Garmin 0104455 LICENSED NON-BROADCAST TRANSMITTER (TAS) AND TRAFFIC ALERT & COLLISION AVOIDANCE SYSTEM (TCAS) PROCESSOR MHz User Manual 190 00587 50
Garmin International Inc LICENSED NON-BROADCAST TRANSMITTER (TAS) AND TRAFFIC ALERT & COLLISION AVOIDANCE SYSTEM (TCAS) PROCESSOR MHz 190 00587 50
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190-00587-50 January, 2012 Revision A
GTS Processor
Installation Manual
DRAFT
Page A GDR 66 Installation Manual
Revision A 190-00587-50
© Copyright 2012
Garmin Ltd. or its subsidiaries
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Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913.397.8200
Aviation Panel-Mount Technical Support Line (Toll Free) 1.888.606.5482
www.garmin.com
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9RB U.K.
+44/ (0) 870.8501241
Garmin AT, Inc.
2345 Turner Rd., SE
Salem, OR 97302 USA
Telephone: 503.581.8101
RECORD OF REVISIONS
Revision Revision Date Description
A 01/06/2012 Initial Release
DRAFT
GTS Processor Installation Manual Page i
190-00587-50 Revision A
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 of 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.
This product, its packaging, and its components contain chemicals known to the
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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.
CURRENT REVISION DESCRIPTION
DOCUMENT PAGINATION
WARNING
Revision Page
Number(s)
Section
Number Description of Change
A All All Initial release
Section Page Range
Table of Contents i – viii
Section 1 1-1 – 1-10
Section 2 2-1 – 2-10
Section 3 3-1 – 3-22
Section 4 4-1 – 4-14
Appendix A A-1 – A-4
Appendix B B-1 – B-10
DRAFT
Page ii GTS Processor Installation Manual
Revision A 190-00587-50
TABLE OF CONTENTS
PARAGRAPH PAGE
Section 1 GENERAL DESCRIPTION .............................................................1-1
1.1 Introduction...................................................................................................................... 1-1
1.2 Equipment Description .................................................................................................... 1-1
1.2.1 GTS Processor Configuration Options.................................................................................1-2
1.3 Interface Summary...........................................................................................................1-2
1.4 Technical Specifications .................................................................................................. 1-2
1.4.1 Environmental Qualification Form.......................................................................................1-2
1.4.2 Physical Characteristics........................................................................................................1-3
1.4.3 General Specifications..........................................................................................................1-3
1.4.4 Power Requirements.............................................................................................................1-3
1.5 Certification ..................................................................................................................... 1-4
1.5.1 GTS Processor TSO/ETSO Compliance ..............................................................................1-4
1.5.2 GTS Processor TSO/ETSO Deviations ................................................................................1-5
1.6 Reference Documents ...................................................................................................... 1-8
1.7 Aviation Limited Warranty.............................................................................................. 1-9
Section 2 INSTALLATION OVERVIEW........................................................2-1
2.1 Introduction...................................................................................................................... 2-1
2.1.1 Unit Configurations ..............................................................................................................2-1
2.1.2 Required Accessories ...........................................................................................................2-1
2.2 Installation Considerations .............................................................................................. 2-3
2.2.1 Antenna Considerations........................................................................................................2-3
2.3 Electrical Bonding ........................................................................................................... 2-3
2.4 Cabling and Wiring..........................................................................................................2-4
2.4.1 Coaxial Cable .......................................................................................................................2-4
2.5 Cooling Requirements ..................................................................................................... 2-9
2.6 Mounting Requirements ................................................................................................ 2-10
Section 3 INSTALLATION PROCEDURE.....................................................3-1
3.1 Unpacking Unit................................................................................................................ 3-1
3.2 Wiring Harness Installation ............................................................................................. 3-1
3.3 Backshell and Configuration Module Assemblies........................................................... 3-3
3.4 GA 58 Antenna Installation ............................................................................................. 3-3
3.5 Sensor Systems Incorporated Low-Profile Antenna Installation..................................... 3-3
3.6 Unit Installation ............................................................................................................... 3-3
3.7 Downloading and Installing the GTS Processor Install Tool .......................................... 3-4
3.8 Downloading and Installing the GTS Assert Log Diagnosis Tool .................................. 3-6
