Garmin 0104450, 0104400 Users Manual

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Page 1

GTS 8XX/GPA 65

Installation Manual

(Includes the GA 58 Antenna)

190-00587-00 April, 2009 Revision 4TP

Page 2

Garmin Ltd. or its subsidiaries

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 International, Inc.

1200 E. 151

Street

Olathe, KS 66062 USA

Telephone: 913-397-8200

Aviation Dealer Technical Support Line (Toll Free): (888) 606-5482

www.garmin.com

Garmin (Europe) Ltd

Liberty House

Bulls Copse Road

Hounsdown Business Park

Southampton, SO40 9RB, UK

Telephone: +44 (0) 8708501241

RECORD OF REVISIONS

Revision

1TP 08/06/08 1TP Release 2TP 9/17/08 Updated manual with various engineering changes 3TP 2/18/09 Updated manual with various engineering changes 4TP Updated manual with various engineering changes

Revision

Date

Description

DOCUMENT PAGINATION

Section Page Range

Table of Contents i – vi

Section 1 1-1 – 1-10 Section 2 2-1 – 2-16 Section 3 3-1 – 3-20

Section 4 4-1 – 4-14 Appendix A A-1 – A-14 Appendix B B-1 – B-18

Page A GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 3

This manual reflects the operation of software version X.XX. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions.

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

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

NOTE

Throughout this document references made to the GTS 8XX shall equally apply to the GTS 800, 820, and 850 except where specifically noted.

WARNING

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

www.garmin.com/prop65

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TABLE OF CONTENTS

PARAGRAPH PAGE

1 GENERAL DESCRIPTION..............................................................................................................1-1

1.1 Introduction........................................................................................................................................1-1

1.2 Equipment Description......................................................................................................................1-1

1.3 Interface Summary.............................................................................................................................1-1

1.4 Technical Specifications....................................................................................................................1-2

1.5 Certification.......................................................................................................................................1-4

1.6 Reference Documents........................................................................................................................1-8

1.7 Limited Warranty...............................................................................................................................1-9

2 INSTALLATION OVERVIEW........................................................................................................2-1

2.1 Introduction........................................................................................................................................2-1

2.2 Installation Considerations ................................................................................................................2-3

2.3 Electrical Bonding .............................................................................................................................2-5

2.4 Cabling and Wiring............................................................................................................................2-5

2.5 Cooling Requirements .....................................................................................................................2-15

2.6 Mounting Requirements ..................................................................................................................2-16

3 INSTALLATION PROCEDURE......................................................................................................3-1

3.1 Unpacking Unit..................................................................................................................................3-1

3.2 Wiring Harness Installation...............................................................................................................3-1

3.3 QMA Connector Insertion and Removal...........................................................................................3-3

3.4 Backshell, Pigtail Circular Connector, and Configuration Module Assemblies................................3-5

3.5 Unit Installation .................................................................................................................................3-5

3.6 GA 58 Antenna Installation.............................................................................................................3-19

3.7 GPA 65 PA/LNA Installation..........................................................................................................3-20

3.8 Continued Airworthiness.................................................................................................................3-20

4 SYSTEM INTERCONNECTS..........................................................................................................4-1

4.1 GTS 8XX Pin Function List ..............................................................................................................4-1

4.2 GPA 65 Pin Function List..................................................................................................................4-6

4.3 Power.................................................................................................................................................4-7

4.4 Serial Data .........................................................................................................................................4-9

4.5 Configuration...................................................................................................................................4-12

4.6 Analog/Discrete...............................................................................................................................4-12

4.7 Mutual Suppression Bus..................................................................................................................4-14

APPENDIX A: OUTLINE & INSTALLATION DRAWINGS..............................................................A-1

APPENDIX B: INTERCONNECT EXAMPLE...................................................................................... B-1

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LIST OF ILLUSTRATIONS

FIGURE PAGE

2-1 GTS 800 Installation with Top and Bottom Directional Antennas....................................................2-7

2-2 GTS 800 Installation with Top and Bottom Monopole Antennas.....................................................2-8

2-3 GTS 800 Installation with Top Directional Antennas and no Bottom Antenna................................2-8

2-4 GTS 820/GTS 850 Installation Top and Bottom Directional Antennas............................................2-9

2-5 GTS 820/GTS 850 Installation with Top Directional and Bottom Monopole Antenna..................2-10

2-6 GTS 820/GTS 850 Installation with Top Directional and no Bottom Antenna...............................2-10

2-7 RG-400/RG-142 Coaxial Cable Stripping Dimensions...................................................................2-14

2-8 Ferrule and Crimp Die Positioning..................................................................................................2-14

2-9 Heat Shrink Positioning...................................................................................................................2-15

2-10 GTS 8XX Vertical Installation Rack (Garmin P/N 115-00781-00) ................................................2-16

2-11 GTS 8XX Horizontal Installation Rack (Garmin P/N 115-00784-00)............................................2-16

3-1 Engaging QMA Connectors...............................................................................................................3-3

3-2 Disengaging QMA Connectors..........................................................................................................3-4

3-3 GTS 8XX Install Tool – Normal Tab................................................................................................3-7

3-4 GTS 8XX Install Tool – Configuration Tab (GTS 800)....................................................................3-8

3-5 GTS 8XX Install Tool – Configuration Tab (GTS 820 and GTS 850)..............................................3-9

3-6 GTS 8XX Install Tool – Upload Tab...............................................................................................3-12

3-7 Self Test...........................................................................................................................................3-15

3-8 Ground Test .....................................................................................................................................3-16

A-1 GTS 8XX Vertical Outline Drawing ................................................................................................A-1

A-2 GTS 8XX Vertical Installation Drawing ..........................................................................................A-3

A-3 GTS 8XX Horizontal Outline Drawing............................................................................................A-5

A-4 GTS 8XX Horizontal Installation Drawing......................................................................................A-7

A-5 GPA 65 Outline Drawing .................................................................................................................A-9

A-6 GPA 65 Installation Drawing .........................................................................................................A-11

A-7 GA 58 Antenna Outline Drawing...................................................................................................A-13

B-1 Notes................................................................................................................................................. B-1

B-2 GTS 820/850/GPA 65 Example Interconnect ................................................................................... B-3

B-3 GTS 800 Example Interconnect........................................................................................................ B-5

B-4 GTS 8XX G1000 Example Interconnect ..........................................................................................B-7

B-5 GTS 8XX GNS 4XX/GNS 5XX/GMX 200 Example Interconnect.................................................B-9

B-6 GTS 8XX/GMA/Altimeter Example Interconnect ......................................................................... B-11

B-7 GTS 8XX Dongle Cable (Non-G 1000 Installations Only).............................................................B-13

B-8 GTS 8XX Discrete Interconnects ................................................................................................... B-15

B-9 GTS 8XX Config Module Example Interconnect .......................................................................... B-17

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LIST OF TABLES

TABLE PAGE

2-1 GPA 65 Minimum Wiring Requirements..........................................................................................2-6

2-2 Cable Types and QMA Connectors.................................................................................................2-11

2-3 Recommended Coaxial Length........................................................................................................2-12

2-4 Coaxial Cable Set Length Tolerance ...............................................................................................2-13

3-1 Socket and Pin Contact part Numbers...............................................................................................3-1

3-2 Socket Contact MIL SPEC M39029/5-115 Crimp Tooling...............................................................3-1

3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling .................................3-2

3-4 Pin Socket Contacts GPN 336-00022-00 MIL SPEC M39029/63-368 and GPN 336-00023-00 Crimp

Tooling...............................................................................................................................................3-2

3-5 Self Test...........................................................................................................................................3-15

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GTS 8XX HARDWARE MOD LEVEL HISTORY

The following table identifies hardware modification (Mod) Levels for the GTS 8XX. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice. Authorized Garmin Sales and Service Centers are encouraged to access the most up-to-date bulletin and advisory information on the Garmin Dealer Resource web site at

www.garmin.com

APPLICABLE

LRU PART

NUMBER

using their Garmin-provided user name and password.

MOD

LEVEL

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF

MODIFICATION

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(

)

1 GENERAL DESCRIPTION

1.1 Introduction

This manual presents mechanical and electrical installation requirements for installing the GTS 8XX/GPA 65 Traffic Advisory System (TAS) and Traffic Collision Avoidance System (TCAS I).

1.2 Equipment Description

The GTS 8XX is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode S (GTS 820 and GTS 850 only) and Mode C transponders to provide Traffic Advisories to the pilot. The GTS 820 and GTS 850 include a GPA 65 power amplifier/low-noise amplifier (PA/LNA) module, which allows for up to 40 nm of active surveillance range as well as Mode S interrogation capability. When installed with a 1090 MHz ADS-B transmit class of equipment the GTS 8XX also utilizes passive surveillance. Traffic is displayed on an external MFD via ARINC 429 and/or Ethernet High Speed Data Bus (HSDB). An aural alert is also provided to inform the crew a traffic advisory (TA) will be displayed.

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. Optional bottom antenna transmit interrogations are omni directional, using a monopole antenna (recommended for fixed gear installations) or a directional antenna (recommended for retractable gear installations). A bottom directional antenna installation gives the benefit of intruder bearing visibility for targets that are shaded from the top directional antenna.

1.2.1 GTS 8XX Model Differences

The following table summarizes the differences between the various GTS 8XX models documented in this manual.

GTS 800 011-01356-00 GTS 820 011-01446-00 GTS 850 011-01553-00

(TAS)

Traffic Advisory System

X X 40 X X X 200

X X X 200

TCAS I

Receiver

Traffic Collision

1090 ES ADS-B

Avoidance System

GPA 65

PA/LNA

(Watts)

Transmit Power

1.3 Interface Summary

The GTS 8XX is designed as an open architecture system that uses typical ARINC 429, RS-232, and Ethernet communications interfaces.

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1.4 Technical Specifications

1.4.1 Environmental Qualification Form

It is the responsibility of the installing agency to obtain the latest revision of the GTS 8XX/GPA Environmental Qualification Form. This form is available directly from Garmin under the following part number:

GTS 8XX Environmental Qualification Form, Garmin part number 005-00323-02 GPA 65 PA/LNA Environmental Qualification Form, Garmin part number 005-00323-22 GA 58 Antenna Environmental Qualification Form, Garmin part number 005-00232-23

To obtain a copy of this form, see the dealer/OEM portion of the Garmin web site (www.garmin.com

1.4.2 Physical Characteristics

Characteristics Specifications

GTS 8XX Width 2.81 inches (7.14 cm) GTS 8XX Height 6.94 inches (17.63 cm) GTS 8XX Depth w/Connector Kit 14.78 inches (37.54 cm) GPA 65 Width 4.25 inches (10.80 cm) GPA 65 Height 1.00 inches (2.54 cm) GPA 65 Depth Not Including Connector And Cable GPA 65 Depth w/Connector And Cable Fully Extended GTS 8XX Unit Weight w/out Connector Kit GTS 8XX Unit Weight with Connector Kit/w Vertical Rack GTS 8XX Unit Weight with Connector Kit/w Horizontal Rack GPA 65 PA/LNA Unit Weight with Pigtail Connector Kit* GA 58 TAS/TCAS Antenna w/screws and o-ring QMA straight connector kit, 4 pcs 0.10 lbs. (0.05 kg) QMA straight connector kit, 1 pc 0.03 lbs. (0.01 kg) QMA right angle connector kit, 4 pcs QMA right angle connector kit, 1 pc 0.05 lbs. (0.02 kg) QMA termination connector kit 0.07 lbs. (0.03 kg)

*Used with the GTS 820 and 850.

7.96 inches (20.22 cm)

16.83 inches (42.75 cm)

9.0 lbs. (4.08 kg)

10.7 lbs. (4.85 kg)

11.5 lbs. (5.22 kg)

1.9 lbs. (0.86 kg)

0.82 lbs. (0.37 kg)

0.18 lbs. (0.08 kg)

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1.4.3 General Specifications

The table below contains general specifications. For detailed environmental specifications, see the Environmental Qualification Form.

