the large FMS knob to scroll to NAV 1 or NAV 2, whichever was replaced. 14. Highlight the software box and press the ENT key to check the box. 15. Use the large FMS knob to scroll to COM 1 or COM 2, whichever was replaced. 16. Highlight the software box and press the ENT key to check the box. 17. Highlight the configuration box and press the ENT key to check the box. 18. Use the large FMS knob to scroll to GIA 1 – AUDIO or GIA 2 – AUDIO, whichever was replaced.

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19. Highlight the software box and press the ENT key to check the box 20. Use the large FMS knob to scroll to GIA 1 – GPS or GIA 2 – GPS, whichever was replaced. 21. Highlight the software box and press the ENT key to check the box. 22. Scroll to AUDIO. 23. Highlight the Configuration box and press the ENT key to check the box. 24. Press “Load” softkey. 25. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 26. Acknowledge the prompt by pushing the ENT key.

GSU or GDC/GRS GIA Configuration (For GIA 1 or GIA 2 replacement) NOTE The aircraft will be equipped with a GSU 75 ADAHRS or a combination of GRS and GDC. If the aircraft is equipped with the combination GRS and GDC, the installer will need to load the GRS file then load the GDC file using the following procedure. If the aircraft is equipped with a GSU 75, the GSU 75 is the only file that needs to be loaded. 1. Scroll the cursor to the Group window and select “0X-XXX” (where 0X is the menu position and XXX is the airframe type). 2. Press the ENT key. 3. In the ITEM window highlight either “Baseline Option – GSU75 Installation” or “Baseline Option – Legacy – GRS 77 and GDC 74 Installation” as applicable and press the ENT key on the PFD. 4. Press the CLR ALL softkey. 5. Scroll the cursor to GIA1 or GIA 2 configuration box, whichever was replaced, and press the ENT key to check the box. 6. Press “Load” softkey. 7. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 8. Acknowledge the prompt by pushing the ENT key

GFC 700 (For GIA 1 or GIA 2 replacement) (if installed) 1. In the ITEM window highlight “Option – GFC 700 Installation” and press the ENT key on PFD.

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2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA CERT software box, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

KAP 140 Autopilot (For GIA 2 replacement) (if installed) 1. In the ITEM window highlight “Option – KAP 140 Installation” and press the ENT key on PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA2 configuration box, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

Transponder GIA Configuration (For GIA 1 or GIA 2 replacement) 1. In the ITEM window highlight either “Baseline Option – GTX 335 Installation” or “Baseline Option – GTX 345 Installation, without GTS 800” or “Baseline Option – GTX 345 Installation, with GTS 800” or “Baseline Option – Legacy – GTX 33 ES Installation” (as applicable) and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA1 or GIA 2 configuration box, whichever was replaced, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

ADF GIA Configuration (For GIA 2 replacement and aircraft equipped with a ADF only)

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1. In the ITEM window highlight “Option – KR87 ADF Installation” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA 2 configuration box, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

DME GIA Configuration (For GIA 2 replacement and aircraft equipped with a DME only) 1. Scroll the cursor to the ITEM window highlight “Option – KN63 DME Installation” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA 1 configuration box, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

Traffic System GIA Configuration (For GIA 1 or GIA 2 replacement and aircraft equipped with a Traffic system only) 1. Scroll the cursor to the ITEM window and highlight “Option – GTS 800 Installation, without GTX 345” OR “Option – GTS 800 Installation, with GTX 345” OR “Option – KTA870 TAS Installation” (as applicable) and press the ENT key on PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GIA 1 or GIA 2 configuration box, whichever was replaced, and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

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Stormscope GIA Configuration (For GIA 2 replacement and aircraft equipped with a WX500 system only) 1. Scroll the cursor to the ITEM window highlight “Option – WX500 Installation” and press the ENT key on the PFD. 2. Press the CHK ALL softkey. 3. Press “Load” softkey. 4. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 5. Acknowledge the prompt by pushing the ENT key.

Configuration Manager Update 1. With the system still in configuration mode, scroll to the Configuration Manager page on the PFD. 2. Press the CNFM CFG softkey. 3. Select ok when prompted to “Confirm configuration as expected configuration”. 4. Power cycle the system verify there are no red-Xs or system alerts. 5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 6. If there are no red-Xs or system alerts, continue to Section 7.3.3.

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GIA Test GPS Signal Acquisition

Figure 7-2, Aux – GPS Status Page (MFD) The GIA units should normally acquire a GPS navigation solution within 5 to 10 minutes of startup, provided the aircraft is outside (or indoors with a GPS repeater). Select the Aux – GPS Status page on the MFD. Two softkeys on the bottom of the display allow the user to toggle between GPS 1 and GPS 2. Verify that both receivers show 3D DIFF NAV on the MFD. NOTE It may be necessary to temporarily disable or move away from GPS repeaters while testing, as repeaters may adversely affect GPS receiver performance.

VHF COM Interference Test This test must be conducted outside. Use of a GPS repeater inside a hangar may result in a failed test. This procedure assumes that the system is currently set to 25 kHz COM channel spacing. Once the signal acquisition test has been completed successfully, perform the following steps: 1. On the MFD, monitor GPS signal strength bars on the Aux – GPS Status page. 2. On the PFD, ensure that the CDI is set to GPS. If it is not, press the ‘CDI’ softkey until GPS ENR is displayed. 3. Verify that the GPS “INTEG” flag is out of view. 4. Select 121.150 MHz on the No. 1 COM transceiver. 5. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels. 6. During the transmit period, verify that the GPS “INTEG” flag does not come into view on the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD.

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7. Repeat steps 5 and 6 and re-transmit while monitoring GPS 2 signal levels on the MFD. 8. Repeat steps 4 through 7 for each of the following frequencies:  121.175 MHz  121.200 MHz  131.250 MHz  131.275 MHz  131.300 MHz 9. Repeat steps 4 through 8 for the No. 2 COM transceiver (GIA2). 10. On the MFD, select the Aux – System Setup page. 11. Under the COM CONFIG field, change the COM channel spacing from 25 kHz to 8.33 kHz. 12. Go back to the Aux – GPS Status page. 13. Select 121.185 MHz on the No. 1 COM transceiver. 14. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels. 15. During the transmit period, verify that the GPS “INTEG” flag does not come into view on the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD. 16. Repeat steps 14 and 15 and re-transmit while monitoring GPS 2 signal levels on the MFD. 17. Repeat steps 14 through 16 for each of the following frequencies:  121.190 MHz  130.285 MHz  131.290 MHz 18. Repeat steps 14 through 17 for the No. 2 COM transceiver (GIA2). 19. On the MFD, select the Aux – System Setup page and change the COM channel spacing back to 25 kHz.

VOR/LOC/GS Test Check the VOR, ILS, and Glideslope functions with ramp test equipment. Operate the equipment according to the test equipment manufacturer’s instructions. Adjust the RF signal to a level adequate to perform the test. Select the appropriate HSI source by using the CDI softkey.

NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned.

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GFC 700 VOR/LOC/GS Test (if GFC 700 is installed) 1. Simulate a VOR signal on a radial equivalent to the aircraft heading. Tune the NAV 1 and NAV 2 receivers to the simulation frequency. 2. Set the HSI on the PFD to VOR1 by pressing the CDI softkey until VOR1 is selected. Rotate CRS knob to set VOR1 course pointer to aircraft heading. 3. Verify full scale deflection of VOR1 CDI by varying CRS1 selected course at least 10° left and right. Reset course pointer to aircraft heading. 4. Engage the autopilot and press the NAV key on the AFCS mode controller. Using the CRS knob alter course by 10° to the right. Verify the flight director and aircraft controls respond by flying to the VOR course. Repeat to the left. 5. Set CRS course pointer to aircraft heading. 6. Simulate a Localizer/Glideslope signal. Tune this signal on NAV 1 and NAV 2 receiver. Set the PFD HSI to LOC1 by pressing CDI softkey until LOC1 is selected. Use the test equipment to center the deviation bars (localizer and glideslope) on the PFD. 7. Press the APR key on the AFCS mode controller. Verify that the LOC and PIT annunciations are green and ALTS and GS are white on the PFD. Apply right/left and up/down localizer/glideslope signals using the test equipment. Verify that the Flight Director and flight controls respond appropriately. 8. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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7.4 GEA 71 or GEA 71B Engine/Airframe Unit Original GEA 71 or GEA 71B Reinstalled No software or configuration loading is required if the removed GEA is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the return-to-service checks in Section 9. New, Repaired or Exchange GEA 71 or GEA 71B Installed If a new, repaired or exchange GEA is installed, the correct software and configuration files must be loaded to the unit. See Section 7.4.1.