3.9 Post Installation Configuration & Checkout.................................................................... 3-9
3.9.1 GTS Processor Configuration/Checkout for Different Installation Types ...........................3-9
3.9.2 Using the GTS Processor Install Tool ................................................................................3-10
3.9.3 Suppression Bus I/O Check................................................................................................3-16
3.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and Configuration...........3-17
3.9.5 Calibration/Self Test...........................................................................................................3-17
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PARAGRAPH PAGE
3.9.6 Ramp Test and Return To Service Test..............................................................................3-20
3.9.7 Antenna Verification ..........................................................................................................3-22
3.10 Continued Airworthiness ............................................................................................. 3-23
Section 4 SYSTEM INTERCONNECTS..........................................................4-1
4.1 GTS Processor Pin Function List..................................................................................... 4-1
4.1.1 P8001 (Digital) .....................................................................................................................4-1
4.1.2 P8002 (Analog/Discrete) ......................................................................................................4-3
4.1.3 P8003 (Power Supply)..........................................................................................................4-6
4.2 Power ............................................................................................................................... 4-7
4.2.1 Aircraft Power Functions......................................................................................................4-7
4.3 Serial Data........................................................................................................................ 4-8
4.3.1 RS-232..................................................................................................................................4-8
4.3.2 RS-422..................................................................................................................................4-8
4.3.3 ARINC 429...........................................................................................................................4-9
4.3.4 Ethernet.................................................................................................................................4-9
4.3.5 USB ....................................................................................................................................4-10
4.4 Configuration ................................................................................................................. 4-10
4.4.1 Configuration Module ........................................................................................................4-10
4.5 Analog/Discrete .............................................................................................................4-10
4.5.1 Heading Input .....................................................................................................................4-10
4.5.2 Inputs From Compass System/Directional Gyros ..............................................................4-11
4.5.3 Audio ..................................................................................................................................4-12
4.5.4 Active Low Discrete Inputs................................................................................................4-12
4.5.5 Active High Discrete Inputs ...............................................................................................4-13
4.5.6 Annunciator Output ............................................................................................................4-14
4.6 Mutual Suppression Bus ................................................................................................ 4-14
Appendix A Outline and Installation Drawings .............................................A-1
Appendix B Interconnect Examples ................................................................B-1
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Page iv GTS Processor Installation Manual
Revision A 190-00587-50
LIST OF FIGURES
FIGURE PAGE
Section 1 GENERAL DESCRIPTION .............................................................1-1
Section 2 INSTALLATION OVERVIEW........................................................2-1
Figure 2-1 GTS Processor Installation with Top and Bottom Directional Antennas ........... 2-5
Figure 2-2 GTS Processor Installation with Top Directional and
Bottom Monopole Antennas.................................................................................................. 2-5
Figure 2-3 GTS 855/GTS 825 Installation with Top Directional Antenna and
No Bottom Antenna ...............................................................................................................2-6
Figure 2-4 Heat Shrink Positioning ...................................................................................... 2-8
Figure 2-5 GTS Processor Vertical Installation Rack (Garmin P/N 011-02572-00).......... 2-10
Figure 2-6 GTS Processor Horizontal Installation Rack (Garmin P/N 115-00784-00) ..... 2-10
Section 3 INSTALLATION PROCEDURE.....................................................3-1
Figure 3-1 GTS Processor Install Tool – Installation ........................................................... 3-4
Figure 3-2 GTS Processor Install Tool – Installation ........................................................... 3-5
Figure 3-3 GTS Processor Install Tool – Installation ........................................................... 3-5
Figure 3-4 GTS Processor Install Tool – Installation ........................................................... 3-5
Figure 3-5 GTS Processor Install Tool – Installation ........................................................... 3-6
