Garmin G600 Maintenance Manual

Maintenance Manual Contains Instructions for Continued Airworthiness for STC SA02571SE Aircraft make, model, registration number, and serial number along with the applicable STC configuration information must be completed in Appendix A and saved with aircraft permanent records.

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Rev. 1 Page viii DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES 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. For questions or additional information, refer to WWW.GARMIN.COM/PROP65. WARNING Perchlorate Material – special handling may apply. Refer to WWW.DTSC.CA.GOV/ HAZARDOUSWASTE/PERCHLORATE. WARNING Failure to properly configure the EIS gauges per the POH/AFM and other approved data could result in serious injury, damage to equipment, or death. CAUTION To avoid damage to the GDU 700( )/1060, take precautions to prevent Electrostatic Discharge (ESD) when handling the unit, connectors, and associated wiring. ESD damage can be prevented by touching an object of the same electrical potential as the unit before handling the unit itself. CAUTION THE GDU 700( )/1060 HAS A SPECIAL ANTI-REFLECTIVE COATED DISPLAY THAT IS SENSITIVE TO SKIN OILS, WAXES, AND ABRASIVE CLEANERS. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. CLEAN THE DISPLAY WITH A CLEAN, LINT-FREE CLOTH AND A CLEANER THAT IS SAFE FOR ANTI-REFLECTIVE COATINGS. CAUTION Do not store any G500/G600TXi component in or near water. WARNING Warnings indicate that injury or death is possible if the instructions are disregarded. CAUTION Cautions indicate that damage to the equipment is possible. NOTE Notes provide additional information.

Rev. 1 Page ix TABLE OF CONTENTS 1 INTRODUCTION ......................................................................................................... 1-1 1.1 Purpose ..........................................................................................................................................1-1 1.2 Scope .............................................................................................................................................1-1 1.3 Organization ..................................................................................................................................1-1 1.4 Applicability..................................................................................................................................1-1 1.5 Publications ...................................................................................................................................1-2 1.6 Revision and Distribution..............................................................................................................1-2 1.7 Terminology and Acronyms..........................................................................................................1-2 2 SYSTEM DESCRIPTION ............................................................................................ 2-1 2.1 System Overview...........................................................................................................................2-1 2.2 LRU Description, Control, and Operation.....................................................................................2-5 3 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................... 3-1 3.1 Airworthiness Limitations.............................................................................................................3-1 3.2 Servicing Information....................................................................................................................3-2 3.3 Maintenance Intervals....................................................................................................................3-2 3.4 Visual Inspection...........................................................................................................................3-4 3.5 Electrical Bonding Check..............................................................................................................3-4 3.6 RVSM Periodic Maintenance (Socata TBM 700/850 Only).........................................................3-5 3.7 Overhaul Period.............................................................................................................................3-6 3.8 Special Inspection Requirements...................................................................................................3-6 3.9 Application of Protective Treatments............................................................................................3-6 3.10 Data Relative to Structural Fasteners ............................................................................................3-7 3.11 Additional Instructions ..................................................................................................................3-7 4 TROUBLESHOOTING ................................................................................................ 4-1 4.1 General System Troubleshooting ..................................................................................................4-1 4.2 Connector Information ..................................................................................................................4-2 4.3 Troubleshooting Flow Charts......................................................................................................4-22 5 EQUIPMENT MAINTENANCE AND CHECKOUT PROCEDURES................... 5-1 5.1 GDU 1060/700 ..............................................................................................................................5-3 5.2 GCU 485......................................................................................................................................5-10 5.3 EIS Annunciator ..........................................................................................................................5-12 5.4 GDC 72........................................................................................................................................5-14 5.5 GSU 75(), GRS 79.......................................................................................................................5-16 5.6 GAD 43/43e.................................................................................................................................5-18 5.7 GEA 110......................................................................................................................................5-20 5.8 GBB 54........................................................................................................................................5-23 5.9 GMU 44.......................................................................................................................................5-25 5.10 GTP 59.........................................................................................................................................5-28 5.11 Backup GPS Antenna..................................................................................................................5-29 5.12 EIS Sensors..................................................................................................................................5-31 5.13 Calibration ...................................................................................................................................5-39 5.14 Uploading Software.....................................................................................................................5-41 5.15 System Checks.............................................................................................................................5-41 APPENDIX A INSTALLATION SPECIFIC INFORMATION.......................................... A-1 A.1 General Information .....................................................................................................................A-1 A.2 LRU Information..........................................................................................................................A-2 A.3 Equipment Location .....................................................................................................................A-3 A.4 Wire Routing - Single Engine ......................................................................................................A-4

Rev. 1 Page x TABLE OF CONTENTS CONTINUED A.5 Wire Routing - Twin Engine ........................................................................................................A-5 A.6 Saved Configuration File..............................................................................................................A-6 A.7 Print Configuration Log................................................................................................................A-6 A.8 GDU 1060 EIS Gauge Layout Template......................................................................................A-7 A.9 GDU 700P EIS Gauge Layout Template .....................................................................................A-8 A.10 GDU 700L EIS Gauge Layout Template .....................................................................................A-9

Rev. 1 Page xi LIST OF FIGURES Figure 2-1 Entering the configuration mode on the GDU.....................................................................2-3 Figure 2-2 GDU 700P MFD, PFD or EIS Display Configuration ........................................................2-5 Figure 2-3 GDU 700P Features and Controls .......................................................................................2-6 Figure 2-4 The GDU 700L EIS unit......................................................................................................2-7 Figure 2-5 GDU 700L Features and Controls .......................................................................................2-8 Figure 2-6 The GDU 1060 functioning as an MFD/PFD and MFD/PFD/EIS......................................2-8 Figure 2-7 GDU 1060 Features and Controls........................................................................................2-9 Figure 2-8 GCU 485 (P/N 011-03582-01 Shown) ..............................................................................2-10 Figure 2-9 Garmin Backup GPS Antenna...........................................................................................2-10 Figure 2-10 GSU 75() ADAHRS Unit ..................................................................................................2-11 Figure 2-11 GRS 79 AHRS Unit...........................................................................................................2-11 Figure 2-12 GDC 72 ADC Unit ............................................................................................................2-12 Figure 2-13 GMU 44 Magnetometer.....................................................................................................2-12 Figure 2-14 GTP 59 Outside Air Temperature Probe ...........................................................................2-13 Figure 2-15 GBB 54 Backup Battery ....................................................................................................2-13 Figure 2-16 GEA 110 Engine Interface.................................................................................................2-14 Figure 2-17 GAD 43 (Left) and GAD 43e (Right)................................................................................2-15 Figure 2-18 Engine Annunciator...........................................................................................................2-16 Figure 2-19 Carburetor Temperature Probe ..........................................................................................2-16 Figure 2-20 Oil Temperature Probe ......................................................................................................2-16 Figure 2-21 Fuel Flow Sensor FT-60 (Left) and FT-90 (Right) ...........................................................2-17 Figure 2-22 Brass Pressure Sensor........................................................................................................2-17 Figure 2-23 Stainless Steel Pressure Sensor..........................................................................................2-17 Figure 4-1 62 pin D-sub connectors numbering scheme for female/male contacts ..............................4-2 Figure 4-2 GDU 700P Connectors ........................................................................................................4-3 Figure 4-3 GCU 485 Connector ............................................................................................................4-7 Figure 4-4 View of J721 Connector looking at GDC 72.......................................................................4-8 Figure 4-5 View of J751 Connector looking at GSU 75() ..................................................................4-10 Figure 4-6 View of J791 Connector looking at GRS 79 .....................................................................4-12 Figure 4-7 GAD 43/43e J431/P431 connector looking at unit............................................................4-14 Figure 4-8 GAD 43e J432/P432 Connector looking at unit................................................................4-15 Figure 4-9 GAD 43e J433/P433 Connector looking at unit................................................................4-16 Figure 4-10 GEA 110 Connectors.........................................................................................................4-17 Figure 4-11 GEA 110 J1101/P1101 Connector looking at unit ............................................................4-17 Figure 4-12 GEA 110 J1102/P1102 Connector looking at unit ............................................................4-18 Figure 4-13 GBB 54 J541/P541 Connector...........................................................................................4-20 Figure 4-14 GDU Alert Message Troubleshooting...............................................................................4-23 Figure 4-15 GDU Config and Battery Alert Message Troubleshooting ...............................................4-24 Figure 4-16 PFD Alert Message Troubleshooting ................................................................................4-25 Figure 4-17 AHRS/ADC Alert Message Troubleshooting ...................................................................4-26 Figure 4-18 Terrain Alert Message Troubleshooting............................................................................4-27 Figure 4-19 Traffic Alert Message Troubleshooting.............................................................................4-28 Figure 4-20 Audio/Weather Alert Message Troubleshooting...............................................................4-29 Figure 4-21 External LRU Failure Message Troubleshooting..............................................................4-30 Figure 4-22 External LRU Service Message Troubleshooting .............................................................4-31 Figure 4-23 GAD Fault Message Troubleshooting...............................................................................4-32 Figure 4-24 GAD Fault Message Troubleshooting Continued .............................................................4-33 Figure 4-25 EIS Gauge Troubleshooting ..............................................................................................4-34

Rev. 1 Page xii LIST OF FIGURES CONTINUED Figure 5-1 GDU 1060 Installation.........................................................................................................5-3 Figure 5-2 GDU 700P Installation ........................................................................................................5-4 Figure 5-3 Integrated ADC Module Installation ...................................................................................5-6 Figure 5-4 Configuration Module Installation ......................................................................................5-8 Figure 5-5 GCU 485 Installation.........................................................................................................5-10 Figure 5-6 Panel Cutout for GCU 485 ................................................................................................5-11 Figure 5-7 EIS Caution and Warning Annunciator Installation..........................................................5-12 Figure 5-8 GDC 72 Installation (Sheet Metal Shelf Example) ...........................................................5-14 Figure 5-9 GSU 75() Installation (Sheet Metal Shelf Example) .........................................................5-16 Figure 5-10 GAD 43 Installation (Sheet Metal Shelf Example) ...........................................................5-18 Figure 5-11 GEA 110 Installation (Mounted Directly to Airframe Example)......................................5-20 Figure 5-12 GEA 110 Installation (Mounted on a Tray Example) .......................................................5-21 Figure 5-13 GBB 54 Installation (Sheet Metal Shelf Example)............................................................5-23 Figure 5-14 GBB 54 Battery Cell Replacement....................................................................................5-25 Figure 5-15 GMU 44 Installation (Universal Mount Example)............................................................5-27 Figure 5-16 GTP 59 Installation (Aircraft with Metallic Skin Example) .............................................5-28 Figure 5-17 Backup GPS Antenna Installation (Non-removable Installation Example) ......................5-29 Figure 5-18 Backup GPS Antenna Installation (Removable Installation Example) .............................5-30 Figure 5-19 Carburetor Temperature Sensor Installation Example ......................................................5-32 Figure 5-20 Oil Temperature Sensor Installation Example...................................................................5-33 Figure 5-21 Brass Sensor Installation, Coupling Mount Example........................................................5-35 Figure 5-22 Stainless Steel Sensor Installation, Housing Mount Example...........................................5-36 Figure 5-23 Fuel Flow Transducer Installation.....................................................................................5-38 Figure 5-24 Airspeed Configuration Type ............................................................................................5-43 Figure A-1 GDU 1060 EIS Gauge Template ........................................................................................A-7 Figure A-2 GDU 700P EIS Gauge Layout Template............................................................................A-8 Figure A-3 GDU 700L EIS Gauge Layout Template ...........................................................................A-9

Rev. 1 Page xiii LIST OF TABLES Table 1-1 Reference Documentation ...................................................................................................1-2 Table 2-1 AML STC Installed Sensors................................................................................................2-2 Table 2-2 G500/600 TXi LRU Electrical Load ...................................................................................2-5 Table 3-1 Periodic Maintenance ..........................................................................................................3-2 Table 3-2 Electrical bonding requirements..........................................................................................3-5 Table 4-1 G500/G600 TXi Failures .....................................................................................................4-1 Table 5-1 Pressure Sensor Equipment List ........................................................................................5-34 Table 5-2 LRU Status Indicators........................................................................................................5-42 Table 5-3 Airspeed Test Points..........................................................................................................5-44 Table 5-4 Advanced Airframe Specific Configuration Data – Arc Ranges.......................................5-46 Table 5-5 Advanced Airframe Specific Configuration Data – Markings..........................................5-48 Table 5-6 Air Data Test Points...........................................................................................................5-50 Table 5-7 Altitude Hold Check Log...................................................................................................5-52

Rev. 1 Page 1-1 1 INTRODUCTION 1.1 Purpose..............................................................................................................................................1-1 1.2 Scope.................................................................................................................................................1-1 1.3 Organizaton.......................................................................................................................................1-1 1.4 Applicability .....................................................................................................................................1-1 1.5 Publications.......................................................................................................................................1-2 1.6 Revision and Distribution.................................................................................................................1-2 1.7 Terminology and Acronyms .............................................................................................................1-2 1.7.1 Terminology...............................................................................................................................1-2 1.7.2 Acronyms ...................................................................................................................................1-3 1.1 Purpose This document is designed for use by the installing agency of the Garmin G500/G600 TXi PFD/MFD/EIS System as a Maintenance Manual and ICA in response to FAR Part 23.1529, and Part 23 Appendix G. This ICA includes information required by the operator to adequately maintain the Garmin G500/G600 TXi system installed under AML STC. 1.2 Scope This document provides Maintenance instructions and identifies the Instruction for Continued Airworthiness for the modification of the aircraft for installation of the Garmin G500/G600 TXi PFD/MFD/ EIS System installed under AML STC. 1.3 Organization The following outline briefly describes the organization of this manual Section 2.1: System Overview Provides a description of the G500/G600 TXi System equipment installed by this STC. Section 2.2: LRU Description, Control, and Operation Provides basic control and operation information specifically tailored to maintenance practices. Section 3: Instructions for Continued Airworthiness Provides instructions for continued airworthiness of the G500/G600 TXi System LRUs. Section 4: Troubleshooting Provides troubleshooting information including connector information, pinouts and flowcharts to aid in diagnosing and resolving problems with G500/G600 TXi system equipment. Section 5: Equipment Maintenance and Checkout Procedures Provides instructions for the removal and replacement of G500/G600 TXi System LRUs including system checkout procedures. Appendix A: Installation Specific Information Provides a template to record aircraft specific installation and configuration data for the G500/G600 TXi System. 1.4 Applicability This document applies to all aircraft with the G500/G600 TXi system installed in accordance with AML STC SA02571SE. Modification of an aircraft by this STC obligates the aircraft operator to include the maintenance information provided by this document in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program.

Rev. 1 Page 1-2 1.5 Publications In addition to this manual, the following documents are recommended for performing maintenance on the G500/G600 TXi system. It is the responsibility of the owner/operator to ensure the latest applicable versions of these documents are used during operation, servicing, or maintenance of the G500/G600 TXi system. 1.6 Revision and Distribution This document is required for maintaining the continued airworthiness of the aircraft. Garmin Dealers may obtain the latest revision of this document at the Garmin Dealer Resource Center, website. Dealers are notified of manual revision changes via a Garmin Service Bulletin posted to the Dealer Resource Center. Owner and operators may obtain the latest revision of this document at www.flyGarmin.com or by contacting a Garmin dealer. Garmin contact information is available at www.flyGarmin.com. 1.7 Terminology and Acronyms 1.7.1 Terminology Except where specifically noted, references made to the “GDU 1060/700” will apply to the GDU 1060, GDU 700P, and GDU 700L equally. Except where specifically noted, references made to the “G500/G600 TXi system” will apply to an installed system with one or more GDU 1060 or GDU 700 and all LRUs interfaced to the GDU. Except where specifically noted, references made to Garmin products with a “()” designation after the model number refer to all sub-models in that series. (i.e., a reference to GDU 700() refers to both the GDU 700P and the GDU 700L variants). Throughout this document references will be made to metallic aircraft. For the purposes of this manual, metallic aircraft will be those with an aluminum skin. Nonmetallic aircraft refers to all other aircraft (e.g., wooden aircraft, aircraft with composite skin, or aircraft with tube and fabric construction). Unless otherwise stated, all units of measure are US standard units. Table 1-1 Reference Documentation Document Garmin P/N Equipment List, G500,G600 TXi Part 23 AML STC 005-00795-D1 AFMS, G500/G600 TXi Part 23 AML STC 190-01717-B2 G500/G600 TXi Part 23 AML STC Installation Manual 190-01717-B3