Characteristics Specifications

Operating Temperature Range -55°C to +70°C. Humidity 95% non-condensing Altitude Range -1,500 ft to 55,000 ft Software Compliance RTCA/DO-178B levels B, C, and D Hardware Compliance RTCA/DO-254 Level C Environmental Compliance RTCA/DO-160E

1.4.4 Power Requirements

Characteristics Specifications

GTS 8XX Power Requirements 14/28 Vdc. See the Environmental Qualification Form for

details on surge ratings and minimum/maximum operating

voltages.

GTS 800 Power Consumption 1.1 +/- 0.2 A typical 1.5 A max operating @ 28 Vdc

2.2 +/- 0.2 A typical 2.6 A max operating @ 14 Vdc

GTS 820/850 Power Consumption 1.3 +/- 0.2 A typical 1.6 A max operating @ 28 Vdc

2.7 +/- 0.3 A typical 3.2 A max operating @ 14 Vdc

GTS 8XX Boot-up Current Draw 4.0 A @ 28 Vdc for 70 ms

5.6 A @ 14 Vdc for 100 ms

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1.5 Certification

The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft. The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements.

The following table provides a list of applicable TSO/ETSOs for the GTS 8XX/GPA 65.

1.5.1 TSO/ETSO Compliance

Applicable

LRU

GTS 850

GPA 65

GTS 800 GTS 820

GPA 65

GTS 800 GTS 820 GTS 850

Function TSO/ETSO Category

Traffic Alert and Collision Avoidance System (TCAS I) Airborne Equipment

Traffic Advisory System (TAS) Airborne Equipment

Extended Squitter Automatic Dependent Surveillance – Broadcast (ADS-B) and Traffic Information Service – Broadcast (TIS-B) Equipment Operating on the Radio Frequency of 1090 Megahertz (MHz)

TSO-C118

ETSO-C118

TSO-C147

ETSO-C147

TSO-C166a

Applicable

LRU SW Part

Numbers

006-B0551-()

Class A 006-B0551-()

Class A0/Type 1 Receiving

Only*

Class A1/Type 1 Receiving

Only*

006-B0551-() 006-C0081-()**

Applicable

CLD Part Numbers

006-C0081-()**

006-C0092-()***

006-C0081-()**

006-C0092-()***

* Equipment is Class A0 when installed with a single antenna, Class A1 when installed with diversity antennas. **GTS 8XX only ***GPA 65 only

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1.5.2 TSO/ETSO Deviations

1.5.2.1 GTS 800

TSO/ETSO Deviation

TSO-C147 1. Garmin was granted a deviation from TSO-C147 section 1.c to use RTCA DO-160E, instead of

RTCA DO-160D as the standard for Environmental Conditions and Test Procedures for Airborne Equipment.

RTCA DO-197A

RTCA DO-185A

RTCA DO-260A

1. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the Interrogations Spectrum requirement of RTCA DO-185A section 2.2.3.3 instead of the requirement of RTCA DO197A section 2.2.3.2.1

3. Garmin was granted a deviation from RTCA DO-197A section 2.2.9.1 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.

4. Garmin was granted a deviation from RTCA DO-197A section 2.2.11 to use the suppression pulse on the aircraft suppression bus specified by RTCA DO-185A section 2.2.3.12 (70 +/-1 µs from top antenna and 90 +/-1 µs from bottom antenna) instead of 100 +/-5 µs.

1. Garmin was granted a deviation to use DO-185A as modified by Appendix 1 of TSO-C119B and ‘RWG Recommended Modification 2.0 to TSO-C119B.’

2. Garmin was granted a deviation from RTCA DO-185A section 2.2.3.8.2 Mode S signal definition.

3. Garmin was granted a deviation from RTCA DO-185A section 2.2.4.4.2.2.b to use the Enhanced Preamble Detection method of RTCA DO-260A Appendix I section I.4.1.

4. Garmin was granted a deviation from RTCA DO-185A section 2.2.4.4.2.2.c to use the Baseline Multi-sample bit and confidence declaration technique of RTCA DO-260A Appendix I section I.4.2.3.1.

5. Garmin was granted a deviation from RTCA DO-185A section 2.4.2.1.1.4.

1. Garmin was granted a deviation from RTCA DO-260A section 2.2.4.3.4.7.3.b to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260A section

2.2.4.4.3.1 instead of section 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185A.

2. Garmin was granted a deviation from RTCA DO-260A section 2.2.4.4.2 to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260A section 2.2.4.4.3.1 instead of section 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185A.

3. Garmin was granted a deviation from RTCA DO-260A section 2.2.4.5.b to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260A section 2.2.4.4.3.1 instead of section 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185A.

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1.5.2.2 GTS 820

TSO/ETSO Deviation

TSO-C147

RTCA DO-197A

RTCA DO-185A

RTCA DO-260A

1. Garmin was granted a deviation from TSO-C147 section 1.c to use RTCA DO-160E, instead of RTCA DO-160D as the standard for Environmental Conditions and Test Procedures for Airborne Equipment.

2. Garmin was granted a deviation from TSO-C147 Appendix 1 section 1.6 to use selective Mode S interrogations as specified by RTCA DO-185A section 2.2.3.8.1 and 2.2.3.9 following all the applicable protocols for Mode-S surveillance interrogations in the NAS as stated in DO-1 85A and DO-181C.

2. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.5 to use the “Mode C Only All-Call” format specified by RTCA DO-185A section 2.2.3.8.1 instead of the “Mode C” format for ATCRBS interrogations.

1. Garmin was granted a deviation to use DO-185A as modified by Appendix 1 of TSO-C119B and ‘RWG Recommended Modification 2.0 to TSO-C119B.’

2. Garmin was granted a deviation from RTCA DO-185A section 2.2.3.8.2 Mode S signal definition.

3. Garmin was granted a deviation from RTCA DO-185A section 2.2.4.4.2.2.b to use the Enhanced Preamble Detection method of RTCA DO-260A Appendix I section I.4.1.

4. Garmin was granted a deviation from RTCA DO-185A section 2.2.4.4.2.2.c to use the Baseline Multi-sample bit and confidence declaration technique of RTCA DO-260A Appendix I section I.4.2.3.1.

5. Garmin was granted a deviation from RTCA DO-185A section 2.4.2.1.1.4.

1. Garmin was granted a deviation from RTCA DO-260A section 2.2.4.3.4.7.3.b to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260A section

2.2.4.4.3.1 instead of section 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185A.

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1.5.2.3 GTS 850

TSO/ETSO Deviation

TSO-C118

RTCA DO-197A

RTCA DO-185A

RTCA DO-260A

1. Garmin was granted a deviation from TSO-C118 section a.(2) to use RTCA DO-160E, instead of RTCA DO-160B as the standard for Environmental Conditions and Test Procedures for Airborne Equipment.

3. Garmin was granted a deviation from RTCA DO-197A section 2.2.6 to use selective Mode S interrogations following all the applicable protocols for Mode-S surveillance interrogations in the NAS as stated in DO-185A and DO-181C.

4. Garmin was granted a deviation from RTCA DO-197A section 2.2.9.1 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.

5. Garmin was granted a deviation from RTCA DO-197A section 2.2.11 to use the suppression pulse on the aircraft suppression bus specified by RTCA DO-185A section 2.2.3.12 (70 +/-1 µs from top antenna and 90 +/-1 µs from bottom antenna) instead of 100 +/-5 µs.

1. Garmin was granted a deviation to use RTCA DO-185A as modified by Appendix 1 of TSOC119B and ‘RWG Recommended Modification 2.0 to TSO-C119B’.

2. Garmin was granted a deviation from RTCA DO-185A section 2.2.3.8.2 Mode S signal definition.

3. Garmin was granted a deviation from RTCA DO-185A section 2.2.4.4.2.2.b to use the Enhanced Preamble Detection method of RTCA DO-260A Appendix I section I.4.1.

4. Garmin was granted a deviation from RTCA DO-185A section 2.2.4.4.2.2.c to use the Baseline Multi-sample bit and confidence declaration technique of RTCA DO-260A Appendix I section I.4.2.3.1.

1. Garmin was granted a deviation from RTCA DO-260A section 2.2.4.3.4.7.3.b to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260A section

2.2.4.4.3.1 instead of section 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185A.

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1.6 Reference Documents

The following publications are sources of additional information for installing the GTS 8XX. Before installing the GTS 8XX, the technician should read all referenced materials along with the manual.

Part Number Document

190-00313-11 Jackscrew Backshell Installation Instructions 190-00303-00 G1000 System Installation Manual

190-00303-04 190-00903-00 G1000 System Maintenace Manual LJ/VLJ 190-00907-00

G1000 Line Maintenance and Configuration Manual

G1000 System Maintenance Manual Standard Piston/Turboprop Aircraft

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1.7 Limited Warranty

This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within this period, Garmin will at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts or labor, provided that the customer shall be responsible for any transportation cost. This warranty does not cover failures due to abuse, misuse, accident or unauthorized alteration or repairs.

THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.

IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not allow the exclusion of incidental or consequential damages, so the above limitations may not apply to you.

Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.

To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center near you, call Garmin Customer Service at one of the numbers shown below.

Products sold through online auctions are not eligible for rebates or other special offers from Garmin. Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an original or copy of the sales receipt from the original retailer is required. Garmin will not replace missing components from any package purchased through an online auction.

Garmin International, Inc. Garmin (Europe) Ltd. 1200 E. 151st Street Liberty House Olathe, KS 66062, U.S.A. Bulls Copse Road Phone: 800/800.1020 Hounsdown Business Park FAX: 913/397.0836 Southampton, SO40 9RB, UK Telephone: 44 (0) 8708501241

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2 INSTALLATION OVERVIEW

2.1 Introduction

This section provides hardware equipment information for installing the GTS 8XX/GPA 65 and related hardware. Installation of the GTS 8XX/GPA 65 should follow the aircraft TC or STC requirements. Cabling is fabricated by the installing agency to fit each particular aircraft. The guidance of FAA advisory circulars AC 43.13-1B and AC 43.13-2A, where applicable, may be found useful for making retro-fit installations that comply with FAA regulations.

2.1.1 Unit Configurations

The GTS 8XX and GPA 65 are available under the following part numbers:

Applicable

Item

GTS 800, (011-01356-00) 006-B0551-() 006-C0081-() 010-00519-00 GTS 820, (011-01446-00) 006-B0551-() 006-C0081-() 010-00562-00 GTS 850, (011-01553-00) 006-B0551-() 006-C0081-() 010-00563-00 GPA 65, (011-01347-00) 006-B0551-() 006-C0092-() 010-10721-00

LRU Software Part Numbers

Applicable Custom

Logic Device

Part Numbers

Garmin P/N

2.1.2 Required Accessories

NOTE

Refer to the Dealer’s Only portion of www.garmin.com for instructions on determining what accessories are needed.

Each of the following accessories are provided separately from the GTS 8XX and GPA 65 unit and are required to install the unit.

Installation Racks* Garmin P/N

GTS 8XX Vertical Installation Rack 115-00781-00 GTS 8XX Horizontal Installation Rack 115-00784-00

* Only one is required.

GTS 8XX/GPA 65 Installation Manual Page 2-1 190-00587-00 Revision 4TP

Page 20

For a GTS 800 installation with a single GA 58 directional antenna, two QMA Connector Kits (4 pieces, either straight or right angle) are required.

For a GTS 800 installation with dual GA 58 directional antennas, four QMA Connector Kits (4 pieces, either straight or right angle) kits are required.

For a GTS 800 installation with a single GA 58 directional antenna and a monopole antenna, two QMA Connector Kits (4 pieces, either straight or right angle) and one QMA Connector Kit (1 piece, either straight or right angle) are required.