Figure 3-6 GTS Processor Install Tool – Installation ........................................................... 3-6
Figure 3-7 GTS Assert Log Diagnosis Tool – Installation.................................................. 3-7
Figure 3-8 GTS Assert Log Diagnosis Tool – Installation ................................................... 3-7
Figure 3-9 GTS Assert Log Diagnosis Tool – Installation.................................................. 3-8
Figure 3-10 GTS Assert Log Diagnosis Tool – Installation................................................ 3-8
Figure 3-11 GTS Assert Log Diagnosis Tool – Installation................................................ 3-8
Figure 3-12 GTS Processor Install Tool – Normal Tab...................................................... 3-11
Figure 3-13 GTS Processor Install Tool – Configuration Tab (GTS 825 and GTS 855)... 3-12
Figure 3-14 GTS Processor Install Tool – Upload Tab ...................................................... 3-15
Figure 3-15 GTS Processor Install Tool – Assert Tab........................................................ 3-16
Figure 3-16 Self Test ..........................................................................................................3-19
Figure 3-17 Ground Test Enable, GTS Processor Install Tool........................................... 3-20
Figure 3-18 GND TEST Softkey ........................................................................................ 3-20
Section 4 SYSTEM INTERCONNECTS..........................................................4-1
Figure 4-1 View of J8001 connector from back of unit ....................................................... 4-1
Figure 4-2 View of J8002 connector from back of unit ....................................................... 4-3
Figure 4-3 View of J8003 connector from back of unit ....................................................... 4-6
Appendix A Outline and Installation Drawings .............................................A-1
Figure A-1 GTS Processor Vertical Outline Drawing......................................................... A-1
Figure A-2 GTS Processor Vertical Installation Drawing.................................................. A-2
Figure A-3 GTS Processor Horizontal Outline Drawing..................................................... A-3
Figure A-4 GTS Processor Horizontal Installation Drawing............................................... A-4
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FIGURE PAGE
Appendix B Interconnect Examples ................................................................B-1
Figure B-1 GTS Processor Interconnect Example Notes .....................................................B-1
Figure B-2 GTS Processor Interconnect Example................................................................B-2
Figure B-3 GTS Processor Garmin Integrated Flight Deck Interconnect Example .............B-3
Figure B-4 GTS Processor Field Approved (Retrofit) Garmin Integrated
Flight Deck Interconnect Example ........................................................................................B-4
Figure B-5 GTS Processor GNS 4XX/5XX/GMX 200 Interconnect Example....................B-5
Figure B-6 GTS Processor GMA/HSI/Altimeter Interconnect Example .............................B-6
Figure B-7 GTS Processor Dongle Cable (see Sections 3.7 and 3.8.6)................................B-7
Figure B-8 GTS Processor Discrete Interconnect Example .................................................B-8
Figure B-9 GTS Processor Configuration Module Interconnect Example...........................B-9
Figure B-10 GTS Processor Dual Transponder Interconnect Example..............................B-10
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Revision A 190-00587-50
LIST OF TABLES
TABLE PAGE
Section 1 GENERAL DESCRIPTION .............................................................1-1
Table 1-1 Compatible Transponders..................................................................................... 1-2
Table 1-2 Configuration Options.......................................................................................... 1-2
Table 1-3 Physical Characteristics........................................................................................ 1-3
Table 1-4 General Specifications.......................................................................................... 1-3
Table 1-5 Maximum Operation Current Draw ..................................................................... 1-3
Table 1-6 Maximum Boot-Up Current Draw ....................................................................... 1-3
Table 1-7 TSO/ETSO Compliance ....................................................................................... 1-4
Table 1-8 TSO/ETSO Deviations ......................................................................................... 1-5
Table 1-9 Reference Documents........................................................................................... 1-8
Section 2 INSTALLATION OVERVIEW........................................................2-1
Table 2-1 Unit Configuration ............................................................................................... 2-1
Table 2-2 Required Accessories ........................................................................................... 2-1
Table 2-3 Connector Kits...................................................................................................... 2-2
Table 2-4 Optional Accessories............................................................................................ 2-2
Table 2-5 Antennas............................................................................................................... 2-2
Table 2-6 Configuration Module .......................................................................................... 2-2
Table 2-7 Recommended Coaxial Length ............................................................................ 2-7
Table 2-8 Coaxial Cable Set Length Tolerance.................................................................... 2-8
Section 3 INSTALLATION PROCEDURE.....................................................3-1
Table 3-1 Socket and Pin Contact Part Numbers ................................................................. 3-1