LRU Replacement Procedure GEA 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GEA1 in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.4.2 17. If there are no red-Xs or system alerts, continue to Section 7.4.3.

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Legacy Replacement Procedure GEA (Alternate Method) To load the GEA complete the following subsections in order as they apply to the aircraft.

GEA Configuration (For GEA replacement) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 5. Activate the cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X - XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Cessna XXX – Baseline Configuration” (where XXX is the airframe type) and Press ENT key on the PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GEA. 9. Highlight the software box and press the ENT key to check the box. 10. Highlight the Configuration box and press the ENT key to check the box. 11. Press “Load” softkey. 12. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 13. Acknowledge the prompt by pushing the ENT key.

CAN Bus Fuel Probe Configuration (For GEA replacement) (if installed) 1. In the ITEM window highlight “Option – CAN BUS FUEL LEVEL SENSORS” and press the ENT key on the PFD. 2. Press the CLR ALL softkey. 3. Scroll the cursor to GEA configuration box and press the ENT key to check the box. 4. Press “Load” softkey. 5. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 6. Acknowledge the prompt by pushing the ENT key.

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Configuration Manager Update 1. With the system still in configuration mode, scroll to the Configuration Manager page on the PFD. 2. Press the CNFM CFG softkey. 3. Select ok when prompted to “Confirm configuration as expected configuration” 4. Power cycle the system verify there are no red-Xs or system alerts. 5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 6. If there are no red-Xs or system alerts, test the GEA per Section 7.4.3.

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GEA Test On the MFD (normal mode), check the indication for each of the sensor or monitor inputs with the aircraft engines off. In general, verify all engine and system instruments show valid static normal values and markings, with no red Xs or erratic indications. Reference Figure 7-3 for normal engine instrument markings (figure may not reflect actual aircraft installation). If individual engine readings do not appear normal or have a red-X over them, refer to the G1000 Nav III Line Maintenance Manual.

Figure 7-3, Normal Engine Instrument Markings (MFD)

If no other service is to be performed and individual GEA input testing is not required, continue to the return-to-service checks in Section 9.

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7.5 GTX 335R, GTX 345R, or GTX 33 Transponder Original GTX is Reinstalled No software or configuration loading is required if the removed GTX 335R, GTX 345R, or GTX 33 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to GTX 335R, GTX 345R, or GTX 33 Test Section 7.5.4. New, Repaired or Exchange GTX is Installed If a new, repaired or exchange GTX 335R, GTX 345R, or GTX 33 is installed, the correct software and configuration files must be loaded to the unit. See Section 7.5.1.

LRU Replacement Procedure GTX1 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GTX1 in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.5.2. 17. If there are no red-Xs or system alerts, continue to Section 7.5.3.

Legacy Replacement Procedure GTX (Alternate Method) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD.

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5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X - XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Baseline Option – GTX 335 Installation” OR “Baseline Option – GTX 345 Installation, without GTS 800” or “Baseline Option – GTX 345 Installation, with GTS 800” or “Baseline Option – Legacy – GTX 33 ES Installation” (as applicable). Press ENT key on the PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GTX. 9. Highlight the software box(es) and press the ENT key to check the box. 10. Highlight the Configuration box and press the ENT key to check the box. 11. Press “Load” softkey. 12. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 13. Acknowledge the prompt by pushing the ENT key. 14. Deactivate the cursor. 15. Scroll to the Configuration Manager page. 16. Press the CNFM CFG softkey. 17. Select ok when prompted to “Confirm configuration as expected configuration” 18. Power cycle the system verify there are no red-Xs or system alerts. 19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 20. If there are no red-Xs or system alerts, continue to Section 7.5.3.

Transponder Configuration 1. If not applied, apply power to the G1000 system and put all displays into config mode. 2. On the PFD, select the AIRCRAFT CONFIGURATION page. 3. For GTX 33 unit replacement only, press the Set GTX #1 softkey and acknowledge the PFD prompt by pressing the ENT key. GTX 335R and 345R units automatically save the registration number, no action is needed for these units. 4. After completing transponder configuration, deactivate the cursor.

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Figure 7-4, Aircraft Registration

GTX 335R, GTX 345R, or GTX 33 Test Operation of the GTX 335R, GTX 345R, or GTX 33 Mode-S transponder is accomplished using the PFD or the MFD. Refer to G1000 Cessna Nav III Cockpit Reference Guide, listed in Table 1-1, for basic operation. The integrated transponder/altitude reporting system must be verified in accordance with Title 14 of the Code of Federal Regulations (14 CFR) §§ 91.411 and 91.413, every 24 calendar months, or any time the transponder is removed. This test requires the use of a Mode S ramp generator. Specific instructions for operating the ramp tester are contained in the applicable operator's manual. Refer to 14 CFR Part 43 Appendices E and F for testing criteria. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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7.6 GSU 75 ADAHRS (if installed) Original GSU unit is Reinstalled No software or configuration loading is required if the removed GSU 75 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Perform a pitot - static system leak check and continue to Section 9. New, Repaired or Exchange GSU unit is Installed If a new, repaired or exchange GSU unit is installed, the correct software and configuration files must be loaded to the unit. New GSU 75 Configuration Module is Installed The correct configuration files must be loaded if the GSU75 configuration module has been replaced.

LRU Replacement Procedure GSU 1. Open the MFD PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GRS1 in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Select GDC 1 in the LRU dropdown box. 12. Press the CHK All softkey. 13. Press the Load softkey. 14. Press ENT to acknowledge the process was complete. 15. Deactivate the cursor. 16. Scroll to the Configuration Manager page. 17. Press the CNFM CFG softkey. 18. Select ok when prompted to “Confirm configuration as expected configuration” 19. Power cycle the system verify there are no red-Xs or system alerts. 20. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.6.2. 21. If there are no red-Xs or system alerts, continue to Section 7.7.3 for the air data portion of the GSU and Section 7.10.5 for the AHRS portion of the GSU.

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Legacy Replacement Procedure GSU (Alternate Method) (if installed) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X - XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Baseline Option – GSU75 Installation”. Press ENT key on PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GSU - AHRS. 9. Highlight the software box and press the ENT key to check the box. 10. Highlight the Configuration box and press the ENT key to check the box. 11. Use the large FMS knob to scroll to GSU – ADC. 12. Highlight the software box and press the ENT key to check the box. 13. Highlight the Configuration box and press the ENT key to check the box. 14. Press “Load” softkey. 15. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 16. Acknowledge the prompt by pushing the ENT key. 17. Deactivate the cursor. 18. Scroll to the Configuration Manager page. 19. Press the CNFM CFG softkey. 20. Select ok when prompted to “Confirm configuration as expected configuration” 21. Power cycle the system verify there are no red-Xs or system alerts. 22. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 22. If there are no red-Xs or system alerts, continue to Section 7.7.3 for the air data portion of the GSU and Section 7.10.5 for the AHRS portion of the GSU.

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7.7 GDC 74A Air Data Original GDC unit is Reinstalled No software or configuration loading is required if the removed GDC 74 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Perform a pitot - static system leak check and continue to Section 9 if no other service is performed. New, Repaired or Exchange GDC unit is Installed If a new, repaired or exchange GDC unit is installed, the correct software and configuration files must be loaded to the unit. New GDC 74A Configuration Module is Installed The correct configuration files must be loaded if the GDC 74A configuration module has been replaced.

LRU Replacement Procedure GDC 74A (if installed) 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GDC1 in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.7.2. 17. If there are no red-Xs or system alerts, continue to Section 7.7.3.

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Legacy Replacement Procedure GDC 74A (Alternate Method) (if installed) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X - XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Baseline Option – Legacy – GRS77 and GDC 74 Installation”. Press ENT key on the PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GDC. 9. Highlight the software box and press the ENT key to check the box. 10. Highlight the Configuration box and press the ENT key to check the box. 11. Press “Load” softkey. 12. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 13. Acknowledge the prompt by pushing the ENT key. 14. Deactivate the cursor. 15. Scroll to the Configuration Manager page. 16. Press the CNFM CFG softkey. 17. Select ok when prompted to “Confirm configuration as expected configuration” 18. Power cycle the system verify there are no red-Xs or system alerts. 19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 20. If there are no red-Xs or system alerts, continue to Section 7.7.3.

Air Data Test (GSU 75 or GDC 74A) The G1000 system must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1-2 and appropriate regulations. When the GDC unit is tested in accordance with 14 CFR Part 43, Appendix E, note the following exceptions:  Do not perform paragraph (b)(1)(iv) Friction  Do not perform paragraph (b)(1)(vi) Barometric Scale Error The following Air Data Test is to be performed in addition to or in conjunction with any other regulated tests. This test must be performed with a calibrated Air Data Test Set (ADTS) with a combined accuracy/repeatability specification of less than ±20 feet for the test altitude range.