For GTS 820 and 850 installations, add two QMA Connector Kits (4 pieces, either straight or right angle) for the GPA 65 connections.

One QMA Termination Connector Kit (4 pieces) is required for single antenna installations.

Connector Kits Garmin P/N

QMA Right Angle Connector Kit (4 pieces) 011-01364-00 QMA Straight Connector Kit (4 pieces) 011-01364-01 QMA Right Angle Connector Kit (1 piece) 011-01364-02 QMA Straight Connector Kit (1 piece) 011-01364-03 QMA Termination Connector Kit (4 pieces) 011-01364-04 GTS 8XX Connector Kit 011-01360-00 GPA 65 Circular Connector Kit 011-01365-00 USB-B Pigtail (non-G1000 installations only) 011-01782-00

Antennas Garmin P/N

GA 58 Directional Antenna, (011-01346-00) 010-10720-00* Monopole Antenna 010-10160-00 or

L-Band Monopole Antenna that meets

TSO-C74c

*010-10720-00 includes mounting screws and o-ring, unless specifically requested to exclude.

Configuration Module Garmin P/N

Configuration Module (non-G1000 installations only)

011-00979-20

Page 2-2 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 21

2.2 Installation Considerations

Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GTS 8XX/GPS 65.

2.2.1 Antenna Considerations

Antenna installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such antenna installations incorporate alteration (penetration) of the cabin pressure vessel by connector holes and/or mounting arrangements. For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations, it is recommended that the installer proceed according to any of the following listed alternatives:

1. Obtain approved antenna installation design data from the aircraft manufacturer.

2. Obtain an FAA approved STC, pertaining to, and valid for the antenna installation.

3. Contact the FAA Aircraft Certification Office in the appropriate Region and request identification

of FAA Designated Engineering Representatives (DERs) who are authorized to prepare and approve the required antenna installation engineering data.

4. Obtain FAA Advisory Circular AC-183C and identify a DER from the roster of individuals in it.

5. Contact an aviation industry organization such as the Aircraft Electronics Association for

assistance.

For all composite aircraft, antenna installation requires that a ground plane be fabricated on the internal surface of the aircraft directly under the antenna. The TAS/TCAS antenna pattern is dependent upon a ground plane under the antenna. The minimum recommended antenna ground plane dimensions are 18” x 18” for composite aircraft.

A fabricated doubler plate assembly supplied by the installing agent or antenna vendor may be required inside the fuselage to complete the antenna hardware installation.

NOTE

For all GTS 8XX installations, a monopole antenna is recommended if installing an optional bottom mounted antenna on a fixed-gear aircraft, while retractable-gear aircraft may use either a monopole or a directional bottom mounted antenna. The target bearing accuracy may be degraded for bottom directional antenna installations on aircraft with fixed gear.

GTS 8XX/GPA 65 Installation Manual Page 2-3 190-00587-00 Revision 4TP

Page 22

2.2.1.1 TAS/TCAS Antenna Location

To achieve proper interrogation and surveillance volumes the following GTS 8XX antenna installation guidelines should be followed.

The GTS 8XX requires a top-mounted directional antenna. An optional bottom mounted directional or L-band monopole antenna can be installed in conjunction with the top-mounted directional antenna.

Antenna locations are critical to maintain the surveillance coverage across all azimuth and elevation angles. Locations shall be chosen so the top mounted and bottom mounted antenna will represent same range and bearing to an intruder. The mounting location, geometry, and surroundings of the antenna can affect the system performance. The following guidance provides information to aid the installer in ensuring that the most optimum location is selected for the installation of the antenna. Because meeting all of these installations guidelines may not be possible on all aircraft, these guidelines are listed in order of importance to achieve optimum performance. The installer must use best judgment to balance the installation guidelines.

Installations must be thoroughly tested to verify that performance degradation as a result of antenna placement is not an issue for the TAS/TCAS system as well as other systems.

1. As far as physically possible, the top directional antenna shall be mounted at the most forward

location.

2. The TAS/TCAS antenna(s) shall be mounted on the aircraft skin so that the horizontal base is

horizontal to within +/-5° in longitudinal and lateral axes when the aircraft is in level flight.

3. The TAS/TCAS antenna(s) shall be mounted on a flat section of the fuselage to reduce the gap

formed between the base plate and the fuselage when normal mounting torque is applied.

4. It is recommended that all antennas be mounted at least 20 inches away (measured from center to

center) from the TAS/TCAS antenna(s).

5. Ground plane considerations shall include minimization of any discontinuities such as overlapped

un-riveted airframe skins, cowlings, or hatches. It is recommended that all such discontinuities be at least 18 inches from the nearest edge of the TAS/TCAS antenna.

6. For installations using a bottom mounted antenna, it is recommended that the top and bottom

antennas be located near the same vertical line through the aircraft such that they represent the same range and bearing to an intruder.

7. The top and bottom mounted TAS/TCAS Antenna shall be as close as possible to the aircraft

centerline.

8. It is recommended that no antenna be mounted in front of the TAS/TCAS antenna(s).

Page 2-4 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 23

2.3 Electrical Bonding

Electrical equipment, supporting brackets, and racks should be electrically bonded to the aircraft’s main structure. Refer to SAE ARP 1870 section 5 when surface preparation is required to achieve electrical bond. The electrical bond should achieve direct current (DC) resistance less than or equal to 2.5 milliohms to local structure to where the equipment is mounted. Compliance should be verified by inspection using a calibrated milliohm meter. An equivalent OEM procedure may also be substituted. There may be OEM-specific reasons for electrically isolating equipment or having a higher bond resistance. These reasons should be rationalized upon installation approval. In general, Garmin recommends that all GTS 8XX equipment be electrically bonded.

The antenna ground plane and doubler plate must be electrically bonded to the antenna baseplate. The electrical bond must achieve direct current (DC) resistance less than or equal to 2.5 milliohms.

For composite aircraft, the antenna baseplate must be electrically bonded to the common ground of other installed equipment for lightning purposes. This can be achieved through the antenna mounting screws.

2.4 Cabling and Wiring

Use #24 AWG or larger diameter wire for all connections unless otherwise specified. The minimum diameter wire size for all GTS 8XX installation wiring is #24 AWG, except in the case of Aircraft Power and Aircraft Ground and both shall be a minimum of #18 AWG. Refer to Table 2-1 for GPA 65 wiring specifications.

A single circuit breaker shall be dedicated to the GTS 8XX unless specifically approved by the manufacturer on a case by case basis, or allowed by the STC. Do not attempt to combine more than one unit on the same circuit breaker unless it is specified on an aircraft manufacturer approved drawing, or STC documentation, for the specific installation requiring a combined configuration.

The current rating for each standard density 37-pin D-sub connector pin is 5 Amps, and the current rating for each high density 78-pin D-sub connector pin is 2 Amps. A 14 Vdc installation requires a minimum of two Aircraft Power and two Aircraft Ground wires in the harness. A 28 Vdc installation requires a minimum of one Aircraft Power and one Aircraft Ground wires in the harness.

It is the responsibility of the installing agency to take into account wire sizing based on the length and number of wires, current draw of the unit, D-sub connector pin current rating, and the unit’s internal protection requirements.

NOTE

GTS 8XX/GPA 65 Installation Manual Page 2-5 190-00587-00 Revision 4TP

Page 24

The maximum wiring length from the GTS 8XX to the GPA 65 is 45 feet.

Table 2-1. GPA 65 Minimum Wiring Requirements

Line

Number of

Pins/Wires

Length of Wire

Wire Gauge

Specification

+35V 2 Up To 45' #24 AWG

2 Up To 45' #24 AWG

+6V

1 Up To 30' #22 AWG 1 Up To 20' #24 AWG 2 Up To 45' #24 AWG

-5V

1 Up To 30' #22 AWG 1 Up To 20' #24 AWG

Ground 3 Up To 45' #24 AWG

The contacts used to facilitate the use of #18 AWG wire for Aircraft Power and Aircraft Ground have expanded-diameter barrels that extend out from the back of the standard D-sub connector body to accommodate the larger diameter wire. Appropriate heat shrink tubing should be utilized to provide sufficient insulation from surrounding contacts.

Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference. Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and routing near aircraft control cables.

NOTE

All appliance to antenna cabling shall bundle top channels as a group and bottom channels as a group to prevent incorrect wiring between top and bottom channels.

A visual inspection shall be performed to verify that all coaxial cables are connected properly, before attempting to operate the equipment.

Page 2-6 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 25

2.4.1 Coaxial Cable

The GTS 800 requires two sets of coaxial cable assemblies and the GTS 820/850 requires three sets of coaxial cable assemblies when a directional GA 58 antenna (or other Garmin approved antenna) is used for both top and bottom. Each set consists of four coaxial cable assemblies.

Each set of four cables must be assembled using the same type of coaxial cable in order to meet phase and attenuation matching requirements. In order for the system to operate in compliance with manufacturer specifications, the coaxial cable assemblies must not exceed the attenuation specifications as stated in this document. This section explains in further detail the coaxial cable and termination requirements.

2.4.1.1 GTS 800 Installations

NOTE

A monopole antenna is required if installing an optional bottom mounted antenna on all fixed-gear aircraft. Retractable-gear aircraft can use either a monopole or a directional bottom mounted antenna.

A GTS 800 installation with both top and bottom mounted directional antennas uses one set of coaxial cables for the four GTS 800 TOP jacks (J1 TOP, J2 TOP, J3 TOP, J4 TOP) that are connected to the corresponding top antenna jacks J1, J2, J3 and J4. A second set of coaxial cables are used for the four GTS 800 BTM jacks (J1 BTM, J2 BTM, J3 BTM, J4 BTM) that are connected to the corresponding bottom antenna jacks J1, J2, J3 and J4. Each cable assembly shall not exceed the maximum attenuation of 2.5dB at 1090MHz as shown in Figure 2-1.

Figure 2-1. GTS 800 Installation with Top and Bottom Directional Antennas

If an optional bottom mount monopole antenna is installed, a single coaxial cable must be used to connect the GTS 800 bottom jack J1 BTM to the monopole antenna jack. The coaxial cable assembly shall not exceed the maximum attenuation of 2.5dB at 1090MHz as shown in Figure 2-2 and stated in Table 2-4. Each of the remaining GTS 800 bottom jacks (J2 BTM, J3 BTM, J4 BTM) are to be terminated using a QMA 2 watt termination as specified in Table 2-2.

GTS 8XX/GPA 65 Installation Manual Page 2-7 190-00587-00 Revision 4TP

Page 26

Figure 2-2. GTS 800 Installation with Top and Bottom Monopole Antennas

If no bottom mount antenna is installed, each of the GTS 800 bottom jacks (J1 BTM, J2 BTM, J3 BTM and J4 BTM) must be terminated with a QMA 2 watt termination as specified in Table 2-2 and shown in Figure 2-3.

Figure 2-3. GTS 800 Installation with Top Directional Antennas and No Bottom Antenna

Page 2-8 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 27

2.4.1.2 GTS 820 and GTS 850 Installations

GTS 820 and GTS 850 installation with both top and bottom mount directional antennas use one set of coaxial cables for the four GTS 820 or GTS 850 TOP jacks (J1 TOP, J2 TOP, J3 TOP, J4 TOP) that are connected to the corresponding GPA 65 processor unit jacks (J1U, J2U, J3U, J4U).

Each top cable assembly shall not exceed the maximum attenuation of 3.0dB at 1090MHz as shown in Figure 2-4 and stated in Table 2-3. Each bottom cable assembly shall not exceed the maximum attenuation of 2.5dB at 1090MHz as shown in Figure 2-4 and stated in Table 2-3.

