Garmin GTS 8 Series Maintenance Manual
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Garmin GTS 8 Series Maintenance Manual

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GTS 8XX
Part 23 AML STC Maintenance Manual
with Instructions for Continued Airworthiness
Aircraft Make, Model, Registration Number, and Serial
Number, and accompanying STC configuration
information in Appendix A, must be completed and saved
with aircraft permanent records.
190-01279-01
July 2018
Revision 2

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  • Page 1 GTS 8XX Part 23 AML STC Maintenance Manual with Instructions for Continued Airworthiness Aircraft Make, Model, Registration Number, and Serial Number, and accompanying STC configuration information in Appendix A, must be completed and saved with aircraft permanent records. 190-01279-01 July 2018 Revision 2...
  • Page 2 Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to...
  • Page 3 Updated title of Appendix A to “Aircraft Installation Record.” Added GDU 7XX equipment reference to Table A-1 GTS 8XX System Interfaces to A.2.1 Garmin Equipment. Updated aircraft profile to Figure A-2 Equipment Location and Wire Routing - Twin Engine Airplane.
  • Page 4 Information in this document is subject to change without notice. For updates and supplemental flyGarmin.com information regarding the operation of Garmin products, visit DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES WARNING A Warning means injury or death is possible.

  • Page 5: Table Of Contents

    TABLE OF CONTENTS INTRODUCTION..........................1-1 Scope ............................1-2 Organization ..........................1-2 Definitions and Abbreviations ....................1-3 Related Publications ........................1-3 Distribution..........................1-4 GENERAL DESCRIPTION ......................2-1 System Overview ........................2-2 Equipment Description.......................2-2 Electrical Current Requirements ....................2-2 Interface Summary ........................2-3 Ground Plane..........................2-4 CONTROL AND OPERATION.......................3-1 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS............4-1 Airworthiness Limitations......................4-2 Servicing Information ........................4-2 Maintenance Intervals ........................4-3...
  • Page 6 LIST OF FIGURES Figure 2-1 GTS 8XX System Interface Diagram ..................2-3 Figure 3-1 GTS 8XX Traffic System Controls ..................3-1 Figure 5-1 GTS Assert Log Diagnosis Tool ..................5-3 Figure 7-1 GTS Processor Install Tool - Normal Tab ................7-4 Figure 7-2 GTS Processor Install Tool - Configuration Tab ..............7-6 Figure 7-3 GTS Processor Install Tool - Upload Tab ................7-7 Figure 7-4...
  • Page 7 Data Source Status Icons .......................7-6 Table 7-3 Ramp Test Intruder Scenario ....................7-10 Table A-1 GTS 8XX System Interfaces to Garmin Equipment ............A-3 Table A-2 GTS 8XX System Interfaces to Other Equipment ...............A-4 Table A-3 GTS 8XX Equipment Locations ..................A-5 Table B-1 Composite Airframe Bonding Strap Assembly ..............B-5 Table B-2 Bonding Strap Assembly for Air-craft with Tubular Airframes ........
  • Page 8 1 INTRODUCTION 1.1 Scope........................... 1-2 1.2 Organization........................1-2 1.3 Definitions and Abbreviations .................... 1-3 1.3.1 Definitions ..........................1-3 1.3.2 Abbreviations ..........................1-3 1.4 Related Publications ......................1-3 1.5 Distribution ......................... 1-4 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page 1-1...

  • Page 9: Scope

    1.1 Scope This document provides maintenance instructions and Instructions for Continued Airworthiness (ICA) for the GTS 8XX Traffic System as installed under STC SA02121SE. This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and 14 CFR Part 23 Appendix G. 1.2 Organization The following outline briefly describes the organization of this manual: Section 2: System Description...

  • Page 10: Definitions And Abbreviations

    1.3 Definitions and Abbreviations 1.3.1 Definitions “GTS 8XX system” refers to the complete system, including GTS 800/820/850/825/855, antennas, and associated equipment. “GTS Processor” refers to the GTS 825 or 855 LRU at the core of the GTS 8XX system. “GTS 8X0” refers to the GTS 800, 820, or 850 LRU at the core of the GTS 8XX system. 1.3.2 Abbreviations The following terminology is used within this document:...

  • Page 11: Distribution

    Owner/operators may obtain the latest revision of this document from A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant. 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev.