Rev. 1 Page 1-3 1.7.2 Acronyms The following terminology is used within this document. AC: Alternating Current ICA: Instructions for Continued Airworthiness ADAHRS: Air Data Attitude Heading Reference System ILS: Instrument Landing System ADC: Air Data Computer LCD: Liquid Crystal Display ADF: Automatic Direction Finder LOC: Localizer ADS-B: Automatic Dependent Surveillance Broadcast LRU: Line Replaceable Unit AFMS: Aircraft Flight Manual Supplement MFD: Multi-Function Display AHRS: Altitude and Heading Reference System NPT: National Pipe Taper AML: Approved Model List OAT: Outside Air Temperature A/P: Autopilot ODA: Organization Designation Authorization ASI: Airspeed Indicator PFD: Primary Flight Display BIT: Built-In Test POH: Pilots Operating Handbook CFR: Code of Federal Regulations PPS: Pulse Per Second CHT: Cylinder Head Temperature RNAV: Area Navigation DC: Direct Current RPM: Revolutions Per Minute DME: Distance Measuring Equipment RVSM: Reduced Vertical Separation Minimum EGT: Exhaust Gas Temperature SBAS: Satellite Based Augmentation System EIS: Engine Indicating System SD: Secure Digital ES: Extended Squitter SDI: Source/Destination Identifiers FAA: Federal Aviation Administration STC: Supplemental Type Certificate FAR: Federal Aviation Regulation TAS: Traffic Advisory System FD: Flight Director TAWS: Terrain Awareness System FIS-B: Flight Information Services Broadcast SSM: Sign/Status Matrix GAD: Garmin Interface Adapter TCAS: Traffic Collision Avoidance System GBB: Garmin Backup Battery TCAD: Traffic Collision Avoidance Device GCU: Garmin Control Unit TIS: Traffic Information Service GDC: Garmin Data Computer TSO: Technical Standard Order GDU: Garmin Display Unit UAT: Universal Access Transceiver GEA: Garmin Engine Adapter UTC: Coordinated Universal Time GMU: Garmin Magnetometer Unit VOR: VHF Omni-Directional Range GPS: Global Position System WAAS: Wide Area Augmentation System GSR: Garmin Services WXR: Weather Radar GRS Garmin Reference System GTP: Garmin Temperature Probe GWX: Garmin Weather Radar HSI: Horizontal Situation Indicator IAS: Indicated Air Speed

Rev. 1 Page 2-1 2 SYSTEM DESCRIPTION 2.1 System Overview..............................................................................................................................2-1 2.1.1 PFD Functionality ......................................................................................................................2-1 2.1.2 MFD Functionality.....................................................................................................................2-2 2.1.3 EIS Functionality........................................................................................................................2-2 2.1.4 Entering Configuration Mode ....................................................................................................2-3 2.1.5 SD Card Location Options .........................................................................................................2-3 2.1.6 Save/Load SD.............................................................................................................................2-4 2.1.7 Electrical Load Information .......................................................................................................2-5 2.2 LRU Description, Control, and Operation........................................................................................2-5 2.2.1 GDU 700P Display.....................................................................................................................2-5 2.2.2 GDU 700L Display ....................................................................................................................2-7 2.2.3 GDU 1060 Display.....................................................................................................................2-8 2.2.4 GCU 485 Control Unit ...............................................................................................................2-9 2.2.5 Backup GPS Antenna...............................................................................................................2-10 2.2.6 Integrated ADAHRS Unit ........................................................................................................2-10 2.2.7 GSU 75() ADAHRS Unit.........................................................................................................2-11 2.2.8 GRS 79 AHRS Unit .................................................................................................................2-11 2.2.9 GDC 72 ADC Unit...................................................................................................................2-12 2.2.10 GMU 44 Magnetometer ...........................................................................................................2-12 2.2.11 GTP 59 OAT Probe..................................................................................................................2-13 2.2.12 GBB 54 Backup Battery...........................................................................................................2-13 2.2.13 GEA 110 Engine Interface .......................................................................................................2-14 2.2.14 GAD 43/43e Adapter ...............................................................................................................2-15 2.2.15 EIS Components.......................................................................................................................2-16 2.1 System Overview The G500/G600 TXi installation can provide PFD, MFD, and EIS functions. Three display models, the GDU 700P, GDU 700L, and GDU 1060 are used to convey the information. The G500/G600 TXi system utilizes engine sensors and the GEA 110 engine adapter to provide EIS functions. 2.1.1 PFD Functionality The PFD provides attitude, heading, airspeed, altitude and vertical speed. Optional features such as Synthetic Vision, autopilot control and annunciation, HSI map overlays, and more can also be provided by the PFD. The minimum PFD installation consists of: • GDU 700P or GDU 1060 display • ADAHRS Capability (must have one of the following): ◦ GRS 77 AHRS and GDC 74() ADC ◦ GRS 79 AHRS and GDC 72() ADC ◦ GSU 75() ADAHRS ◦ Internal ADAHRS (Part of the GDU) • GMU 44 magnetometer • GTP 59 temperature probe • External WAAS GPS navigation source

Rev. 1 Page 2-2 2.1.2 MFD Functionality The multifunction flight display provides at a minimum a moving map display. The display can optionally provide traffic, terrain, audio, and weather functions depending on installed equipment. In addition, the MFD can be used as an integrated standby PFD when installed in accordance with the integrated standby configuration described in the G500/G600 TXi Part 23 AML STC Installation Manual (P/N:190-01717- B3). The MFD minimum system installation consists of: • GDU 700P or GDU 1060 display • External WAAS GPS navigation source 2.1.3 EIS Functionality The EIS is an optional feature for single and twin engine reciprocating engine equipped aircraft. The EIS will display 4 and 6 cylinder engine data and select airframe parameters. The EIS can display engine and airframe operating parameters on the GDU. The EIS gauges include optional gauges and those required by the aircraft POH and manufacturer. This manual only provides information for the EIS sensors installed per the G500/G600 TXi AML STC. Table 2-1 lists the sensors that are maintained in this manual. Refer to the applicable maintenance data and/ or TSO manual for other sensors that are interfaced to the EIS. Table 2-1 AML STC Installed Sensors Function Manufacturer P/N Garmin P/N Oil Press Garmin 150 PSIG pressure, (Brass) 011-04202-30 Kulite APT-20GX-1000-150G (Stainless) 494-30032-00 Oil Temp UMA T3B3-2.5G 494-70009-00 Manifold Press Garmin 30 PSIA Press, (Brass) 011-04202-00 Kulite APT-20GX-1000-25A 494-30030-00 Fuel Press Garmin 75 PSIG Press, (Brass) 011-04202-20 Garmin 15 PSIG Press, (Brass) 011-04202-10 Kulite APT-20GX-1000-50G 494-30031-00 Kulite APT-20GX-1000-15G 494-30029-00 Fuel Flow EI FT-60 494-10001-00 EI FT-90 494-10001-01 RPM N/A (Magneto P-lead) N/A Carb Air Temp UMA T3B10-SG 494-70010-00

Rev. 1 Page 2-3 2.1.4 Entering Configuration Mode The configuration mode of the GDU 1060/700 can be accessed by holding down the inner knob located at the bottom right of the unit as shown in Figure 2-1 upon initial power up. The knob must be pressed until the splash screen shown in Figure 2-1 disappears and the configuration menu appears. Figure 2-1 Entering the configuration mode on the GDU 2.1.5 SD Card Location Options The GDU 1060/700 has two SD card slots that can be used for various tasks. The following list describes what tasks can be performed from which SD card slot: • Either Slot ◦ Installer Unlock ◦ Feature Enablement ◦ Screenshots (If a card is present in both slots the screenshot will print to the top slot only) ◦ Update databases • Top/Left Slot Only ◦ Software updates ◦ GSU/GRS Log Downloads ◦ Flight Log Download ◦ Save configuration to SD card ◦ Save error log to SD card ◦ Load configuration from SD card • Bottom/Right Slot ◦ Update Databases (faster)

Rev. 1 Page 2-4 2.1.6 Save/Load SD The aircraft configuration settings can be saved to an SD card as well as loaded from an SD card using the following procedures. To save your aircraft configuration settings to an SD card: 1. Insert an SD card into the Top/Left slot of any GDU 1060/700 in the system 2. Power on all GDUs in the G500/G600 TXi system in configuration mode 3. From the Home screen, select SD save 4. Enter the name you would like the configuration saved as 5. Select Enter To load your aircraft configuration settings from an SD card: NOTE Loading the system configuration from an SD card will overwrite the current system configuration and is not reversible. It is recommended to always save your current configuration to the SD card first before loading a new configuration. 1. Insert an SD card into the Top/Left slot of any GDU 1060/700 in the system 2. Power on all GDUs in the G500/G600 TXi system in configuration mode 3. Ensure you have set the GDU ID’s, SYS ID Source, and feature enablements before continuing 4. From the Home screen, select SD load 5. Select the Aircraft Configuration File you want to load 6. Select the To GDU to which you want to load configuration settings NOTE Information not contained in the selected Aircraft Configuration File will be grayed out and cannot be selected. 7. Select the check box next to the configuration to be loaded 8. Select SD Load 9. Verify the loaded configuration(s) are identical to those recorded in the aircraft’s permanent records. 10. Perform Configuration Ground Check in Section 5.15.1. If any interfaces have a yellow triangle present on the system summary after loading a configuration from the SD card, verify the interface settings match the configuration settings stored with the permanent aircraft records. If the settings do not match, the configuration must be corrected by a Garmin dealer.

Rev. 1 Page 2-5 2.1.7 Electrical Load Information Electrical load information for the G500/G600 Txi system LRU’s is provided below. Appendix A of this document contains details specific to the load changes for the specific aircraft installation. Table 2-2 G500/600 TXi LRU Electrical Load 2.2 LRU Description, Control, and Operation 2.2.1 GDU 700P Display The GDU 700P is a 7 inch LCD portrait-oriented panel mount control and display unit. The GDU 700P can be configured as a PFD, MFD, or EIS display. The GDU 700P is available with or without an integrated ADAHRS. The GDU 700P requires a compatible GPS/SBAS navigator for MFD and PFD functionality. Figure 2-2 GDU 700P MFD, PFD or EIS Display Configuration LRU 14 Volt Current Draw 28 Volt Current Draw Typical Maximum Typical Maximum GDU 700( ) 3.0 A 6.0 A 1.5 A 3.0 A GDU 1060 5.0 A 8.0 A 2.5 A 4.0 A GRS 79/GMU 44 480 mA 958 mA 240 mA 479 mA GRS 77/GMU 44 600 mA 1 A 300 mA 1 A GSU 75( )/GMU 44/GTP 59 760 mA 958 mA 380 mA 479 mA GDC 72/GTP 59 420 mA 958 mA 210 mA 479 mA GDC 74( )/GTP 59 410 mA 480 mA 200 mA 235 mA GAD 43 410 mA 720 mA 210 mA 350 mA GAD 43e 790 mA 1.22 A 390 mA 590 mA GCU 485 120 mA 357 mA 64 mA 179 mA GEA 110 0.30 A 0.60 A 0.15 A 0.30 A

Rev. 1 Page 2-6 The GDU 700P has numerous features and controls as shown in Figure 2-3. These features and controls are: • Power Button - Pressing and releasing the power button with the unit powered on will cause a dialog box to appear that allows the display to be powered off or under certain circumstances switched to a backup display layout. Pressing and holding the button for 5 seconds will power off the display with no further prompt. • Photocell - The photocell may be configured to be used by the display to automatically adjust the display back-lighting in reference to ambient light conditions. • Top Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more information on SD card options. • Bottom Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more information on SD card options. • Dual Concentric Knobs - Control knobs that can be used to scroll and select through various options on the display. The outer knob is used to scroll through available screens on the PFD or MFD. Pressing the knob acts as an enter or selection of the currently highlighted information. Figure 2-3 GDU 700P Features and Controls Power Button Photocell Top Card Slot Bottom Card Slot Dual Concentric Knob

Rev. 1 Page 2-7 2.2.2 GDU 700L Display The GDU 700L is a 7 inch LCD landscape-oriented panel mount control and display unit. Figure 2-4 The GDU 700L EIS unit The GDU 700L has numerous features and controls as shown in Figure 2-5. These features and controls are: • Power Button - Pressing and releasing the power button with the unit powered on will cause a dialog box to appear that allows the display to be powered off or under certain circumstances switched to a backup display layout. Pressing and holding the button for 5 seconds will power off the display with no further prompt. • Photocell - The photocell may be configured to be used by the display to automatically adjust the display back-lighting in reference to ambient light conditions. • Left Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more information on SD card options. • Right Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more information on SD card options. • Dual Concentric Knobs - Control knobs that can be used to scroll and select through various options on the display. Pressing the knob acts as an enter or selection of the currently highlighted information.

Rev. 1 Page 2-8 Figure 2-5 GDU 700L Features and Controls 2.2.3 GDU 1060 Display The GDU 1060 is a 10.6” LCD panel mount control and display unit capable of displaying PFD and MFD data with optional EIS display. The GDU 1060 may be optionally equipped with an integrated ADAHRS or must be interfaced to an external ADC/AHRS LRU. Shown below is a combined PFD/MFD/EIS display. The GDU 1060 requires interface with a compatible GPS/SBAS navigator. Figure 2-6 The GDU 1060 functioning as an MFD/PFD and MFD/PFD/EIS Power Key Photocell Left Card Slot Right Card Slot Dual Concentric Knob

Rev. 1 Page 2-9 The GDU 1060 has numerous features and controls as shown in Figure 2-7. These features and controls are: • Power Button - Pressing and releasing the power button with the unit powered on will cause a dialog box to appear that allows the display to be powered off or under certain circumstances switched to a backup display layout. Pressing and holding the button for 5 seconds will power off the display with no further prompt. • Photocell - The photocell may be configured to be used by the display to automatically adjust the display back-lighting in reference to ambient light conditions. • Top Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more information on SD card options. • Bottom Card Slot - A Card slot in the display that accepts standard SD cards. See Section 2.1.5 for more information on SD card options. • Dual Concentric Knobs - Control knobs that can be used to scroll and select through various options on the display. Figure 2-7 GDU 1060 Features and Controls 2.2.4 GCU 485 Control Unit The GCU 485 is a panel mount remote control unit that provides an alternate method of controlling the G500/G600 TXi PFD display parameters. The GCU 485 Control Unit is available in variations containing different numbers of buttons. All variations contain three knobs in the same configuration as shown below. Power Key Photocell Top Card Slot Bottom Card Slot Right Dual Concentric Knob Left Dual Concentric Knob

Rev. 1 Page 2-10 The GCU 485 installation is optional. Figure 2-8 GCU 485 (P/N 011-03582-01 Shown) 2.2.5 Backup GPS Antenna GDU 1060 and GDU 700 PFD and MFD displays have an optional backup GPS. If a backup GPS antenna is installed, the backup GPS is automatically used when the primary GPS source is lost. The backup GPS antenna is located on the instrument panel glare shield. Figure 2-9 Garmin Backup GPS Antenna 2.2.6 Integrated ADAHRS Unit The GDU 1060/700P has an optional integrated ADAHRS unit that provides flight altitude, vertical speed, airspeed, attitude, OAT, and heading data for flight instrumentation. The AHRS portion is contained internally within the GDU 1060/700P. An Integrated ADC module is then plugged in to the AHRS board and attached to the back of the GDU 1060/700P. The internal ADAHRS receives data from the GMU 44 and GTP 56 that are connected to the GDU 1060/700P. The integrated ADAHRS utilizes GPS signals sent from the GPS/SBAS navigator. Attitude, heading, and air data can be sent using ARINC 429 digital signals to external LRUs and the GAD43/43e.

