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

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

Garmin®, flyGarmin®, and flyGarmin.com® are registered trademarks of Garmin International or its subsidiaries. GDU™, GDL™, GNS™, GTN™, GTS™, and GTX™ are trademarks of Garmin International or its subsidiaries. These trademarks may not be used without the express permission of Garmin.

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190-01279-01	GTS 8XX Part 23 AML STC Maintenance Manual
Rev. 2	Page i

		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	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.”
	1.4	Added GTS 8X0/GPA 65 (GTS 800/GTS 820/GTS 850) Installation (P/N 190-00587-00).
	2.3	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.
	4.3
		Updated procedure for antenna visual inspection - suspected lightning strike to include
		inspection criteria.
	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.
	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	Added GDU 7XX equipment reference to Table A-1 GTS 8XX System Interfaces to
		Garmin Equipment.
	A.3	Updated aircraft profile to Figure A-2 Equipment Location and Wire Routing - Twin
		Engine Airplane.
	Appendix B	Updated title of Appendix B to “Electrical Bonding Procedures.”
		Added flag notes for Figure B-7.
	B.3	Added 5:1length-to-width ratio requirement.
		Added bonding strap restriction of six inches.
	B.4	Added bonding strap restriction of six inches.

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Rev. 2	Page ii

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

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

WARNING

A Warning means injury or death is possible.

CAUTION

A Caution means that damage to the equipment is possible.

NOTE

A Note provides additional information.

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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

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Rev. 2	Page iv

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

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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

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Rev. 2	Page vi

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

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.

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1.3 Definitions and Abbreviations

1.3.1Definitions

“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.

1.3.2Abbreviations

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 (P/N 190-01279-00) may be abbreviated as the “STC IM.”

1.4 Related Publications

Part Number	Document
005-00738-01	Master Drawing List, GTS 8XX Part 23 AML STC
005-00738-02	Equipment List, GTS 8XX Part 23 AML STC
190-00587-00	GTS 8X0/GPA 65 (GTS 800/GTS 820/GTS 850) Installation Manual
190-00587-02	GTS Traffic Systems Pilot’s Guide
190-00587-50	GTS Processor (GTS 825/855/8000) Installation Manual
190-00587-51	GTS Processor Maintenance Manual
190-01279-00	GTS 8XX Part 23 AML STC Installation Manual
700704	L-Band/DME Blade Antenna P/N L10-611-( ) Limitations and Installation Instructions
700784	Dayton-Granger Inc. General Installation Instructions for Antennas

190-01279-01	GTS 8XX Part 23 AML STC Maintenance Manual
Rev. 2	Page 1-3

1.5 Distribution

This document contains instructions required to maintain continued airworthiness of the GTS 8XX system. When this document is revised, every page will be revised to indicate the current revision level. Garmin dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center website.

Owner/operators may obtain the latest revision of this document from flyGarmin.com.

A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant.

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2	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
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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 visibility for targets that are shaded from the top directional antenna. Target bearing accuracy may be degraded on fixed gear aircraft with a bottom directional antenna.

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	14V Current Draw		28V Current Draw
		Typical	Maximum	Typical	Maximum
	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	3.1 A

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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	•	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

Mode A/C

Interrogations

Mode S Interrogations

Broadcast Messages

1

X

0

0

R

3

z

Mode A/C/S

M

H

z

M

Replies

H

R

0

X

3

Mode S Squitter

1

0

TX

1

9

z

0

H

M

M

H

0

z

9

TX

0

1

Optional

Bottom

Top

Antenna

Antenna

				Mode C Interrogations
				Broadcast Messages
				Mode S Interrogations
										1
										0
										3
		X								0
										H
		T			Mode C Replies					M
										z
	z									T
	H				Mode S Replies					X
	M
0				Mode S Squitters						1
3		X
0										0
1		R								9
		z								0
		H								M
		M								H
	0					Optional				z
	9									R
	0									X
		1	Top				Bottom
		Directional				Directional or
			Antenna			Monopole
						Antenna
						Suppression Bus

			Mode A/C
			Interrogations
			Mode S Interrogations			0
			Broadcast Messages
X						1
						3
R
					0
z						M
H						H
M			Mode A/C/S			z
0						R
3						X
0			Replies
1
	TX		Mode S Squitter		1
					9
z					0
					0
H
						M
M						H
0						z
9						T
0						X
1

Optional

Top

Bottom

Antenna

Antenna

Mode S Transponder

Compatible TX/RX interface required for power programming

	Pressure Altitude*
	Transponder
	Serializer						OR
	Magnetic Heading*						OR
	(optional)
							OR
	GPS PVT*
	(optional)
	Radar Altimeter						OR
	(optional)
						TRFC Mute
						(Optional)
	LRU			Data
Data Source			ARINC 429
	Options
	HSDB			RS-232
Discrete I/O				Analog I/O

*The HSDB interface can perform all of the listed interface functions in place of separate analog/digital interfaces.