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1. For GSU 75 installations, gain access to the aft avionics compartment in the tail of the aircraft. Locate the tee fittings in the pitot and static lines just forward of the GSU 75 and remove the capped nuts. Drain any condensation from the lines and tees. Reinstall the capped nuts onto the tees and tighten, ensuring caps are facing downward.

NOTE: If tee fittings are not installed in the pitot and static lines, disconnect the lines directly from the GSU 75 and drain any condensation from the lines. Reconnect the pitot and static lines to the GSU 75 and tighten the nuts. 2. Perform pitot static system leak check as described in Chapter 34 of the appropriate Cessna Maintenance Manual (refer to Table 1-1 for Manual details.) 3. Connect the pitot/static tester to the aircraft pitot and static ports. 4. Verify that the PFD altimeter baro setting is set to 29.92 in Hg (1013.25 mb). 5. Start the PFD in configuration mode and navigate to the GRS page. The values for altitude and airspeed are shown on the AHRS/AIR DATA INPUT table as B ALT and IAS for AIR DATA 1. 6. Simulate the altitudes shown in Table 7-1. Wait for ADTS to report that target values have been achieved. 7. On Table 7-1, record the altitude (B ALT) displayed on the PFD for AIR DATA 1 for each altitude. 8. Simulate the airspeeds shown in Table 7-1. 9. On Table 7-2, record the airspeed (IAS) displayed on the PFD for AIR DATA 1 for each airspeed. 10. Verify that the indicated altitudes and airspeeds are within allowable tolerances. 11. File the results with the aircraft maintenance records. If either the pilot or copilot air data system does not meet the tolerances specified, have maintenance checks performed on the air data system or the pitot/static system. Table 7-1, Altitude Test Points PFD Altitude Reading Test Set Altitude Allowed Tolerance (from B ALT field) 0 +/- 20 500 +/- 20 1000 +/- 20 1500 +/- 20 2000 +/- 20 4000 +/- 25 8000 +/- 30 11000 +/- 35 14000 +/- 40 17000 +/- 45 20000 +/- 50

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Table 7-2, Airspeed Test Points PFD Airspeed Reading Test Set Airspeed Allowed Tolerance (from IAS field) 50 +/- 5.0 80 +/- 3.0 100 +/- 2.0 120 +/- 2.0 150 +/- 2.0 180 +/- 2.0

Static Port Vertical Speed (Rate of Climb) Test 1. Command ADTS to change the altitude at the rates shown in the table below. 2. Wait for ADTS to report that target rates have been achieved. 3. Verify that the Rate of Climb reported by the Vertical Speed field on the PFD are within the tolerances specified in Table 7-3. Table 7-3, Vertical Speed Table Vertical Speed, feet/minute Allowed tolerance, ±feet/minute 2000 100 1000 50 500 45 200 45 0 N/A (No VS Display) -200 45 -500 45 -1000 50 -2000 100

OAT Probe Check 1. Ensure the outside air temperature (OAT) probes and a calibrated thermometer stabilize at ambient temperature. 2. Verify that the OAT measurement shown on the PFD, in degrees Celsius, indicate within 2 °C of the ambient temperature as measured by the calibrated thermometer. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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7.8 GRS 77 and GMU 44 Magnetometer (if installed) Original GRS is Reinstalled If the original GRS is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. If the GRS rack was not removed or loosened, continue to the GRS/GMU Test Section 7.10.5. If the GRS rack was removed or loosened, continue to the GRS/GMU Calibration Procedures Section 7.10. New, Repaired or Exchange GRS is Installed If a new, repaired or exchange GRS is installed, then software must be loaded. New GRS Configuration Module is Installed If the GRS configuration module is replaced, no software loading is required. Continue to the GRS/GMU Calibration Procedures Section 7.10.

LRU Replacement Procedure GRS 77 (if installed) 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GRS1 in the LRU dropdown box. 8. Verify all boxes are checked. If they are not checked, press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.8.2. 17. If there are no red-Xs or system alerts and the GRS rack(s) were not removed or loosened, continue to the GRS/GMU Test Section 7.10.5. 18. If there are no red-Xs or system alerts and the GRS rack(s) was removed or loosened, continue to the GRS/GMU Calibration Procedures Section 7.10.

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Legacy Replacement Procedure GRS 77 (Alternate Method) (if installed) 1. Insert the software loader card in the top slot of the PFD. 2. Power on the MFD and PFD in configuration mode. 3. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X - XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Baseline Option – Legacy – GRS77 and GDC74 Installation”. Press ENT key on the PFD. 7. Press the CLR ALL softkey. 8. Use the large FMS knob to scroll to GRS 9. Highlight the software box and press ENT. 10. Press “Load” softkey. 11. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 12. Acknowledge the prompt by pushing the ENT key. 13. Deactivate the cursor. 14. Scroll to the Configuration Manager page. 15. Press the CNFM CFG softkey. 16. Select ok when prompted to “Confirm configuration as expected configuration” 17. Power cycle the system verify there are no red-Xs or system alerts. 18. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 17. If there are no red-Xs or system alerts and the GRS rack(s) were not removed or loosened, continue to the GRS/GMU Test Section 7.10.5. 18. If there are no red-Xs or system alerts and the GRS rack(s) was removed or loosened, continue to the GRS/GMU Calibration Procedures Section 7.10.

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7.9 GMU 44 Magnetometer Original GMU 44 is Reinstalled If the original GMU 44 is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GRS/GMU Test Section 7.10.5. New, Repaired or Exchange GMU 44 is Installed If a new, repaired or exchange GMU 44 is installed, then software must be loaded.

LRU Replacement Procedure GMU 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GMU1 in the LRU dropdown box. 8. Verify all boxes are checked. If they are not checked, press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.9.2. 17. If there are no red-Xs or system alerts, continue to Section 7.10.

Legacy Replacement Procedure GMU1 (Alternate Method) 1. Insert the software loader card in the top slot of the PFD. 19. Power on the MFD and PF1 in configuration mode. 20. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 21. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 22. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X – XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. G1000 Supplemental Maintenance Manual Page 7-32 Textron Nav III Series Revision 4 190-02128-04

23. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight either “Baseline Option – GSU75 Installation” or “Baseline Option – Legacy – GRS77 and GDC74 Installation” as applicable. Press ENT key on the PFD. 24. Press the CLR ALL softkey. 25. Scroll to GMU. 26. Highlight the Software box. 27. Press the ENT key. 28. Press “Load” softkey. 29. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….”COMPLETE” in the summary box. 30. Acknowledge the prompt by pushing the ENT key. 31. Deactivate the cursor. 32. Scroll to the Configuration Manager page. 33. Press the CNFM CFG softkey. 34. Select ok when prompted to “Confirm configuration as expected configuration” 35. Power cycle the system verify there are no red-Xs or system alerts. 36. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 37. If there are no red-Xs or system alerts, continue to Section 7.10.

7.10 GSU/GRS/GMU Calibration Procedures GSU/GRS/GMU Recalibration Criteria The following calibration procedures are provided for the GRS/GSU and GMU 44:  Pitch/Roll Offset: (Procedure A1, PROVIDED IN SECTION 7.10.1)  Magnetometer Calibration: (Procedure B, PROVIDED IN SECTION 7.10.3)  Engine Run-Up Vibration Test: (Procedure D, PROVIDED IN SECTION 7.10.4)  Magnetometer Interference Test: (Procedure E, PROVIDED IN SECTION 5.13.4) Follow the steps given for each procedure on-screen at the GRS/GMU CALIBRATION page. Note that the CALIBRATE command cannot be selected and activated until the installer acknowledges all required steps have been carried out by pressing the ENT key on each step.

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Table 7-4, Required GRS/GMU Calibrations Calibrations Required Procedure A1: Procedure B: Procedure D: GSU 75 GSU/GRS/GMU Engine Run-up Condition or GRS 77 Magnetic Vibration Pitch/Roll Calibration Test Offset GMU 44 was removed and reinstalled. (no None Required. change in serial number) Continue to GSU/GRS/GMU Test Section. GMU 44 was replaced with new unit. X (New serial number) GRS AHRS or GSU ADAHRS was removed and/or replaced. The mounting tray was None Required. NOT removed and the mounting tray bolts Continue to GSU/GRS/GMU Test Section. were NOT loosened. GRS AHRS or GSU ADAHRS was removed and/or replaced. The mounting tray WAS removed and/or mounting tray bolts WERE X X X loosened. GRS AHRS or GSU ADAHRS Configuration X X X Module was replaced.

