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GTS 825 TAS
User manual
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Garmin GTS 825 TAS, GTS 800 TAS User manual

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
© 2014-2018 Garmin International or its subsidiaries
All Rights Reserved
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RECORD OF REVISIONS
Revision Revision Date Description
1 05/01/2014 Initial Release.
2
07/25/2018
Added information pertaining to the GTS 800, 820, and 850.
CURRENT REVISION DESCRIPTION
Section Description of Change
Updated “GTS Processor” to “GTS 800/820/850/825/855.”
1.3.1
1.4 Added GTS 8X0/GPA 65 (GTS 800/GTS 820/GTS 850) Installation (P/N 190-00587-00).
2.3
4.3
5.1 Added “GTS 8X0 Install Tool (P/N 006-A0242-00).”
5.3 Updated “Baro Altitude” fault to “Pressure Altitude” in Table 5-1 GTS 8XX System Faults.
6.1 Added Section 6.1 GTS 8X0.
Updated “GTS Processor LRU” to “GTS 825 or 855 LRU.”
Added “GTS 8X0 refers to the GTS 800, 820, or 850 LRU at the core of the GTS 8XX system.”
Added GTS 800 and GTS 820/850 requirements to Table 2-1 GTX 8XX System Current Requirements.
Updated procedure for antenna visual inspection to define inspection criteria.
Updated procedure for antenna visual inspection - suspected lightning strike to include inspection criteria.
6.2 Added Section 6.2 GPA 65.
7.3 Added content for GTS 8X0 Install Tool (P/N 006-A0242-00).
7.3.1 Added note regarding GTS 8XX install tools.
Appendix A Updated title of Appendix A to “Aircraft Installation Record.”
A.2.1
A.3
Appendix B Updated title of Appendix B to “Electrical Bonding Procedures.”
B.3
B.4 Added bonding strap restriction of six inches.
Added GDU 7XX equipment reference to Table A-1 GTS 8XX System Interfaces to Garmin Equipment.
Updated aircraft profile to Figure A-2 Equipment Location and Wire Routing - Twin Engine Airplane.
Added flag notes for Figure B-7.
Added 5:1length-to-width ratio requirement.
Added bonding strap restriction of six inches.
190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page ii
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
WARNING
CAUTION
NOTE
This document may contain information that is subject to the Export Administration Regulations (EAR) issued by the United States Department of Commerce (15 CFR, Chapter VII, Subchapter C) and may not be exported, released, or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license.
Information in this document is subject to change without notice. For updates and supplemental information regarding the operation of Garmin products, visit
flyGarmin.com.
DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES
A Warning means injury or death is possible.
A Caution means that damage to the equipment is possible.
A Note provides additional information.
TABLE OF CONTENTS
1 INTRODUCTION..............................................................................................................................1-1
1.1 Scope ..........................................................................................................................................1-2
1.2 Organization ...............................................................................................................................1-2
1.3 Definitions and Abbreviations ...................................................................................................1-3
1.4 Related Publications...................................................................................................................1-3
1.5 Distribution.................................................................................................................................1-4
2 GENERAL DESCRIPTION.............................................................................................................2-1
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
3 CONTROL AND OPERATION.......................................................................................................3-1
4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS.........................................................4-1
4.1 Airworthiness Limitations..........................................................................................................4-2
4.2 Servicing Information ................................................................................................................4-2
4.3 Maintenance Intervals ................................................................................................................4-3
5 TROUBLESHOOTING ....................................................................................................................5-1
5.1 Troubleshooting Software ..........................................................................................................5-2
5.2 Assert Log Diagnosis .................................................................................................................5-3
5.3 System Faults .............................................................................................................................5-4
6 EQUIPMENT REMOVAL AND RE-INSTALLATION...............................................................6-1
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
7 RETURN TO SERVICE ...................................................................................................................7-1
7.1 Maintenance Records .................................................................................................................7-2
7.2 Return to Service Requirements.................................................................................................7-2