  • Page 12: General Description

    2 GENERAL DESCRIPTION 2.1 System Overview........................ 2-2 2.2 Equipment Description ....................... 2-2 2.3 Electrical Current Requirements..................2-2 2.4 Interface Summary......................2-3 2.5 Ground Plane ........................2-4 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page 2-1...

  • Page 13: System Overview

    2.1 System Overview The GTS 8XX system is designed to use active interrogations of Mode S and Mode C transponders to provide Traffic Advisories (TA) to the pilot. Traffic is displayed on a multifunction display (MFD) via ARINC 429 and/or High Speed Data Bus (HSDB). An overview of the GTS 8XX system and its interfaces are shown in Figure 2-1.

  • Page 14: Interface Summary

    2.4 Interface Summary The GTS 8XX system is designed as an open architecture system that uses ARINC 429, RS-232, and HSDB communications interfaces, as well as analog and discrete inputs and outputs. GTS 8XX interfaces include: • Three RS-232 Inputs/Outputs •...

  • Page 15: Ground Plane

    2.5 Ground Plane Ground plane definition varies with airframe type and aircraft model, as defined in Table 2-2. Refer to the periodic test and reconditioned resistance values corresponding to these ground plane definitions when performing the equipment bonding test per Section 4.3. Ensure that all GTS 8XX system antenna coaxial cables are disconnected during resistance checks.

  • Page 16: Control And Operation

    3 CONTROL AND OPERATION The GTS 8XX system includes functions that can be controlled via configured displays or external switches. Figure 3-1 summarizes GTS 8XX system control. Refer to display documentation for traffic system control details. Operate/Standby The Operate/Standby function toggles the GTS 8XX system between Operate and Standby modes. Operate/Standby may be controlled through a compatible display or external switch.

  • Page 17: Instructions For Continued Airworthiness

    Special Tools ..........................4-2 4.3 Maintenance Intervals......................4-3 This document is designed for use by the installing agency of the Garmin GTS 8XX Traffic System as Instructions for Continued Airworthiness in response to 14 CFR 23.1529 and 14 CFR 23 Appendix G. This ICA includes information required by the operator to adequately maintain the GTS 8XX system installed under the Approved Model List (AML) STC.

  • Page 19: Maintenance Intervals

    4.3 Maintenance Intervals Maintenance Item Interval Description/Procedure Visually inspect the GTS 8XX system antenna(s) for the following: • Environmental seal damage or decomposition • Cracks in the antenna body • Mounting structure damage or deformation • Corrosion on metallic structures If the antenna is not properly attached, or the antenna seal shows signs of damage or deterioration, complete the following procedure: 1.
  • Page 20 Maintenance Item Interval Description/Procedure An electrical bonding test must be performed on all GTS 8XX system antennas. The test procedure is: Antenna electrical bonding test 1. Gain access to the antenna. (Not applicable to composite 2. Disconnect the coaxial cable connector(s) from the antenna. VFR-only models) 3.
  • Page 21 Maintenance Item Interval Description/Procedure In the event of a suspected or actual lightning strike to the aircraft, the bonding components for the Equipment bonding visual Suspected or GTS 8XX: bonding straps and associated hardware (if applicable) must be inspected. If any damage is inspection –...

  • Page 22: Troubleshooting

    5 TROUBLESHOOTING 5.1 Troubleshooting Software....................5-2 5.1.1 GTS Install Tool.........................5-2 5.1.2 GTS Assert Log Diagnosis Tool ....................5-2 5.2 Assert Log Diagnosis......................5-3 5.3 System Faults........................5-4 This section provides information to assist troubleshooting if problems occur after completing the maintenance. Refer to the GTS 8XX System Configuration Log, retained in the aircraft permanent records, for a list of the interfaced equipment and system configuration data.

  • Page 23: Troubleshooting Software

    5.1.1 GTS Install Tool Complete the following procedure to install the GTS Install Tool. From the Garmin Dealer Resource Center, download either the GTS Processor Install Tool (P/N 006-A0242-10) for the GTS 825/855 or the GTS 8X0 Install Tool (P/N 006-A0242-00) for the GTS 800/820/850.