Rev. 1 Page 2-11 2.2.7 GSU 75() ADAHRS Unit The GSU 75/75B ADAHRS is a remote LRU that provides flight altitude, vertical speed, airspeed, attitude, OAT, and heading data for flight instrumentation. The GSU 75 / 75B receives data from the GMU 44 magnetometer and GTP 59 OAT probe. The GSU 75 / 75B utilizes GPS signals sent from the GPS/SBAS navigator. Attitude, heading, and air data is sent using ARINC 429 digital signals to the GDU 1060/700P and GAD 43/43e. An RS-232 digital connection is used for maintenance and configuration information. The GSU 75B is configured through the GDU 1060/700P using a feature unlock card that contains airframe specific air data corrections suitable for RVSM functionality in select applications. Figure 2-10 GSU 75() ADAHRS Unit 2.2.8 GRS 79 AHRS Unit The GSU 79 AHRS is a remote LRU that provides attitude and heading data for flight instrumentation. The GSU 79 receives data from the GMU 44 magnetometer. The GSU 79 utilizes GPS signals sent from the GPS/SBAS navigator. Attitude and heading data is sent using ARINC 429 digital signals to the GDU 1060/ 700P and GAD 43/43e. An RS-232 digital connection is used for maintenance and configuration information. Figure 2-11 GRS 79 AHRS Unit

Rev. 1 Page 2-12 2.2.9 GDC 72 ADC Unit The GDC 72 Air Data Computer receives information from the existing aircraft Pitot-Static system and the GTP 59 OAT probe. The GDC 72 provides pressure altitude, airspeed, vertical speed, and OAT data to the G500/G600 TXi system. The GDC 72 provides data to the G500/G600 TXi using ARINC 429 digital interfaces, as well as RS-232 for maintenance and configuration information. Figure 2-12 GDC 72 ADC Unit 2.2.10 GMU 44 Magnetometer The GMU 44 magnetometer senses magnetic field information and sends the data to the GSU 75/75B, integrated ADAHRS, or GRS 77/79 AHRS to determine aircraft magnetic heading. This unit receives power directly from the AHRS source and communicates with the AHRS using an RS-485 digital interface. Figure 2-13 GMU 44 Magnetometer

Rev. 1 Page 2-13 2.2.11 GTP 59 OAT Probe The GTP 59 is a remote-mount temperature probe that interfaces to the ADC for OAT display and true airspeed computations. The GTP 59 is mounted externally on the aircraft, usually near or inside air inlet ducts, the underside of wing access panels, or on the empennage below the horizontal stabilizer. Figure 2-14 GTP 59 Outside Air Temperature Probe 2.2.12 GBB 54 Backup Battery The GBB 54 supplies power to the GDU 700P, internal ADAHRS, essential EIS sensors, and a single GEA 110 in the event of total electrical power loss. Figure 2-15 GBB 54 Backup Battery

Rev. 1 Page 2-14 2.2.13 GEA 110 Engine Interface The GEA 110 is a remote-mount engine interfacing and monitoring module used for gathering sensor input parameters from the engine and processing the signals for the G500/G600 TXi system. The GEA 110 can be mounted to the back assembly of the GDU 1060 or it can be remotely mounted in the fuselage or in the engine compartment. The GEA 110 communicates with the G500/G600 TXi using an RS-485 digital interface. Figure 2-16 GEA 110 Engine Interface

Rev. 1 Page 2-15 2.2.14 GAD 43/43e Adapter The GAD 43 adapter is an optional adapter that provides attitude, heading, and yaw input information for third-party autopilot systems. It also provides a synchro heading output that can be used to provide synchro heading to other systems. The GAD 43/43e can provide the following information in analog format: • Pitch and roll for the autopilot (synchro) • Pitch and roll for weather radar stabilization (50 and 200 mV/degree) • Heading (synchro) • Yaw rate (100, 200, 333 and 600 mV/degree/sec) OR • The GAD 43/43e can provide an analog baro-correction output like the Honeywell KEA 130/130A and KEA 346 (P/N 006-0362-0008 through -0011 only) encoding altimeters. With the GDU 1060/700 in configuration mode, the GAD 43/43e also allows the installer to set the analog attitude and heading outputs to specific values without the need for removing any gyros and using a tilt table. The GAD 43e provides all of the functions of the GAD 43. In addition, it allows the G500/G600 TXi to receive data from marker beacon receivers, synchro (ARINC 407) ADF receivers, DME systems, and analog radar altimeters. It also allows the G500/G600 TXi to provide altitude preselect and vertical speed control to compatible autopilots. Figure 2-17 GAD 43 (Left) and GAD 43e (Right)

Rev. 1 Page 2-16 2.2.15 EIS Components 2.2.15.1 Engine Annunciator An engine annunciator will only be installed if the EIS display is not installed within 8 inches of the center of the pilots field of view. Figure 2-18 Engine Annunciator 2.2.15.2 Carburetor Temperature Probe The carburetor temperature probe is a Type-K thermocouple (Chromel and Alumel) probe. Figure 2-19 Carburetor Temperature Probe 2.2.15.3 Oil Temperature Probe The oil temperature probe is a Type-K thermocouple (Chromel and Alumel) probe. Figure 2-20 Oil Temperature Probe

Rev. 1 Page 2-17 2.2.15.4 Fuel Flow Sensors The fuel flow sensor is incorporated in an aluminum housing that is installed in-line to the engine fuel supply. There are two STC approved options available for installation to suit most aircraft applications. Figure 2-21 Fuel Flow Sensor FT-60 (Left) and FT-90 (Right) 2.2.15.5 Brass Pressure Sensors The brass pressure sensors are small sensors that are supplied with a compatible plug. Depending on the installation these sensors may be used to measure oil, fuel, and manifold pressure. Figure 2-22 Brass Pressure Sensor 2.2.15.6 Stainless Steel Pressure Sensors The stainless pressure sensors are unamplified high reliability sensors for harsh installation environments. There are four sensors available to measure oil, fuel, and manifold pressure. Figure 2-23 Stainless Steel Pressure Sensor 2.2.15.7 P-Lead RPM Pickup A wire with two parallel resistors in-line connects from each P-lead, at the Magneto or the ignition switch, to the GEA 110 to sense RPM.

Rev. 1 Page 3-2 3.2 Servicing Information There are no servicing requirements for the G500/G600 TXi system. In the event of a system or LRU failure, troubleshoot the G500/G600 TXi system in accordance with Section 4. 3.2.1 Periodic Maintenance Instructions G500/G600 TXi system LRUs are designed to detect internal failures. A thorough self-test is executed automatically upon application of power to the units, and built-in tests are continuously executed while the LRUs are operating. Detected errors are indicated on the GDU 1060/700() display via failure annunciations, system messages, or a combination of the two. A list of reported errors for the system can be printed in the form of a maintenance log using the instructions provided in Section 4.1. 3.2.2 Special Tools A milliohm meter with an accuracy of ± 0.1 milliohms (or better) is required to measure the electrical bonding between the G500/G600 TXi system components and aircraft ground. A pitot-static ground tester is required for ADC and standby instrument checkout procedures and maintenance. 3.3 Maintenance Intervals Table 3-1 Periodic Maintenance Item Description/ Procedure Interval G500/G600 TXi System Visual Inspection All installed system LRUs, switches, knobs, and wiring harnesses must be inspected to ensure continued integrity of the installation. The inspection must be performed in accordance with Section 3.4. 12 Calendar Months GBB 54 Backup Battery Check Perform a Backup Battery Check as described in Section 5.13.5. If the GBB 54 does not pass the Backup Battery Check the battery cell must be replaced using the procedure found in Section 5.8.2. 12 Calendar Months EIS Annunciator Lamp Check If an EIS annunciator is installed, perform a check of the annunciator lamps using the following procedure: 1. Power on the GDU 1060/700 in configuration mode per the instructions in Section 2.1.4. 2. Navigate to Diagnostics → Discrete Outputs. 3. Toggle the State of the Engine Caution and Engine Warning discrete outputs to on (The bar at the bottom of the state button on the GDU will illuminate green). 4. Verify that the respective engine annunciator lights have illuminated. 5. Toggle the State of the Engine Caution and Engine Warning discrete outputs to off. 12 Calendar Months

Rev. 1 Page 3-3 RVSM Checks (TBM 700/850 Only) Perform the air data checks and autopilot altitude hold checks as specified in Section 3.6. 24 Calendar Months AHRS Magnetic Field Model Update The GSU 75(), GRS 79, and GDU 1060/700P Integrated ADAHRS utilize an Earth magnetic field model which is updated once every five years as part of the Aviation Database maintained by the owner/operator. If the magnetic model is not up to date, the unit will issue an alert upon startup indicating the model has expired. A service bulletin containing the updated magnetic field model and instructions for installation can be obtained from the dealer resource center or by contacting Garmin. Every 5 years Electrical Bonding Check Perform an electrical bonding check of the G500/G600 TXi system LRUs in accordance with Section 3.5. Every 2000 Flight hours or 10 years, whichever comes first GDU 1060/700 Cooling Fan Replacement It is recommended that the cooling fan on the GDU 1060/700 be replaced every 3000 fan operating hours. The number of hours the fan has been operating can be viewed using the following procedure: 1. Power on the GDU 1060/700 in configuration mode per the instructions in Section 2.1.4. 2. Navigate to Diagnostics → Temp & Power Stats. 3. The cooling fan operating hours can be found under Power Statistics as “Fan OPER Hours”. The cooling fan replacement procedure is contained in Section 5.1.2. Recommende d every 3000 fan operating hours Altimeter Checks Test according to 14 CFR §43 Appendix E. See the pitot-static checkout procedure in Section 5.15.2 for system specific checkout procedure. Interval must be in accordance with Title 14 CFR §91.411 and 91.413 Lightning Damage Check Conduct an inspection of the G500/G600 TXi system in accordance with Section 3.8. After a suspected or actual lightning strike Equipment Removal and Replacement Removal and replacement of the G500/G600 TXi system LRUs can be accomplished by referring to Section 5 of this manual for instructions. On Condition Cleaning GDU 1060/ 700 front panel The front bezel, keypad, and display can be cleaned with a soft cotton cloth dampened with clean water. DO NOT use any chemical cleaning agents. Care should be taken to avoid scratching the surface of the display. On Condition Item Description/ Procedure Interval

Rev. 1 Page 3-4 3.4 Visual Inspection Operation of the G500/G600 TXi system is not permitted unless an inspection, as described in this section, has been completed within the preceding 12 calendar months. Conduct the following visual inspection of the G500/G600 TXi system LRUs and associated wiring harnesses to ensure installation integrity: WARNING Ensure the GBB 54 vent tube is not pointed towards personnel or equipment before blowing shop air through the tube. Any obstructions in the tube will be ejected at high speed and can cause serious injury or property damage. 1. Inspect all units for security of attachment, including visual inspection of brackets and other supporting structure attaching all units to the airframe. 2. Inspect all switches, annunciators, knobs and buttons for legibility. 3. Visually inspect each unit’s wiring (including electrical bonding straps), overbraid, and connectors for chafing, deterioration, damage or wear. 4. Visually check for any signs of corrosion. 5. Visually inspect the GBB 54 vent tube and connectors for damage/corrosion and ensure there are no obstructions in the vent tube. The vent tube can be checked for obstructions by disconnecting the vent tube from the GBB 54 and blowing shop air through the tube from the battery connector side to the exterior of the aircraft. 3.4.1 Aluminum Foil Tape (non-metallic aircraft only) Any aluminum foil tape used in the G500/G600 TXi installation for grounding of a GSU 75/75B, GDC 72, GRS 79, GAD 43/43e, or GEA 110 (see Appendix A of this document) must be inspected every 12 calendar months. The inspection must verify that the foil tape is not torn, damaged, or showing signs of corrosion. If any of these conditions is found, the tape must be replaced in accordance with Section 4 of the G500/G600 TXi Part 23 AML STC Installation Manual. 3.5 Electrical Bonding Check G500/G600 TXi LRU electrical bonding must be checked every 2000 flight hours or ten (10) years, whichever occurs first. During the check, any cables normally attached to the LRU must be disconnected from the LRU. Resistance must be measured from a bare metal portion of the LRU to an airframe grounding location. The airframe grounding location should be as close to the LRU as possible unless Display Backlight The display backlight LEDs are rated by the manufacturer as having a usable life of at least 36,000 hours. This life may be more or less than the rated time depending on the operating conditions of the GDU 1060/700. Over time the backlight lamp may dim and the display may not perform as well in direct sunlight conditions. The user must determine by observation when the display brightness is not suitable for its intended use. Contact a Garmin factory repair station when the backlight lamp requires service. On Condition Item Description/ Procedure Interval

Rev. 1 Page 3-5 otherwise noted in the following table. If measured resistance is greater than applicable values in the following table, bonding must be improved to meet applicable requirements for a new installation in accordance with Section 4 of the G500/G600 TXI Part 23 AML STC Installation Manual. Table 3-2 Electrical bonding requirements Notes: [1] For remote LRUs bonded back to the instrument panel via an installed aluminum foil ground plane, bonding measurement must be taken between the remote LRU and the instrument panel. 3.6 RVSM Periodic Maintenance (Socata TBM 700/850 Only) Maintain all RVSM equipment in accordance with the manufacturer’s maintenance and performance requirements. The encoding altimeter must be checked as specified in the Socata Maintenance Manual Section 05-10-01, ATA Chapter 34. The RVSM critical areas must be inspected as specified in Socata Maintenance Manual Section 05-10-01, ATA Chapter 53. The air data systems must be checked within the preceding 24 months as specified in the Socata Maintenance Manual Section 34-11-00 except for the altitude displays and altitude alerter. The altitude displays and altitude alerter must be checked in accordance with Section 5.15.3 of this manual. Socata Maintenance Manual test procedures may be adapted to complete all other air data system checks required in Section 5.15.2. The autopilot altitude hold performance must be checked within the preceding 24 months in accordance with the RVSM In-flight altitude hold check described in Section 5.15.3.3. LRU Maintenance Requirement GDU 1060/700 GCU 485 Engine Annunciator 20 Milliohms GSU 75/75B GDC 72 GRS 79 GAD 43/43e 5 Milliohms GEA 110 5 Milliohm (remote mounted) n/a (GDU 1060 mounted) GTP 59 5 Milliohm (Or electrically isolated per Appendix D of G500/ G600 TXi Part 23 AML STC Installation Manual) GMU 44 10 Milliohm (Or electrically isolated per Appendix D of G500/ G600 TXi Part 23 AML STC Installation Manual)

Rev. 1 Page 3-6 3.7 Overhaul Period The system does not require overhaul at a specific time period. Power on self-test and continuous BIT will monitor the health of the G500/G600 TXi system. If any LRU indicates an internal failure, the unit may be removed and replaced. See ��������� of this document for fault�������������������� 3.8 Special Inspection Requirements After a suspected lightning strike, the following actions must be performed for the specified LRU: GTP 59 OAT Inspect the GTP 59 OAT for signs of lightning damage. Check the self-sealing washer (P/N 212-00026-00) used on the probe tip outside of the aircraft for any evidence of melting or lack of seal. Replace washer if damaged. If there is evidence of lightning strike to the OAT or any lightning damage, replace the GTP 59 OAT. Tube and fabric aircraft must replace the OAT bond strap (if installed) in accordance with Section 4.6.2 of the G500/G600 TXi Part 23 AML STC Installation Manual. GMU 44 Aircraft with a GMU mounted in the wingtip of metallic aircraft with non-metallic wingtip covers must inspect the magnetometer installation for the following conditions: • Check the GMU 44 magnetometer body and mount for scorching, soot, melting, pitting, denting, or discoloration. • Check P441 and J441 for melting or pin damage. • Check the cable overbraid for pinching, melting or evidence of arcing. • Check the lug for evidence of arcing and verify that the lug is still secured to the overbraid. • Check electrical bonding between the GMU 44 overbraid and adjacent aircraft structure. Resistance should be less than 5 mΩ. • If any of these checks shows evidence of a lightning strike, replace the overbraid assembly in accordance with Figure 4-54 of the G500/G600 TXi Part 23 AML STC Installation Manual. Perform the magnetic interference check in accordance with Section 6.6.4 of the G500/G600 TXi Part 23 AML STC Installation Manual. The purpose of this check is to ensure the structure around the GMU 44 did not get magnetized by the lightning event to the point of affecting GMU 44 performance. GBB 54 Battery Vent Tube Aircraft with a GBB 54 battery must inspect the battery vent tube using the following procedure: 1. Gain access to the GBB 54 and both ends of the vent tube. 2. Check the battery vent grounding strap for evidence of arcing or damage. 3. Check the end of the vent tube that protrudes through the aircraft skin for scorching, soot, melting, pitting, denting, or discoloration. If any of these checks show evidence of a lightning strike, replace the vent tube and grounding strap in accordance with Section 4.5.6 of the G500/G600 TXi Part 23 AML STC Installation Manual. 3.9 Application of Protective Treatments None.

Rev. 1 Page 3-7 3.10 Data Relative to Structural Fasteners Data relative to structural fasteners, such as type, torque, and installation requirements can be found in Section 5 of this manual. 3.11 Additional Instructions None.

Rev. 1 Page 4-1 4 TROUBLESHOOTING 4.1 General System Troubleshooting......................................................................................................4-1 4.1.1 System Maintenance Log...........................................................................................................4-2 4.2 Connector Information......................................................................................................................4-2 4.2.1 GDU 1060/700 ...........................................................................................................................4-3 4.2.2 GCU 485 ....................................................................................................................................4-7 4.2.3 GDC 72 ......................................................................................................................................4-8 4.2.4 GSU 75() ..................................................................................................................................4-10 4.2.5 GRS 79 ....................................................................................................................................4-12 4.2.6 GAD 43/43e .............................................................................................................................4-14 4.2.7 GAD 43e ..................................................................................................................................4-15 4.2.8 GEA 110...................................................................................................................................4-17 4.2.9 GBB 54.....................................................................................................................................4-20 4.2.10 GMU 44....................................................................................................................................4-21 4.2.11 GTP 59 .....................................................................................................................................4-21 4.3 Troubleshooting Flow Charts .........................................................................................................4-22 This section provides information to assist troubleshooting if fault codes are displayed on the GDU or problems occur after completing system maintenance. See Appendix A of this document retained in the aircraft permanent records for a list of the interfaced equipment and system configuration data. When troubleshooting the G500/G600 TXi system, refer to wire routing drawings and interconnect diagrams retained in Appendix A of this document or with the aircraft’s permanent records. 4.1 General System Troubleshooting Before troubleshooting the G500/G600 TXi system, use the Configuration log tool to print the current configuration log to ensure that system configuration settings match those recorded in the aircraft’s permanent records. If the current aircraft configuration does not match the configuration log retained with the aircraft permanent records, load the saved configuration from the SD card retained with the permanent aircraft records. If this cannot be accomplished, or does not correct the configuration, the configuration must be corrected by a Garmin dealer using an installer unlock card and the configuration instructions provided in Section 5 of the G500/G600 TXi Part 23 AML STC Installation Manual (P/N:190-01717-B3). Basic troubleshooting of the G500/G600 TXi system can be accomplished using the instructions provided in Table 4-1. Table 4-1 G500/G600 TXi Failures Symptom Recommended Action GDU 1060/700() Blank 1) Check power/ground wiring for GDU. 2) Press the power button until the Garmin logo is visible. Configuration Mode pages grayed out with an installer unlock card 1) Ensure a GDU master configuration module is selected. 2) Ensure a functional configuration module is present. 3) Ensure the GDU ID’s are set for all GDU’s EIS Gauge Fault/Failure Troubleshoot the problem using the EIS Gauge Troubleshooting flowchart provided in Section 4.3.