A second set of coaxial cables are used to connect the four GPA 65 antenna jacks (J1A, J2A, J3A, J4A) to the corresponding top antenna jacks (J1, J2, J3, J4). Each cable assembly shall not exceed the maximum attenuation of 0.4dB at 1090MHz as shown in Figure 2-4 and stated in Table 2-3. A third set of coaxial cables are used to connect the four LRU BTM jacks (J1 BTM, J2 BTM, J3 BTM, J4 BTM) to the corresponding bottom antenna jacks (J1, J2, J3, J4). Each cable assembly shall not exceed the maximum attenuation of 2.5dB at 1090MHz as shown in Figure 2-4.

Figure 2-4. GTS 820 and GTS 850 Installation with Top and Bottom Directional Antenna

If an optional bottom mount monopole antenna is installed, a single coaxial cable must be used to connect the GTS 820 or GTS 850 J1 BTM jack to the monopole antenna jack. The cable assembly shall not exceed the maximum attenuation of 2.5dB at 1090MHz as shown in Figure 2-5 and stated in Table 2-3. Each of the remaining GTS 820 or GTS 850 bottom jacks (J2 BTM, J3 BTM, J4 BTM) are to be terminated using a QMA 2 watt termination as specified in Table 2-2.

GTS 8XX/GPA 65 Installation Manual Page 2-9 190-00587-00 Revision 4TP

Page 28

Figure 2-5. GTS 820 and GTS 850 Installation with Top Directional and Bottom Monopole

Antenna

If no bottom mount antenna is installed, each of the GTS 820 or GTS 850 bottom jacks (J1 BTM, J2 BTM, J3 BTM and J4 BTM) shall be terminated with a QMA 2 watt termination as specified in Table 2-2 and shown in Figure 2-6.

Figure 2-6. GTS 820 and GTS 850 Installation with Top Directional and No Bottom

Antenna

Page 2-10 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 29

NOTE

Any QMA terminations used other than those specified in Table 2-2 will constitute the installation as being non-compliant with the manufacturer’s installation standards.

2.4.1.3 Fabrication of Coaxial Cable Assemblies

The installing agency may fabricate cable assemblies by terminating either M17/128-RG400 or M17/60-RG142 coaxial cable with available QMA connector kits. Table 2-2 lists recommend cable types to be used with specified QMA connectors for the GTS 8XX.

Table 2-2. Cable Types and QMA Connectors

Connector

Type

QMA Right

Angle

QMA

Straight

Cable Type Manufacturer

RG 400, RG 142,

ECS 311901

ECS 311501, ECS 311601, ECS 421601,

PIC S67163

RG 400, RG 142,

ECS 311901

ECS 311501, ECS 311601, ECS 421601,

PIC S67163

Amphenol 930-189P-51A

Garmin 330-00500-00

Amphenol 930-191P-51A

ECS 930-191P-51A

PIC 110477

Amphenol 930-192P-51S

Garmin 330-00500-01

Amphenol 930-190P-51S

ECS 930-190P-51S

PIC 110476

Connector

Part Number

Garmin Order Number

4 Piece Kit 1 Piece Kit

011-01364-00 011-01364-02

N/A

011-01364-01 011-01364-03

N/A

QMA 50

Load

Termination

N/A

Amphenol 930-187P-51T

011-01364-04 N/A

Garmin 330-00500-02

The recommended coaxial cable lengths in Table 2-3 are for reference only. Along with standard MIL-C17/128-RG400 or MIL-C-17/60-RG142, Table 2-3 lists recommended antenna cable vendors along with the cable type that each specific vendor offers. The recommended coaxial cable lengths are defined as the end to end length of a non-terminated coaxial cable. The attenuation values listed in Table 2-3 include the maximum attenuation of both the maximum length of coaxial cable and two RF coaxial connectors at a frequency of 1090 MHz. It is the installing agencies responsibility to ensure that the coaxial cable assemblies built meet the manufacturer’s attenuation specifications in order to comply with the manufacturer’s installation standards.

NOTE

Any in-line or bulkhead penetrations must be evaluated separately. It is the installing agency’s responsibility to show airworthiness of the installed fabricated or purchased coaxial cable assemblies.

GTS 8XX/GPA 65 Installation Manual Page 2-11 190-00587-00 Revision 4TP

Page 30

Table 2-3. Recommended Coaxial Length

Attenuation

Loss

0.4 dB

1' 10"

[0.55m]

2' 0"

[0.60m]

2' 5"

[0.74m]

3' 3"

[0.99m]

3' 5"

[1.04m]

4' 2"

[1.27m]

4' 0"

[1.21m]

Loss

0.5 dB

2' 7"

[0.79m]

2' 9"

[0.84m]

3' 4"

[1.02m]

4' 6"

[1.37m]

4' 6"

[1.37m]

5' 7"

[1.70m]

5' 5"

[1.60m]

Loss

1.5 dB

9' 0"

[2.74m]

10' 5"

[2.94m]

11' 6"

[3.50m]

15' 8"

[4.77m]

16' 1"

[4.90m]

19' 8"

[5.99m]

18' 5"

[5.61m]

Loss

2.0 dB

12' 0"

[3.66m]

13' 0"

[3.96m]

15' 5"

[4.70m]

21' 0"

[6.40m]

21' 5"

[6.55m]

26' 5"

[8.05m]

25' 0"

[7.62m]

Supplier Information

Loss

2.5 dB

15' 5"

[4.70m]

16' 6"

[5.03m]

19' 6"

[5.94m]

26' 8"

[8.13m]

27' 6"

[8.38m]

33' 5"

[10.19m]

31' 6"

[9.60m]

Loss

3.0 dB

18' 8"

[5.68m]

20' 1"

[6.12m]

23' 10"

[7.26m]

32' 7"

[9.93m]

33' 6"

[10.21m]

40' 10"

[12.44m]

38' 3"

[11.65m]

Attenuation

15.5

14.45

12.16

8.93

8.7

7.12

7.5

(dB/100ft)

ECS Type

311901

421601

311601

311501

S67163

Vendor: Electronic Cable Specialists

5300 W. Franklin Drive Franklin, WI 53132 Tel: 800327-9473 414-4215300 Fax: 414421-5301

www.ecsdirect.c

PIC Type

Vendor: PIC Wire and Cable

N53 W24747 S Corporate Circle Sussex, WI 530890330 Tel: 800742-3191 262-2460500 Fax: 262246-0450

www.picwire.c

M17/128

-RG400 M17/60-

RG142

M17/127

-RG393

See current issue of Qualified Products List QPL-17.

RG Type

MIL-C-17 Type

RG-400

RG-142

RG-393

RG types are obsolete and are shown for reference only; replaced by M17 type numbers.

Page 2-12 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 31

The coaxial cable lengths in each coaxial cable assembly set used to connect the GTS 800 TOP and BOTTOM jacks to the top and bottom antenna jacks, the TOP GTS 820 or GTS 850 jacks to the GPA 65 jacks, and the BOTTOM GTS 820 or GTS 850 jacks to the directional antenna jacks, shall be within 2 inches of each other.

The coaxial cable assembly lengths in each coaxial cable assembly set between the GPA 65 jacks and directional antenna jacks for the GTS 820 or GTS 850 shall be within 0.25 inches of each.

Table 2-4. Coaxial Cable Set Length Tolerance

Coaxial Cable Set Length Tolerance*

GTS 800 TOP/BOTTOM to top and bottom

2" of each other

antenna GTS 820 and/or 850 TOP to GPS 65 2" of each other GTS 820 and/or GTS 850 BOTTOM to

directional antenna GPA 65 to directional antenna (for the GTS

820 and/or GTS 850

2" of each other

0.25" of each other

* Ensure cables do not exceed the maximum lengths as stated in Table 2-3.

NOTE

It is recommended that a color band be placed on both ends of each cable to match the color marking designating the mating jack connector.

NOTE

It is recommended that the nominal end to end coaxial cable (non-terminated) length for each set be recorded for the specific installation in the event that a particular coaxial cable assembly associated with an installed set should require replacement.

GTS 8XX/GPA 65 Installation Manual Page 2-13 190-00587-00 Revision 4TP

Page 32

2.4.1.4 Coaxial Cable Assembly Instructions

The following assembly instructions apply to coaxial cables assemblies using QMA connectors specified in Table 2-2 for use with RG-400 or RG-142 cable types:

1. Slide the heat shrink sleeve and crimp ferrule onto the cable.

2. Strip the cable to the dimensions shown in Figure 2-7.

Figure 2-7. RG-400/RG-142 Coaxial Cable Stripping Dimensions

3. Slide the center contact onto the center conductor of the cable. Ensure the center conductor of the

cable is visible through the inspection hole of the center contact and crimp using Tyco tool 354940-1 and die assembly 220189-3, or Tyco tool 354940-1 and die assembly 91901-1, or Tyco tool 69478-1.

4. Expand the shielding braid and insert the crimped center contact into the connector body until the

cable dielectric is flush with the dielectric inside the connector body. Insure the shield braid does not enter the connector body.

Figure 2-8. Ferrule and Crimp Die Positioning

5. Slide the crimp ferrule over the shielding braid to the back of the connector body. Position the

crimp tool flush with the back of the connector body and crimp using Tyco tool 35940-1 and die assembly 220189-3, or Tyco tool 354940-1 and die assembly 91901-1, or Tyco tool 69478-1. The crimp tool should be positioned such that a “bellmouth” (see figure 2-8) is present in the crimp ferrule on the coaxial cable side of the crimp after crimping.

6. Slide heat shrink sleeve to back of connector body and shrink in place. Ensure that the heat

shrink does not protrude past the connector body back end once it is shrunk into place. It is recommended that the color-coded heat shrink tubing provided in the kit be used.

Page 2-14 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 33

Figure 2-9. Heat Shrink Positioning

NOTE

Use of QMA connectors other than those specified in Table 2-2 for coaxial cable assemblies fabricated by the installing agency using either M17/128-RG400 or M17/60-RG142 coaxial cable will constitute the cable assemblies as being non-compliant with the manufacturer’s installation standards.

2.4.1.5 Coaxial Cable Assem bly Repair and Rework

In the event that an individual coaxial cable assembly requires rework, between a GTS 800 jack and antenna jack, a TOP GTS820/850 jack and GPA 65 jack or a BTM GTS 820/850 jack and antenna jack, the repairable coaxial cable may be reduced in length a maximum of two inches.

In the event that rework is required on a coaxial cable assembly between a GPA 65 jack and antenna jack on a GTS 820/850 installation, complete replacement of the cable assembly shall be required in lieu of rework.

Refer to Table 2-3 for recommended maximum cable assembly lengths for cable assemblies fabricated by the installer.

2.5 Cooling Requirements

The GTS 8XX and GPA 65 meet all TSO requirements without external cooling. A 5/8” diameter air fitting is provided on the rear of the GTS 8XX for the purpose of admitting cooling air if desired. If a form of forced air cooling is installed, make certain that rainwater cannot enter and be sprayed on the equipment.

For G1000 installations refer to the G1000 System Installation manual, Garmin part number 190-00303-00, for more information on cooling requirements.

GTS 8XX/GPA 65 Installation Manual Page 2-15 190-00587-00 Revision 4TP

Page 34

2.6 Mounting Requirements

The GTS 8XX can be mounted vertically or horizontally using the installation racks shown below. Refer to Appendix A for outline and installation drawings.

Figure 2-10. GTS 8XX Vertical Installation Rack (Garmin P/N115-00781-00)

Figure 2-11. GTS 8XX Horizontal Installation Rack (Garmin P/N115-00784-00)

Page 2-16 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 35

3 INSTALLATION PROCEDURE

3.1 Unpacking Unit

Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment. If the unit is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return the unit to Garmin until the carrier has authorized the claim. Retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement.

3.2 Wiring Harness Installation

Allow adequate space for installation of cables and connectors. The installer shall supply and fabricate all of the cables. All electrical connections are made through two 78-pin high-density D subminiature connectors, one 37-pin standard density connector, and one 19-pin circular connector (GTS 820 and GTS 850 only). Section 4 defines the electrical characteristics of all input and output signals. Required connectors and associated hardware are supplied with the connector kit.