  • Page 24: Assert Log Diagnosis

    This tool allows for troubleshooting the GTS Assert Log using a computer (installed with Microsoft Windows XP or later and Microsoft, NET Framework 2.0 SP2 or later) and is available for download from the Garmin Dealer Resource Center. A detailed user guide is found under the Help menu of the Assert Diagnosis Tool.

  • Page 25: System Faults

    GTS 8XX system faults will annunciate on interfaced compatible displays, such as the GDU 620 and on the GTS Install Tool’s Normal tab. Fault descriptions and corrective actions are listed in Table 5-1. NOTE If any system fault persists after performing the associated troubleshooting actions, return the GTS 8XX to Garmin for service. Table 5-1 GTS 8XX System Faults Fault...
  • Page 26 Fault Description Corrective Action 1. Cycle GTS 8XX power and run self-test. [1] Receive frequency synthesizer is not 1090 MHz locked. 2. Analyze the assert log. See Section 5.2. 1. Check antenna installation and all cable connections and run self-test. Ensure that self-test occurs in an area free of buildings and large structures that might reflect signals.

  • Page 27: Equipment Removal And Re-Installation

    6 EQUIPMENT REMOVAL AND RE-INSTALLATION 6.1 GTS 8X0 ..........................6-2 6.2 GPA 65 ..........................6-2 6.3 GTS Processor ........................6-3 6.4 Configuration Module......................6-3 6.5 Antenna Coaxial Cable ....................... 6-4 6.6 Directional Antenna ......................6-6 6.7 Omni-directional (Monopole) Antenna ................6-7 This section contains procedures and requirements for removal and re-installation of GTS 8XX equipment.

  • Page 28: Gts 8X0

    6.1 GTS 8X0 Removal 1. Ensure there is no power supplied to the GTS 8X0. 2. Gain access to the GTS 8X0. See Appendix A for equipment locations. 3. Disconnect the D-sub and QMA antenna coaxial cable connectors from the GTS 8X0. 4.

  • Page 29: Gts Processor

    6.3 GTS Processor Removal 1. Ensure there is no power supplied to the GTS 8XX. 2. Gain access to the GTS 8XX. See Appendix A for equipment locations. 3. Disconnect the D-sub and antenna coaxial cable connectors from the GTS 8XX. 4.

  • Page 30: Antenna Coaxial Cable

    6.5 Antenna Coaxial Cable The GTS 8XX system has stringent coaxial cable requirements. Any damaged or malfunctioning section of antenna coaxial cable must be replaced. The replacement must include the entire cable length from connector to connector. See Table 6-1. NOTE To avoid attenuation issues, replace coaxial cables with identical part numbers.

  • Page 31: Table 6-1 Recommended Coaxial Cable Length

    Coaxial Cable Assembly Repair and Replacement An individual coaxial cable may be repaired with a maximum reduction in length of two inches from the length specified in Table 6-1. Table 6-1 Recommended Coaxial Cable Length Connector Connector Length Length Length Length Length Cable Loss...

  • Page 32: Directional Antenna

    6.6 Directional Antenna Removal 1. Ensure there is no power supplied to the GTS 8XX. 2. Remove sealant from the antenna’s fasteners. 3. Remove the fasteners attaching the antenna to the fuselage. 4. Remove environmental seal between the antenna and fuselage skin and pull the antenna away from the fuselage.

  • Page 33: Omni-Directional (Monopole) Antenna

    6.7 Omni-directional (Monopole) Antenna Removal 1. Ensure there is no power supplied to the GTS 8XX. 2. Remove sealant from the antenna’s fasteners. 3. Remove the fasteners attaching the antenna to the fuselage. 4. Remove environmental seal between the antenna and fuselage skin and pull the antenna away from the fuselage.

  • Page 34: Return To Service

    7 RETURN TO SERVICE 7.1 Maintenance Records......................7-2 7.2 Return to Service Requirements ..................7-2 7.2.1 GTS 8XX............................7-2 7.2.2 GTS 8XX Configuration Module....................7-2 7.2.3 Antenna ............................7-2 7.3 Configuration and Checkout ....................7-3 7.3.1 GTS 8XX Install Tools ......................7-3 7.4 System Checkout ........................ 7-8 7.4.1 System Test and Audio Check ....................7-8 7.4.2...