Table 3-2 Socket Contact MIL SPEC M39029/5-115 Crimp Tooling................................. 3-1
Table 3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling.... 3-2
Table 3-4 Pin Socket Contacts GPN 336-00022-00 MIL SPEC M39029/63-368 and
GPN 336-00023-00 Crimp Tooling....................................................................................... 3-2
Table 3-5 Self Test.............................................................................................................. 3-19
Section 4 SYSTEM INTERCONNECTS..........................................................4-1
Table 4-1 P8001 Connector .................................................................................................. 4-1
Table 4-2 P8002 Connector .................................................................................................. 4-3
Table 4-3 P8002 Connector .................................................................................................. 4-6
Table 4-4 Aircraft Power ...................................................................................................... 4-7
Table 4-5 Remote Power ...................................................................................................... 4-7
Table 4-6 Power On/Off Matrix ........................................................................................... 4-7
Table 4-7 RS-232.................................................................................................................. 4-8
Table 4-8 RS-422.................................................................................................................. 4-8
Table 4-9 ARINC 429........................................................................................................... 4-9
Table 4-10 Ethernet .............................................................................................................. 4-9
Table 4-11 USB .................................................................................................................. 4-10
Table 4-12 Configuration Module ...................................................................................... 4-10
Table 4-13 26 Volt AC References..................................................................................... 4-10
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TABLE PAGE
Table 4-14 Radar Altimeter ................................................................................................ 4-11
Table 4-15 Inputs From Compass System/Directional Gyros ............................................ 4-11
Table 4-16 Audio ................................................................................................................ 4-12
Table 4-17 Active Low Discrete Inputs.............................................................................. 4-12
Table 4-18 Active High Discrete Inputs ............................................................................. 4-13
Table 4-19 Annunciator Output.......................................................................................... 4-14
Table 4-20 Mutual Suppression Bus................................................................................... 4-14
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GTS Processor Installation Manual Page 1-1
190-00587-50 Revision A
1 GENERAL DESCRIPTION
1.1 Introduction
This manual presents mechanical and electrical installation requirements for installing the GTS Processor
as a Traffic Advisory System (TAS) (GTS 825), Traffic Collision Avoidance System (TCAS I) (GTS 855),
and Traffic Collision Avoidance System (TCAS II) (GTS 8000).
1.2 Equipment Description
The GTS Processor is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations
of Mode S and Mode A/C transponders to provide Traffic Advisories and Resolution Advisories (GTS
8000 only) to the pilot. When installed in a system the GTS Processor can be configured as a TAS (GTS
825) or can be upgraded to a TCAS I (GTS 855) or TCAS II (GTS 8000) by purchasing an enablement
card from Garmin. The GTS Processor meets the TSO/ETSO requirements for the configured traffic
system function (TAS, TCAS I, or TCAS II). When installed with a 1090 MHz ADS-B transmit class of
equipment the GTS Processor 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) or resolution advisory (RA) (GTS 8000 only) 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, and thus reducing potential garble on the 1090 MHz
band. For GTS 825 and GTS 855 installations, a bottom monopole or directional (highly recommended)
antenna is optional. For GTS 8000 installations, a bottom monopole or directional (highly recommended)
antenna is required. Bottom antenna transmit interrogations and broadcasts (GTS 8000 only) are omni
directional, using a monopole antenna or a directional antenna. A bottom directional antenna installation
gives the benefit of intruder bearing visibility for targets that are shaded from the top directional antenna.
The target bearing accuracy may be degraded for bottom directional antenna installations on aircraft with
fixed gear.
GTS Processor installations, configured as a GTS 855 TCAS I or GTS 825 TAS,
require a Garmin-approved transponder capable of receiving TCAS II broadcast
data.
GTS Processor installations, configured as a GTS 8000 TCAS II, require a GTX
3000 or other Garmin-approved RTCA DO-185A/B compatible transponder.
The GTS Processor is not to be installed in an aircraft with a TSO-C119a-only
compatible transponder.
A co-installed mode S transponder should be connected to the mutual suppression
bus, and meet the mutual suppression requirements of DO-181A or later
NOTE
NOTE
NOTE
NOTE
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Page 1-2 GTS Processor Installation Manual
Revision A 190-00587-50
Refer to Table 1-1 for a list of compatible transponders.
1. Remote mounted transponders require a compatible controller. Contact Garmin for details.
2. Factory update is required to allow ADS-B functionality.
3. GTX Software version 6.11 or higher.
4. GTX Software version 6.10 or higher.
1.2.1 GTS Processor Configuration Options
Table 1-2 lists the GTS Processor surveillance configuration options, enabled at the time of installation.