7.3 Configuration and Checkout ......................................................................................................7-3
7.4 System Checkout........................................................................................................................7-8
APPENDIX A AIRCRAFT INSTALLATION RECORD...................................................................A-1
A.1 General Installation Information ...............................................................................................A-2
A.2 Interfaced Equipment ................................................................................................................A-3
A.3 Equipment Locations and Wire Routing...................................................................................A-5
A.4 Configuration Log .....................................................................................................................A-8
A.5 Aircraft Wiring Diagrams .........................................................................................................A-9
APPENDIX B ELECTRICAL BONDING PROCEDURES...............................................................B-1
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
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 GTS Processor Install Tool - Assert Tab .............................................................................7-7
Figure 7-5 GTS Processor Install Tool - Normal Tab ...........................................................................7-9
Figure 7-6 Target Aircraft Position for Traffic Display Flight Check ................................................7-11
Figure A-1 Equipment Location and Wire Routing - Single-Engine Airplane ....................................A-6
Figure A-2 Equipment Location and Wire Routing - Twin Engine Airplane ......................................A-7
Figure A-3 GTS 8XX System Configuration Log ................................................................................A-8
Figure B-1 Electrical Bonding Preparation – Nut Plate .......................................................................B-2
Figure B-2 Electrical Bonding Preparation – Bolt/Nut Joint ................................................................B-2
Figure B-3 Electrical Bond Preparation – Terminal Lug .....................................................................B-2
Figure B-4 Fiberglass Insulation for Carbon Material ......................................................................... B-4
Figure B-5 Aluminum Tape Joint ......................................................................................................... B-6
Figure B-6 Aluminum Tape Ground Termination ................................................................................B-6
Figure B-7 GTS Processor Aluminum Tape Installation ..................................................................... B-7
Figure B-8 Electrical Bonding Using Conductive Clamp .................................................................. B-11
LIST OF TABLES
Table 2-1 GTS 8XX System Current Requirements .............................................................................2-2
Table 2-2 Ground Plane Definitions and Ground Path Resistance Requirements ................................2-4
Table 5-1 GTS 8XX System Faults .......................................................................................................5-4
Table 6-1 Recommended Coaxial Cable Length ...................................................................................6-5
Table 7-1 GTS 8XX System Flag Status ............................................................................................... 7-5
Table 7-2 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 ........................................ B-10
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
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
This section provides a description of the equipment installed by this STC. An overview of the GTS 8XX system interface is also provided.
Section 3: Control and Operation
This section provides basic control and operation information in relation to maintenance practices. Basic GTS configuration and software loading is also described.
Section 4: Instructions for Continued Airworthiness
This section provides instructions to maintain continued airworthiness of the GTS 8XX system and system airworthiness limitations.
Section 5: Troubleshooting
This section provides troubleshooting information to diagnose and resolve problems with GTS 8XX system equipment.
Section 6: Equipment Removal and Reinstallation
This section provides instructions for the removal and re-installation of GTS 8XX system equipment.
Section 7: Return to Service
This section specifies return to service procedures to be performed upon completion of maintenance of GTS 8XX system equipment.
Appendix A: Aircraft Installation Record
This appendix is used to record information for a specific GTS 8XX system installation.
Appendix B: Electrical Bonding Procedures
This appendix provides special bonding procedures for non-metallic aircraft.
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:
AML Approved Model List ADS-B Automatic Dependent Surveillance-Broadcast CFR Code of Federal Regulations DME Distance Measuring Equipment FAA Federal Aviation Administration HSDB High Speed Data Bus ICA Instructions for Continued Airworthiness LRU Line Replaceable Unit MFD Multi-Function Display SL Sensitivity Level STC Supplemental Type Certificate TA Traffic Advisory TAS Traffic Advisory System TCAS Traffic Alert and Collision Avoidance System TSO Technical Standard Order
In this manual, references to GTS 8XX Part 23 AML STC Installation Manual abbreviated as the “STC IM.”