See Appendix B for examples of interconnect wiring diagrams. Construct the actual harness in accordance with aircraft manufacturer authorized interconnect standards.

Table 3-1. Socket and Pin Contact Part Numbers

78 Pin High Density D-Subminiature Connectors P8001 & P8002

37 Pin Standard Density D-Subminiature Connector P8003

19 Pin Circular Connector P651

Manufacturer

High Density Pin

(P8001 & P8002)

Garmin P/N 336-000 21-00 336-00022-00 N/A 336-00023-00 Military P/N M39029/58 -360 M39029/63-368 M39029/5-115 N/A

Positronic * * * FC6018D

AMP * 205090-1 * *

ITT Cannon * 031-1007-042 * 031-1007-054**

*Identify manufacturer part number by MIL SPEC identification ** Use only positioner part numbers ITT Cannon 980-0005-722, Astro Tools 616245 a nd Daniels MFG K250

Standard

Socket

(P8003)

Circular

Connector

Socket

(P651)

Standard Socket

(P8003)

Table 3-2. Socket Contact MIL SPEC M39029/5-115 Crimp Tooling

Manufacturer

Hand Crimping

Tool

Positioner

Insertion/Extraction

Tool

Tools Option 1

Military P/N M22520/1-01

Daniels

AF8 TH1A M81969/14-11*

M22520/1-02 M81969/14-11*

Tools Option 2

Military P/N M22520/2-01

Daniels

* Indicates plastic insertion/extraction tool

AFM8 K1S M81969/14-11*

M22520/2-02 M81969/14-11*

GTS 8XX/GPA 65 Installation Manual Page 3-1 190-00587-00 Revision 4TP

Page 36

Table 3-3. Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling

Manufacturer

Military P/N M22520/2-01 M22520/2-09 M81969/1-04

Daniels AFM8 K42 M81969/1-04

Positronics 9507 9502-4 M81969/1-04

ITT Cannon 995-0001-584 M22520/2-09

Tyco-AMP 601966-1 601966-6

Astro 615717 615725 M81969/1-04

Amphenol 9507 9502-4 M81969/1-04

* Indicates plastic insertion/extraction tool

Hand Crimping

Tool

Positioner

Insertion/Extraction

Tool

274-7048-000*

MIL SPEC M81969/14-01

91067-1

MIL SPEC M81969/1-04

Table 3-4. Pin Socket Contacts GPN 336-00022-00 MIL SPEC M39029/63-368 and GPN

336-00023-00 Crimp Tooling

Manufacturer

Hand

Crimping

Tool

22 AWG Socket Contact

GPN 336-00022-00

(M39029/63-368)

Positioner

Insertion/Extraction

Tool

18 AWG Socket Contact

GPN 336-00023-00

Positioner

Insertion/Extraction

Tool

Military P/N M22520/2-01 M22520/2-08 M81969/1-02 N/A M81969/1-02

Daniels AFM8 K13-1 M81969/1-02 K774 M81969/1-02

Positronics 9507 9502-5 M81969/1-02 9502-11 M81969/1-02

980-0005-722**

ITT Cannon 995-0001-584 995-0001-604 980-2000-426*

Tyco-AMP 601966-1 601966-5

ASTRO 615717 615724 M81969/1-02 616245** N/A

Amphenol 9507 N/A N/A 9502-11 M81969/1-02

* Indicates plastic insertion/extraction tool ** Use only positioner part numbers ITT Cannon 980-0005-722, Astro Tools 616245 a nd Daniels MFG K250 for

contact part number ITT Cannon 031-1007-001

91067-2 or

M81969/1-02

Daniels K250**

N/A N/A

N/A

Page 3-2 GTS 8XX/GPA 65 Installation Manual Revision 4TP 190-00587-00

Page 37

NOTES

1. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject

to change without notice.

2. Extracting a contact used for #18 AWG requires that the wire barrel be cut off from the

contact. It may also be necessary to push the pin out from the face of the connector when using and extractor due to the absence of the wire. A new contact must be used when reassembling the connector.

3. Contacts for #16 AWG and Contact Crimp Tooling: Contact Garmin for information regarding

contacts and contact crimp tooling. Note 2 also applies.

4. Alternate Contacts for Use With #18 AWG: As an alternative to the Positronic contacts listed,

and provided in the installation kit, if the need arises the installer may use contacts made by ITT Cannon under P/N 031-1007-001. The particular contact is not compatible with the Daniels MFG K774, Positronics 9502-11 or Amphenol 9502-11 positioners, though. Only use postioner part numbers Daniels MFG K250, ITT Cannon 980-0005-722 and Astro 616245.

3.3 QMA Connector Insertion and Removal

To engage the QMA connectors, use the outer sleeve of the QMA plug to align the connectors and insert the plug onto the jack until it snaps into place. There will be an audible “snap” when the connectors are fully engaged, refer to Figure 3-1. No tools are required for the insertion of a QMA plug onto a QMA jack.

Engage

Outer Sleeve

Figure 3-1. Engaging QMA Connectors

GTS 8XX/GPA 65 Installation Manual Page 3-3 190-00587-00 Revision 4TP

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CAUTION

Do not pull on the cable when removing the QMA plug from the jack.

To disengage the QMA connectors, pull back firmly on the outer sleeve of the QMA plug away from the jack connector (refer to Figure 3-2). This will disengage the locking mechanism that secures the plug connector to the jack connector. Pulling on or disengaging the QMA connectors in any other way is not recommended and may cause damage to both the connectors and coaxial cable.

Disengage

Figure 3-2. Disengaging QMA Connectors

Outer Sleeve

CAUTION

Side-loading of the QMA connectors should be avoided during both the insertion and removal of the connectors. It is recommended service loops with adequate length of coaxial cable be used to insure that side-loading on the connectors is minimized once the cable is securely fastened in the aircraft. Excessive side-loading may result in damage or premature failure of the QMA connectors.

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3.4 Backshell, Pigtail Circular Connector, and Configuration Module Assemblies

The GTS 8XX connector kits includes three Garmin backshell assemblies. The backshell assembly houses the configuration module, if applicable. Garmin’s backshell also gives the installer the ability to easily terminate shield grounds at the backshell housing.

Refer to the Jackscrew Backshell Installation Instructions (Garmin part number 190-00313-11) for backshell assembly instructions.

Refer to the GPA 65 Pigtail Circular Connector Installation Instructions (Garmin part number 190-00313-XX) for pigtail assembly instructions.

Refer to the Jackscrew Configuration Module Installation Instructions (Garmin part number 190-00313-10) for configuration module assembly instructions.

3.5 Unit Installation

Refer to the outline and installation drawings shown in Appendix A of this manual

GTS 8XX/GPA 65 Installation Manual Page 3-5 190-00587-00 Revision 4TP

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3.5.1 Post Installation Configuration & Checkout

Before beginning the installation calibration, the installer must perform a visual inspection to verify the coaxial cables are installed correctly based upon the system and antenna configuration.

NOTE

Tests performed with a ramp tester should be performed away from buildings that may reflect the signal. Local air traffic control should be advised if the ramp tester has an altitude programmed into it that may cause interaction with other TCAS-equipped traffic.

The following actions need to be performed after the equipment is installed:

1. GTS 8XX Configuration Options

2. CDTI (Cockpit Display of Traffic Information) Display setup and configuration

3. Calibration

4. Self test

5. Ramp test and return to service tests

6. Antenna verification

3.5.2 GTS 8XX Configuration Options

GTS 8XX Configuration is performed using a computer (installed with Microsoft Windows XP or later) and the GTS 8XX Install Tool, Garmin part number 006-A0242-00. The tool is available for download from the Dealers Only portion of the Garmin website (www.garmin.com).

G1000 Installations:

When installed as part of the G1000 integrated flight deck, the GTS 8XX must have FAA approved configuration data. Configuration data is loaded to the GTS 8XX from an aircraft-specific G1000 software loader card.

For basic configuration information refer to the G1000 Line Maintenance and Configuration Manual (190-00303-04), G1000 System Maintenance Manual LJ/VLJ (190-00903-00), or the G1000 System Maintenance Manual Standard Piston/Turboprop Aircraft (190-00907-00). For actual installation/checkout, use only aircraft manufacturer approved or STC checkout procedures.

Non-G1000 Installations:

Configuration and software uploading is accomplished by using a computer (installed with Microsoft Windows XP or later) and the GTS 8XX Install Tool. An optional USB pigtail installed in the wiring harness may be used.

The GTS 8XX Install Tool allows for configuration, diagnostics, and upload of GTS 8XX software. The following GTS 8XX modes are accessible with the GTS 8XX Install Tool.

• Normal Mode – Allows selection of Traffic Mode to Standby, Operate, or Test. Reports

System Faults, Status Flags, and Operating Status. Allows Ground Test Mode to be Enabled or Disabled.

• Configuration Mode – Allows selection of installation options

• Upload Mode – Allows upload of software to GTS 8XX unit

• Debug Mode – Runs system diagnostics

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3.5.2.1 Normal System Mode Tab

The Normal tab displays various faults, flags, and operational information. When the Normal tab is selected, the unit is commanded to Normal System Mode.

Normal Mode –

System Faults:

Status Flags:

Traffic Mode Status:

Ground Test:

Figure 3-3. GTS 8XX Install Tool – Normal Tab

Red Bold text indicates that a fault is active.

Gray text indicates that there is no active fault. (System Faults are described in the Self-Test section.)

Black Bold text indicates that a flag is set. Gray text indicates that the flag is not set. (Status Flags are described in the Self-Test section.)

Standby – Unit is not transmitting or receiving data Operate – Unit is interrogating and processing received data Test – Allows special transmit interrogation rates and data patterns to be initiated (Selected mode is active.)

Enabled Disabled (Ground Test is described in the Ramp Test and Return to Service Tests section.

GTS 8XX/GPA 65 Installation Manual Page 3-7 190-00587-00 Revision 4TP

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3.5.2.2 Configuration System Mode Tab

The Configuration tab displays configuration data and allows the installer to change the installation configuration. When the Configuration tab is selected, the unit is commanded to Configuration System Mode.

Figure 3-4. GTS 8XX Install Tool – Configuration Tab (GTS 800)

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Figure 3-5. GTS 8XX Install Tool – Configuration Tab (GTS 820 and GTS 850)

The Configuration tab displays installation configuration options. Changes made in the Configuration tab are not immediately committed to the GTS. Changed options will be colored yellow until ‘Set Active’ is selected.

Configuration Mode –

Barometric Altitude Source:

Note: At least one source must be selected (same altitude source used for the transponder).

Primary A429 RX Channels 1 - 6 or Disabled Secondary A429 RX Channels 1 - 6 or Disabled COM RS-232 Ports 1 - 5 or Disabled

Magnetic Heading Source (optional):

Primary A429 RX Channels 1 - 6 or Disabled Secondary A429 RX Channels 1 - 6 or Disabled

Radio Altitude Source (optional): A429 A429 RX Channels 1 - 6 or Disabled Analog Disabled

ARINC 552 ARINC 552A Bonzer MK10X Collins ALT50 Collins ALT55 King KRA10 King KRA405 Sperry AA100 Terra TRA3000 Terra TRA3500

GTS 8XX/GPA 65 Installation Manual Page 3-9 190-00587-00 Revision 4TP

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GPS Position/Velocity/Time Source:

Note: At least one source required for ADS-B IN functionality.

Primary A429 RX Channels 1 - 6 or Disabled Secondary A429 RX Channels 1 - 6 or Disabled

Traffic Display Destination:

Note: At least one source is required.

Primary A429 TX Channels 1 - 6 or Disabled

COM RS-232 Ports 1 - 5 or Disabled

Transponder 1 & 2 Communication:

Note: At least Transponder 1 RX and TX required for GTS 820 and GTS 850. Primary should be configured for channels wired to Transponder 1. Secondary should be configured for channels wired to Transponder 2 in a dual transponder installation.