*Requires upgrade using GTX Processor TCAS I/TCAS II Enablement Process. See Section XXX for instructions.
1.3 Interface Summary
The GTS Processor is designed as an open architecture system that uses typical ARINC 429, RS-232, and
Ethernet communications interfaces.
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 Processor
Environmental Qualification Form. To obtain a copy of this form, see the dealer/OEM portion of the
Garmin web site (www.garmin.com). This form is available directly from Garmin under the following part
number:
GTS Processor Environmental Qualification Form, Garmin part number 005-00630-02
Table 1-1 Compatible Transponders
GTX Transponder
Model
Capable of
Receiving TCAS II
Broadcast Data
(Required for GTS
Processor)
ADS-B Capable RTCA DO-185A/B
Compatible
GTX 330/330D Yes(3) Yes(2) No
GTX 330 ES/330D ES Yes(3) Yes No
GTX 33/33D(1) Yes(3) Yes(2) No
GTX 33 ES/33D ES(1) Yes(3) Yes No
GTX 328 Yes(4) No No
GTX 3000 Yes Yes Yes
Table 1-2 Configuration Options
Model
Number
Garmin Part
Number
Applicable
TSO
Traffic
Advisory
System
(TAS)
Traffic
Alert and
Collision
Avoidance
System
(TCAS I)
Traffic
Alert and
Collision
Avoidance
System
(TCAS II)
1090 ES
ADS-B
Receiver
Transmit
Power
(Watts)
GTS 825 011-02571-00 TSO-C147 X X 400
GTS 855* 011-02571-00 TSO-C118 X X 400
GTS 8000* 011-02571-00 TSO-C119c X X 400
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1.4.2 Physical Characteristics
1.4.3 General Specifications
Table 1-4 contains general specifications. For detailed environmental specifications, see the
Environmental Qualification Form.
1.4.4 Power Requirements
Tables list the power requirements for the GTS Processor
Table 1-3 Physical Characteristics
Characteristics Specifications
GTS Processor Width w/out rack 3.42 inches (86.9 mm)
GTS Processor Height w/out rack 6.25 inches (158.8 mm)
GTS Processor Width with vertical rack 3.67 inches (93.1 mm)
GTS Processor Height with vertical rack 6.74 inches (171.1 mm)
GTS Processor Depth with vertical rack 15.48 inches (396.7 mm)
GTS Processor Width with horizontal rack 6.42 inches (163.1 mm)
GTS Processor Height with horizontal rack 4.10 inches (104.1 mm)
GTS Processor Depth with horizontal rack 14.79 inches (375.7 mm)
GTS Processor Depth w/Connector Kit 14.78 inches (375.4 mm)
GTS Processor Unit Weight w/out Connector Kit 11.30 lbs (5.13 kg)
GTS Processor Unit Weight with Connector Kit w/Vertical Rack 12.65 lbs (5.74 kg)
GTS Processor Unit Weight with Connector Kit w/Horizontal Rack 13.25 lbs (6.01 kg)
Table 1-4 General Specifications
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 level B
Hardware Compliance RTCA/DO-254 Level B
Environmental Compliance RTCA/DO-160F
Table 1-5 Maximum Operation Current Draw
Characteristics Specifications
GTS Processor Power Consumption 2.5 A max operating at 28.0 Vdc
5.0 A max operating at 14.0 Vdc
Table 1-6 Maximum Boot-Up Current Draw
Characteristics Specifications
GTS Processor Boot-Up Current Draw 2.5 A at 28.0 Vdc for 700 ms
5.0 A at 14.0 Vdc for 700 ms
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Revision A 190-00587-50
1.5 Certification
The conditions and tests required for TSO/ETSO 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/ETSO standards. TSO/
ETSO 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 tables provide a list of applicable TSO/ETSOs for the GTS Processor.
1.5.1 GTS Processor TSO/ETSO Compliance
When installed as a system, the GTS Processor, which includes a GA 58 (or other Garmin approved
antenna), and a CDTI (Cockpit Display of Traffic Information) comprise what Garmin considers to be a
minimum generic GTS Processor system installation. The GTS Processor lacks a display and by itself is
an incomplete system and cannot completely meet the requirements of TSO-C119c/ETSO-C119c,
TSO-C118/ETSO-C118 or TSO-C147/ETSO-C147.