Rev. 1 Page 4-2 4.1.1 System Maintenance Log The G500/G600 TXi system has a maintenance and error log that can be accessed or printed to assist with system maintenance and troubleshooting. The maintenance and error log can be accessed using the following procedure: 1. Power all GDU 1060/700 units into configuration mode in accordance with Section 2.1.4. 2. On GDU1 navigate to Diagnostics → Maintenance / Error Log → Maintenance Log. The maintenance and error log can be printed using the following procedure: 1. Power all GDU 1060/700 units into configuration mode in accordance with Section 2.1.4. 2. Insert an SD card into the top/left SD card slot. 3. Press the SD Save button. 4. Enter a name for the configuration file to be saved as and then select Enter. 5. Once the save process is completed, eject the SD card from the GDU and insert it into a computer. 6. On the computer navigate to the SD card drive and open the “maintenance_logs” directory. 7. Open the .htm file with the name that you entered in step 4. 8. The file should open in your computer internet browser and can be printed using your selected internet browser print function (in most cases pressing the “ctrl” and “p” buttons simultaneously will access this function). The maintenance log will display reported system faults, the Alert message that is displayed on the GDU for that fault (if any), frequency, most recent occurrence time of the fault, and any additional information about the fault that might be helpful. If any faults are reported on the maintenance log, refer to the troubleshooting flowcharts contained in Section 4.3. 4.2 Connector Information This section contains connector information and description of pin functions for all LRUs that can be installed as part of G500/G600 TXi STC. All D-sub connectors follow a similar pin numbering scheme as that shown in Figure 4-1. (view is from the contact side of the connector) Figure 4-1 62 pin D-sub connectors numbering scheme for female/male contacts An Alert message is displayed on the GDU or present in the Maintenance log Troubleshoot the alert message using the flowcharts provided in Section 4.3 Symptom Recommended Action

Rev. 1 Page 4-3 4.2.1 GDU 1060/700 NOTE GDU 700() and GDU 1060 displays have identical connectors and pin functions. GDU 700() and GDU 1060 displays have seven connectors: • J1/P1 - 26 pin female contact HD-D-sub • J2/P2 - 44 pin female contact HD-D-sub • J3/P3 - 62 pin female contact HD-D-sub • J4/P4 - 78 pin female contact HD-D-sub • J5/P5 - TNC connector (Not Used) • J6/P6 - TNC connector (Not Used) • J7/P7 - TNC connector Figure 4-2 GDU 700P Connectors ��� ���������� ����������

Rev. 1 Page 4-4 J1/P1 Connector J2/P2 Connector * Denotes active low Pin Function I/O Pin Function I/O 1 AIRCRAFT POWER 2 IN 14 BATTERY CHARGE OUT OUT 2 AIRCRAFT POWER 2 IN 15 BATTERYGND -- 3 AIRCRAFT POWER 2 IN 16 BATTERY RS-232 GND -- 4 AIRCRAFT POWER 2 IN 17 USE BATTERY OUT OUT 5 BATTERY CHARGE OUT OUT 18 BATTERY POWER IN IN 6 BATTERY GROUND -- 19 AIRCRAFT POWER 1 IN 7 BATTERY RS-232 IN IN 20 AIRCRAFT POWER 1 IN 8 BATTERY GROUND -- 21 AIRCRAFT POWER 1 IN 9 BATTERY POWER IN IN 22 AIRCRAFT POWER 1 IN 10 AIRCRAFT GND -- 23 BATTERY GND -- 11 AIRCRAFT GND -- 24 BATTERY RS-232 OUT OUT 12 AIRCRAFT GND -- 25 STANDBY POWER IN IN 13 AIRCRAFT GND -- 26 BATTERY POWER IN IN Pin Function I/O Pin Function I/O 1 RS-485 1A I/O 23 ETHERNET OUT 4A OUT 2 RS-485 1B I/O 24 GND -- 3 LIGHTING BUS HI IN 25 RESERVED -- 4 LIGHTING BUS LO IN 26 MAGNETOMETER GND -- 5 OAT POWER OUT 27 RS-232 IN 2 IN 6 OAT PROBE IN HI IN 28 RS-232 IN 1 IN 7 OAT PROBE IN LO IN 29 CONFIG MODULE GND -- 8 COMPOSITE VIDEO IN 2 IN 30 CONFIG MODULE CLOCK OUT 9 AUDIO OUT LO OUT 31 ETHERNET IN 1B IN 10 AUDIO OUT HI OUT 32 ETHERNET OUT 1B OUT 11 GND -- 33 ETHERNET IN 2B IN 12 RS-232 GND 2 -- 34 ETHERNET OUT 2B OUT 13 RS-232 GND 1 -- 35 ETHERNET IN 3B IN 14 COMPOSITE VIDEO IN 1 IN 36 ETHERNET OUT 3B OUT 15 CONFIG MODULE PWR OUT 37 ETHERNET IN 4B IN 16 ETHERNET IN 1A IN 38 ETHERNET OUT 4B OUT 17 ETHERNET OUT 1A OUT 39 DEMO MODE SELECT* IN 18 ETHERNET IN 2A IN 40 LRU POWER OUT 1 OUT 19 ETHERNET OUT 2A OUT 41 MAGNETOMETER PWR OUT OUT 20 ETHERNET IN 3A IN 42 RS-232 OUT 2 OUT 21 ETHERNET OUT 3A OUT 43 RS-232 OUT 1 OUT 22 ETHERNET IN 4A IN 44 CONFIG MODULE DATA I/O

Rev. 1 Page 4-5 J3/P3 Connector Pin Function I/O Pin Function I/O 1 DISC OUT 3 HI OUT 32 LATERAL - FLAG OUT OUT 2 DISC OUT 4 HI OUT 33 VERTICAL - FLAG OUT OUT 3 RS-232 OUT 3 OUT 34 DISC IN 1 LO IN 4 RS-232 IN 3 IN 35 DISC IN 2 LO IN 5 RS-232 OUT 4 OUT 36 DISC IN 3 LO IN 6 RS-232 IN 4 IN 37 DISC IN 4 LO IN 7 VERTICAL SUPERFLAG OUT OUT 38 ANALOG IN 1B IN 8 LATERAL SUPERFLAG OUT OUT 39 ANALOG IN 1A IN 9 LATERAL +LEFT OUT OUT 40 A/P AC REF LO IN 10 LATERAL + RIGHT OUT OUT 41 A/P AC REF HI IN 11 LATERAL +FLAG OUT OUT 42 FD PITCH UP IN 12 VERTICAL +FLAG OUT OUT 43 DISC OUT 1 LO OUT 13 VERTICAL +UP OUT OUT 44 RS-485 2A I/O 14 VERTICAL +DOWN OUT OUT 45 RS-485 2B I/O 15 A/P COURSE ERROR LO -- 46 RS-485 3A I/O 16 A/P COURSE ERROR HI OUT 47 RS-485 3B I/O 17 A/P HEADING ERROR LO -- 48 DISC OUT 7 LO OUT 18 A/P HEADING ERROR HI OUT 49 DISC OUT 2 LO OUT 19 FD ROLL LEFT IN 50 DISC OUT 5 LO OUT 20 FD ROLL RIGHT IN 51 DISC OUT 6 LO OUT 21 FD PITCH DOWN IN 52 RESERVED -- 22 LRU POWER OUT 2 OUT 53 DISC OUT 2 HI OUT 23 GND -- 54 DISC OUT 1 HI OUT 24 GND -- 55 DISC OUT 3 LO OUT 25 RS-232 GND 3 -- 56 DISC OUT 4 LO OUT 26 RS-232 GND 4 -- 57 DISC IN 1 HI IN 27 LRU POWER OUT 3 OUT 58 DISC IN 2 HI IN 28 TIME MARK IN 2A IN 59 DISC IN 3 HI IN 29 TIME MARK IN 2B IN 60 DISC IN 4 HI IN 30 TIME MARK IN 1A IN 61 RS-485 4A I/O 31 TIME MARK IN 1B IN 62 RS-485 4B I/O

Rev. 1 Page 4-6 J4/P4 Connector J7/P7Connector Pin Function I/O Pin Function I/O 1 ARINC 429 IN 1A IN 40 GLIDESLOPE #2 +FLAG IN 2 ARINC 429 IN 2A IN 41 GLIDESLOPE #2 -FLAG IN 3 ARINC 429 IN 3A IN 42 GLIDESLOPE #1 +FLAG IN 4 ARINC 429 IN 4A IN 43 GLIDESLOPE #1 -FLAG IN 5 ARINC 429 IN 5A IN 44 ANALOG OUT 1B OUT 6 ARINC 429 IN 6A IN 45 ANALOG OUT 1A OUT 7 ARINC 429 IN 7A IN 46 RS-485 5A I/O 8 ARINC 429 IN 8A IN 47 ARINC 708/453 IN 1A IN 9 ARINC 429 IN 9A IN 48 ARINC 708/453 IN 1B IN 10 ARINC 429 IN 10A IN 49 ARINC 708/453 IN TERM A 11 ARINC 429 IN 11A IN 50 ARINC 708/453 IN TERM B -- 12 RS-232 GND 7 -- 51 DISC OUT 9 LO OUT 13 RS-232 IN 7 IN 52 DISC OUT 10 LO OUT 14 RS-232 OUT 7 OUT 53 ARINC 429 OUT 1A OUT 15 RS-232 GND 6 -- 54 ARINC 429 OUT 2A OUT 16 RS-232 IN 6 IN 55 ARINC 429 OUT 3A OUT 17 RS-232 OUT 6 OUT 56 ARINC 429 OUT 4A OUT 18 RS-232 GND 5 -- 57 ADF X/COS IN IN 19 RS-232 IN 5 IN 58 ADF Y/SIN IN IN 20 RS-232 OUT 5 OUT 59 ADF DC REF IN IN 21 ARINC 429 IN 1B IN 60 DISC OUT LOW 13 OUT 22 ARINC 429 IN 2B IN 61 DISC OUT LOW 8 OUT 23 ARINC 429 IN 3B IN 62 GLIDESLOPE #2 +UP IN IN 24 ARINC 429 IN 4B IN 63 GLIDESLOPE #2 +DN IN IN 25 ARINC 429 IN 5B IN 64 GLIDESLOPE #1 +UP IN IN 26 ARINC 429 IN 6B IN 65 GLIDESLOPE #1 +DN IN IN 27 ARINC 429 IN 7B IN 66 RS-485 5B I/O 28 ARINC 429 IN 8B IN 67 VOR/LOC COMPOSITE #1 LO IN 29 ARINC 429 IN 9B IN 68 VOR/LOC COMPOSITE #1 HI IN 30 ARINC 429 IN 10B IN 69 VOR/LOC COMPOSITE #2 LO IN 31 ARINC 429 IN 11B IN 70 VOR/LOC COMPOSITE #2 HI IN 32 RESERVED -- 71 DISC OUT LO 11 OUT 33 RS-232 GND 8 -- 72 DISC OUT LO 12 OUT 34 RS-232 IN 8 IN 73 ARINC 429 OUT 1B OUT 35 RS-232 OUT 8 OUT 74 ARINC 429 OUT 2B OUT 36 DISC IN 5 LO IN 75 ARINC 429 OUT 3B OUT 37 DISC IN 6 LO IN 76 ARINC 429 OUT 4B OUT 38 DISC IN 7 LO IN 77 ARINC 429 OUT 5A OUT 39 DISC IN 8 LO IN 78 ARINC 429 OUT 5B OUT Pin Name I/O N/A BACKUP GPS ANT --

Rev. 1 Page 4-7 4.2.2 GCU 485 The GCU 485 has a single connector: • J4851/P4851 - 15-pin male contact HD D-Sub Figure 4-3 GCU 485 Connector J4851/P4851 Connector Pin Function I/O 1 RS-232 OUT 1 OUT 2 RS-232 IN 1 IN 3 RS-232 OUT 2 OUT 4 RS-232 IN 2 IN 5 POWER GROUND -- 6 SIGNAL GROUND -- 7 AIRCRAFT_POWER_1 IN 8 SIGNAL GROUND -- 9 AIRCRAFT_POWER_2 IN 10 RESERVED -- 11 LIGHTING BUS HI IN 12 LIGHTING BUS LO IN 13 RESERVED* -- 14 RESERVED -- 15 POWER GROUND --

Rev. 1 Page 4-8 4.2.3 GDC 72 GDC 72 has a single connector: • J721/P721 78-pin female contact HD D-Sub Figure 4-4 View of J721 Connector looking at GDC 72 J721/P721 Connector Pin Function I/O Pin Function I/O 1 ARINC 429 OUT 1A OUT 40 RESERVED -- 2 ARINC 429 OUT 1B OUT 41 RESERVED -- 3 ARINC 429 OUT 2A OUT 42 ARINC 429 IN 1A IN 4 OAT LO IN 43 ARINC 429 IN 1B IN 5 OAT HI IN 44 ARINC 429 IN 2A IN 6 OAT POWER OUT 45 RESERVED -- 7 ARINC 429 OUT 1B OUT 46 RESERVED -- 8 ARINC 429 OUT 3A OUT 47 RESERVED -- 9 ARINC 429 OUT 3B OUT 48 SIGNAL GROUND -- 10 RESERVED -- 49 ARINC 429 OUT 2A OUT 11 RESERVED -- 50 ARINC 429 OUT 2B OUT 12 RESERVED -- 51 RESERVED -- 13 RESERVED -- 52 RESERVED -- 14 AIRCRAFT POWER 1 IN 53 CONFIG MODULE POWER OUT 15 SIGNAL GROUND -- 54 CONFIG MODULE DATA I/O 16 AIRCRAFT POWER 2 IN 55 CONFIG MODULE CLOCK OUT 17 RS232 OUT 2 OUT 56 DISCRETE IN 1* IN 18 RS232 IN 2 IN 57 SYS ID 2* IN 19 RESERVED -- 58 RESERVED -- 20 RESERVED -- 59 RESERVED -- 21 ARINC 429 OUT 3A OUT 60 RESERVED -- 22 ARINC 429 OUT 3B OUT 61 RESERVED -- 23 ARINC 429 OUT 2B OUT 62 ARINC 429 IN 3A IN 24 SIGNAL GROUND -- 63 ARINC 429 IN 3B IN 25 RESERVED -- 64 ARINC 429 IN 2B IN 26 SIGNAL GROUND -- 65 RESERVED -- 27 ARINC 429 OUT 1A OUT 66 RESERVED -- 28 RESERVED -- 67 RESERVED -- 29 RESERVED -- 68 SIGNAL GROUND -- 30 SIGNAL GROUND -- 69 RS 232 OUT 1 OUT 31 SIGNAL GROUND -- 70 RS 232 IN 1 IN 32 SIGNAL GROUND -- 71 RESERVED -- 33 SIGNAL GROUND -- 72 RESERVED -- 34 AIRCRAFT GROUND 1 -- 73 SIGNAL GROUND -- 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 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

Rev. 1 Page 4-9 *Indicates active low 35 SPARE -- 74 CONFIG MODULE GROUND -- 36 AIRCRAFT GROUND 2 -- 75 SYS ID 1* IN 37 SIGNAL GROUND -- 76 DISCRETE IN 3* IN 38 RESERVED -- 77 DISCRETE IN 4 IN 39 RESERVED -- 78 DISCRETE IN 2* IN

Rev. 1 Page 4-10 4.2.4 GSU 75() GSU 75() has a single connector: • J751/P751 78-pin female contact HD D-Sub Figure 4-5 View of J751 Connector looking at GSU 75() J751/P751 Connector Pin Function I/O Pin Function I/O 1 ARINC 429 OUT ADC 1A OUT 40 PPS IN 1 B IN 2 ARINC 429 OUT ADC 1B OUT 41 PPS IN 2 A IN 3 ARINC 429 OUT ADC 2A OUT 42 ARINC 429 IN ADC 1A IN 4 OAT LO IN 43 ARINC 429 IN ADC 1B IN 5 OAT HI IN 44 ARINC 429 IN ADC 2A IN 6 OAT POWER OUT 45 ARINC 429 IN AHRS 1A IN 7 ARINC 429 OUT ADAHRS 1B OUT 46 ARINC 429 IN AHRS 1B IN 8 ARINC 429 OUT ADAHRS 3A OUT 47 ARINC 429 IN AHRS 3A IN 9 ARINC 429 OUT ADAHRS 3B OUT 48 SIGNAL GROUND -- 10 RS-422 IN A IN 49 ARINC 429 OUT ADAHRS 2A OUT 11 RS-422 IN B IN 50 ARINC 429 OUT ADAHRS 2B OUT 12 RS-232 OUT AHRS 3 OUT 51 RS-232 OUT AHRS 1 OUT 13 MAGNETOMETER POWER OUT OUT 52 RS232 IN AHRS 1 IN 14 AIRCRAFT POWER 1 IN 53 CONFIG MODULE POWER OUT 15 SIGNAL GROUND -- 54 CONFIG MODULE DATA I/O 16 AIRCRAFT POWER 2 IN 55 CONFIG MODULE CLOCK OUT 17 RS-232 OUT ADC 2 OUT 56 DISCRETE IN 1* IN 18 RS-232 IN ADC 2 IN 57 SYS ID 2* IN 19 RESERVED -- 58 RESERVED IN 20 RESERVED -- 59 RESERVED I/O 21 ARINC 429 OUT ADC 3A OUT 60 PPS IN 1A IN 22 ARINC 429 OUT ADC 3B OUT 61 PPS IN 2B IN 23 ARINC 429 OUT ADC 2B OUT 62 ARINC 429 IN ADC 3A IN 24 SIGNAL GROUND -- 63 ARINC 429 IN ADC 3B IN 25 PPS SELECT IN 64 ARINC 429 IN ADC 2B IN 26 SIGNAL GROUND -- 65 ARINC 429 IN AHRS 2A IN 27 ARINC 429 OUT ADAHRS 1A OUT 66 ARINC 429 IN AHRS 2B IN 28 ARINC 429 OUT ADAHRS 3A OUT 67 ARINC 429 IN AHRS 3B IN 29 ARINC 429 OUT ADAHRS 3B OUT 68 RS-232 ADC 1 GROUND -- 30 SIGNAL GROUND -- 69 RS-232 OUT ADC 1 OUT 31 RS-232 AHRS 3 GROUND -- 70 RS-232 IN ADC 1 IN 32 RS-232 AHRS 1 GROUND -- 71 RS-232 OUT AHRS 2 OUT 33 MAGNETOMETER GROUND -- 72 RS-232 IN AHRS 2 IN 34 AIRCRAFT GROUND 1 -- 73 RS-232 AHRS 2 GROUND -- 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 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