Procedure A1: GSU 75 or GRS 77 Pitch/Roll Offset Calibration This first procedure must be carried out with the engine off. 1. Level the aircraft to within 0.25° of zero pitch and zero roll. (Follow instructions in the appropriate Cessna Nav III Series Maintenance Manual, listed in Table 1-1, for leveling) 2. Start the PFD in Configuration mode. 3. Go to the GRS Page Group and select the GRS/GMU Calibration page at the PFD. This page is protected and the following softkey password must be entered at the PFD to continue:  9  10  11  12 (Far Right softkey)

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Figure 7-5, GRS/GMU Calibration, Pitch/Roll Offset

NOTE On the calibration pages, “GRS” includes GRS and GSU units.

4. Ensure that the GRS 1 is selected in the SELECT GRS UNIT window on the PFD. 5. Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH / ROLL OFFSET. 6. Press the ENT key. 7. Use the cursor to highlight Step 1 in the BEFORE CALIBRATION window. 8. Follow the checklist items displayed on the PFD and press the ENT key as each step is completed or confirmed. 9. When the CALIBRATE field is blinking, press the ENT button to begin the procedure. 10. After several seconds, a new checklist appears in the lower half of the PFD. Press the ENT key as each step is confirmed. When the CONFIRM AIRCRAFT IS LEVEL field is blinking, press the ENT key to continue. 11. The result of the pitch/roll offset compensation is displayed on the PFD. If successful, the AHRS records the required pitch and roll offsets, informs the operator of a successful conclusion and returns to normal operation. 12. Press the ENT key on the PFD to conclude this procedure for GRS 1.

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Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure (Optional) NOTE The Magnetometer Calibration Procedure that follows in Section 7.10.3 (Calibration Procedure B) must be carried out at a site that is determined to be free of magnetic disturbances. If it is unsure whether the site is ‘clean’, the technician should verify that the site is ‘clean’ by following the guidance provided in Section 7.10.2. The technician may skip Section 7.10.2 if the site condition is acceptable.

Typically, a compass rose is an acceptable location to perform the magnetometer calibration procedure. However, because not all compass roses are well maintained, even an existing compass rose should be regularly evaluated using the method described here to determine if it is free of magnetic disturbances. If evaluation of an existing compass rose indicates that magnetic disturbances are present, then an alternative location must be found to perform the Magnetometer Calibration Procedure.

A G1000-equipped airplane that has completed the pitch/roll offset compensation procedure (Procedure A-1, Section 7.10.1) can be used to evaluate a candidate site for magnetic disturbances and determine whether it is a suitable location to perform the magnetometer calibration procedure. The magnetometer calibration procedure itself contains the logic to simultaneously survey the location for magnetic cleanliness while it is computing the magnetometer calibration parameters. In order to evaluate a candidate site, the Magnetometer Calibration Procedure must be performed twice: once turning clockwise around the site, and once turning counter-clockwise. Both times, the procedure should be conducted as described in Section 7.10.3 of this document, with the exception of the direction of turns around the site. NOTE Although Section 7.10.3 indicates that the Magnetometer Calibration Procedure should be performed by making a series of clockwise turns around the site, the procedure can also be performed by making counter-clockwise turns for the purpose of evaluating the site for magnetic disturbances.

If the PFD displays the “CALIBRATION SUCCESSFUL / SITE IS CLEAN” message upon completion of the Magnetometer Calibration Procedure in each clockwise and counter- clockwise direction, then the candidate site is sufficiently free of magnetic disturbances and is acceptable for performing the Magnetometer Calibration Procedure. It is important to obtain successful result in both the clockwise and counter-clockwise directions to ensure that the magnetometer sweeps over a large enough area at the candidate site. If the PFD displays either the “MAG FIELD AT SITE NOT UNIFORM” or “MAG FIELD AT SITE DIFFERS FROM IGRF MODEL” message upon completion of the Magnetometer Calibration Procedure in either of the two directions, then the site contains magnetic disturbances that are too large.

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Procedure B: GSU 75 or GRS 77 and GMU 44 Magnetic Calibration NOTES Procedure A-1 (Section 7.10.1) must first be successfully accomplished before performing Procedure B, only for situations where the GSU/GRS was replaced with a new unit. On the calibration pages, “GRS” refers to whichever GRS or GSU unit is installed.

1. Start the following the procedures referenced in the appropriate Cessna Nav III AFM as listed in Table 1-1. 2. After aircraft engine startup, taxi the aircraft to a properly calibrated compass rose. 3. At the compass rose, align the aircraft to a heading of magnetic north (5°). CAUTION Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free of environmental magnetic disturbances. Attempting to carry out this maneuver on a typical ramp area may not yield a successful calibration. The accuracy of the AHRS/ADAHRS cannot be guaranteed if this calibration is not performed on a magnetically clean compass rose or equivalent. If the compass rose condition is not known, it is recommended that the technician follow the guidance in Section 7.10.2.

4. Restart the PFD in configuration mode. 5. Go to the GRS Page Group on the PFD. 6. Select the GRS/GMU Calibration page and enter the following softkey password:  9  10  11  12 (far right softkey) 7. Use the FMS small knob to highlight GRS/GSU for calibration and press the ENT key. 8. Using the FMS small knob, select MAGNETOMETER. Press the ENT button. 9. Use the cursor to highlight the first step in the BEFORE CALIBRATION window. 10. Follow the checklist items displayed on the PFD and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. 11. The PFD display advises the operator when to turn the aircraft, when to stop, and when to turn again. 12. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 25° to 30° of turn from the last heading, the PFD display advises the operator to stop the aircraft. NOTE Due to the difficulties in executing smooth, accurate turns the PFD may incorrectly interpret a station and instruct to “HOLD POSITION” prior to full

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completion of a 30 turn. If this scenario is encountered, it is best for the operator to ignore the “HOLD POSITION” command and instead use outside references to complete the approximate 30 turn. Instead of using the PFD instruction to turn as a real-time indication of when to turn, simply judge the 30° (±5°) turn increments of the aircraft by using the compass rose radials. Dwelling at these 30 increments for the time recommended by the PFD should result in successful calibration.

13. The PFD guides the operator to dwell at multiple headings around a complete circle. NOTE Due to high winds or excessive airframe vibration, the operator may encounter a condition where the PFD restarts the 18-second countdown without full completion of the previous countdown. If this is encountered more than once for a given station, the operator should begin turning to the next station (approximately 30). A minimum of 2 successful stations per quadrant is required, where a successful station is a full 18-second countdown followed by instruction to move. Ensure that at least 2 stations per quadrant are completed. Thus, it may sometimes be required to dwell at a station after a countdown restart. A maximum of 30 stations is allowed for the entire calibration procedure. If too many countdown restarts are encountered, the calibration will fail with the message, “TOO MANY STATIONS.”

14. Repeat the turn-and-stop process until the PFD advises that a successful calibration is complete. The GRS AHRS/GSU ADAHRS then enters its normal operational mode. Press the ENT button on the PFD to conclude this procedure.

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Procedure D: Engine Run-Up Vibration Procedure

NOTES On the calibration pages, “GRS” refers to whatever GRS or GSU unit is installed. Calibration Procedure D is performed in order to guarantee that the ADAHRS/AHRS mounting is sufficiently rigid and insensitive to vibration. This procedure must be performed for both GSU/GRS units installed in the aircraft. Calibration Procedures A1 and B (Sections 7.10.1 and 7.10.3 respectively) are not required prior to this procedure.

Figure 7-6, GRS/GMU Calibration, Engine Run-Up

1. Restart the PFD in configuration mode. 2. Use the FMS small knob to highlight GRS 1 for calibration and press the ENT key. The SELECT PROCEDURE field is not blinking. 3. Initiate the AHRS engine run-up vibration test procedure by performing the following steps: a) Select the ENGINE RUN-UP TEST procedure and press the ENT key. b) Follow the checklist items displayed on the PFD, and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. 4. The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over a period of 1-2 minutes. 5. When the operator has completed the engine run-up and the engine is back to an idle setting, press the ENT key to indicate that the process is complete. When this is done, the TEST COMPLETE field stops blinking.

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6. The PFD informs the operator if the installation has passed or failed the vibration test. If the test fails, the specific measurements causing the failure are identified and associated numeric values are displayed on the PFD.