  • Page 35: Maintenance Records

    Feature control of the GTS 8XX as a TAS or TCAS I is stored in the GTS P8001 backshell configuration module. Replacement of the configuration module will require that the TAS or TCAS I feature be re-enabled. Contact Garmin Aviation Product Support for details.

  • Page 36: Configuration And Checkout

    Microsoft Windows XP or later) and the GTS Processor Install Tool (P/N 006-A0242-10) for the GTS 825/855 or the GTS 8X0 Install Tool (P/N 006-A0242-00) for the GTS 800/820/850. The tool is available for download from the Garmin Dealer Resource Center.

  • Page 37: Figure 7-1 Gts Processor Install Tool - Normal Tab

    7.3.1.1 Normal Tab The Normal tab, shown in Figure 7-1, displays GTS 8XX system status during normal operation, including operating status, antenna alpha values, system faults, and status flags. The Normal tab is also used to enable or disable GTS 8XX system ground test.

  • Page 38: Table 7-1 Gts 8Xx System Flag Status

    Ground Test The Ground Test feature simulates aircraft flight conditions of 50,000 feet altitude and 0º heading for the purpose of conducting the ramp and return to service tests described in Section 7.4.3. Table 7-1 GTS 8XX System Flag Status Flag Active Flag Description Transponder #1 Active...

  • Page 39: Figure 7-2 Gts Processor Install Tool - Configuration Tab

    Table 7-2 Data Source Status Icons Icon Status Active Inactive Unknown Figure 7-2 GTS Processor Install Tool - Configuration Tab Saving or Canceling Configuration Settings • The Set Active key saves highlighted configuration settings to the GTS 8XX configuration module and reboots the GTS 8XX with the configuration settings •...

  • Page 40: Figure 7-3 Gts Processor Install Tool - Upload Tab

    The Assert tab can be used to generate an assert log, which can be diagnosed using the Assert Log Diagnosis Tool (P/N 006-A0244-00) or submitted to Garmin Technical Support for troubleshooting. See Section 5.2 for download and installation instructions. 1. Select Get Assert Log to retrieve the assert log from the GTS 8XX.

  • Page 41: System Checkout

    7.4 System Checkout This section details aspects of the GTS 8XX system checkout. It includes traffic audio and system interface checks, plus detailed procedures for conducting Ramp and Return to Service Test procedures. An alternate flight check procedure is also provided. 7.4.1 System Test and Audio Check Verify that the GTS 8XX system produces aural alerts.

  • Page 42: Figure 7-5 Gts Processor Install Tool - Normal Tab

    7.4.2 Interface Check Using the applicable install tool, verify there are no system faults (bold red text) shown on the Normal tab of the GTS Processor Install Tool (P/N 006-A0242-10) or GTS 8X0 Install Tool (P/N 006-A0242-00). Then verify status flags are present (bold black text) for interfaces that are connected and valid. See Figure 7-5.

  • Page 43: Table 7-3 Ramp Test Intruder Scenario

    2. Using the Configuration tab of GTS Install Tool, set all A429/Analog Radar Altitude Sources to Disabled (see Figure 7-2).The GTS 8XX inputs must be in an on-ground state to enter Ground Test mode. This may be accomplished by one of the following methods: Squat switch input indicates on-ground.

  • Page 44: Figure 7-6 Target Aircraft Position For Traffic Display Flight Check

    7.4.3.1 Alternate Flight Check A flight check of the GTS 8XX system may be performed in the event a TIC TR220 or other ramp tester is unavailable. The flight check is performed with the GTS 8XX system test aircraft in addition to a target aircraft with an operating transponder installed.
  • Page 45 5. To verify the 12 o’clock position, maneuver the target aircraft approximately within 4 NM directly ahead of the test aircraft while maintaining a 1,000-foot altitude separation. Obtain a visual of the target aircraft and verify the target aircraft is depicted at the 12 o’clock position on the traffic display.

  • Page 46: Appendix A Aircraft Installation Record

    APPENDIX A AIRCRAFT INSTALLATION RECORD A.1 General Installation Information..................A-2 A.2 Interfaced Equipment......................A-3 A.2.1 Garmin Equipment ........................A-3 A.2.2 Other Equipment ........................A-4 A.3 Equipment Locations and Wire Routing ................A-5 A.4 Configuration Log......................A-8 A.5 Aircraft Wiring Diagrams ....................A-9 A copy of this appendix must be used to record information for installation of the GTS 8XX system on a specific aircraft.