Rev. 1 Page 4-11 *Indicates active low 35 RESERVED -- 74 CONFIG MODULE GROUND -- 36 AIRCRAFT GROUND 2 -- 75 SYS ID 1* IN 37 RS-232 ADC 2 GROUND -- 76 DISCRETE IN 3* IN 38 RESERVED -- 77 DISCRETE IN 4 IN 39 RESERVED I/O 78 DISCRETE IN 2* IN

Rev. 1 Page 4-12 4.2.5 GRS 79 The GRS 79 has a single connector: • J791/P791 78-pin female contact HD D-Sub Figure 4-6 View of J791 Connector looking at GRS 79 J791/P791 Connector Pin Function I/O Pin Function I/O 1 ARINC 429 OUT 1A OUT 40 PPS IN 1 B IN 2 ARINC 429 OUT 1B OUT 41 PPS IN 2 A IN 3 ARINC 429 OUT 2A OUT 42 RESERVED -- 4 RESERVED -- 43 RESERVED -- 5 RESERVED -- 44 RESERVED -- 6 RESERVED -- 45 ARINC 429 IN 1A IN 7 ARINC 429 OUT 1B OUT 46 ARINC 429 IN 1B IN 8 ARINC 429 OUT 3A OUT 47 ARINC 429 IN 3A IN 9 ARINC 429 OUT 3B OUT 48 SIGNAL GROUND -- 10 RS-422 IN A IN 49 ARINC 429 OUT 2A OUT 11 RS-422 IN B IN 50 ARINC 429 OUT 2B OUT 12 RS-232 OUT 3 OUT 51 RS-232 OUT 1 OUT 13 MAGNETOMETER POWER OUT OUT 52 RS-232 IN 1 IN 14 AIRCRAFT POWER 1 IN 53 CONFIG MODULE POWER OUT 15 SIGNAL GROUND -- 54 CONFIG MODULE DATA I/O 16 AIRCRAFT POWER 2 IN 55 CONFIG MODULE CLOCK OUT 17 RESERVED -- 56 DISCRETE IN 1* IN 18 RESERVED -- 57 SYS ID 2* IN 19 RESERVED -- 58 RESERVED IN 20 RESERVED -- 59 RESERVED I/O 21 ARINC 429 OUT 3A OUT 60 PPS IN 1A IN 22 ARINC 429 OUT 3B OUT 61 PPS IN 2B IN 23 ARINC 429 OUT 2B OUT 62 RESERVED -- 24 SIGNAL GROUND -- 63 RESERVED -- 25 PPS SELECT IN 64 RESERVED -- 26 SIGNAL GROUND -- 65 ARINC 429 IN 2A IN 27 ARINC 429 OUT 1A OUT 66 ARINC 429 IN 2B IN 28 RESERVED -- 67 ARINC 429 IN 3B IN 29 RESERVED -- 68 SIGNAL GROUND -- 30 SIGNAL GROUND -- 69 RESERVED -- 31 SIGNAL GROUND -- 70 RESERVED -- 32 SIGNAL GROUND -- 71 RS-232 OUT 2 OUT 33 MAGNETOMETER GROUND -- 72 RS-232 IN 2 IN 34 AIRCRAFT GROUND 1 -- 73 SIGNAL GROUND -- 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 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

Rev. 1 Page 4-13 *Indicates active low 35 SPARE -- 74 CONFIG MODULE GROUND -- 36 AIRCRAFT GROUND 2 -- 75 SYS ID 1* IN 37 SIGNAL GROUND -- 76 DISCRETE IN 3* IN 38 RESERVED -- 77 DISCRETE IN 4 IN 39 RESERVED I/O 78 DISCRETE IN 2* IN

Rev. 1 Page 4-14 4.2.6 GAD 43/43e The GAD 43 has a single connector: • J431/P431 50-pin female contact D-Sub Figure 4-7 GAD 43/43e J431/P431 connector looking at unit *Indicates active low Pin Function I/O Pin Function I/O 1 RESERVED -- 26 WXR ROLL OUT LO (50 mV/deg) -- 2 HEADING VALID OUT* OUT 27 SPARE DISC IN* 2 IN 3 ATTITUDE VALID RELAY NO -- 28 WXR ROLL OUT HI (50 mV/deg) OUT 4 ATTITUDE VALID RELAY NC -- 29 ROLL DC OUT OUT 5 AP INTERLOCK RELAY COMMON -- 30 ROLL SYNCHRO OUT X OUT 6 +26 VDC OUT OUT 31 PITCH SYNCHRO OUT X OUT 7 HDG SYNCHRO OUT Y OUT 32 ARINC 429 IN B IN 8 HDG SYNCHRO OUT X OUT 33 RS-232 OUT OUT 9 10VAC REF IN HI IN 34 26VAC LO -- 10 10VAC REF IN LO IN 35 5VAC OUT LO -- 11 SPARE DISC OUT* 2 OUT 36 5VAC OUT HI OUT 12 WXR PITCH OUT HI (50mV/deg) OUT 37 115VAC REF IN LO IN 13 PITCH DC OUT OUT 38 115VAC REF IN HI IN 14 ROLL SYNCHRO OUT Y OUT 39 26VAC REF IN HI IN 15 PITCH SYNCHRO OUT Y OUT 40 YAW RATE / BARO CORRECTION GND -- 16 ARINC 429 IN A IN 41 HDG SYNCHRO OUT Z OUT 17 RS-232 IN IN 42 PITCH AC OUT LO (60 Mv/DEG OR 200 Mv/DEG) -- 18 26VAC OUT HI OUT 43 WXR PITCH OUT LO (50 mV/deg) -- 19 YAW RATE / BARO CORRECTION OUT OUT 44 ROLL SYNCHRO OUT Z -- 20 ATTITUDE VALID RELAY COMMON -- 45 PITCH SYNCHRO OUT Z OUT 21 AP INTERLOCK RELAY VALID NC -- 46 RS-232 GND -- 22 AP INTERLOCK RELAY VALID NO -- 47 AIRCRAFT GROUND -- 23 ROLL AC OUT HI (54 mV/deg or 200 mV/deg) OUT 48 AIRCRAFT GROUND -- 24 PITCH AC OUT HI (60 mV/deg or 200 mV/deg) OUT 49 AIRCRAFT POWER 1 IN 25 ROLL AC OUT LO (54 mV/deg or 200 mV/deg) -- 50 AIRCRAFT POWER 2 IN 1 2 3 4 5 6 7 8 9 10 11 13 14 15 16 17 18 19 12 20 21 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 41 40 39 38 45 44 43 42 49 48 46 47 50

Rev. 1 Page 4-15 4.2.7 GAD 43e GAD 43e has three connectors: • J431/P431 50-pin female contact D-Sub (same as GAD 43 J431/P431 shown in Section 4.2.6) • J432/P432 78-pin female contact HD D-Sub • J433/P433 26-pin female contact HD D-Sub Figure 4-8 GAD 43e J432/P432 Connector looking at unit Pin Function I/O Pin Function I/O 1 ALTITUDE PRESELECT DATA I/O 40 DME RQST HI / DME SYNC IN HI I/O 2 GROUND -- 41 DME RQST LO / DME SYNC IN LO I/O 3 RS-232 IN 2 IN 42 DME RNAV RQST OUT OUT 4 RS-232 OUT 2 OUT 43 ARINC 429 OUT 1A OUT 5 RS-232 GND 2 -- 44 ARINC 429 OUT 1B OUT 6 OUTER MARKER EXT LAMP IN IN 45 GROUND -- 7 MIDDLE MARKER EXT LAMP IN IN 46 ILS ENERGIZE #1 IN* IN 8 INNER MARKER EXT LAMP IN IN 47 ILS ENERGIZE #2 IN* IN 9 RADAR ALT VALID IN IN 48 GLIDESLOPE #1 VALID IN IN 10 GROUND -- 49 GLIDESLOPE #2 VALID IN IN 11 RESERVED -- 50 DME EXT TUNE K50 IN IN 12 RESERVED -- 51 DME SUPERFLAG IN IN 13 RESERVED -- 52 DME HOLD OUT* OUT 14 RESERVED -- 53 ALT HOLD* OUT 15 GROUND -- 54 GROUND -- 16 RESERVED -- 55 RESERVED -- 17 VS CMD OUT 56 RESERVED -- 18 GROUND -- 57 RESERVED -- 19 ALTITUDE ERROR OUT + OUT 58 PRESELECT MON+ POWER IN 20 ALTITUDE ERROR OUT - OUT 59 PRESELECT MON+ OUT OUT 21 ALTITUDE PRESELECT CLOCK I/O 60 DME CLOCK HI I/O 22 GROUND -- 61 DME CLOCK LO I/O 23 DME ARINC 429 IN A IN 62 DME DATA HI I/O 24 DME ARINC 429 IN B IN 63 DME DATA LO I/O 25 GROUND -- 64 AIRCRAFT GROUND -- 26 RESERVED -- 65 DME EXT TUNE M8/MA/M0 IN IN 27 RESERVED -- 66 DME EXT TUNE M4/ME/M1 IN IN 28 RESERVED -- 67 DME EXT TUNE M2/MC/M2 IN IN 29 RESERVED -- 68 DME EXT TUNE M1/MD/M3 IN IN 30 PRESELECT ADDR 0 / AP DISC SW IN 69 DME EXT TUNE K800/KA/K0 IN IN 31 PRESELECT ADDR 1 IN 70 DME EXT TUNE K400/KE/K1 IN IN 32 GROUND -- 71 DME EXT TUNE K200/KC/K2 IN IN 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 62 61 60 59 58 57 56 55 54 53 52 51 1 2 3 4 5 6 7 8 9 10 11 13 14 15 16 17 12 19 20 21 25 24 23 22 18 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 50 49 48 47 46 45

Rev. 1 Page 4-16 *Indicates active low Figure 4-9 GAD 43e J433/P433 Connector looking at unit 33 RESERVED -- 72 DME EXT TUNE K100/KD/K3 IN IN 34 VS SELECT CTRL* / KNOB IN MOTION* OUT 73 GROUND -- 35 DME COM NAV 1* / CH 1-2 SELECT* I/O 74 RESERVED -- 36 DME COM NAV 2* I/O 75 RESERVED -- 37 RESERVED -- 76 GROUND -- 38 GROUND -- 77 RESERVED -- 39 RESERVED -- 78 RESERVED -- Pin Function I/O 1 VOR/LOC COMPOSITE #1 HI IN 2 VOR/LOC COMPOSITE #1 LO IN 3 VOR/LOC COMPOSITE #2 HI IN 4 VOR/LOC COMPOSITE #2 LO IN 5 GROUND -- 6 GLIDESLOPE #1 +UP IN IN 7 GLIDESLOPE #1 +DN IN IN 8 GLIDESLOPE #2 +UP IN IN 9 GLIDESLOPE #2 +DN IN IN 10 RESERVED -- 11 GROUND -- 12 ADF BEARING X IN 13 ADF BEARING Y IN 14 ADF BEARING Z (GND) -- 15 RADAR ALT IN HI IN 16 RADAR ALT IN LO IN 17 GROUND -- 18 GROUND -- 19 FD PITCH UP OUT/GS #2 VALID OUT OUT 20 FD PITCH DOWN OUT (GND) -- 21 FD ROLL RIGHT OUT/GS #1 VALID OUT OUT 22 FD ROLL LEFT OUT (GND) -- 23 FD PITCH UP IN/GS #2 +FLAG IN 24 FD PITCH DOWN IN/GS #2 -FLAG IN 25 FD ROLL RIGHT IN/GS #1 +FLAG IN 26 FD ROLL LEFT IN/GS #2 -FLAG IN 9 18 19 20 21 26 25 24 23 22 1 2 3 4 5 6 7 8 10 11 13 14 15 16 17 12

Rev. 1 Page 4-17 4.2.8 GEA 110 GEA110 has two connectors: • J1101/P1101 15-pin female contact HD D-Sub • J1102/P1102 78-pin female contact HD D-Sub Figure 4-10 GEA 110 Connectors Figure 4-11 GEA 110 J1101/P1101 Connector looking at unit Pin Function I/O 1 AV PWR IN 1 IN 2 RESERVED -- 3 DISCRETE OUT 1 OUT 4 RS 485 2A I/O 5 RS 485 1A I/O 6 AV PWR IN 2 IN 7 RESERVED -- 8 DISCRETE OUT 2 OUT 9 RS 485 2B I/O 10 RS 485 1B I/O 11 DISCRETE IN 5 IN 12 SYS ID #1 IN 13 SYS ID #2 IN 14 GND -- 15 GND -- 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1

Rev. 1 Page 4-18 Figure 4-12 GEA 110 J1102/P1102 Connector looking at unit Pin Function I/O Pin Function I/O 1 CHT 1 (+) IN 40 EGT 1 (+) IN 2 CHT 2 (+) IN 41 EGT 2 (+) IN 3 CHT 3 (+) IN 42 EGT 3 (+) IN 4 CHT 4 (+) IN 43 EGT 4 (+) IN 5 CHT 5 (+) IN 44 EGT 5 (+) IN 6 CHT 6 (+) IN 45 EGT 6 (+) IN 7 GENERAL PURPOSE 1 (+) IN 46 CARB TEMP (+) IN 8 GENERAL PURPOSE 2 (+) IN 47 OIL TEMP (+) IN 9 +10 VDC OUT 48 OIL PRESSURE (+) IN 10 FUEL PRESSURE (+) IN 49 GND -- 11 DISCRETE IN 1 IN 50 MANIFOLD PRESSURE (+) IN 12 FUEL QUANTITY 1 / GENERAL PURPOSE 3 (+) IN 51 DISCRETE IN 3 IN 13 FUEL QUANTITY 3 / GENERAL PURPOSE 5 (+) IN 52 FUEL QUANTITY 2 / GENERAL PURPOSE 4 (+) IN 14 GND IN 53 FUEL QUANTITY 4 / GENERAL PURPOSE 6 (+) IN 15 FUEL FLOW 1 IN 54 GND -- 16 FUEL FLOW 2 IN 55 SHUNT 1 (-) IN 17 +12 VDC OUT 56 SHUNT 2 (-) IN 18 RPM IN 1 (+) IN 57 BUS 1 IN 19 RPM IN 2 (+) IN 58 BUS 2 IN 20 CONFIG. MOD PWR OUT 59 CONFIG MOD CLOCK OUT 21 CHT 1 (-) IN 60 EGT 1 (-) IN 22 CHT 2 (-) IN 61 EGT 2 (-) IN 23 CHT 3 (-) IN 62 EGT 3 (-) IN 24 CHT 4 (-) IN 63 EGT 4 (-) IN 25 CHT 5 (-) IN 64 EGT 5 (-) IN 26 CHT 6 (-) IN 65 EGT 6 (-) IN 27 GENERAL PURPOSE 1 (-) IN 66 CARB TEMP (-) IN 28 GENERAL PURPOSE 2 (-) IN 67 OIL TEMP (-) IN 29 +5 VDC OUT 68 OIL PRESSURE (-) IN 30 FUEL PRESSURE (-) IN 69 +12 VDC OUT 31 DISCRETE IN 2 IN 70 MANIFOLD PRESSURE (-) IN 32 FUEL QUANTITY 1 / GENERAL PURPOSE 3 (-) IN 71 DISCRETE IN 4 IN 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 62 61 60 59 58 57 56 55 54 53 52 51 1 2 3 4 5 6 7 8 9 10 11 13 14 15 16 17 12 19 20 21 25 24 23 22 18 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 50 49 48 47 46 45

Rev. 1 Page 4-19 33 FUEL QUANTITY 3 / GENERAL PURPOSE 5 (-) IN 72 FUEL QUANTITY 2 / GENERAL PURPOSE 4 (-) IN 34 GND -- 73 FUEL QUANTITY 4 / GENERAL PURPOSE 6 (-) IN 35 SHUNT 1 (+) IN 74 GND -- 36 SHUNT 2 (+) IN 75 SPARE -- 37 RPM IN 1 (-) IN 76 +5 VDC OUT 38 RPM IN 2 (-) IN 77 BUS 3 IN 39 CONFIG MOD DATA I/O 78 CONFIG MOD GND --

Rev. 1 Page 4-20 4.2.9 GBB 54 GBB 54 has one connector: • J541/P541 15-pin HD D-Sub Figure 4-13 GBB 54 J541/P541 Connector Pin # Function I/O 1 POWER IN IN 2 POWER IN IN 3 GROUND -- 4 STANDBY OUT 5 GROUND -- 6 GROUND -- 7 BATTERY POWER OUT 8 BATTERY POWER OUT 9 POWER IN IN 10 GROUND -- 11 RS-232 TX OUT 12 RS-232 RX IN 13 PWR ON REQ IN 14 GROUND -- 15 BATTERY POWER OUT 1 15 VIEW IS LOOKING AT THE UNIT 5 2 3 4 6 7 8 9 10 11 12 13 14

Rev. 1 Page 4-21 4.2.10 GMU 44 J441/P441 Connector looking at pigtail 4.2.11 GTP 59 The GTP 59 temperature probe does not have a connector. Rather, a 3-conductor shielded cable extends from the sensor for interface with a GDU or GDC unit. 3-Conductor Shielded Cable Pin # Function I/O 1 SIGNAL GROUND -- 2 RS-485 OUT B Out 3 SIGNAL GROUND -- 4 RS-485 OUT A Out 5 SPARE -- 6 POWER GROUND -- 7 SPARE -- 8 RS-232 IN In 9 +12 VDC POWER In Conductor Color Name I/O White Probe Power Lead In Blue Resistive Element HI Out Orange Resistive Element LO Out

Rev. 1 Page 4-22 4.3 Troubleshooting Flow Charts This section provides troubleshooting flow charts for most system failures and alert messages. It is recommended that system troubleshooting and repair only be completed by a Garmin dealer. If a specific alert or fault condition is not listed, or the fault still exists after completing the given corrective action, contact Garmin Aviation Technical Support at the number listed for your specific region on the “Support” tab of the FlyGarmin.com website.