Primary RX A429 RX Channels 1 - 6 or Disabled

Primary TX A429 TX Channels 1 - 6 or Disabled Secondary RX A429 RX Channels 1 - 6 or Disabled Secondary TX A429 TX Channels 1 - 6 or Disabled

Top Antenna: Model None

Monopole Garmin GA58 Sensor Systems

Cable loss (dB) 0.2 – 4.0

Note: Cable loss information is described in Fabrication of Coaxial Cable Assemblies section.

Bottom Antenna: Model None

Monopole Garmin GA58 Sensor Systems

Cable loss (dB) 0.2 – 4.0

Note: Cable loss information is described in Fabrication of Coaxial Cable Assemblies section.

Note: All A429 options have the ability to select High or Low speed.

Note: If an input is inactive, a

If an input is active, a

If an input is in an unknown state, a

will be displayed.

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Volume Level:

Allows audio volume level selection from 0 to -63 dB in 0.5 dB increments.

Maximum audio output is at least 80 mW into a 600 Ohm load. (6.93 Vrms)

Voice Gender:

Enter voice preference selection.

Gear/Wheel:

Enter type of aircraft gear design.

ADSB TX Capable:

Indicate whether aircraft is equipped with ADS-B transmitter.

Squat ‘on-ground’ Sense: Indicate type of sense switch.

Mode S ID (HEX):

Applicable to GTS 820 and GTS 850 only. Enter Mode S transponder ID (must match the

Mode S ID used by the transponder).

Set Active:

Must select Set Active to enable the settings on the GTS 8XX.

Revert Changes:

Select to show current GTS 8XX settings.

An incorrect configuration will be reverted back to previous settings.

Note: Default is “disabled” for all inputs and outputs.

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3.5.2.3 Upload System Mode Tab

The Upload tab displays version information for Boot Block, Region List, System, FPGA, Audio, Magnetic Variation. Boot Block updating is not allowed. For other files, select the appropriate image files and select upload.

Figure 3-6. GTS 8XX Install Tool – Upload Tab

3.5.2.4 Debug Tab

The Debug tab is reserved and not available for field installation use.

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3.5.3 CDTI Display Setup and Configuration

For configuration of the displays, refer to their respective installation manuals.

• 500 Series Installation Manual (190-00181-02)

• GMX 200 Installation Manual (190-00607-04)

• GDU 620 Installation Manual (190-00601-04)

• G1000 Line Maintenance and Configuration Manual (190-00303-04)

• G1000 System Maintenance Manual LJ/VLJ (190-00903-00)

3.5.4 Self Test

A self-test feature tests the (aural) alarm, atte mpts self calibration, and activates ea ch display element in a pre-determined sequential pattern to allow visual verification that display outputs issued by the digital processor can be correctly interpreted by the pilot.

NOTE

Self tests may be performed indoors but signal multi-path from building walls may be a factor. If problems are experienced, self tests should be performed outside away from buildings, and where local traffic is not a factor.

With the GTS 8XX powered up and Standby indicated on the CDTI, cycle the GTS 8XX to Self Test. The self test feature of the GTS 8XX tests the following i nternal parameters as well as performs calibration of various components in the GTS 8XX:

a) Calibration data fault – Stored factory calibration parameters are invalid. Return unit to Garmin

for service.

b) Configuration data fault – Stored system configuration parameters are invalid or Mode S address

is invalid (All 0’s or F’s ). Fault will persist until configuration is corrected. Attempt configuration per the Configuration Section.

c) FPGA fault – Check of the FPGA image failed. Fault will persist until valid FPGA image is

loaded. If upload of FPGA image was recently attempted, retry the upload. Otherwise, return unit to Garmin for service.

d) ROM fault – Internal non-volatile memory failure, or invalid data image detected. If upload of

audio image or IGRF magnetic field image was recently attempted, retry the upload. Otherwise return unit to Garmin for service.

e) Execution fault – CPU execution fault has occurred. Cycle power and retry self test. If fault

persists, return unit to Garmin for service.

f) Electrical fault – One of the internal electrical voltages are out of range. Fault will persist until

power is cycled. Check aircraft power supply. If fault persists, return unit to Garmin for service.

g) Whisper Shout fault – Transmitted power is out of tolerance. Check cable loss configuration,

antenna installation and all cable connections and retry self test. If fault persists, return unit to Garmin for service.

h) Transmit Power fault - One of the internal transmitter power source voltages are out of range.

Fault will persist until power is cycled. Check aircraft power supply. If fault persists, return unit to Garmin for service.

i) 1030 MHz Frequency Source fault - Transmit Frequency synthesizer is not locked. Cycle power

and retry self test. If fault persists, return unit to Garmin for service.

j) 1090 MHz Frequency Source fault - Receive Frequency synthesizer is not locked. Cycle power

and retry self test. If fault persists, return unit to Garmin for service.

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k) Receiver Calibration fault. Check antenna installation and all cable connections and retry self

test. Ensure that self test occurs in area free of buildings and large objects that can reflect signals. If fault persists, return unit to Garmin for service.

NOTE

Receiver self-calibration is performed prior to the transmitter self-calibration. In the event that a receiver calibration fault occurs, a transmitter self-calibration will not be performed.

l) Transmitter Calibration fault. Check antenna installation and all cable connections and retry self

test. Ensure that self test occurs in area free of buildings and large objects that can reflect signals. If fault persists, return unit to Garmin for service.

NOTE

A transmitter self-calibration can only be performed after a successful receiver selfcalibration.

m) Barometric Altitude Input fault – Own ship barometric altitude calculation is invalid or has timed

out. Check wiring to source of barometric altitude and ensure that source is operating. Fault will clear as soon as valid barometric altitude data is received.

n) Main Board Temperature fault – Main board temperature or RF receiver temperature is greater

than 90° Celsius or less than -60° Celsius. Fault will persist until internal temperature returns to acceptable range.

o) TCAS Equipage Timeout fault – TCAS Equipage data is not being received or has timed out for

800ms. Check wiring to TCAS Equipage data source and ensure that source is operating. Fault will clear as soon as valid TCAS Equipage data is received.

The self test feature also checks the following external parameters:

a) Mag Variation – Magnetic variation data (difference between ‘True’ North and Magnetic North)

is available.

b) GPS Status – GPS Position, Velocity and Time data is available c) Display #1 status - Check of Traffic display #1 discrete input is inactive for 2 or more seconds. d) Display #2 status - Check of Traffic display #2 discrete input is inactive for 2 or more seconds. e) Radio Altimeter Input status – Radio altimeter is installed and radio altimeter input status is

inactive.

f) Magnetic Heading Input status – Invalid magnetic heading data is received. g) Maintenance/Data logger Input status – Data logger is inhibited if active. h) Self Test Inhibit status – Self test is inhibited if active.

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When the display receives an indication that a pilot initiated Self Test is in progress, this state is clearly annunciated on the traffic display and the following test patterns will be executed.

Figure 3-7. Self Test

Table 3-5. Self Test

Intruder #1 (transmitted in intruder number field)

2.0 NM Vertical Rate = Climbing, relative altitude = –200 feet TA, Bearing = –90 degrees

Intruder #2 (transmitted in intruder number field)

3.625 NM Vertical Rate = Descending, relative altitude = –1,000 feet Prox Traffic, Bearing = +33.75 degrees

Intruder #3 (transmitted in intruder number field)

3.625 NM No vertical rate, relative altitude = +1,000 feet Other traffic, bearing = –33.75 degrees.

Audio annunciation shall be:

GTS 800/820 - “TAS system Passed” or “TAS system Failed” GTS 850 - “TCAS system Passed” or “TCAS system Failed”

Any faults and flags are also displayed on the Normal tab of the GTS8XX Install Tool. Faults that occur will be colored in red and flags will be colored in black.

If self test fails, refer to the diagnostics data to determine a cause.

Insure that no Intruder appears at close range to own aircraft.

NOTE

If the intruder appears at close range to own aircraft, verify that the mutual suppression line is connected between GTS 8XX and other L-band equipment (transponder, DME, etc.).

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3.5.5 Ramp Test and Return To Service Test

Using a ramp tester, such as a TIC TR220 or equivalent, make the following setup and measurements to verify GTS 8XX operational and surveillance functional.

To select a scenario that will properly converge and intercept the GTS 8XX, the GTS 8XX must be in Ground Test mode. To enable Ground Test mode, the aircraft must be on the ground and the GTS 8XX must be in Normal System mode and in Standby.

Activate ground test mode by clicking ‘Enable’ in the Ground Test field on the Normal tab of the GTS 8XX Install Tool.

Figure 3-8. Ground Test

This simulates the GTS to be airborne at 50,000 ft with magnetic heading of 0°.

NOTE

The GTS 8XX will not accept the Ground Test command unless the unit is in Standby and the squat switch indicates the aircraft is on the ground.

Position the test set directional antenna with a clear line of sight to the GTS 8XX antenna at 90 degrees. With the GTS 8XX powered up and in Standby mode indicated on the CDTI, cycle the GTS 800 to “Operate”.

Select the following scenario: Set the intruder type as ATCRBS.

Intruder Start Distance Intruder Start Altitude Vertical Speed Velocity 10 NM 50,000 ft 0 fpm. 360 Kts

Initiate the intruder scenario and observe the following:

• Traffic should be acquired at approximately 10 NM at 90 degree bearing and co-altitude.

Observe intruder closes on own aircraft at a rate of .1 NM/sec.

• The intruder should transition from Other Traffic (displayed as an open diamond with 00

displayed above), to proximate traffic (displayed as a filled white diamond with 00

displayed above), to a Traffic Advisory (TA) alarm.

• The appropriate TA symbology (yellow filled circle with 00 displayed above, and an audio

annunciation of "Traffic! 3 O'clock! At Altitude! 3 Miles!"), displayed when the

intruder approaches within 3 NM.

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3.5.6 Antenna Verification

The first step in antenna verification is to verify auto-calibration operates without indicating a fault.

1. With the GTS 8XX powered up and “Standby” indicated on the CDTI cycle the GTS 8XX to

“Operate”. Each time the GTS 8XX transitions between these modes a self test of the antenna circuit is initialized. If the antenna connection is not correct the CDTI will display “Failure” indicating it will be necessary to recheck the antenna coaxial connections. If the CDTI displays “Operate” without indicating a fault, proceed to the next step of antenna verification.

Using a ramp tester, such as a TIC TR220 or equivalent, make the following set up and measurements to assure the antenna is properly connected and the GTS 8XX is operational.

2. Position the test set directional antenna with a clear line of sight to the GTS8XX antenna.

3. Ensure that the transmitter or receiver (RX/TX) that you are testing is significantly closer to the

ramp tester than another operating RX/TX, or erroneous and inaccurate results may occur. All four quadrants (forward, starboard, aft, and port) will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the CDTI.

4. Using the ramp tester, select the proper antenna gain and distance to aircraft.

5. Position ramp test set at 0 degrees.

6. Turn the test set on.

7. Connect the directional antenna to the ramp test set.

8. Set the multifunction test set to perform “TCAS” testing. Configure the GTS 8XX to the

normal operating mode.

9. Program a static intruder per the following scenario:

NOTE

See ramp test set operators manual to set the following parameters

Intruder Start Distance Intruder Start Altitude Vertical Speed Velocity 2 NM 50,000 0 fpm. 0 Kts

10. Set the intruder type as ATCRBS.

11. Verify a target is annunciated on the GTS 8XX TAS/TCAS display at the correct bearing of

approximately 0 degree azimuth at 2 NM and co-altitude (read as 00 above a filled diamond indicating proximate traffic).

12. Toggle intruder traffic to standby or off.

13. Reposition ramp test set and directional antenna to a starboard position of 90 degrees.

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14. Reengage the same intruder scenario as above.