  • Page 47: General Installation Information

    A.1 General Installation Information Aircraft Aircraft Make and Model: Serial Number: Registration Number: Part Number: Serial Number: Mod Level: Top Directional Antenna Model: Part Number: Serial Number: Bottom Antenna [N/A] Directional Bottom Antenna Type: Omni-directional (Monopole) Model: Part Number: Serial Number: Software Versions Main: FPGA:...

  • Page 48: Table A-1 Gts 8Xx System Interfaces To Garmin Equipment

    A.2.1 Garmin Equipment Table A-1 may be used to document GTS 8XX system interfaces with other Garmin equipment installed in the aircraft. GTS 8XX system interfaces to all equipment listed in Table A-1 are covered by this STC. Refer to installation-specific interconnect diagrams retained with the aircraft’s permanent records for detailed...

  • Page 49: Table A-2 Gts 8Xx System Interfaces To Other Equipment

    A.2.2 Other Equipment Use Table A-2 to document GTS 8XX system interfaces with other equipment installed in the aircraft but not listed in Table A-1. Refer to the STC IM to determine whether interfaces between the GTS 8XX and equipment not listed in Table A-1 are covered by this STC. Table A-2 GTS 8XX System Interfaces to Other Equipment Model(s) Interface...

  • Page 50: Equipment Locations And Wire Routing

    A.3 Equipment Locations and Wire Routing Record locations of the equipment of the GTS 8XX system in Table A-3. Table A-3 GTS 8XX Equipment Locations Location Description Notes GTS 8XX Top Antenna Bottom Antenna (Optional) Figure A-1 and Figure A-2 depict approximate locations of the GTS 8XX system components as well as the following details in a single-engine and twin-engine airplane, respectively: ...

  • Page 51: Figure A-1 Equipment Location And Wire Routing - Single-Engine Airplane

    Figure A-1 Equipment Location and Wire Routing - Single-Engine Airplane 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page A-6...

  • Page 52: Figure A-2 Equipment Location And Wire Routing - Twin Engine Airplane

    Figure A-2 Equipment Location and Wire Routing - Twin Engine Airplane 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page A-7...

  • Page 53: Configuration Log

    A.4 Configuration Log Figure A-3 is an electronic fillable configuration log. Acrobat Reader 8.0 or later is necessary to view and fill out the form. You can download Acrobat Reader by visiting www.adobe.com. Pressure Altitude Source Magnetic Heading Source [N/A] [Disabled] Rx Channel: [Disabled]...

  • Page 54: Aircraft Wiring Diagrams

    A.5 Aircraft Wiring Diagrams Attach the aircraft wiring diagrams showing the equipment installed by this STC or a markup of the interconnect diagrams from the STC installation manual detailing which equipment is installed and how it is connected. 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev.

  • Page 55: Appendix Belectrical Bonding Procedures

    APPENDIX B ELECTRICAL BONDING PROCEDURES B.1 Considerations for Untreated or Bare Dissimilar Metals............B-2 B.2 Preparation of Aluminum Surfaces..................B-3 B.3 Composite Aircraft ......................B-4 B.4 Tube and Fabric Aircraft.....................B-9 Refer to SAE ARP 1870 Section 5 when surface preparation is required to achieve electrical bond. 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev.

  • Page 56: Considerations For Untreated Or Bare Dissimilar Metals

    B.1 Considerations for Untreated or Bare Dissimilar Metals The correct material finish is important when mating untreated or bare dissimilar metals. Materials should be galvanically-compatible. When corrosion protection is removed to make an electrical bond, any exposed area after the bond is completed should be protected again. Additional guidance can be found in AC 43.13-1B and SAE ARP 1870.

  • Page 57: Preparation Of Aluminum Surfaces

    B.2 Preparation of Aluminum Surfaces The following general procedure is recommended to prepare an aluminum surface for proper electrical bonding: 1. Clean grounding location with solvent. 2. Remove non-conductive films or coatings from the grounding location. 3. Apply a chemical conversion coat, such as Alodine 1200, to the bare metal. 4.