Rev. 1 Page 4-23 Figure 4-14 GDU Alert Message Troubleshooting G D U A lert M essag es If fau lt still exists , con tact G arm in . The G D U has exceeded its overtem p threshold G D U cooling fan failure O R G D U cooling fan obstruction R eplace cooling fan in accordance w ith S ection 5.1 .2 D isplay H ot, display dim m ed C ooling fan failed C ause C orrective A ctio n C o rrective A ction G D U S oftw are M ism atch O ne or m ore G D U s in the system have a different softw are version S ervice R equired C ause C o rrective A ction B acklight calibration lost C orrective A ctio n J2 P in 39 on the G D U is grounded Inspect G D U connectors and w iring to rem ove the signal from the D em o M ode S elect P in D em o m ode , do not use in flight C au se C o rrective A ction R eturn the G D U to G arm in for service E nsure all G D U s have the sam e system softw are installed V erify cooling fan ports are clear If m essage is in conjunction w ith “F an F ailure detected” m essage , R eplace cooling fan in accordance w ith S ection 5.1.2 M ain tenan ce L og M essage M ain ten an ce L og M essage

Rev. 1 Page 4-24 Figure 4-15 GDU Config and Battery Alert Message Troubleshooting Battery/Configuration Alert Messages If fault still exists, contact Garmin. Return GBB 54 to Garmin for Service Battery unavailable: fault detected Battery unavailable: communication lost Corrective Action Corrective Action Service Required Multiple master config modules detected. More than one GDU is configured as “Master” Ensure only one GDU is configured as “Master” under the “GDU Type” configuration window Cause Corrective Action External config module has been overwritten System configuration module has failed or is missing This message is expected if a configuration module has been replaced External config module cannot be written to, read from, or is not detected in the system External config module has been overwritten by internal config module Service Soon Cause Cause Corrective Action Corrective Action Internal Config module has been overwritten This message is expected if a GDU has been replaced Internal Config module has been overwritten by harness config module Cause Corrective Action Battery unavailable: power output failed Corrective Action The battery capacity test has not been successfully completed or Capacity test not run in last 392 days Verify that the GBB 54 battery cell is fully charged Battery unavailable: capacity test required Cause Corrective Action Run the battery capacity test in accordance with Section 5.13.8 Verify GDU configuration matches printed configuration log Inspect config module wiring and connector for bent, damaged, missing pins/wires Replace external configuration module in accordance with Section 5.1.4 or Section 5.1.5 Verify GDU configuration Verify GBB 54 and GDU wiring and connections Verify that GBB 54 battery cell is charged Verify GBB 54 and GDU wiring and connections If configuration does not match printed log, load GDU configuration from saved SD card Verify GDU configuration matches printed configuration log If configuration does not match printed log, load GDU configuration from saved SD card Maintenance Log Message Maintenance Log Message Maintenance Log Message Maintenance Log Message

Rev. 1 Page 4-25 Figure 4-16 PFD Alert Message Troubleshooting PFD Fault Messages If fault still exists, contact Garmin. HDG Fail GPS 1/2 interface failed. GPS TIME MARK 1/2 FAIL Improper installation of GMU 44 and/or AHRS OR Excessive magnetic interference The PFD has not received a pulse in 3 seconds or more Cause Perform Magnetic Interference check in Section 6.6.4 Verify GMU 44 and AHRS mounting locations are within ±3° of level and no more than 6° of each other(see LRU installation instructions in G500/G600 Txi Part 23 AML Installation Manual (P/N:190-01717- B3) for more information) Verify the GPS source is on and has a clear view of the sky Inspect GPS antenna, wiring, and connections Verify the GPS source is on and has a clear view of the sky Corrective Action GPS 1/2 inoperative Cause A GPS source has lost communication OR A GPS source is reporting failed Corrective Action Service Soon Cause Corrective Action AHRS 1/2 not receiving GPS aiding The AHRS has reported that no GPS data is being received Verify the GPS source is on and has a clear view of the sky AHRS 1/2 not receiving GPS Aiding Cause Corrective Action GDU( ) GPU monitor restarted the unit. An internal data check has failed and restarted the GDU GDU( ) GPU monitor restarted the unit Cause Corrective Action NAV 1/2 interface/unit failed A NAV source has lost communication OR A NAV source is reporting failed If reporting failed, troubleshoot in accordance with NAV unit maintenance manual. Verify the NAV source is on and not reporting failed NAV 1/2 inoperative Cause Corrective Action Inspect GPS antenna, wiring, and connections Contact Garmin Technical Support Verify GDU and GPS configuration settings Verify GDU and GPS configuration settings Inspect GPS antenna, wiring, and connections Verify GDU and GPS configuration settings Inspect NAV wiring, connections, and configuration settings Maintenance Log Message Maintenance Log Message Maintenance Log Message Maintenance Log Message Maintenance Log Message

Rev. 1 Page 4-26 Figure 4-17 AHRS/ADC Alert Message Troubleshooting AHRS/ADC Fault Messages If fault still exists, contact Garmin. The AHRS has detected an in tarmac anomaly at the given location The AHRS has detected a local earth anomaly at the given location If this error shows up repeatedly conduct the magnetic interference check in Section 6.6.4 of the G500/G600 Txi Part 23 AML STC Installation Manual (PN: 190- 01717-B3) AHRS 1/2 reports an in-tarmac magnetic anomaly AHRS 1/2 reports a local earth magnetic anomaly Cause Cause Corrective Action Corrective Action Service required ADC 1/2 reports configuration error ADC reports config error OR RVSM is not enabled in the system but the ADC is expecting RVSM If RVSM is expected, ensure RVSM feature is enabled in Feature Enablement page. Cause Corrective Action ADC 1/2 reports SSEC unavailable or failed AHRS 1/2 is not receiving true airspeed Wrong RVSM aircraft configuration OR ADC 2 selected on PFD 1 Verify ADC 1/2 configuration and wiring. ADC loss of communication OR No GTP 59 signal Cause Cause Corrective Action Corrective Action ADC 1/2 airspeed error correction is unavailable The alert flag has been set by the ADC ADC 1/2 error correction inoperative Cause Corrective Action The designated AHRS Magnetic Model is out of date AHRS 1/2 magnetic model database needs update Cause Corrective Action Communication lost with GMU 44 OR GMU 44 installation incorrect Inspect GMU 44 wiring and connections AHRS 1/2 not receiving valid magnetometer data Cause Corrective Action Perform AHRS magnetic model maintenance in accordance with Table 3-1 Ensure GMU 44 installation is within ±3° of level and less than 6° difference from the AHRS unit in accordance with G500/G600 Txi AML STC installation manual If other ADC or AHRS faults are present correct those faults first. Verify ADC power Inspect GTP 59, connections, and wiring. Inspect ADC/ AHRS wiring and connections Replace ADC config module Verify ADC 1/2 configuration and wiring. Maintenance Log Message Maintenance Log Message If this error shows up repeatedly conduct the magnetic interference check in Section 6.6.4 of the G500/G600 Txi Part 23 AML STC Installation Manual (PN: 190- 01717-B3)

Rev. 1 Page 4-27 Figure 4-18 Terrain Alert Message Troubleshooting Terrain/TAW S Alert Messages If fault still exists, contact Garm in. TAW S FAIL Audio Failed OR Database error OR Internal failure See external TAW S unit manual for troubleshooting instructions Cause Verify audio system is online and terrain database is loaded Verify terrain alerting configuration Reload Terrain database Verify primary GPS is on and has a clear view of the sky Inspect GPS antenna and wiring Corrective Action TAW S N/A Cause GDU is operating from backup GPS OR Primary GPS is not receiving a signal Corrective Action Ext. TAW S Fail Corrective Action See external TAW S unit manual for troubleshooting instructions Ext. TAW S N/A Corrective Action Backup GPS is active OR No Primary GPS signal OR Outside database region TER N/A Cause Corrective Action Database corrupted or missing OR Internal failure Reload terrain database Verify terrain database is loaded and current. TER FAIL Cause Corrective Action TAW S/TER config not set OR External TAW S and GDU mismatch (rotorcraft / fixed-wing) Check TAW S/ Terrain configuration settings Verify External TAW S and GDU have the same aircraft type configured Service TAW S. Invalid Config. Corrective Action Verify primary GPS is on and has a clear view of the sky Inspect GPS antenna and wiring Verify Terrain database coverage Maintenance Log Message

Rev. 1 Page 4-28 Figure 4-19 Traffic Alert Message Troubleshooting T raffic A le rt M es sa g es If fau lt still e xis ts , c o n tac t G arm in . T rou blesh oo t de vice failu re in acco rd an ce w ith T A S /T C A S LR U m a in ten an ce m a nua l T rou blesh oo t de vice failu re in accord an ce w ith A D S -B LR U m a in ten an ce m a nu al T A S /T C A S fu nction ino pe ra tive A D S tra ffic a le rtin g fu nctio n in ope rative C o rre ctiv e A c tio n C o rre ctiv e A c tio n T rou blesh oo t d evice fa ilure in accord an ce w ith A D S -B LR U m a in ten an ce m a nu al 10 90 E S tra ffic re ceiver fa ult C o rre ctiv e A ctio n U A T traffic / da ta rece iver fault C o rre ctiv e A ctio n A D S tra ffic fu nction ino pera tive C o rrec tiv e A c tio n T ra ffic /F IS -B functio ns ino perative C o rrec tive A c tio n T ro ub le sh oo t de vice failu re in a cco rda nce w ith A D S -B LR U m a in te na nce m a nua l T rou blesh oo t d evice failu re in a ccorda nce w ith U A T LR U m ainten an ce m an ua l T rou blesh oo t d evice failu re in acco rd an ce w ith A D S -B LR U m a in ten an ce m a nu al

Rev. 1 Page 4-29 Figure 4-20 Audio/Weather Alert Message Troubleshooting Audio/WX Radar Fault Messages If fault still exists, contact Garmin. TAWS audio data missing or corrupt GWX requires service Audio Failed OR Database Failed OR Internal failure See maintenance log message for specific failure condition Cause Verify audio system is online and terrain database is loaded Verify terrain alerting configuration Troubleshoot in accordance with audio device maintenance manual Verify audio device is online Inspect audio device connections and wiring Remove GWX and contact Garmin to return unit for service Corrective Action Audio Inoperative Cause Audio device failed OR Audio clip failed to play Corrective Action Cause Corrective Action ARINC 708 weather radar requires service See A708 weather radar maintenance manual for specific failure Remove A708 weather radar and contact appropriate company for repair Weather radar needs service Cause Corrective Action Connection to WX radar lost OR Improper configuration Weather radar inoperative Cause Corrective Action Weather radar is not receiving one or more inputs Display failure OR Attitude in failure OR Control fault Verify WX radar and GDU configuration Inspect WX radar wiring and connections Cause Corrective Action Check power and wiring to WX radar Verify correct WX radar configuration Troubleshoot in accordance with audio device maintenance manual Maintenance Log Message

Rev. 1 Page 4-30 Figure 4-21 External LRU Failure Message Troubleshooting E x te rn a l L R U A le rt M e s s a g e s If fa u lt s till e x is ts , c o n ta c t G a rm in . S a te llite w e a th e r in o p e ra tiv e G S R 5 6 w e a th e r n o t re g is te re d C o m u n ica tio n lo st w ith G S R 5 6 C o m u n ica tio n lo st w ith G S R 5 6 G D L 6 9 /6 9 a h a s e ith e r lo st co m m u n ica tio n w ith G D U o r is re p o rtin g a fa ile d co n d itio n C a u s e In sp e ct G S R 5 6 w irin g a n d co n n e cto rs . R e g iste r th e G S R 5 6 w e a th e r fu n ctio n a s d e sc rib e d in th e G 5 0 0 /G 6 0 0 T xi A M L S T C In sta lla tio n M a n u a l In sp e ct G D L 6 9 / 6 9 a w irin g a n d co n n e cto rs . C o rre c tiv e A c tio n S a te llite w e a th e r n o t re g is te re d C a u s e T h e G S R 5 6 w e a th e r fu n ctio n h a s n o t b e e n re g iste re d C o rre c tiv e A c tio n S iriu s X M re c e iv e r in o p e ra tiv e C a u s e C o rre c tiv e A c tio n S to rm s c o p e is n o t c o n fig u re d o r o p e ra tin g p ro p e rly S to rm sco p e is re p o rtin g fa ile d In sp e ct sto rm sco p e w irin g a n d c o n n e ctio n s C a u s e C o rre c tiv e A c tio n G C U 4 8 5 c o m m u n ic a tio n lo s t T h e G D U h a s lo s t c o m m u n ica tio n w ith th e G C U 4 8 5 C o n tro lle r U n a v a ila b le C a u s e C o rre c tiv e A c tio n C o m m u n ic a tio n lo s t w ith s to rm s c o p e T h e G D U h a s lo st co m m u n ica tio n w ith th e sto rm s co p e In sp e c t s to rm sco p e w irin g a n d co n n e ctio n s V e rify p o w e r to s to rm sco p e is o n S to rm s c o p e in o p e ra tiv e C a u s e C o rre c tiv e A c tio n E n su re a ll L R U s in th e sys te m a re o n lin e . V e rify p o w e r to G C U 4 8 5 is o n In sp e ct G C U 4 8 5 w irin g a n d co n n e ctio n s V e rify sto rm sc o p e co n fig u ra tio n se ttin g s M a in te n a n c e L o g M e s s a g e M a in te n a n c e L o g M e s s a g e M a in te n a n c e L o g M e s s a g e M a in te n a n c e L o g M e s s a g e

Rev. 1 Page 4-31 Figure 4-22 External LRU Service Message Troubleshooting External LRU Service Alerts If fault still exists, contact Garm in. Service Soon External LRU Reports config module needs service Stormscope is reporting invalid heading Check GAD 43/ 43e configuration settings AHRS does not have valid heading OR Improper configuration The GDU configuration does not match the GAD 43/43e configuration Cause Inspect wiring and connectors for damaged or missing connections Verify GDU configuration settings This message is expected if in conjunction with “HDG FAIL” message, “HDG FAIL” must be troubleshot and corrected first. Inspect connector pins and wiring to external LRU config module Replace External LRU config module Verify the correct GAD 43/43e configuration settings on the GDU interfaces page Corrective Action Cause The external LRU config module is missing or has failed Corrective Action Cause Corrective Action External LRU reports service required The external LRU is reporting that service is required Return External LRU to Garmin for service. Cause Corrective Action ADC 1/2 or AHRS 1/2 config does not match the GDU config GDU and external AHRS/ADC LRU report different configuration versions Cause Corrective Action Receiving data from the wrong side LRU. Incorrect SDI on external LRU OR Incorrect GDU configuration settings Verify GDU configuration matches installation wiring/ port configuration Inspect external LRU SDI strapping pins to ensure correct SDI Service Required Cause Corrective Action GEA did not accept configuration The GEA 110 did not accept the GDU configuration. Ensure the proper EIS configuration procedure is being followed in the G500/G600 Txi AML STC Installation Manual Section 5 Cause Corrective Action Update the GAD 43/43e configuration on the GDU “GAD 43 interface settings page” Verify ADC/AHRS interface settings on GDU and copy the configuration to the ADC/AHRS Maintenance Log Message Maintenance Log Message