NOTE Should a failure occur, the technician may perform the Engine Run-up test up to 3 times successively before corrective action must be taken. If the test does not pass after three attempts, then the installation should not be considered reliable until the source of the vibration problem is identified and remedied. In the event of repeated failure of the engine run-up test, record the values that are reported to be out of range for future reference. The following are potential causes for failure of the engine run-up test: a) Vibration motion of GSU/GRS and/or GMU44 caused by neighboring equipment and/or supports. b) Mounting screws and other hardware for GSU/GRS and/or GMU44 not firmly attached. c) GSU/GRS connector not firmly attached to unit. d) Cabling leading to GSU/GRS or GMU44 not firmly secured to supporting structure. e) An engine / propeller that is significantly out of balance. 7. Press the ENT key on the PFD to conclude this procedure, then the aircraft can be taxied back and the engine can be shut down for final testing. Continue to Section 7.10.5.

GSU/GRS/GMU Test Start the displays in normal mode. The ADAHRS/AHRS attitude and heading information displayed should become valid within 1 minute of power-up as shown in Figure 7-7 if at least one GPS receiver has a valid position. If GPS is unavailable, the ADAHRS/AHRS initialization may take up to 2 minutes.

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Figure 7-7, Normal Mode AHRS Check If no other service is to be performed, continue to the return-to-service checks in Section 9.

This area intentionally blank.

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7.11 GDL 69A or GDL 69A SXM Data Link (if installed) Original GDL 69A/69A SXM is Reinstalled No software or configuration loading is required if the removed GDL 69A is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GDL 69A/69A SXM Test Section 7.11.3. New, Repaired or Exchange GDL 69A/69A SXM is Installed If a new, repaired or exchange GDL 69A/69A SXM is installed, the correct software and configuration files must be loaded to the unit, then the SiriusXM Satellite Radio subscription must be reactivated. See the SiriusXM Activation Instructions listed in Table 1-2.

LRU Replacement Procedure 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GDL69 in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.11.2. 17. If there are no red-Xs or system alerts, continue to Section 7.11.3.

Legacy Replacement Procedure GDL69 (Alternate Method) 1. Insert the software loader card in the top slot of the PFD. 38. Power on the MFD and PFD in configuration mode. 39. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 40. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD.

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41. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X – XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 42. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Baseline Option – GDL 69A SXM Installation” or “Baseline Option – Legacy – GDL 69 Installation” as applicable. Press ENT key on the PFD. 43. Press the CLR ALL softkey. 44. Using the large FMS knob scroll down to the GDL software box and press ENT. 45. Scroll down to the GDL configuration box and press ENT. 46. Press the Load softkey. 47. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box.

NOTE

If the software load fails, cycle power to the GDL 69A only and confirm that the software part number and version are updated in the DATA window on the MFD. Then, press ENT button on the PFD to check the GDL 69A SXM SOFTWARE and CONFIGURATION check boxes and press LOAD softkey again to resume the software update.

48. Press ENT key on the PFD to acknowledge upload complete. 49. Deactivate cursor. 50. Scroll to the Configuration Manager page. 51. Press the CNFM CFG softkey. 52. Select ok when prompted to “Confirm configuration as expected configuration” 53. Power cycle the system verify there are no red-Xs or system alerts. 54. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 55. If there are no red-Xs or system alerts, continue to Section 7.11.3.

GDL 69A Test If a SiriusXM Satellite Radio subscription has already been activated for the GDL 69A/69A SXM, then power up the G1000 and go to the Aux – Information page and verify that the GDL 69A/69A SXM is working properly. Refer to the Cockpit Reference Guide, listed in Table 1-2, for details on Sirius XM Radio weather and music operation. If the GDL 69A/69A SXM is replaced (new unit), the owner must re-activate the subscription, using the new GDL 69A/69A SXM’s Radio ID number(s). Refer to the GDL 69A/69A SXM Satellite Radio Activation Instructions, listed in Table 1-2, for details on the activation process. As a final operations check, make sure there are no MANIFEST errors shown on the PFD for the GDL 69A/69A SXM. If no other service is to be performed, continue to the return-to-service checks in Section 9. G1000 Supplemental Maintenance Manual Page 7-43 Textron Nav III Series Revision 4 190-02128-04

7.12 GSA 81 Servos (if installed) Original Servo(s) Reinstalled No software loading is required if the removed servo(s) is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the return-to-service checks in Section 9. New, Repaired or Exchange Servo(s) Installed If a new, repaired or exchange servo is installed, the correct software files and certification gains must be loaded to the unit.

LRU Replacement Procedure GSA81 Servos 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select the installed GSA CTRL in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Select the installed GSA MON in the LRU dropdown box. 12. Press the CHK All softkey. 13. Press the Load softkey. 14. Press ENT to acknowledge the process was complete. 15. Deactivate the cursor. 16. Scroll to the Configuration Manager page. 17. Press the CNFM CFG softkey. 18. Select ok when prompted to “Confirm configuration as expected configuration” 19. Power cycle the system verify there are no red-Xs or system alerts. 20. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.12.2. 21. If there are no red-Xs or system alerts, continue to return to service checks in Section 9.

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Legacy Replacement Procedure GSA81 Servos (Alternate Method) 1. Insert the software loader card in the top slot of the PFD. 56. Power on the MFD and PFD in configuration mode. 57. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 58. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD. 59. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X – XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 60. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob highlight “Option – GFC 700 Installation”. Press ENT key on the PFD. 61. Press the CLR ALL key. 62. Scroll to highlight the installed servo. 63. Highlight the software box and press the ENT key to check the box. 64. Scroll to highlight the installed servo cert line. 65. Highlight the software box and press the ENT key to check the box. 66. Press the Load softkey. 67. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. 68. Press ENT key on the PFD to acknowledge upload complete. 69. Deactivate cursor. 70. Scroll to the Configuration Manager page. 71. Press the CNFM CFG softkey. 72. Select ok when prompted to “Confirm configuration as expected configuration” 73. Power cycle the system verify there are no red-Xs or system alerts. 74. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 75. If there are no red-Xs or system alerts, continue to return to service checks in Section 9.

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7.13 Garmin Traffic Systems (GTS 800) (if installed) Original GTS Reinstalled No software or configuration loading is required if the removed GTS is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GTS Test Section 7.13.3. New, Repaired or Exchange GTS Installed If a new, repaired or exchange GTS is installed, the correct software and configuration files must be loaded to the unit. See Section 7.13.1 and then continue to the GTS Test Section 7.13.3.

LRU Replacement Procedure GTS 1. Open the MFD, PFD (ESS BUS), and PFD (AVN BUS 1) circuit breakers. 2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present. 3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses. 4. Turn on Avionics electrical busses. 5. Power on the MFD and PFD in configuration mode. 6. Using the PFD, scroll to the LRU replacement page. 7. Activate the cursor and select GTS in the LRU dropdown box. 8. Press the CHK All softkey. 9. Press the Load softkey. 10. Press ENT to acknowledge the process was complete. 11. Deactivate the cursor. 12. Scroll to the Configuration Manager page. 13. Press the CNFM CFG softkey. 14. Select ok when prompted to “Confirm configuration as expected configuration” 15. Power cycle the system verify there are no red-Xs or system alerts. 16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or re- load the system using the legacy method in Section 7.13.2. 17. If there are no red-Xs or system alerts, continue to Section 7.13.3.

Legacy Replacement Procedure GTS (Alternate Method) 1. Insert the software loader card in the top slot of the PFD. 76. Power on the MFD and PFD in configuration mode. 77. Select no when “Do you want to update system files” is displayed on the screen of the PFD. 78. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD.

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79. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “0X – XXX” (where 0X is the menu position and XXX is the airframe type) and press ENT key on the PFD. 80. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight “Option – GTS 800 Installation, without GTX 345” or “Option – GTS 800 Installation, with GTX 345” as applicable. Press ENT key on the PFD. 81. Press the CHK All softkey. 82. Press the Load softkey. 83. Monitor load progress. Verify software load completes without errors as indicated by the following:  Green “PASS” in the Configuration and Software columns for each item loaded.  “Upload Complete………….COMPLETE” in the summary box. 84. Press ENT key on PFD to acknowledge upload complete. 85. Deactivate cursor. 86. Scroll to the Configuration Manager page. 87. Press the CNFM CFG softkey. 88. Select ok when prompted to “Confirm configuration as expected configuration” 89. Power cycle the system verify there are no red-Xs or system alerts. 90. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5. 91. If there are no red-Xs or system alerts, continue to Section 7.13.3.

GTS Antenna Functional Check The following test assures the GA 58 traffic antennas and coaxial cables are properly connected. 1. On the MAP-TRAFFIC MAP page of the MFD, press the OPERATE softkey. A self-test of the antenna circuit is initialized. If the MFD displays FAILURE at the upper left corner of the traffic display area, it will be necessary to recheck the coaxial connections. If MFD displays OPERATING without indicating a fault, proceed to the next step of antenna verification. 2. Ensure that the transmitter or receiver (RX/TX) that you are testing is significantly closer to the ramp tester than another operating RX/TX, or erroneous and inaccurate results may occur. All four quadrants (0, 90, 180 and 270 degrees) will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the MAP-TRAFFIC MAP page of the MFD.