  • Page 58: Composite Aircraft

    B.3 Composite Aircraft Use the following guidance when repairing or replacing electrical bonding components. Use aluminum tape (3M P/N 438 or other adhesive-backed dead soft aluminum foil with minimum metal thickness of 7.2 mils) when replacing existing aluminum foil that has been damaged. If using a bonding tape, a maximum length-to-width ratio of 7:1 must be maintained (i.e., up to seven inches in length for every one inch in width).

  • Page 59: Table B-1 Composite Airframe Bonding Strap Assembly

    2. Ensure the existing ground location is prepared in accordance with Appendix Section B.2. 3. Route the aluminum tape between the GTS 8XX install rack and the grounding location. If needed to maintain the length-to-width ratio, the tape width can be overlapped in more than one strip. If two or more pieces of tape must be joined end-to-end, they can be joined as illustrated in Figure B-5.

  • Page 60: Figure B-5 Aluminum Tape Joint

    3" ADHESIVE SIDE APPLY ALUMINUM TAPE PATCH OVER JOINT FOLD ALUMINUM TAPE JOINT ADHESIVE SIDE ADHESIVE SIDE 1" APPLY ALUMINUM TAPE TO SECONDARY STRUCTURE SECONDARY STRUCTURE Figure B-5 Aluminum Tape Joint SECONDARY STRUCTURE 0.063" ALUMINUM PLATE GROUND STUD-COMMON TO INSTRUMENT PANEL ALUMINUM BONDING STRAP TAPE...

  • Page 61: Figure B-7 Gts Processor Aluminum Tape Installation

    GTS PROCESSOR (VERTICAL MOUNT) ALUMINUM PLATE 7:1 LENGTH-TO-WIDTH RATIO MEASUREMENT BEGINS AT LAST POINT OF ELECTRICAL CONTACT WITH MOUNTING RACK ALUMINUM TAPE AIRCRAFT STRUCTURE GTS PROCESSOR (VERTICAL MOUNT) ALUMINUM PLATE ALUMINUM TAPE AIRCRAFT STRUCTURE (E.G. EQUIPMENT SHELF) Figure B-7 GTS Processor Aluminum Tape Installation Sheet 1 of 2 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual...
  • Page 62 NOTES: MINIMUM THICKNESS OF ALUMINUM PLATE IS 0.032 INCHES. ALUMINUM PLATE LENGTH AND WIDTH MUST BE AT LEAST 0.5 INCHES LARGER THAN GTS PROCESSOR FOOTPRINT. REMOVE ALL BURRS AND SHARP EDGES. RADIUS ALL SHARP CORNERS (0.125-INCH MINIMUM, 0.25-INCH RECOMMENDED). MINIMUM DIMENSIONS SHOWN IN DRAWING. IF MULTIPLE STRIPS OF TAPE ARE USED TO CREATE THE SIX-INCH TAPE WIDTH, ENSURE THAT PLATE IS IN CONTACT WITH ALL STRIPS OF TAPE.

  • Page 63: Tube And Fabric Aircraft

    B.4 Tube and Fabric Aircraft If it is necessary to replace the existing bonding clamp, install a new conductive clamp for bonding in accordance with AC 43.13-1B Chapter 11 and the following criteria: • Use cadmium plated steel clamp, nut, and washers. Only AN735-6 and larger diameter clamps are permitted for the bonding location.

  • Page 64: Table B-2 Bonding Strap Assembly For Air-Craft With Tubular Airframes

    Table B-2 Bonding Strap Assembly for Air-craft with Tubular Airframes Item Number Description See Figure B-8 FOR CONDUCTIVE CLAMP Bonding clamp, AN735-X (AN735-6 or larger is required), Steel Tinned copper flat braid, 3/4”, QQB575F36T781 Tinned copper tubular braid, 7/16”, QQB575R30T437 Terminal lug, #10, uninsulated, MS20659-130 Bolt, #10, AN3-XA Lock washer, #10, NASM25338-43...

  • Page 65: Figure B-8 Electrical Bonding Using Conductive Clamp

    MOUNTING PLATE AIRCRAFT FRAME Figure B-8 Electrical Bonding Using Conductive Clamp Sheet 1 of 2 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page B-11...
  • Page 66 TUBE CLAMP TONGUES SHELF Figure B-8 Electrical Bonding Using Conductive Clamp Sheet 2 of 2 190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page B-12...

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