Rev. 1 Page 4-32 Figure 4-23 GAD Fault Message Troubleshooting G A D Fault M essages If fault still exists , contact G arm in. G A D reports pitch deviation Error detected in one or m ore analog pitch outputs O R AC reference is not being provided Error detected in one or m ore analog yaw rate outputs C ause Verify correct w iring for analog pitch outputs from G AD 43/43e Verify AC reference voltage is on and w iring is correct Verify correct wiring for analog roll outputs from G AD 43/43e Verify AC reference voltage is on and w iring is correct Verify correct w iring for analog yaw rate outputs from G AD 43/43e C orrective A ction G AD reports roll deviation C ause Error detected in one or m ore analog roll outputs O R AC reference is not being provided Corrective A ction G AD reports yaw rate deviation C ause C orrective Action ARIN C 429 heading data from the AH R S has tim ed out Inspect AR IN C 429 data bus wiring from AH R S to G AD 43/43e Verify AH R S is powered on G AD reports AH R S A429 att tim eout C ause C orrective Action G AD 43/43e has received a pitch value greater than ±90deg from the AH RS G A D reports AH R S pitch out of range C ause Corrective A ction The AH RS has flagged the heading output as invalid due to an internal AHR S m onitor fault If the error persists, return the AH R S to G arm in for service G AD reports AH R S A429 att invalid C ause C orrective Action The AHR S has flagged the heading output as invalid due to an internal AH R S m onitor fault If the error persists, return the AH R S to G arm in for service G A D reports AH R S attitude invalid C ause C orrective A ction If the error persists, return the AH R S to G arm in for service M aintenance Log M essage

Rev. 1 Page 4-33 Figure 4-24 GAD Fault Message Troubleshooting Continued G A D Fault M essages C ont. If fau lt still exists , co ntact G arm in . G A D reports pow er supply fault O ne or m ore internal pow er supply has reported a fault Internal softw are has failed a C R C check C au se If the error persists, return the A H R S to G arm in for service Inspect A C reference to G A D 43/43e w iring and ensure AC reference source is pow ered on R eload G A D 43/ 43e softw are C orrective A ction G A D reports A C reference lost C ause A C reference voltage is not being provided to the G A D 43/43e C orrective A ction G A D reports application S C I integrity fault C ause C orrective A ction The internal G AD 43/ 43e configuration data does not pass C R C check G A D reports configuration integrity fault C ause C orrective A ction A n internal com ponent has faulted G A D reports unit fault C ause C orrective A ction G A D 43/43e internal calibration has becom e corrupted R eturn the G A D 43/43e to G arm in for service G A D reports calibration integrity fault C ause C orrective A ction C om m unication w ith G A D 43/43e has been lost If the error persists, return the G A D 43/43e to G arm in for service C heck R S - 232 w iring to G A D 43/43e C au se C orrective A ction R eturn the G A D 43/43e to G arm in for service If the error persists, return the G A D 43/43e to G arm in for service U pdate G A D 43/ 43e configuration from the interface settings screen If the error persists, return the G AD 43/43e to G arm in for service Inspect G A D 43/ 43e to G D U R S- 232 w iring and G A D 43/43e pow er w iring. M aintenance Log M essage

Rev. 1 Page 4-34 Figure 4-25 EIS Gauge Troubleshooting EIS Gauges If fault still exists, contact Garmin. Unstable RPM Resistor failure OR Poor connection OR Interference Starting vibrator is installed. Normal operation with P- Lead RPM input. Cause Disconnect P-Lead signal wires at both ends. Verify wire is more than 400KOhms. Replace wire and parallel resistors if less than 400KOhms. Verify wiring and connections Route signal wires away from spark plug leads and power wires Disconnect P-Lead signal wire at both ends of suspect mag. Verify wire is more than 400 KOhms. Replace wire and parallel resistors if less than 400KOhms. Verify wiring and connections Corrective Action Loss of RPM during mag. check Cause Resistor failure OR Poor connection Corrective Action RPM is erratic during engine start/ cranking Replace fuel probe Fuel quantity gauge inaccurate Corrective Action Poor connection OR Air/contamination in the sensor OR Incorrect sensor config. OR Interference Fuel flow indication unstable Cause Corrective Action Fuel flow requires calibration Calibrate fuel flow. Limited to 15% in GDU Normal Mode. More adjustment will require a different K-Factor. Fuel totalizer inaccurate Cause Corrective Action Verify wiring and connections Purge fuel lines of air, verify sensor orientation, clean the sensor. Configure sensor with ‘Hi’ filtering option Cause Poor connection OR Fuel probe malfunction OR Probe out of calibration Cause Verify wiring and connections None Corrective Action Route wires away from spark plug leads and power wires, install EMI shield Replace fuel flow transducer Replace fuel flow transducer Recalibrate fuel tank probes Pressure line drain plugged/line blocked OR Sensor failure Verify manifold pressure line vent (if installed) is clear. Verify fuel is not trapped in the manifold pressure line. Manifold pressure unstable Cause Corrective Action Replace manifold pressure sensor Pressure line blocked OR Sensor out of cal. OR Sensor failure Verify manifold pressure line is clear. Manifold pressure inaccurate Cause Corrective Action Recalibrate manifold pressure sensor (brass sensor only) Replace manifold pressure sensor

Rev. 1 Page 5-1 5 EQUIPMENT MAINTENANCE AND CHECKOUT PROCEDURES 5.1 GDU 1060/700..................................................................................................................................5-3 5.1.1 Removal .....................................................................................................................................5-4 5.1.2 Cooling Fan Replacement ..........................................................................................................5-5 5.1.3 Integrated ADC Module Replacement.......................................................................................5-6 5.1.4 Configuration Module Replacement ..........................................................................................5-7 5.1.5 Master Configuration Module Replacement..............................................................................5-8 5.1.6 Re-installation ............................................................................................................................5-9 5.2 GCU 485.........................................................................................................................................5-10 5.2.1 Removal ...................................................................................................................................5-10 5.2.2 Re-Installation ..........................................................................................................................5-11 5.3 EIS Annunciator .............................................................................................................................5-12 5.3.1 Removal ...................................................................................................................................5-12 5.3.2 Re-Installation ..........................................................................................................................5-13 5.4 GDC 72...........................................................................................................................................5-14 5.4.1 Removal ...................................................................................................................................5-14 5.4.2 Re-Installation ..........................................................................................................................5-15 5.4.3 Checkout...................................................................................................................................5-15 5.5 GSU 75(), GRS 79..........................................................................................................................5-16 5.5.1 Removal ...................................................................................................................................5-16 5.5.2 Installation................................................................................................................................5-17 5.5.3 Checkout...................................................................................................................................5-17 5.6 GAD 43/43e....................................................................................................................................5-18 5.6.1 Removal ...................................................................................................................................5-19 5.6.2 Re-Installation ..........................................................................................................................5-19 5.6.3 Checkout...................................................................................................................................5-19 5.7 GEA 110 .........................................................................................................................................5-20 5.7.1 Removal ...................................................................................................................................5-22 5.7.2 Re-Installation ..........................................................................................................................5-22 5.7.3 Checkout...................................................................................................................................5-22 5.8 GBB 54 ...........................................................................................................................................5-23 5.8.1 Removal ...................................................................................................................................5-24 5.8.2 Battery Cell Replacement.........................................................................................................5-24 5.8.3 Re-Installation ..........................................................................................................................5-25 5.8.4 Checkout...................................................................................................................................5-25 5.9 GMU 44..........................................................................................................................................5-25 5.9.1 Removal ...................................................................................................................................5-26 5.9.2 Re-Installation ..........................................................................................................................5-26 5.9.3 Checkout...................................................................................................................................5-26 5.10 GTP 59............................................................................................................................................5-28 5.10.1 Removal ...................................................................................................................................5-28 5.10.2 Re-Installation ..........................................................................................................................5-29 5.10.3 Checkout...................................................................................................................................5-29 5.11 Backup GPS Antenna .....................................................................................................................5-29 5.11.1 Removal ...................................................................................................................................5-30 5.11.2 Installation................................................................................................................................5-30 5.11.3 Checkout...................................................................................................................................5-30 5.12 EIS Sensors.....................................................................................................................................5-31 5.12.1 Carburetor/Induction Air Temperature ....................................................................................5-32

Rev. 1 Page 5-2 5.12.2 Oil Temperature Sensor ...........................................................................................................5-33 5.12.3 Pressure Sensors.......................................................................................................................5-34 5.12.4 Fuel Flow..................................................................................................................................5-37 5.12.5 RPM .........................................................................................................................................5-38 5.13 Calibration ......................................................................................................................................5-39 5.13.1 Attitude/Heading ......................................................................................................................5-39 5.13.2 Autopilot Calibration................................................................................................................5-39 5.13.3 Analog NAV Calibration .........................................................................................................5-39 5.13.4 Fuel Level Calibration..............................................................................................................5-39 5.13.5 Backup Battery Check..............................................................................................................5-39 5.13.6 External Systems (Weather Radar) Calibration .......................................................................5-40 5.14 Uploading Software........................................................................................................................5-41 5.15 System Checks................................................................................................................................5-41 5.15.1 Configuration Ground Check...................................................................................................5-41 5.15.2 Pitot-Static and Airspeed Tape Settings Checks......................................................................5-42 5.15.3 RVSM System Checkouts (Socata TBM 700/850 only)..........................................................5-48 This section provides the procedures to remove, replace, or install required and optional LRUs that are part of the G500/G600 TXi system. Refer to Section 4 for the definition of connectors and pin functions for G500/G600 TXi system LRUs. Before performing any maintenance on the G500/G600 TXi system all information in Appendix A must be filled out. It is highly recommended to save the system configuration to an SD card and print the configuration log before replacing any system LRUs. NOTE A GDU 1060/700() without an integrated ADAHRS may be removed, replaced with a new GDU, or the old GDU reinstalled without an installer unlock card as long as the configuration module is not replaced. NOTE Any AHRS unit (including a GDU with integral ADAHRS) may be removed or replaced without using an installer unlock card as long as the unit mounting brackets or support structure (i.e Instrument Panel, mounting bracket, avionics shelf) is not loosened or removed. If the mounting is loosened, additional calibrations and configurations will be necessary that require the use of an installer unlock card.

Rev. 1 Page 5-3 5.1 GDU 1060/700 Figure 5-1 GDU 1060 Installation 1 4 2 8 3 4 � � NOTES � ������������������������������������������������������������������������������������������������������������ ������������������������������������������������������������������������� ����������������������������������� � ��������������������������������� ������������ QTY ITEM PART NUMBER DESCRIPTION � � ���������� ������������������������������������������������������������������������������������������� � � ������������ ��������������������������������������������������������������������������� � � ����������� �������������������������������������������������������������������������������������������

Rev. 1 Page 5-4 Figure 5-2 GDU 700P Installation NOTE The GDU 700L uses the same fastener and torque specifications as the GDU 700P in Figure 5-2 above. 5.1.1 Removal Remove the GDU 1060/700 using the following procedure: 1. Ensure the current configuration is saved to an SD card in accordance with the instructions contained in Section 2.1.6. 2. Turn off the GDU and remove power for the GDU. 1 4 2 8 3 4 � � NOTES � ��������������������������������������������������������������������������������������� ���������������������������������������������������������������������������������������������� � � ��������������������������������� � ��������������������������������� ������������ QTY ITEM PART NUMBER DESCRIPTION � � ���������� ������������������������������������������������������������������������������������������� � � ������������ ��������������������������������������������������������������������������� � � ����������� �������������������������������������������������������������������������������������������

Rev. 1 Page 5-5 3. Remove the four(4) screws retaining the GDU in the instrument panel shown as item 1 in figure 5- 1 or figure 5-2 above. 4. Gently pull the GDU out from the instrument panel far enough to access the cable connectors and ADC module (if installed). 5. Remove the cable connectors from the back of the GDU. 6. If an integrated ADAHRS is installed in the GDU, Loosen the four(4) thumbscrews securing the ADC module to the rear of the GDU as shown in figure 5-3 below and gently separate the module from the GDU. If the ADC module is being replaced, proceed to Section 5.1.3. 5.1.2 Cooling Fan Replacement NOTE The GDU cooling fan replacement kit (P/N: K00-01080-00) must be obtained from an authorized Garmin dealer. In order for the GDU warranty to remain valid this procedure must be accomplished by an authorized Garmin dealer. NOTE Resetting the fan operation hours requires the use of an Installer unlock card. The GDU 1060/700 cooling fan has a recommended replacement interval of 3000 hours. After 3000 hours of operation the cooling fan should be replaced using the following procedure: 1. Remove the GDU from the instrument panel in accordance with Section 5.1.1. 2. Remove the four(4) screws securing the fan module to the rear of the GDU and discard the o-rings. 3. Grasp the fan module and gently pull the module out of the GDU. 4. Visually inspect the inside of the fan module receptacle on the back of the GDU for the following: ◦ Verify that the four rubber gaskets around the fan screw mounting holes and are not torn, damaged, or missing. If any of these conditions are found replace all four gaskets(not included in fan replacement kit). ◦ Inspect the 4-pin electrical connector for the fan module for damage or corrosion. If any damage is found, return the GDU to Garmin for service. 5. Place the new o-rings included in the fan replacement kit on the four fan mounting screws. 6. Place the new cooling fan module in the fan well of the GDU with the electrical connector oriented on the upper side near the J7 connector. CAUTION It may be necessary to slightly move the fan module within the fan well to align the connector pins and connector body. If the module does not press into the back of the GDU with slight pressure, the connector may not be aligned. If the connector cannot be aligned, remove the module again and inspect the pins on the fan module and the connector on the GDU for straightness or damage. Applying too much pressure to the fan module with the connector out of alignment could cause damage to the fan module, GDU connector, or both. 7. Slide the fan module evenly into the fan well on the GDU and gently press the module into the back of the GDU.

Rev. 1 Page 5-6 8. Insert the four fan mounting screws with o-rings into the mounting holes on the fan module and tighten evenly to 8 ± 1 LBF-IN. 9. Install the GDU in accordance with Section 5.1.6. 10. Once GDU installation and checkout has been accomplished, reset the GDU cooling fan hour counter using the following procedure: a. Power on the GDU 1060/700 in configuration mode per the instructions in Section 2.1.4. b. Navigate to Diagnostics → Temp & Power Stats. c. Press Reset Fan Hours. 5.1.3 Integrated ADC Module Replacement To replace the integrated ADC module perform the following procedure: 1. Remove the GDU 1060/700 in accordance with Section 5.1.1. 2. Mark pitot and static lines with ‘P’ and ‘S’, if not already marked, near ADC connections. Figure 5-3 Integrated ADC Module Installation REF. FITTING, 1/8-27 ANPT TYP. 2 PLCS REF. 011-03457-00 ADC MODULE, GDU 700/1060 DISPLAY REF. THUMB SCREW

Rev. 1 Page 5-7 3. Remove pitot and static line from 1/8-27 fittings shown in Figure 5-3 above. 4. Install Pitot and Static lines in new ADC module 1/8-27 fittings. 5. Install GDU 1060/700 in accordance with Section 5.1.6. 5.1.4 Configuration Module Replacement To replace a GDU 1060/700 configuration module, perform the following procedure: NOTE �������������������������������������������������������������������������������������������� ��������������������������� NOTE All item numbers in this procedure reference Figure 5-4. 1. Remove the GDU in accordance with Section 5.1.1. 2. Remove the backshell cover(7) from connector P2 by removing two screws(8). 3. Remove the screw(10) securing the configuration module(1) to the backshell(6). 4. Lift the configuration module(1) out of the backshell(6) and disconnect the wiring harness(3) from the module. 5. Inspect the wiring harness(3) and connector pins(4) for damage, loose wiring, or corrosion. Replace all deficient components if any of these conditions are found. 6. Connect harness to new configuration module. 7. Install new configuration module in connector backshell(6) and re-install cover(7).

Rev. 1 Page 5-8 8. Re-Install GDU 1060/700 in accordance with Section 5.1.6. Figure 5-4 Configuration Module Installation NOTE The GDU will automatically copy the system configuration to the new configuration module upon the first power-up. 5.1.5 Master Configuration Module Replacement NOTE Replacement of the G500/G600 TXi system Master configuration module requires the use of an Installer unlock card and must be performed by an authorized Garmin Dealer. Physical replacement of the master configuration module is identical to the configuration module replacement procedure provided in Section 5.1.4. Following the master configuration module replacement, the system ID will have changed. Any feature unlocks and databases will need to be re-issued for the new system ID by a Garmin dealer. To return the system to service from this condition perform the following steps:

Rev. 1 Page 5-9 NOTE �������������������������������������������������������������������������������������������� ��������������������������� 1. If multiple GDU 1060/700 displays are installed in the system, choose one GDU to act as the new master GDU. 2. Power on all LRUs in the G500/G600 TXi system with all GDUs in configuration mode. 3. From the home screen on each GDU navigate to GDU Type. 4. Configure all GDU ID’s, locations, and unit configurations to match the recorded configuration settings in the configuration log printout. 5. Ensure that Master is selected on the GDU that has been chosen to act as the master configuration module. 6. At this point the G500/G600 TXi system will have a new system ID. System features will need to be unlocked and the system databases will need to be re-installed. The System ID must be updated on Flygarmin.com and then new databases can be downloaded. 7. Insert the feature unlock card in the bottom or right slot of any GDU in the system 8. Navigate to Home → System Management → Feature Enablement and enable system features. 9. Insert the SD card with the saved aircraft configuration file in the Top or left slot of any GDU in the system. 10. Navigate to Home → SD Load 11. Select the aircraft configuration file you wish to load. 12. Select the GDU to configure, and the desired configuration settings to load. 13. Select SD Load. 14. Follow on screen commands. 15. Perform the Configuration Ground check in Section 5.15.1. 5.1.6 Re-installation To replace the GDU 1060/700 perform the following procedure: 1. If equipped with an integrated ADAHRS, align the ADC module with the back of the GDU as shown in Figure 5-3 above and gently press the module into place. 2. Tighten the four(4) thumb screws that secure the ADC module to the back of the GDU to 10 ± 1 LBF-IN. 3. Connect the four(4) wiring connectors and any installed antenna wires to the back of the GDU and tighten the retaining screws. 4. Place the GDU in the instrument panel cutout. 5. Install the four screws (item 1) as shown in Figure 5-1 and Figure 5-2 and tighten to 8 ± 1 LBF-IN. 6. Perform the configuration mode ground check in Section 5.15.1.