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3. Set up a stationary intruder by selecting the following on the ramp tester:  Intruder type: ATCRBS.  Intruder Start Distance: 2 nm  Intruder Start Altitude: 600 feet above field elevation  Vertical Speed: 0 fpm  Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario.) 4. Position ramp tester at 0 degrees. 5. Initiate the intruder scenario and verify a target is annunciated on the MAP-TRAFFIC MAP page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co-altitude (read as +06 above a filled diamond indicating proximate traffic). 6. On the ramp tester, toggle intruder traffic to standby or off. 7. Reposition ramp tester and reengage the same intruder scenario for 90, 180 and 270 degrees. 8. Verify a target is annunciated on the MAP-TRAFFIC MAP page of the MFD at the same bearing as the ramp tester. 9. If the bearing is not as anticipated or multiple targets are displayed during tests, verify the following:  Coax cable connectors are properly secured at the bulkhead adapter fittings, GA 58 antennas, and GTS unit  Connections are made to the proper channels and color-coded heat shrink is the same color on both ends of coax cables  Connectors are correctly installed on coax cables. Note: These tests are conducted at field elevation. Additional local traffic targets may appear and are not an indication of improper system operation. Note: When an IFR6000 ramp tester is used with a GTS 800, the IFR6000 must be configured for a distance that is 4 times the actual distance. For example, if the ramp tester is located 10 ft away from an aircraft, the IFR6000 should be configured as if it were 40 ft away from the aircraft. This will adjust the MTL setting of the IFR6000 such that it will see the GTS 800 low power interrogations and reply to the interrogations.

GTS Ramp Functional Check The following test provides a scenario that will converge and intercept the GTS to assure proper operational and surveillance functions.

1. On the MAP-TRAFFIC MAP page of the MFD, press the OPERATE softkey. 2. Position ramp tester at 90 degrees. 3. Select the following on the ramp tester:  Intruder type: ATCRBS.

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 Intruder Start Distance: 10 nm  Intruder Start Altitude : 600 ft above field altitude  Vertical Speed: 0 fpm  Velocity:600 kts 4. Initiate the intruder scenario and observe the following:  Traffic should be acquired at approximately 10 NM at 90 degree bearing and co- altitude. Observe intruder closes on own aircraft at a rate of 0.1 NM/sec. Verify that only a single target is displayed in the expected quadrant.  The intruder should transition from Other Traffic (displayed as an open diamond with +06 displayed above), to proximate traffic (displayed as a filled white diamond with +06 displayed above), to a Traffic Advisory (TA) alarm (yellow filled circle with +06 displayed above.)

NOTE

The aural TA annunciations are muted if the height above terrain is below 400 feet.

Note: When an IFR6000 ramp tester is used with a GTS 800, the IFR6000 must be configured for a distance that is 4 times the actual distance. For example, if the ramp tester is located 10 ft away from an aircraft, the IFR6000 should be configured as if it were 40 ft away from the aircraft. This will adjust the MTL setting of the IFR6000 such that it will see the GTS 800 low power interrogations and reply to the interrogations

7.14 GSR 56 Original GSR 56 Reinstalled No software or configuration loading is required if the removed GSR 56 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GSR 56 Functional Check Section 7.14.2. New, Repaired or Exchange GSR 56 Installed If a new, repaired or exchange GSR 56 is installed, the correct software and configuration files must be loaded to the unit. See Section 3.6 and then continue to the GSR 56 Functional Check Section 7.14.2.

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Activation of Garmin Connext In order to activate the optional GSR 56 for Garmin Connext, contact Garmin Product Support at one of the following numbers (M-F, 7:00 a.m. to 7:00 p.m. Central Standard Time, - Central USA):  1.866.739.5687 (toll free in USA)  +1.913.440.1135 (worldwide)

 Have the following information ready prior to calling: o Aircraft tail number, serial number, manufacturer, and model o GSR 56 serial number o G1000 system ID number o Name of aircraft owner and contact information o Credit card information Garmin Product Support will provide additional information for activation of data services.

To obtain the G1000 system ID number and unit serial numbers, accomplish the following: 1. Turn the large FMS knob on the MFD to select the AUX page group. 2. Turn the small FMS knob to select the SYSTEM STATUS page. Record the SYSTEM ID number shown in the AIRFRAME field. This number is unique for each G1000 system. 3. Press the LRU softkey to activate the cursor in the LRU INFO field. Use the large FMS knob to scroll the cursor to GSR1 (if GSR 56 is installed). Record the GSR 56 serial number shown in the LRU INFO field.

GSR 56 Functional Check 1. Power up the aircraft. 2. Using the large FMS knob, select the AUX page group on the MFD. Using the small FMS knob, select the AUX-TELEPHONE page. 3. Ensure the system is showing Iridium signal strength (best if aircraft is outside). 4. Press TEL button on the pilot’s GMA. 5. Press the DIAL softkey on the MFD. 6. Enter the test phone number in the ENTER PHONE NUMBER field using the GCU keypad. 7. Press the ENT key on the GCU keypad to accept the phone number. 8. Press the ENT key on the GCU keypad to initiate the dialing sequence. 9. When call is complete, press the HANGUP softkey on the AUX – TELEPHONE page on the MFD to end the call.

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8. Subsystem Functional Checks 8.1 Stormscope Functional Check (if installed) Refer to the G1000 Nav III Line Maintenance Manual for Stormscope Functional Checks. If no other service is to be performed, continue to the return-to-service checks in Section 9.

8.2 TAWS Functional Check For Functional Check of the TAWS-B system, refer to the G1000 Nav III Line Maintenance Manual.

8.3 FliteCharts Functional Check FliteCharts is enabled by default. 1. If Dual Charts are installed, ensure FlightCharts are set as the preferred charts. 2. With the G1000 in Normal Mode, use the MFD FMS knob to select Aux – System Status page, then select MFD1 DB softkey. 3. Use the small FMS knob to scroll to CHART. 4. Verify “FliteCharts” is displayed in blue text adjacent to “CHART”. 5. Verify the FliteCharts database cycle number is displayed in blue text and the FliteCharts database is current. 6. Deactivate the cursor and use the MFD large FMS knob to select the Map - Navigation Map page then press the Charts softkey. 7. Verify the airport chart is displayed and the following softkeys are displayed (some softkeys may be grayed out):  CHRT OPT  APR  Show Map  WX  INFO-1  NOTAM  DP  Go Back  STAR

8. Press the CHRT OPT softkey and verify the following softkeys are displayed (some softkeys may be grayed out):  All  Header  Plan  Profile  Minimums  Fit WDTH  Full SCN  Back G1000 Supplemental Maintenance Manual Page 8-1 Textron Nav III Series Revision 4 190-02128-04

9. If no other service is to be performed, continue to the return-to-service checks in Section 9. 8.4 ChartView Functional Check ChartView must be enabled using a ChartView Enable Card. Reference Section 3.7.1 for enabling procedures. NOTE The required ChartView databases are subscription-based and are to be procured by the aircraft owner directly from Jeppesen.

1. Ensure ChartView are set as the preferred charts. 2. With the G1000 in Normal Mode, use the MFD FMS knob to select ‘Aux – System Status’ page, then select MFD1 DB softkey. 3. Use the small FMS knob to scroll to CHART. 4. Verify “ChartView” is displayed in blue text adjacent to CHART. 5. Verify the ChartView database cycle number is displayed in blue text and the ChartView database is current. 6. Deactivate the cursor and use the large MFD FMS knob to select the Navigation Map Page then press the Charts softkey. 7. Verify the airport chart is displayed and the following softkeys are displayed(some softkeys may be grayed out):  CHRT OPT  APR  Show Map  WX  INFO-1  NOTAM  DP  Go Back  STAR 8. Press CHRT OPT softkey and verify the following softkeys are displayed (some softkeys may be grayed out):  All  Header  Plan  Profile  Minimums  Fit WDTH  Full SCN  Back 9. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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8.5 SafeTaxi Functional Check The maximum map ranges for enhanced detail are configurable by the flight crew. When zoomed in close enough to show the airport detail, the map reveals runways with numbers, taxiways with identifying letters/numbers, and airport landmarks including ramps, buildings, control towers, and other prominent features. Resolution is greater at lower map ranges. When the aircraft location is within the screen boundary, including within SafeTaxi ranges, an airplane symbol is shown on any of the navigation map views for enhanced position awareness. Any map page that displays the navigation view can also show the SafeTaxi airport layout, within the maximum configured range. The following is a list of pages where the SafeTaxi feature can be seen:  Navigation Map Page  Inset map  HSI map  Weather Datalink Page  Airport Information Page  Intersection Information Page  NDB Information Page  VOR Information Page  User Waypoint Information Page  Trip Planning Page  Nearest Pages

1. Use the FMS knob on the MFD to select Map - Navigation Map page. 2. On the MFD, press MENU. With Map Settings highlighted, press ENT on the MFD. Rotate the small MFD FMS knob to select the Aviation group and press the ENT key on MFD. 3. Turn the MFD large FMS Knob to scroll through the Aviation Group options to ‘SafeTaxi’. 4. Turn the MFD small FMS Knob to display the range of distances. 5. Turn the MFD FMS Knob to select 1.5nm as the distance for maximum SafeTaxi display range, and then press the MFD ENT key to complete the selection. 6. Using the MFD range knob, select a range of 1.5nm or less. Verify SafeTaxi display represents the current aircraft location and the airport layout. 7. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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8.6 DME Functional Check For DME Functional Check, refer to the G1000 Nav III Line Maintenance Manual.