15. Verify a target is annunciated on the GTS 8XX TAS/TCAS display at the correct bearing of

approximately 90 degree azimuth at 2 NM and co-altitude.

16. Toggle intruder traffic to standby or off.

17. Reposition ramp test set and directional antenna to an aft position of 180 degrees.

18. Reengage the same intruder scenario as above.

19. Verify a target is annunciated on the GTS 8XX TAS/TCAS display at the correct bearing of

approximately 180 degree azimuth at 2 NM and co-altitude.

20. Toggle intruder traffic to standby or off.

21. Reposition ramp test set and directional antenna to a port position of 270 degrees.

22. Reengage the same intruder scenario as above.

23. Verify a target is annunciated on the GTS 8XX TAS/TCAS display at the correct bearing of

approximately 270 degree azimuth at 2 NM and co-altitude.

24. Toggle intruder traffic to standby or off.

25. If the bearing is not as anticipated, recheck the antenna coaxial connections and verify the

correct antenna type is selected.

NOTE

If multiple targets are displayed during the antenna tests, recheck the antenna coaxial connections.

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3.6 GA 58 Antenna Installation

Refer to the GA 58 installation drawing shown in Appendix A of this manual.

CAUTION

Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may damage the electrical connections to the antenna. Use of these type sealants may void the antenna warranty.

1. Refer to the GA 58 installation drawing shown in Appendix A for the mounting cutout.

2. For composite aircraft, fabricate a ground plane under the antenna base plate on the internal

surface of the aircraft with recommended minimum dimensions of 18” x 18”, with center of ground plane under the center of the antenna baseplate. Refer to notes in Antenna Considerations section and Electrical Bonding section of this document.

3. For metal skin aircraft, do NOT remove paint on outer skin of aircraft under the footprint of the

antenna baseplate. The painted surface prevents corrosion.

4. Install a doubler plate to reinforce the aircraft skin as necessary.

5. Place the supplied O-ring, 251-00011-00, in the groove on the bottom surface of the antenna.

6. Mount the antenna to the airframe with the four supplied #8-32 stainless steel screws, 211-

60209-16. Washers and locking nuts (not provided, may be part of doubler plate) are required to secure the antenna. Apply torque evenly across all mounting screws.

7. Ensure that the antenna base and aircraft skin are in continuous contact.

8. Fillet seal the antenna and gasket to the fuselage using a good quality electrical grade sealant,

MIL-S-8802B or equivalent. Run a bead of the sealant along the edge of the antenna where it meets the exterior aircraft skin. Use caution to ensure that the antenna connector is not contaminated with sealant. Seal the mounting screws with sealant.

9. Connect the four antenna cables ensuring each cable is connected to the correct antenna

connector. Each antenna connector and cable has a matching color band.

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3.7 GPA 65 PA/LNA Installation

Refer to the GPA 65 installation drawing shown in Appendix A of this manual.

1. Assemble the wiring harness and circular connector per Section 3.4.

2. Assemble the coaxial cables per Section 2.4.1.

3. Mount the unit to a suitable mounting location using #8-32 pan head screws (4 ea)

(not provided).

4. Connect the circular connector and eight coaxial cables ensuring each coaxial cable is

connected to the correct jack connector. Each jack connector and cable has a matching color band.

3.8 Continued Airworthiness

Maintenance of the GTS 8XX and GPA 65 is “on condition” only.

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4 SYSTEM INTERCONNECTS

4.1 GTS 8XX Pin Function List

4.1.1 P8001 (Digital)

View of J8001 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

21 22 23 24 25 26 27

1 2 3 4 5 6 7 8 9 10 11121314151617181920

Pin Pin Name I/O

1 CONFIG MODULE GROUND -2 RS-232 OUT 1 Out 3 RS-232 IN 1 In 4 SIGNAL GROUND -5 RS-232 OUT 2 Out 6 RS-232 IN 2 In 7 SIGNAL GROUND -8 RS-232 OUT 3 Out

9 RS-232 IN 3 In 10 SIGNAL GROUND -11 RS-232 OUT 4 Out 12 RS-232 IN 4 In 13 SIGNAL GROUND -14 ARINC 429 OUT 1 A Out 15 ARINC 429 OUT 1 B Out 16 ARINC 429 IN 1 A In 17 ARINC 429 IN 1 B In 18 SIGNAL GROUND -19 GPS PPS 1 IN In 20 SIGNAL GROUND -21 CONFIG MODULE POWER OUT Out 22 SIGNAL GROUND -23 ARINC 429 OUT 2 A Out 24 ARINC 429 OUT 2 B Out 25 ARINC 429 IN 2 A In 26 ARINC 429 IN 2 B In 27 SIGNAL GROUND -28 ARINC 429 OUT 3 A Out 29 ARINC 429 OUT 3 B Out 30 ARINC 429 IN 3 A In 31 ARINC 429 IN 3 B In 32 SIGNAL GROUND -33 ARINC 429 OUT 4 A Out 34 ARINC 429 OUT 4 B Out 35 ARINC 429 IN 4 A In 36 ARINC 429 IN 4 B In 37 RS-422 IN A In 38 RS-422 IN B In

43 44 45 46 47 48 49 50 51 52 53 54 55 565758 59

41 42

30 31 32 33 34 35 36 37 38 39

28 29

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Connector P8001, continued

Pin Pin Name I/O

39 SIGNAL GROUND -40 CONFIG MODULE DATA I/O 41 SIGNAL GROUND -42 ARINC 429 OUT 5 A Out 43 ARINC 429 OUT 5 B Out 44 ARINC 429 IN 5 A In 45 ARINC 429 IN 5 B In 46 SIGNAL GROUND -47 ARINC 429 OUT 6 A Out 48 ARINC 429 OUT 6 B Out 49 ARINC 429 IN 6 A In 50 ARINC 429 IN 6 B In 51 SIGNAL GROUND -52 ETHERNET OUT A Out 53 ETHERNET OUT B Out 54 ETHERNET IN A Out 55 ETHERNET IN B Out 56 SIGNAL GROUND -57 RS-422 OUT A Out 58 RS-422 OUT B Out 59 SIGNAL GROUND -60 CONFIG MODULE CLOCK Out 61 TOP PA/LNA DATA RS-422 OUT A Out 62 TOP PA/LNA DATA RS-422 OUT B Out 63 TOP PA/LNA DATA RS-422 IN A In 64 TOP PA/LNA DATA RS-422 IN B In 65 RESERVED -66 RESERVED -67 RESERVED -68 RESERVED -69 SPARE -70 SPARE -71 SPARE -72 SPARE -73 GPS PPS IN 2 HI In 74 GPS PPS IN 2 LO In 75 USB VBUS POWER In 76 USB DATA HI I/O 77 USB DATA LO I/O 78 USB GROUND --

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4.1.2 P8002 (Analog/Discrete)

View of J8002 connector from back of unit

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

21 22 23 24 25 26 27

1 2 3 4 5 6 7 8 9 10 11121314151617181920

Pin Pin Name I/O

1 SIGNAL GROUND --

2 RESERVED --

3 RESERVED --

4 RESERVED --

5 SIGNAL GROUND --

6 AIR/GROUND* In

7 SPARE --

8 TRAFFIC DISPLAY 1 STATUS VALID* In

9 TRAFFIC DISPLAY 2 STATUS VALID* In 10 GEAR DOWN AND LOCKED* In 11 TA INHIBIT* 1 In 12 TA INHIBIT* 2 In 13 RESERVED -14 SELF TEST INHIBIT PROGRAM* In 15 TA INTRUDER DISPLAY LIMIT 16 PROGRAM * In 16 TA INTRUDER DISPLAY LIMIT 8 PROGRAM * In 17 TA INTRUDER DISPLAY LIMIT 4 PROGRAM * In 18 TA INTRUDER DISPLAY LIMIT 2 PROGRAM * In 19 TA INTRUDER DISPLAY LIMIT 1 PROGRAM * In 20 RESERVED -21 SIGNAL GROUND -22 RESERVED -23 RESERVED -24 RESERVED -25 RESERVED -26 RESERVED -27 RESERVED -28 RESERVED -29 RESERVED -30 RESERVED -31 RESERVED -32 RESERVED -33 RESERVED -34 RESERVED -35 RESERVED -36 RESERVED -37 RESERVED -38 RESERVED -39 SIGNAL GROUND -40 SIGNAL GROUND -41 HEADING X HI In

43 44 45 46 47 48 49 50 51 52 53 54 55 565758 59

41 42

30 31 32 33 34 35 36 37 38 39

28 29

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Connector P8002, continued

Pin Pin Name I/O

42 HEADING X LO (GROUND) -43 SIGNAL GROUND -44 HEADING Y HI In 45 HEADING Y LO (GROUND) -46 SIGNAL GROUND -47 SPARE -48 EXTERNAL SUPPRESSION I/O I/O 49 SIGNAL GROUND -50 TA DISPLAY ENABLE* Out 51 AURAL TA ALERT* Out 52 SPARE -53 VISUAL TA ALERT* Out 54 TRAFFIC SYSTEM STATUS VALID* Out 55 RESERVED -56 RESERVED -57 SIGNAL GROUND -58 ALERT AUDIO OUT HI Out 59 ALERT AUDIO OUT LO Out 60 HEADING Z HI (GROUND) In 61 HEADING Z LO (GROUND) -62 SIGNAL GROUND -63 26 VAC HEADING REF HI In 64 26 VAC HEADING REF LO In 65 SIGNAL GROUND -66 SPARE -67 SPARE -68 HEADING VALID In 69 HEADING VALID* In 70 SIGNAL GROUND -71 ANALOG RADAR ALTIMETER HI In 72 ANALOG RADAR ALTIMETER LO In 73 SIGNAL GROUND -74 SELF TEST INITIALIZE SELECT* In 75 TRAFFIC OPERATE/STANDBY* In 76 ANALOG RADAR ALTIMETER VALID In 77 SPARE -78 SIGNAL GROUND --

An asterisk (*) following a signal name denotes that the signal is Active Low. Refer to Section 4.6.4 for signal description.

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4.1.3 P8003 (Power Supply)

View of J8003 connector from back of unit

4623

22 23 24 25 26 27 28 29 30 31 32 333435 36

8109

11 12

13 14

16 17

Pin Pin Name I/O

1 POWER GROUND --

2 AIRCRAFT POWER 1 In

3 AIRCRAFT POWER 1 In

4 AIRCRAFT POWER 2 In

5 AIRCRAFT POWER 2 In

6 POWER GROUND --

7 +6 VDC PA/LNA POWER OUT Out

8 +6 VDC PA/LNA POWER OUT Out

9 RESERVED -10 RESERVED -11 POWER GROUND -12 +35 VDC PA/LNA POWER OUT Out 13 +35 VDC PA/LNA POWER OUT Out 14 POWER GROUND -15 -5 VDC PA/LNA POWER OUT Out 16 -5 VDC PA/LNA POWER OUT Out 17 POWER GROUND -18 TRAFFIC SYSTEM REMOTE POWER ON* In 19 POWER GROUND -20 POWER GROUND -21 POWER GROUND -22 POWER GROUND -23 POWER GROUND -24 POWER GROUND -25 POWER GROUND -26 POWER GROUND -27 POWER GROUND -28 POWER GROUND -29 POWER GROUND -30 POWER GROUND -31 POWER GROUND -32 POWER GROUND -33 POWER GROUND -34 POWER GROUND -35 POWER GROUND -36 TRAFFIC SYSTEM REMOTE POWER OFF In 37 POWER GROUND --

An asterisk (*) following a signal name denotes that the signal is Active Low. Refer to Section 4.6.4 for signal description.