Rev. 1 Page 5-10 5.2 GCU 485 Figure 5-5 GCU 485 Installation 5.2.1 Removal Remove the GCU 485 using the following procedure: 1. Remove power to the GCU 485. 2. Insert a 3/32” hex drive tool into the holes in the top and bottom of the front panel. 3. Turn counter-clockwise until the pawl-latches are able to rotate to a horizontal position. 4. Remove the unit from the panel. 5. Disconnect the electrical connector from the back of the unit. LATCH DETAIL UP LOCKED DOWN

Rev. 1 Page 5-11 5.2.2 Re-Installation NOTE Electrical bond between the airframe and the GCU 485 is accomplished through direct metal-to-metal contact between pawl latches and the back side of the panel. Areas as indicated in figure 5-6 must be free of any surface coatings. Figure 5-6 Panel Cutout for GCU 485 To re-install the GCU 485 perform the following procedure: 1. Connect the electrical connector to the back of the GCU 485. 2. Place the unit in the panel cutout, ensuring that the pawl latches are fully retracted and in the horizontal position. 3. Tighten the pawl latches with a 3/32” hex drive tool inserted through holes in GCU 485 face plate. 4. Torque the latches to 20 +/-2 in-lbs. 5. Restore power to the unit. 1.780in 45.2mm 4.970in 126.2mm R0.06in 1.6mm MAX. TYP. 4 PLCS 1.73in 44mm 0.50in 12.7mm TYP. 2 PLCS 0.64in 16.3mm 0.15in 3.8mm TYP. 2 PLCS SURFACE FOR ELECTRICAL BOND PANEL BACK SIDE TYP. 2 PLCS

Rev. 1 Page 5-12 5.3 EIS Annunciator 5.3.1 Removal The EIS caution and warning annunciator can be removed using the following procedure: 1. Using an Aerospace Optics cap extraction tool (P/N 17-150), locate the two extraction slots positioned on either side of the pushbutton cap. 2. Insert the tool into the extraction slots and pull the cap out from the module. NOTE The cap will rotate 90 degrees on two hinged slide retainer pins to allow access to the module mounting screws. 3. Loosen the two small flat head module mounting screws located behind the pushbutton cap until the module can be removed from the housing. 4. Insert an Aerospace Optics connector extraction tool (P/N 18-234) into the slots at the top and bottom of the electrical connector. 5. Push to release the snap tabs in the switch housing and gently pull the connector out of the module. Figure 5-7 EIS Caution and Warning Annunciator Installation ��������������������������� �������������� ������������ ���������������������������� � � ������������������������� ����� ������ ������ ������������ ������������ ������� � ����� ���������������������������������������������������� �� � �������������������������������������������������������������������������������������������������������������� ���������������������������������������������������������������������������������������������������������������� ��������������������������������������������������������������������������� ��� ���� ����������� ����������� � � ����������������� ������������������������������������������������������������������������������������������ ������������������ ���������������������������������������������������������������������������������

Rev. 1 Page 5-13 5.3.2 Re-Installation Re-installation of the annunciator is accomplished using the following procedure: 1. Orient the keyed electrical connector to the module and press together until locked. 2. Orient the annunciator for proper viewing and gently slide the module into the housing until seated. 3. Tighten the mounting screws until the module is fully seated in the housing. 4. Rotate the cap back into position on the module and gently press until secured.

Rev. 1 Page 5-14 5.4 GDC 72 Figure 5-8 GDC 72 Installation (Sheet Metal Shelf Example) 5.4.1 Removal Removal of the GDC 72 Air Data Computer can be accomplished using the following procedure: 1. Remove power to the GDC 72. � ������ ����� ����������� � ������ ����� ��������� ����������� ������������������ ������������������� ������������������ ���������������������� ������������������ ���������������� �������� � � � � � � � � ����� ���������������������������������������������������� �� � �������������������������������������������������������� � ����������������������������������������������������� � ������������������������������������������������������������������������������������������������������������������������ ����������������������������������������������������������������������������������������������� � ����������������������������������� ����������� ��� ���� ����������� ����������� � � ������������ ������������������������������������������������������������������������������ � � ���������� ������������������������������������������������������������������������������������������� � � ������������ ���������������������������������������������������������������������������

Rev. 1 Page 5-15 2. Disconnect electrical connector. 3. Disconnect Pitot-Static lines. 4. Loosen single mounting screw in endplate mount bracket. 5. Lift the side of the GDC 72 where the endplate mount bracket is attached and slide the unit towards the bracket to disengage mounting pawls and remove unit. 5.4.2 Re-Installation 1. Place unit flat on mounting bracket and slide back to engage mounting pawls. 2. Engage mounting screw and torque screw to 15-20 LBF-IN. 3. Connect pitot-static lines. 4. Connect electrical connector. 5.4.3 Checkout Perform a static and pitot system leak test in accordance with the aircraft manufacturers specification and/ or applicable regulations. In accordance with 14 CFR Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GDC 72 are not susceptible to these types of errors. Perform checkout procedures in Section 5.15.2.

Rev. 1 Page 5-16 5.5 GSU 75(), GRS 79 Figure 5-9 GSU 75() Installation (Sheet Metal Shelf Example) NOTE The GRS 79 has the same case and mounting hardware as the GSU 75() with the exception of the Pitot-static ports, which are not present on the GRS 79. Removal and installation procedures are similar for both units. NOTE Loosening of the unit mounting plate and/or the shelf to which the mounting plate is attached requires re-calibration of the AHRS, which requires an installer unlock card. 5.5.1 Removal Removal of the GSU 75() or GRS 79 can be accomplished using the following procedure: 1. Remove power to the unit. 2. Disconnect electrical connector. � ����� ����� ����������� � ����� ����� ��������� ����������� ������������������ ������������������� ������������������ ���������������������������������� ��������������������������� � � � � � � � � ����� ���������������������������������������������������� �� � �������������������������������������������������������� � ����������������������������������������������������� � ������������������������������������������������������������������������������������������������������������������������ ����������������������������������������������������������������������������������������������� � ����������������������������������� ����������� ���� ���� ����������� ����������� � � ������������ ������������������������������������������������������������������������������ � � ��������� ������������������������������������������������������������������������������������������� � � ������������ ���������������������������������������������������������������������������

Rev. 1 Page 5-17 3. Disconnect Pitot-Static lines(GSU75() only). 4. Loosen the two(2) mounting screws on the connector end of the unit. 5. Lift the connector side of the unit and slide the unit towards the connector to remove. 5.5.2 Installation 1. Place the unit on the remote rack. 2. Slide the unit back until the feet are fully engaged with the remote rack. 3. Push down and simultaneously turn each retention screw clockwise. 4. Torque each retention screw to 15-20 in-lbs. 5. Connect Pitot-Static Lines (GSU 75() only). 6. Connect electrical connector. 7. Restore unit power. 5.5.3 Checkout If the mounting bracket bolts have been loosened or bracket mounting(i.e. instrument panel, avionics shelf) has been moved in any way the following AHRS calibration procedures must be performed as described in Section 6 of the G500/G600 TXi Part 23 AML STC Installation Manual (P/N: 190-01717-B3): 1. Pitch/Roll Offset Compensation. 2. Magnetometer Calibration. 3. Compass Swing. 4. Heading offset compensation if required by the previous step. 5. Engine Run-up Vibration check. For the GSU 75() only: Perform a static and pitot system leak test in accordance with the aircraft manufacturers specification and/ or applicable regulations. In accordance with 14 CFR Part 43 Appendix E, paragraph (b)(2), Garmin specifies a test procedure equivalent to Part 43 Appendix E, paragraph (b)(1) with two exceptions. The tests of sub-paragraphs (iv) (Friction) and (vi) (Barometric Scale Error) are not applicable because the digital outputs of the GSU 75() are not susceptible to these types of errors. Perform checkout procedures in Section 5.15.2.

Rev. 1 Page 5-18 5.6 GAD 43/43e NOTE The GAD 43/43e may be removed and re-installed without a GDU installer unlock card. If the unit is replaced with a new GAD 43/43e or if the software is updated, a GDU installer unlock card is necessary to configure the new unit. Figure 5-10 GAD 43 Installation (Sheet Metal Shelf Example) � ����� ����� ��������� ����������� � ����� ����� ����������� ������������������ �������������� � � � � � � ����� ���������������������������������������������������� �� � ���������������������������������������������������� � ����������������������������������������������������� � ������������������������������������������������������������������������������������������������������������ ����������������������������������������������������������������������������������������������������������� � ����������������������������������� ����������� ��� ���� ����������� ����������� � � ������������ ������������������������������������������������������������������������������ � � ���������� ������������������������������������������������������������������������������������������� � � ������������ ���������������������������������������������������������������������������

Rev. 1 Page 5-19 5.6.1 Removal The GAD 43/43e can be removed using the following procedure: 1. Remove power from the GAD 43/43e. 2. Disconnect the electrical connector(s) from the GAD 43/43e. 3. Unscrew the four mounting screws. 5.6.2 Re-Installation Re-installation of the GAD 43/43e is accomplished by performing the removal process in reverse. Torque the mounting screws to the specifications provided in Figure 5-10. 5.6.3 Checkout If the GAD 43/43e has been replaced, perform the following procedure: 1. Insert installer unlock card in the GDU connected to the GAD. 2. Power the G500/G600 TXi system up on configuration mode. 3. Navigate to Interfaces → Adapter → Settings 4. Configure interface settings per the printed configuration log. 5. Perform checkout procedures in Section 6.2 and Section 6.7 of the G500/G600 TXi Part 23 AML STC Installation Manual (P/N: 190-01717-B3)

Rev. 1 Page 5-20 5.7 GEA 110 Figure 5-11 GEA 110 Installation (Mounted Directly to Airframe Example) � ����� ����� ����������� � ����� ����� ��������� ����������� ������������������ ������� � � � � � � � � � � � ����� ���������������������������������������������������� �� � ��������������������������������������������� � ����������������������������������������������������� � ������������������������������������������������������������������������������������������������������������ ����������������������������������������������������������������������������������������������������������� � ���������������������������������� ����������� ���� ���� ����������� ����������� � � ����������� ������������������������������������������������������������������������������������ � � ����������� ������������������������������������������������������������������������������������ � � ���������� ������������������������������������������������������������������������������������������� � � ������������ ���������������������������������������������������������������������������

Rev. 1 Page 5-21 Figure 5-12 GEA 110 Installation (Mounted on a Tray Example) � ����� ����� ����������� � ����� ����� ��������� ������������ ������������������ ������� ������������������ ������������������ ��� � � � �� � � � � ����� ���������������������������������������������������� �� � ���������������������������������������������������������� � ����������������������������������������������������� � ������������������������������������������������������������������������������������������������������������ ����������������������������������������������������������������������������������������������������������� � ����������������������������������� ����������� ���� ���� ����������� ����������� � � ������������ ������������������������������������������������������������������������������ � � ���������� ������������������������������������������������������������������������������������������� �� � ������������ ���������������������������������������������������������������������������

Rev. 1 Page 5-22 5.7.1 Removal To remove the GEA 110, perform the following procedure: 1. Remove power to the GEA 110. 2. Disconnect the two electrical connectors. 3. If the unit is mounted on a tray as shown in Figure 5-12, pull out on the mounting knob and turn counterclockwise to loosen it enough to rotate the arm down and away from the unit 4. If the unit is mounted to the airframe or back of the GDU using screws as shown in Figure 5-11, loosen the four screws securing the unit to the airframe or GDU. 5.7.2 Re-Installation To re-install the GEA 110, perform the removal procedures in reverse. If the unit is mounted to the airframe or back of the GDU, torque the screws to the specification in Figure 5-11. For units that are mounted in a mounting tray, tighten the mounting screw by hand until the unit is secure. If the GEA 110 was replaced, the sensor configurations must be loaded to the new unit using the following procedure: 1. Insert saved configuration SD card in the Top or Left SD card slot of any GDU 1060/700 directly connected to the GEA 110. 2. Power on the GDU that is physically wired to the GEA 110 in configuration mode. 3. Press SD Load. 4. Select the appropriate Aircraft Configuration File. 5. Select the current GDU as the From SD and To GDU. 6. Select the EIS Sensor Configuration check box. 7. Select SD Load. 5.7.3 Checkout Perform the following checkout procedures: 1. Configuration Mode Ground Checks as described in Section 5.15.1. If the GEA 110 does not pass the checks in this step, load the sensor configurations using the procedure in Section 5.7.2 above and perform the checkout procedure again. Perform the following checkout procedure only if the GEA was replaced or did not initially pass the checkout procedure above: 1. EIS Ground Checks as described in Section 6.5 of the G500/G600 TXi Part 23 AML STC Installation Manual (P/N: 190-01717-B3).

Rev. 1 Page 5-23 5.8 GBB 54 Figure 5-13 GBB 54 Installation (Sheet Metal Shelf Example) � � ������ ������ � ������ ����� ����������� � ����� ����� ��������� ����������� � � � � � � � � � � � � � � � � � ������������������������� �� � � � � � ����� ���������������������������������������������������� �� � ���������������������������������������������������� � ����������������������������������������������������� � ������������������������������������������������������������� � ���������������������������������������� � ����������������������������������������������� � ������������������������������������������������������������������������������������������������������������������������������������ ����������������������������������������������������������������������������������� � ����������������������������������� ����������� ��� ���� ����������� ����������� � �� ������������� ��������������������������������������������������������������������� � � ��������� ����������������������������������������������������������� � � ����������� ����������������������������������������������������������� � � ������������ ������������������������������������������������������������������������������ � � ��������� ������������������������������������������������������������������������������������������� � � ������������ ��������������������������������������������������������������������������� ��� � ����������� ������������������������������������������������������������������������� � � ������� ��������������������������������������������������������� � � ������������ ���������������������������������������������������������� � � ������������ ��������������

Rev. 1 Page 5-24 5.8.1 Removal NOTE All item numbers in this section refer to Figure 5-13. To remove the GBB 54 utilize the following procedure: 1. Ensure the GDU connected to the GBB 54 is powered off. 2. Disconnect the electrical connector. 3. Loosen the tube nut(3) and disconnect the vent tube(2) from the battery(1). 4. Remove the four screws(7) holding the GBB 54. 5.8.2 Battery Cell Replacement NOTE The GBB 54 battery cell replacement kit (P/N:010-01331-02) must be obtained from an authorized Garmin dealer. If access is available to remove four bolts (1) on connector side, unit removal is not required. Refer to Figure 5-14. Removal Steps 1. Remove the four bolts (1) and four nuts (7). 2. Pull battery cover (2) from housing (5). 3. Discard gasket (3). 4. Remove four bolts (8) that secure the battery to battery cover 5. Pull battery pack (4) from cover receptacle (2). Replacement Steps 1. Apply Dow Corning 4 dielectric grease, or equivalent, to pins in battery pack connector (6). 2. Push battery pack connector (6) into cover receptacle (2). 3. Apply Loctite 242 (blue) thread-locking compound, or equivalent to bolts (8). 4. Secure battery (4) to cover (2) with bolts (8). 5. In a cross-tightening sequence, torque bolts (8) to 20 to 25 in-lbs. 6. Place gasket (3) over battery pack (4) until flush with battery cover (2). 7. Insert battery cover (2) with gasket (3) and battery pack (4) into housing (5). 8. Insert the four bolts (1) and nuts (7). 9. In cross-tightening sequence, torque bolts (1) to 40 to 60 in-lbs.

Rev. 1 Page 5-25 Figure 5-14 GBB 54 Battery Cell Replacement 5.8.3 Re-Installation To re-install the GBB 54 perform the following procedure: 1. Install four screws(7) securing the GBB 54 and torque to the specification in Figure 5-13. 2. Connect the vent tube to the GBB 54 and tighten the tube nut. 3. Connect the electrical connector. 4. Perform the checkout in Section 5.8.4. 5.8.4 Checkout 1. Perform a Configuration Mode Ground Check as described in Section 5.15.1. 2. Perform the Backup Battery Check as described in Section 5.13.5. 5.9 GMU 44 NOTE Removal, re-installation, or replacement of the GMU 44 will require a recalibration of the AHRS which requires the use of a GDU installer unlock card. In addition, any removal or BATTERY CELL INSERTION (STEP 7) 1 2 3 4 CROSS-TIGHTENING SEQUENCE FOR BOLTS (STEP 9) CROSS-TIGHTENING SEQUENCE FOR BOLTS (STEP 5) FRONT OF BATTERY 1 2 3 5 4 x4 8 6 x4 7 x4 1 2 3 4