1.4 Related Publications
Part Number Document
005-00738-01
005-00738-02
190-00587-00
190-00587-02
190-00587-50
190-00587-51
190-01279-00
700704
700784
Master Drawing List, GTS 8XX Part 23 AML STC Equipment List, GTS 8XX Part 23 AML STC GTS 8X0/GPA 65 (GTS 800/GTS 820/GTS 850) Installation Manual GTS Traffic Systems Pilot’s Guide GTS Processor (GTS 825/855/8000) Installation Manual GTS Processor Maintenance Manual GTS 8XX Part 23 AML STC Installation Manual L-Band/DME Blade Antenna P/N L10-611-( ) Limitations and Installation Instructions Dayton-Granger Inc. General Installation Instructions for Antennas
(P/N 190-01279-00) may be
1.5 Distribution
This document contains instructions required to maintain continued airworthiness of the GTS 8XX system. When this dealers may
document is revised, every page will be revised to indicate the current revision level. Garmin
obtain the latest revision of this document on the Garmin Dealer Resource Center website.
Owner/operators may obtain the latest revision of this document from
A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant.
flyGarmin.com.
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
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.
2.2 Equipment Description
The GTS 8XX is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode S and Mode C transponders to provide Traffic Advisories (TAs) to the pilot.
When properly configured, the GTS 8XX system will utilize passive surveillance to provide ADS-B In traffic. The GTS ADS-B In capability allows the unit to receive traffic data through its 1090 MHz Extended Squitter (1090 ES) receiver. Using the received ADS-B Out broadcasts, the system provides correlated information about target aircraft, including identification, speed, and direction. GPS and magnetic heading inputs to the GTS 8XX are required for ADS-B In to operate. Although ADS-B In relies on 1090ES ADS-B Out broadcasts from other aircraft, it is not necessary for the GTS-equipped aircraft to broadcast an ADS-B Out signal.
Aural alerts are provided to inform the crew of TAs. A top-mounted directional antenna is used to derive bearing of the intruder aircraft, which is displayed with relative altitude to own aircraft. Top antenna transmitted interrogations are directional, reducing the number of transponders that receive the interrogation, thus reducing potential garble on the 1090 MHz band. An optional bottom antenna transmits omni directional interrogations. A bottom directional antenna installation gives the benefit of intruder bearing visibi be degraded on fixed gear aircraft with a bottom directional antenna.
lity for targets that are shaded from the top directional antenna. Target bearing accuracy may
2.3 Electrical Current Requirements
Table 2-1 shows current requirements for the GTS 8XX system.
Table 2-1 GTS 8XX System Current Requirements
LRU
GTS 800 2.2 A 2.6 A 1.1 A 1.5 A
GTS 820/850 2.7 A 3.2 A 1.3 A 1.6 A
GTS Processor 3.5 A 7.5 A 1.7 A
14V Current Draw 28V Current Draw
Typical Maximum Typical Maximum
3.1 A
2.4 Interface Summary
Mode S Transponder
Compatible TX/RX interface
required for power programming
GTS TRAFFIC SYSTEM
Top
Directional
Antenna
Mode C Replies Mode S Replies
Mode S Squitters
Mode C Interrogations
Broadcast Messages
Mode S Interrogations
1
0
9
0
M
H
z
R
X
1
0
9
0
M
H
zR
X
1
0 3
0
M
H z
T
X
Optional
Top
Antenna
Bottom
Antenna
Mode A/C/S
Replies
Mode S Squitter
Mode A/C
Interrogations
Mode S Interrogations
Broadcast Messages
1
0
9
0
M
H
zTX
1
0 9
0
M
H
zTX
1
0
3
0
M
H
z
R
X
1
0
3
0
M
H zR
X
Suppression Bus
Audio Inhibit
Audio Output
Pressure Altitude*
OR
OR
OR
Transponder
Serializer
Magnetic Heading*
(optional)
Radar Altimeter
(optional)
GPS PVT*
(optional)
Data Source
Options
HSDB
Analog I/O
Discrete I/O
RS-232
ARINC 429
LRU Data
OPR/SBY
Self Test
Control/Display*
Unit
Color Display
Knobs/Buttons
Mode S Transponder
(Optional Second Unit)
Compatible TX/RX interface
required for power programming
Optional
Top
Antenna
Bottom
Antenna
Mode A/C/S
Replies
Mode S Squitter
Mode A/C
Interrogations
Mode S Interrogations
Broadcast Messages
1
0
9
0
M
H
zTX
1
0
9
0
M
H
z
T
X
1
0
3
0
M
H
zR
X
1
0
3 0
M H
z
R
X
Display Unit*
Color Display
Pressure Altitude Magnetic Heading
GPS PVT Radio Altitude Air /Gnd Status
Ldg Gear Position
Mode S TX/RX interface
Control/Display
Ldg Gear Position
Air/Gnd Status
OR
Optional
Bottom
Directional or
Monopole
Antenna
GTS 800 TAS GTS 820 TAS
GTS 825 TAS GTS 850 TCAS I GTS 855 TCAS I
Self Test / Alt Filter
OPR/SBY
External control inputs required
if Display Unit is only unit installe
d
Audio Panel
High-Priority
Audio Source
(e.g. ,TAWS)
(Optional)
(Req’d for retractable ldg gear)
*The HSDB interface can perform all of the listed interface functions in place of separate analog/digital interfaces.