8.7 ADF Functional Check For ADF Functional Check, refer to the G1000 Nav III Line Maintenance Manual.

8.8 GTS Traffic System Functional Check This section is applicable to the GTS 800 (TAS) traffic systems. Perform the following tests to verify GTS 800 operational and surveillance functions. Use a ramp tester such as a TIC TR220 or equivalent to perform the tests.

These tests are conducted at field elevation. Note that additional local traffic targets may appear and are not an indication of improper system operation.

Note: Due to running the test at field altitude, additional traffic targets may be present, and are not an indication of improper system operation. Note: When an IFR6000 ramp tester is used with a GTS 800, the IFR6000 must be configured for a distance that is 4 times the actual distance. For example, if the ramp tester is located 10 ft away from an aircraft, the IFR6000 should be configured as if it were 40 ft away from the aircraft. This will adjust the MTL setting of the IFR6000 such that it will see the GTS 800 low power interrogations and reply to the interrogations.

NOTE

The aural TA annunciations are muted if the height above terrain is below 400 feet.

Figure 8-1, Traffic Map

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Antenna Verification The following test assures the antennas and coaxial cables are properly connected. The GTS 800 must be in Ground Test mode. 1. On the Map – Traffic Map page of the MFD, press the TAS OPER softkey. A self-test of the antenna circuit is initialized. If the MFD displays FAILURE at the upper left corner of the traffic display area, it will be necessary to recheck the coaxial connections. If MFD displays OPERATE without indicating a fault, proceed to the next step of antenna verification. 2. Ensure that the transmitter or receiver (TX/RX) that you are testing is significantly closer to the ramp tester than another operating RX/TX, or erroneous and inaccurate results may occur. All four quadrants (0, 90, 180 and 270 degrees) will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the Map – Traffic Map page of the MFD. 3. Set up a stationary intruder by selecting the following on the ramp tester:  Intruder type: ATCRBS.  Intruder Start Distance: 2 nm  Intruder Start Altitude: 600 feet above field elevation  Vertical Speed: 0 fpm  Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario.) 4. Position ramp tester at 0 degrees. 5. Initiate the intruder scenario and verify a target is annunciated on the Map – Traffic Map page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co-altitude (read as +06 above a filled diamond indicating proximate traffic). 6. On the ramp tester, toggle intruder traffic to standby or off. 7. Reposition ramp tester and reengage the same intruder scenario for 90, 180 and 270 degrees. 8. Verify a target is annunciated on the Map – Traffic Map page of the MFD at the same bearing as the ramp tester. 9. If the bearing is not as anticipated or multiple targets are displayed during tests, verify the following:  Coax cable connectors are properly secured at the GA58 antennas and GTS unit.  Connections are made to the proper channels and color-coded heat shrink is the same color on both ends of coax cables  Connectors are correctly installed on coax cables 10. If no other service is to be performed, continue to the return-to-service checks in Section 9.

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Ramp Test The following test provides a scenario that will converge and intercept the GTS 800 to assure proper operational and surveillance functions.

1. On the Map – Traffic Map page of the MFD, press the TAS OPER softkey. 2. Position ramp tester at 90 degrees. 3. Select the following on the ramp tester:  Intruder type: ATCRBS.  Intruder Start Distance: 10 nm  Intruder Start Altitude: 600 ft above field elevation  Vertical Speed: 0 fpm  Velocity: 600 kts 4. Initiate the intruder scenario and observe the following:  Traffic should be acquired at approximately 10 NM at 90 degree bearing and co- altitude. Observe intruder closes on own aircraft at a rate of 0.1 NM/sec. Verify that only a single target is displayed in the expected quadrant.  The intruder should transition from Other Traffic (displayed as an open diamond with +06 displayed above), to proximate traffic (displayed as a filled white diamond with +06 displayed above), to a Traffic Advisory (TA) alarm (yellow filled circle with +06 displayed above.)

NOTE

The aural TA annunciations are muted if the height above terrain is below 400 feet.

If no other service is to be performed, continue to the return-to-service checks in Section 9.

8.9 Search and Rescue Functional Check (if installed) Refer to the G1000 Nav III Line Maintenance Manual for Search and Rescue Functional Check.

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9. G1000 System Return to Service Procedure If a G1000 LRU was replaced, verify the correct LRU software part numbers and versions against the numbers listed on the General Arrangement drawing listed in Table 1-1. Perform the following subsection tests to confirm the G1000 system is operating correctly.

9.1 Display Test Apply aircraft power. On the MFD power-up screen in the upper right corner, find the ‘Cessna XXX System XXXX.XX’ number, where XXX is the airframe type and XXXX-XX is the number of the G1000 System Software Loader Image version number that was used to install the software to the system. (182T image shown for reference, others are similar)

Figure 9-1, MFD Power Up Page

Verify that the System Software Version is the same as listed in Table 1 of the 005- 00620-22 General Arrangement Drawing. Press the MFD ENT key to acknowledge the ‘DEFAULT PROFILE’ Crew Profile option on the MFD (NOTE: The rightmost softkey may also be used).

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Figure 9-2, PFD Power-up System Annunciations

Allow the displays to initialize for approximately one minute. During normal operation, this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid during the first ~40-60 seconds of PFD power-up. After two minutes, verify no Red-X’s are present on the PFD and the MFD. Examples of potential Red-Xs are shown in Figure 9-2. If any Red-X’s are present, stop and troubleshoot per Section 5. Examples of a PFD with no Red-X failure indications are shown in Figure 9-3.

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(Without SVS enabled)

(With SVS enabled) Figure 9-3, PFD Normal Operation

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NOTE

Outputs from the GRS 77 or GSU 75 (AHRS portion) and GMU 44 are not valid until the units have been calibrated.

Check that all COM/NAV fields are valid in the top corners of the PFD. Check that altitude, airspeed, vertical speed, GS, TAS, and OAT fields are valid on PFD. Press the PFD Opt softkey on each PFD. Check that engine instrument fields are valid on the MFD. Verify that no MANIFEST alert messages appear in the lower right corner (press the flashing ALERTS softkey to view alert messages). If any MANIFEST errors appear, the correct software to the related LRU must be loaded before proceeding.

9.2 Display Failure Test

Step Desired Result

MFD Failure Condition: For an MFD failure condition, the following shall occur: 1. Open MFD CB.  MFD goes blank. 2. Verify desired results.  All PFD primary flight information is retained. 3. Close MFD CB.  The COM 1 and NAV 1 tuning fields remain valid and can be tuned by rotating the tuning knobs on PFD.  XPDR fields remain valid and XPDR can adjusted via PFD softkeys. PFD Display Failure Condition: For a PFD failure condition, the following shall occur: 1. Open PFD ESS BUS and PFD AVN BUS 1  PFD goes blank. circuit breakers.  MFD switches automatically to reversionary mode 2. Verify desired results. 3. Close PFD ESS BUS and PFD AVN BUS 1 circuit breakers.

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9.3 Reversion Mode Check Push the red DISPLAY BACKUP button on the GMA. Verify that the PFD and MFD displays enter reversion mode (See Figure 9-4). MFD should have valid altitude, airspeed, vertical speed, COM1, COM2, NAV1, NAV2 and engine instruments.

Figure 9-4, GDU Reversionary Mode De-activate reversion mode by pushing the DISPLAY BACKUP button. Verify PFD and MFD return to normal display modes.