Mode S Transponder

(Optional Second Unit) Compatible TX/RX interface required for power programming

GTS TRAFFIC SYSTEM

GTS 800 TAS

GTS 820 TAS

GTS 825 TAS

GTS 850 TCAS I

GTS 855 TCAS I

OPR/SBY

Self Test

G950/G1000 System*

		Pressure Altitude
		Magnetic Heading
		GPS PVT
		Radio Altitude
		Air /Gnd Status
		Ldg Gear Position
		Mode S TX/RX interface
		Control/Display
	Air/Gnd Status	(Optional)
	Ldg Gear Position	(Req’d for retractable ldg gear)
	Audio Inhibit	High-Priority
		Audio Source
		(e.g.,TAWS)
	Audio Output
		Audio Panel
	OPR/SBY
		External control inputs required
	Self Test /
		if Display Unit is only unit installed
	Alt Filter

Control/Display*			Display Unit*
	Unit
	Color Display		Color Display
	Knobs/Buttons

	Figure 2-1 GTS 8XX System Interface Diagram
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Rev. 2	Page 2-3

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	GTS 8XX Chassis and Ground		Notes
		Reference	Reference (mΩ)
			Periodic Test	Reconditioned
Metal airframe		Nearby metallic	10.0	2.5
		structure
Tube airframe with fabric cover		Nearby metallic	10.0	2.5
		structure
Composite VFR-only Models
Diamond	DA 40, DA 40F	Instrument panel	50.0	25.0
Composite IFR Models
	LC40-550FG,	Nearby aluminum
Cessna	LC41-550FG,	lightning ground	10.0	5.0
	LC42-550FG	bar/strip
		Local grounded
	SR20,	structure (such as
Cirrus	SR22,	seat support	10.0	5.0
	SR22T	structure, entry
		step)
	DA 40,	Nearby structure
		lightning ground	10.0	5.0	[1]
	DA 40F
Diamond		tube
	DA 42,	Nearby lightning	10.0	5.0
	DA 42 N-MG	ground

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.

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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.

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.

Traffic Mute

Figure 3-1 GTS 8XX Traffic System Controls

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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.

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Rev. 2	Page 4-1

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. Remove, clean, and reattach the antenna.
Antenna visual inspection	12 calendar months	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.
		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,
Antenna visual inspection -	Suspected or actual		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
suspected lightning strike	lightning strike
			following steps.
		2. Inspect the antenna and coaxial cable connector ends for damage. If any damage is found on any
			antenna or coaxial cable connector, replace the antenna(s) or coaxial cable(s) in accordance with
			Section 6.
		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.

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Rev. 2	Page 4-3

Maintenance Item	Interval		Description/Procedure
Antenna electrical bonding test		An electrical bonding test must be performed on all GTS 8XX system antennas. The test procedure is:
		1. Gain access to the antenna.
(Not applicable to composite		2.	Disconnect the coaxial cable connector(s) from the antenna.
VFR-only models)		3.	Measure the resistance between the antenna coaxial connector body and a nearby exposed portion
	Every 2000 flight		of aircraft metallic structure (e.g., exposed rivet on fuselage stringer).
		4.	Verify the resistance is less than or equal to 10 mΩ.
	hours or ten years,
		5.	Reconnect the antenna connector(s).
	whichever is first
		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.
	Following removal	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
	and replacement of
			listed in Table 2-2.
	the GTS 8XX install
		In the event of bonding test failure, perform the following procedure:
	rack or bonding
Equipment electrical bonding	components	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.
test	AND
		3.	Ensure that all ground path components are in good condition and properly connected and attached
	Every 2000 flight		to the aircraft.
		4.	Re-install the GTS 8XX and install rack in accordance with Section 6.
	hours or ten years,
		5.	Measure the resistance between the GTS 8XX chassis and the aircraft ground,
	whichever is first
			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	On condition	Remove and replace the GTS 8XX and/or GTS 8XX system antenna.
replacement		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	Suspected or	GTS 8XX: bonding straps and associated hardware (if applicable) must be inspected. If any damage is
inspection – suspected	actual lightning	found, the damaged components must be replaced in accordance with specifications and procedures
lightning strike	strike	shown in Appendix B. If any bonding components are replaced, complete the equipment electrical
		bonding test as described above.
		Conduct a visual inspection of the GTS 8XX installation in accordance with 14 CFR 43 Maintenance,
		Preventative Maintenance, Rebuilding and Alteration, Appendix D. If the equipment fails the visual
		inspection, complete the following procedure:
Equipment visual inspection	12 calendar months	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.

190-01279-01	GTS 8XX Part 23 AML STC Maintenance Manual
Rev. 2	Page 4-5