TRFC Mute
(Optional)
1
0
3
0
M
H
z
T
X
G950/G1000 System*
OR
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 • Alert Audio Output
• Two RS-422 Input/Output • Ten Active Low Discrete Inputs
• Twelve ARINC 429 Inputs/Outputs • Two Active High Discrete Inputs
• Configuration Module • External Suppression Input/Output
• Aircraft Power Input • Four Annunciator Outputs
• Analog Radar Altimeter Input • HSDB Input/Output
• 26 VAC Heading Reference Input
Figure 2-1 GTS 8XX System Interface Diagram
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.
Table 2-2 Ground Plane Definitions and Ground Path Resistance Requirements
Maximum Resistance Between
Aircraft Type/Model
Ground
Reference
GTS 8XX Reference (mΩ)
Periodic Test Reconditioned
Chassis and Ground
Notes
Metal airframe
Tube airframe with fabric cover
Composite VFR-only Models
Diamond
Composite IFR Models
Cessna
Cirrus
Diamond
DA 40, DA 40F Instrument panel 50.0 25.0
LC40-550FG, LC41-550FG, LC42-550FG
SR20, SR22, SR22T
DA 40, DA 40F
DA 42, DA 42 N-MG
Nearby metallic structure
Nearby metallic structure
Nearby aluminum lightning bar/strip
Local grounded structure seat support structure, entry step)
Nearby structure lightning tube
Nearby lightning ground
ground
(such as
ground
10.0 2.5
10.0 2.5
10.0
10.0
10.0 5.0 [1]
10.0 5.0
5.0
5.0
Notes:
[1] Diamond DA 40 and DA 40F with Diamond OSB 40-004/3 incorporated, or aircraft with
similar factory-installed lightning protection supporting IFR operation.
3 CONTROL AND OPERATION
Traffic Mute
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.
Self-Test
The GTS 8XX built-in self-test function may be controlled either through a compatible display or an external switch.
Traffic Mute (optional)
The optional Traffic Mute function mutes traffic audio alerts and is controlled by an external switch.
Figure 3-1 GTS 8XX Traffic System Controls
4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS
4.1 Airworthiness Limitations .................................................................................................. 4-2
4.2 Servicing Information ......................................................................................................... 4-2
4.2.1 Periodic Maintenance ................................................................................................................. 4-2
4.2.2 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.
4.3 Maintenance Intervals
Maintenance Item Interval Description/Procedure
Antenna visual inspection 12 calendar months
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, the following procedure:
1. Remove, clean, and reattach the antenna.
2. Complete the antenna electrical bonding test as described below.
3. Reseal the antenna.
If the antenna is damaged or cracked, remove and replace the antenna in accordance with Section 6 (antenna(s) installed under this STC), or the antenna installation data (antenna(s) not installed under this STC). After installing antenna, complete the antenna electrical bonding test described below (if applicable).
If aircraft structure, at location of the antenna, is deformed or damaged, remove the antenna and repair aircraft structure in accordance with aircraft model-specific structural repair manual. After the aircraft repair is complete, perform the following:
1. Clean and reattach the antenna.
2. Complete the antenna electrical bonding test as described below (if applicable).
3. Reseal the antenna.
complete
Antenna visual inspection ­suspected lightning strike
Suspected or actual lightning strike
In the event of a suspected or actual lightning strike to the aircraft, the GTS 8XX system antenna(s) and antenna cable installation must be inspected.