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9.4 GPS Signal Acquisition This test requires the aircraft to be outside to see the GPS satellites or indoors with a GPS repeater.

Figure 9-5, AUX-GPS Status Page Select the AUX - GPS Status page on the MFD. After the G1000 system has been on for a minimum of two minutes, toggle between GPS 1 and GPS 2 using the two softkeys on the bottom of the display. Verify that both receivers show a 3D GPS Solution in the GPS Status field.

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9.5 GPS Failure Test Before starting this test, create a simple Direct-To flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position. Verify that the phase of flight displayed on the GPS CDI is ENR.

Step Desired Result

Single GPS Failure Condition: For each of the single GPS failure conditions, the following 1. Ensure GPS satellites are acquired. shall remain valid on the PFD throughout the procedure: 2. Place a shroud over the GPS antenna for GIA 1  Attitude and Heading from AHRS. to prevent signal reception. Verify loss of signal  Airspeed, Altitude, Vertical Speed, and OAT from Air on MFD Aux – GPS Status page. Data Computer. 3. Check for desired results.  GPS Course Deviation Indicator 4. Remove shroud from the GIA 1 GPS antenna and allow system to re-acquire satellites. 5. Place a shroud over the GPS antenna for GIA 2 to prevent signal reception. Verify loss of signal on MFD Aux – GPS Status page. 6. Check for desired results. 7. Remove shroud from the GIA 2 GPS antenna. Dual GPS Failure Condition: For a dual GPS failure condition, the following shall occur: 1. Ensure GPS satellites are acquired.  GPS CDI flags LOI on the PFD. 2. Cover both GPS antennas. Verify loss of signal  Attitude and Heading remain valid from both AHRS on Aux – GPS Status page. on the PFD. 3. Check for desired results.  Airspeed, Altitude, Vertical Speed and OAT remain 4. Remove shrouds from GPS antennas. valid from both Air Data Computers on the PFD. 5. Allow both receivers to re-acquire satellite  LOI appears on MFD Map. signals before continuing.  TAWS N/A aural alert & annunciation given. When GPS satellites are re-acquired, verify that the INTEG OK annunciation is given on the HSI in white for a brief period of time then disappears.

After ~10 seconds of stable GPS position reacquisition, verify the TAWS AVAILABLE aural alert is given.

Verify that the system returns to normal navigation mode (GPS CDI restored, LOI annunciation removed, & GPS data magenta).

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9.6 GIA Failure Test

Step Desired Result

GIA 1 Failure Condition: For a GIA 1 failure condition, the following shall occur: 1. Ensure GPS satellites are acquired.  NAV 1 and COMM1 tuning fields on PFD are invalid 2. Open NAV1/ENG (ESS BUS) and NAV1/ENG (red X). (AVN BUS 1) CBs.  Engine data remains valid 3. Verify desired results.  AHRS is using backup GPS source. 4. Close both NAV1/ENG CBs. Allow system to re-acquire satellites and return to normal  AHRS and ADC data remain valid on PFD. display modes.

GIA 2 Failure Condition: For a GIA 2 failure condition, the following shall occur: 1. Open NAV2 CB.  NAV2 and COMM2 tuning fields on PFD are invalid 2. Verify desired results. (red X). 3. Close NAV2 CB. Allow system to re-acquire  Engine data remains valid. satellites and return to normal display modes.  AHRS not receiving backup GPS Information.  AHRS and ADC data remain valid on PFD.

Dual GIA Failure Condition: For a dual GIA failure, the following shall occur: 1. Open NAV1/ENG (ESS BUS), NAV1/ENG  COM1/NAV1 & COM2/NAV2 fields flag invalid. (AVN BUS 1), and NAV 2 CBs.  GPS CDI flags LOI on PFD 2. Check for desired results.  NAV1 & NAV2 CDI loses deviation bar. 3. Restore power to both GIA units.  XPDR field flags invalid on PFD.  Engine Instrument field flags invalid on MFD.  All AHRS & ADC fields remain valid.  Red AFCS status annunciation given.  TAWS FAIL annunciation given.  ADF/DME windows flag invalid.*

*If equipped.

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9.7 GEA Functional Check Verify the MFD engine instruments are displayed and indicate valid readings. Reference figure below for normal EIS Display. Note: 182T model EIS strip is shown. Other models are similar. On GMA, select DISPLAY BACKUP button. Observe MFD in reversion mode and verify all engine instruments are displayed and indicate valid readings.

Normal EIS Display

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9.8 G1000 Backup Path Test With both displays in normal mode and the entire avionics system turned on, verify on PFD there is not a system alert message stating “Failed Data Path". If this message is present, troubleshoot per Section 0 and resolve the issue before continuing.

9.9 GFC 700 Autopilot Clutch Overpower Check The basic operation and checkout of the GFC 700 AFCS is not changed by this STC. Refer to the G1000 NAV III Line Maintenance Manual for specific procedures for the GFC 700 AFCS. Refer to Section 4.7 for the GSM 86 servo gearbox spring cartridge torque check.

NOTE The GFC 700 uses electronic torque limiting as well as mechanical clutches to limit the maximum servo effort. When the system is on the ground, the electronic torque limiting is removed, allowing manual checks of the clutch settings.

1. Move the flight controls through their full range motions. Check for any signs of binding or resistance. 2. Engage the Autopilot by pressing the AP key. 3. Manually overpower the autopilot clutches in pitch and roll. 4. Actuate and hold PITCH TRIM switch in either the NOSE UP or NOSE DOWN direction to disconnect the autopilot. While the trim is running, restrain the aircraft pitch trim wheel and verify that the trim clutch can be overpowered. 5. Verify that the trim wheel moves smoothly in both directions throughout the entire trim range during manual electric trim operation. If the trim wheel hesitates, this may indicate that the pitch trim servo gearbox clutch is slipping. Verify GSM 86 servo gearbox torque and cable tension. 6. If the autopilot servo cannot be overpowered during any of the preceding steps, check the GSM 86 servo gearbox torque per Section 4.7.

9.10 Maintenance Records Record the following information:  Part number of the G1000 software loader card used to perform software loading or software updates.  Record part and serial numbers of any LRU which was replaced.  Record any database updates which were performed during maintenance.  Any other applicable information related to the maintenance work performed on the aircraft.

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APPENDIX A - Garmin Unit Part and Serial Number Cross Reference This table allows shows the unit part number and serial number prefix combinations. SERIAL NUMBER FIRST LRU PART NUMBER THREE DIGITS GIA 63W (LEGACY) 011-01105-20 1HQ GIA 64W 011-03711-00 4SK GDU 1054B (PFD & MFD) 011-03470-70 494 GDU 1050 (PFD & MFD) (ONLY ON 172 011-03470-00 494 WITHOUT AUTOPILOT) GMA 1347 (LEGACY) 011-00809-00 471 GMA 1360 011-03568-00 4FQ GEA 71 (LEGACY) 011-00831-00 467 GEA 71B 011-03682-00 497 011-00882-00 478 GDC 74 (LEGACY) 011-00882-10 206 GRS 77 (LEGACY) 011-00868-10 420 011-00870-00 475 GMU 44 011-00870-10 1CM GSU 75 (OPTIONAL) 011-03094-00 3KY GTX 33 ES (LEGACY) 011-00779-30 891 or 848 GTX 335R (OPTIONAL) 011-03301-00 3EF GTX 345R (OPTIONAL) 011-03303-00 3EH GDL 69A (LEGACY) 011-00987-00 477 GDL 69 SXM (OPTIONAL) 011-03177-10 3NV GSA 81 PITCH SERVO (LEGACY) 011-00878-00 664 GSA 81 ROLL SERVO (LEGACY) 011-00878-00 664 GSA 81 PITCH TRIM SERVO (LEGACY) 011-00878-00 664 GSA 81 PITCH SERVO 011-00878-20 1A1 GSA 81 ROLL SERVO 011-00878-20 1A1 GSA 81 PITCH TRIM SERVO 011-00878-20 1A1 GTS 800 TAS (OPTIONAL) 011-01356-00 15L FLIGHT STREAM 510 (OPTIONAL) 011-03595-00 402 GSR 56 011-02286-01 2HU

G1000 Supplemental Maintenance Manual Page A-1 Textron Nav III Series Revision 4 190-02128-04 Part Information

GPN: 190-02128-04 Description: G1000NXiSMM Txtrn Av Inc NavIII Incl ICA for STC SA01830WI Part Type: Manuals / Printed Literature Lifecycle Phase: Experimental Rev: 4 ECO#179414

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Spec Item Attribution Report 1 of 1 Item: 190-02128-04 Rev:4 ECO#179414 Creation Date: 28-Sep-2018 07:55 AM CST