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4.2 GPA 65 Pin Function List

4.2.1 P651

View of J651 connector from back of unit

Pin Pin Name I/O

A POWER GROUND --

B +35 VDC POWER IN In

C POWER GROUND --

D RESERVED --

E -5 VDC POWER IN In

F PA/LNA DATA RS-422 OUT B Out

G PA/LNA DATA RS-422 OUT A Out H PA/LNA DATA RS-422 IN B In

J PA/LNA DATA RS-422 IN A In

K POWER GROUND --

L +6 VDC POWER IN In

M +35 VDC POWER IN In N RESERVED -P +6 VDC POWER IN In R RESERVED -S -5 VDC POWER IN In

T RESERVED --

U RESERVED -V RESERVED --

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4.3 Power

4.3.1 Aircraft Power Functions

This section covers the power input requirements.

4.3.1.1 Aircraft Power

Pin Name Connector Pin I/O

AIRCRAFT POWER 1 P8003 2 In AIRCRAFT POWER 1 P8003 3 In AIRCRAFT POWER 2 P8003 4 In AIRCRAFT POWER 2 P8003 5 In AIRCRAFT GROUND P8003 21 -AIRCRAFT GROUND P8003 22 -AIRCRAFT GROUND P8003 23 -AIRCRAFT GROUND P8003 24 --

Pins 2 and 3 are internally connected to form AIRCRAFT POWER 1. Pins 4 and 5 are internally connected to form AIRCRAFT POWER 2. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are “diode ORed” to provide aircraft power redundancy.

4.3.1.2 Remote Power

Pin Name Connector Pin I/O

TRAFFIC SYSTEM REMOTE POWER ON* P8003 18 In TRAFFIC SYSTEM REMOTE POWER OFF P8003 36 In

An asterisk (*) following a signal name denotes that the signal is Active Low.

Used to remotely control power.

Remote Power ON* ACTIVE: Vin < 3 VDC or grounded (Unit ON) INACTIVE: Vin > 8 VDC or floating (Unit OFF)

Remote Power OFF ACTIVE: Vin > 8 VDC (Unit OFF) INACTIVE: Vin < 3 VDC or floating (Unit ON)

Active Low Remote Power On

(J8003 Pin 18)

State Level State Level

Inactive Vin > 8 VDC or Open Inactive Vin < 3VDC or Open OFF

Active Vin < 3VDC or Gnd Inactive Vin < 3VDC or Open ON

Inactive Vin > 8 VDC or Open Active Vin > 8 VDC OFF

Active Vin < 3VDC or Gnd Active Vin > 8 VDC OFF

Active High Remote Power Off

(J8003 Pin 36)

Expected Unit State

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4.3.1.3 PA/LNA

Pin Name Connector Pin I/O

+6 VDC PA/LNA POWER OUT P8003 7 Out +6 VDC PA/LNA POWER OUT P8003 8 Out +35 VDC PA/LNA POWER OUT P8003 12 Out +35 VDC PA/LNA POWER OUT P8003 13 Out

-5 VDC PA/LNA POWER OUT P8003 15 Out

-5 VDC PA/LNA POWER OUT P8003 16 Out +6 VDC POWER IN P651 L In +6 VDC POWER IN P651 P In +35 VDC POWER IN P651 B In +35 VDC POWER IN P651 M In

-5 VDC POWER IN P651 E In

-5 VDC POWER IN P651 S In

Used to provide power to the GPA 65.

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4.4 Serial Data

4.4.1 RS-232

Pin Name Connector Pin I/O

RS-232 OUT 1 P8001 2 Out RS-232 IN 1 P8001 3 In RS-232 OUT 2 P8001 5 Out RS-232 IN 2 P8001 6 In RS-232 OUT 3 P8001 8 Out RS-232 IN 3 P8001 9 In RS-232 OUT 4 P8001 11 Out RS-232 IN 4 P8001 12 In

The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5V when driving a standard RS-232 load.

4.4.2 RS-422

Pin Name Connector Pin I/O

RS-422 IN A P8001 37 Out RS-222 IN B P8001 38 In RS-422 OUT A P8001 57 Out RS-422 OUT B P8001 58 In TOP PA/LNA DATA RS-422 OUT A P8001 61 Out TOP PA/LNA DATA RS-422 OUT B P8001 62 Out TOP PA/LNA DATA RS-422 IN A P8001 63 In TOP PA/LNA DATA RS-422 IN B P8001 64 In PA/LNA DATA RS-422 OUT B P651 F Out PA/LNA DATA RS-422 OUT A P651 G Out PA/LNA DATA RS-422 IN B P651 H In PA/LNA DATA RS-422 IN A P651 J In

The RS-422 channels conform to EIA standard RS-422.

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4.4.3 ARINC 429

Pin Name Connector Pin I/O

ARINC 429 OUT 1 A P8001 14 Out ARINC 429 OUT 1 B P8001 15 Out ARINC 429 IN 1 A P8001 16 In ARINC 429 IN 1 B P8001 17 In ARINC 429 OUT 2 A P8001 23 Out ARINC 429 OUT 2 B P8001 24 Out ARINC 429 IN 2 A P8001 25 In ARINC 429 IN 2 B P8001 26 In ARINC 429 OUT 3 A P8001 28 Out ARINC 429 OUT 3 B P8001 29 Out ARINC 429 IN 3 A P8001 30 In ARINC 429 IN 3 B P8001 31 In ARINC 429 OUT 4 A P8001 33 Out ARINC 429 OUT 4 B P8001 34 Out ARINC 429 IN 4 A P8001 35 In ARINC 429 IN 4 B P8001 36 In ARINC 429 OUT 5 A P8001 42 Out ARINC 429 OUT 5 B P8001 43 Out ARINC 429 IN 5 A P8001 44 In ARINC 429 IN 5 B P8001 45 In ARINC 429 OUT 6 A P8001 47 Out ARINC 429 OUT 6 B P8001 48 Out ARINC 429 IN 6 A P8001 49 In ARINC 429 IN 6 B P8001 50 In

The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers.

4.4.4 Ethernet

Pin Name Connector Pin I/O

ETHERNET OUT A P8001 52 Out ETHERNET OUT B P8001 53 Out EHTERNET IN A P8001 54 In ETHERNET IN B P8001 55 In

This Ethernet based HSDB (High Speed Data Bus) meets the hardware aspects of IEEE standard 802.3 for 10 base T Ethernet communications.

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4.4.5 USB

Pin Name Connector Pin I/O

USB VBUS POWER** P8001 75 In USB DATA HI** P8001 76 I/O USB DATA LO** P8001 77 I/O USB GROUND P8001 78 --

**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection. USB TYPE B RECEPTACLE pigtail cable must be wired directly to P8001 to minimize lightning exposure.

This interface is used for unit configuration and software uploads. Conforms to the Universal Serial Bus Version 1.1 standard for a “full-speed” device.

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4.5 Configuration

4.5.1 Configuration Module

Pin Name Connector Pin I/O

CONFIG MODULE GND P8001 1 -CONFIG MODULE PWR OUT** P8001 21 -CONFIG MODULE DATA** P8001 40 I/O CONFIG MODULE CLK** P8001 60 I/O

**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection.

4.6 Analog/Discrete

4.6.1 Heading Input

4.6.1.1 26 Volt AC References

Pin Name Connector Pin I/O

26 VAC HEADING REF HI P8002 63 In 26 VAC HEADING REF LO P8002 64 In

Used to sample AC inputs.

This signal must be the same phase and frequency as the indicator being driven.

Frequency: 400 Hz ± 10% Voltage: 22.6 Vrms to 28.6 Vrms Input Impedance:

>10 kΩ

4.6.1.2 Radar Altimeter

Pin Name Connector Pin I/O

ANALOG RADAR ALTIMETER HI P8002 71 In ANALOG RADAR ALTIMETER LO P8002 72 In

Provides altitude information during approach.

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4.6.2 Inputs From Gyros

Pin Name Connector Pin I/O

HEADING X P8002 41 In HEADING LO (GROUND) P8002 42 -HEADING Y P8002 44 In HEADING LO (GROUND) P8002 45 -HEADING Z (GROUND) P8002 60 In HEADING LO (GROUND) P8002 61 --

Inputs heading information from a directional gyro. 3-wire synchro magnetic heading input, with HEADING Z grounded. Index reference is 0° as specified by ARINC 407.

Frequency: 400Hz ± 10% Voltage: 11.8 Vrms nominal, 13.0 Vrms maximum Input Impedance: Resolution: ± 0.1° or better Accuracy: ± 2°

>10 kΩ

4.6.3 Audio

Pin Name Connector Pin I/O

ALERT AUDIO OUT HI P8002 58 Out ALERT AUDIO OUT LO P8002 59 Out

4.6.4 Active Low Discrete Inputs

Pin Name Connector Pin I/O

AIR/GROUND* P8002 6 In TRAFFIC DISPLAY 1 STATUS VALID* P8002 8 In TRAFFIC DISPLAY 2 STATUS VALID* P8002 9 In GEAR DOWN AND LOCKED* P8002 10 In TA INHIBIT* 1 P8002 11 In TA INHIBIT* 2 P8002 12 In SELF TEST INHIBIT PROGRAM* P8002 14 In TA INTRUDER DISPLAY LIMIT 16 PROGRAM * P8002 15 In TA INTRUDER DISPLAY LIMIT 8 PROGRAM * P8002 16 In TA INTRUDER DISPLAY LIMIT 4 PROGRAM * P8002 17 In TA INTRUDER DISPLAY LIMIT 2 PROGRAM * P8002 18 In TA INTRUDER DISPLAY LIMIT 1 PROGRAM * P8002 19 In DATA RECORDER ENABLE* P8002 20 In HEADING VALID* P8002 69 In SELF TEST INITIALIZE SELECT* P8002 74 In TRAFFIC OPERATE/STANDBY* P8002 75 In

An asterisk (*) following a signal name denotes that the signal is Active Low.

ACTIVE: 0 V ≤ Vin ≤ 3.5 V, or Rin ≤ 375 ohms INACTIVE: 8 V ≤ Vin ≤ 36 V, or Rin ≥ 100k ohms Source current is internally limited to approximately 1 mA max for a grounded input

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4.6.5 Active High Discrete Inputs

Pin Name Connector Pin I/O

HEADING VALID P8002 68 In ANALOG RADAR ALTIMETER VALID P8002 76 In

ACTIVE: 8 V ≤ Vin ≤ 36 V INACTIVE: 0 V ≤ Vin ≤ 3.5 V, or Rin ≥ 100k ohms Sink current is internally limited to approximately 1 mA typical for an input connected to +28VDC.

4.6.6 Annunciator Output

Pin Name Connector Pin I/O

TA DISPLAY ENABLE* P8002 50 Out AURAL TA ALERT* P8002 51 Out VISUAL TA ALERT* P8002 53 Out TRAFFIC SYSTEM STATUS VALID* P8002 54 Out

An asterisk (*) following a signal name denotes that the signal is Active Low.

ACTIVE: 0 V ≤ Vout ≤ 0.5 V or Rout ≤ 10 ohms, sinking up to 500 mA INACTIVE: Rout ≥ 100k ohms to ground, withstanding up to +36 VDC.

4.7 Mutual Suppression Bus

Pin Name Connector Pin I/O

EXTERNAL SUPPRESSION I/O P8002 48 I/O

Mutual Suppression Input/Output bus compliant with ARINC 735A Attachment 8, with the exception that the maximum applied DC steady state voltage is +30.3V. Suppression I/O signal is pulsed under normal operation.

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-1. GTS 8XX Vertical Outline Drawing

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-2. GTS 8XX Vertical Installation Drawing

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-3. GTS 8XX Horizontal Outline Drawing

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-4. GTS 8XX Horizontal Installation Drawing

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-5. GPA 65 Outline Drawing

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-6. GPA 65 Installation Drawing

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APPENDIX A OUTLINE & INSTALLATION DRAWINGS

Figure A-7. GA 58 Antenna Outline Drawing

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