1. Inspect the antenna(s) and surrounding area for structural damage. a. If the antenna is damaged, replace the antenna in accordance with Section 6. b. If the aircraft structure supporting the antenna installation is deformed or damaged,
2. Inspect the antenna and coaxial cable connector ends for damage. If any damage is found on any
3. Ensure that the coaxial cable connectors are securely attached to the antenna connectors.
4. Perform the GTS 8XX system checkout procedure in accordance with Section 5.
remove the antenna and repair in accordance with procedures detailed in the aircraft model-specific structural repair manual. When repair is complete, continue with the following steps.
antenna or coaxial cable connector, replace the antenna(s) or coaxial cable(s) in accordance with Section 6.
190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page 4-3
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
(Not applicable to VFR-only
Equipment electrical bonding test
models)
composite
Every 2000 flight hours
or ten years,
whichever
Following removal and the rack or bonding components
AND
Every 2000 flight hours whichever
is first
replacement of
GTS 8XX install
or ten years,
is first
1. Gain access to the antenna.
2. Disconnect the coaxial cable connector(s) from the antenna.
3. Measure the resistance between the antenna coaxial connector body and a nearby exposed portion of aircraft metallic structure (e.g., exposed rivet on fuselage stringer).
4. Verify the resistance is less than or equal to 10 mΩ.
5. Reconnect the antenna connector(s).
In the event of bonding test failure, perform the following procedure:
1. Remove the antenna, clean, and re-install in accordance with Section 6.
2. Measure the resistance between the antenna coaxial connector body and a nearby exposed portion of aircraft structure (e.g., exposed rivet on fuselage stringer).
3. Verify the resistance is less than or equal to 2.5 mΩ.
1. Disconnect the coaxial cable connector(s) from the GTS 8XX.
2. Disconnect P8001, P8002, and P8003 connectors from the GTS 8XX.
3. Measure the DC resistance between the GTS 8XX chassis and the aircraft ground, as defined in Table 2-2. Verify the resistance is less than or equal to the appropriate periodic test resistance value listed in Table 2-2.
In the event of bonding test failure, perform the following procedure:
1. Remove GTS 8XX and install rack from the aircraft per instructions in Section 6.
2. Ensure that the GTS 8XX and install rack are clean and free of dirt and debris.
3. Ensure that all ground path components are in good condition and properly connected and attached to the aircraft.
4. Re-install the GTS 8XX and install rack in accordance with Section 6.
5. Measure the resistance between the GTS 8XX chassis and the aircraft ground, as defined in Table 2-2.
6. Verify the resistance is less than or equal to the appropriate reconditioned resistance value listed in Table 2-2.
Equipment removal and replacement
On condition
Remove and replace the GTS 8XX and/or GTS 8XX system antenna.
See Section 6 for equipment removal and re-installation instructions.
190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page 4-4
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 inspection – suspected lightning strike
Suspected or actual lightning strike
GTS 8XX: bonding straps and associated hardware (if applicable) must be inspected. If any damage is
found, the damaged components must be replaced in accordance with specifications and procedures
shown in Appendix B. If any bonding components are replaced, complete the equipment electrical
bonding test as described above.
Equipment visual inspection
12 calendar months
Conduct a visual inspection of the GTS 8XX installation in accordance with 14 CFR 43
Preventative Maintenance, Rebuilding and Alteration, Appendix D. If the equipment fails the visual
inspection, complete the following procedure:
1. Correct improper installations and ensure that all mounting racks and fasteners are secure.
2. Correct improper wire routing and ensure that the wire harness is securely mounted. Replace the install rack or any wiring, bonding, or shielding component with obvious defects.
3. If the install rack or any bonding components are replaced, complete the equipment electrical bonding test as described above.
Maintenance,
190-01279-01 GTS 8XX Part 23 AML STC Maintenance Manual Rev. 2 Page 4-5
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