*Equipment is capable of TSO-C166b/ETSO-C166a Class A1S/Type 1 Receiving Only per
RTCA/DO-260B when installed with a single antenna.
*Equipment is capable of TSO-C166b/ETSO-C166a Class A1/Type 1 Receiving Only when installed with
diversity antennas.
*The Class level is dependent upon the installation.
Table 1-7 TSO/ETSO Compliance
GTS
Processor
Configuration
Function TSO/ETSO Category
Applicable
LRU SW Part
Numbers
Applicable
CLD Part
Numbers
GTS 8000
Traffic Alert and Collision
Avoidance System (TCAS
II) Airborne Equipment
TSO-C119c
ETSO-C119c
All
006-B1244-0( )
through
006-B1244-2( )
except
006-B1244-00
through
006-B1244-03
006-C0081-2( )
GTS 855
Traffic Alert and Collision
Avoidance System (TCAS
I) Airborne Equipment
TSO-C118
ETSO-C118
All
006-B1224-0( )
through
006- B1224-2( )
except
006- B1224-00
through
006-B1224-03
006-C0081-2( )
GTS 825 Traffic Advisory System
(TAS) Airborne Equipment
TSO-C147
ETSO-C147 Class A
All
006-B1224-0( )
through
006- B1224-2( )
except
006- B1224-00
through
006- B1224-03
006-C0081-2( )
GTS 8000,
GTS 855, and
GTX 825
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-C166b†
ETSO-C166a†
Class A1S/
Type 1
Receiving
Only*
Class A1/
Type 1
Receiving
Only*
All
006- B1224-0( )
through
006- B1224-2( )
except
006-B1224-00
through
006-B1224-03
006-C0081-2( )
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GTS Processor Installation Manual Page 1-5
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A statement identifying whether the installation is TSO-C166b/ETSO-C166a
Class A1S/Type 1 Receiving Only or TSO-C166b/ETSO-C166a Class A1/Type 1
Receiving Only, per RTCA/DO-260B, should be included in the ship's log during
Installation.
† Installation of this Receiving Only class of equipment is intended only for those aircraft in which a 1090
MHz ADS-B transmit class of equipment, or other complementary ADS-B link transmit class of
equipment (such as UAT), is already installed. When no such ADS-B link transmit class of equipment is
installed, the ADS-B receive functionality is disabled by disabling the 'ADSB TX Capable' configuration
option (see section 3.9.2).
1.5.2 GTS Processor TSO/ETSO Deviations
NOTE
Table 1-8 TSO/ETSO Deviations
TSO/ETSO Deviation
TSO-C118
1. Garmin was granted a deviation from TSO-C118 section a.(1) to use RTCA DO-197A, instead
of RTCA DO-197 as the Minimum Performance Standard
2. Garmin was granted a deviation from TSO-C118 section a.(2) to use RTCA DO-160F, instead of
RTCA DO-160B as the standard for Environmental Conditions and Test Procedures for Airborne
Equipment.
3. Garmin was granted a deviation from TSO-C118 section a.(3)(i) to use RTCA DO-178B instead
of RTCA DO-178A.
4. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the
Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement
of RTCA DO-197A section 2.2.3.2.1.
5. 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-185B section 2.2.3.8.1 instead of the “Mode C” format for
ATCRBS interrogations.
6. 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-185B and DO-181D.
7. 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.
8. 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-185B section 2.2.3.12 (70 +/-1 µs
from top antenna and 90 +/-1 µs from bottom antenna) instead of 100 +/-5 µs.
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Revision A 190-00587-50
Table 1-8 TSO/ETSO Deviations, Continued
ETSO-C118
1. Garmin was granted a deviation from ETSO-C118 section 3.1.1 to use RTCA DO-197A, instead
of RTCA DO-197 as the Minimum Performance Standard.
2. Garmin was granted a deviation from ETSO-C118 section 3.1.2 to use EUROCAE ED-14F,
instead of EUROCAE ED-14D as the standard for Environmental Conditions and Test Procedures
for Airborne Equipment.
3. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the
Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement
of RTCA DO- 197A section 2.2.3.2.1.
4. 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-185B section 2.2.3.8.1 instead of the “Mode C” format for
ATCRBS interrogations.
5. 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.
6. 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-185B section 2.2.3.12 (70 +/-1 μs
from top antenna and 90 +/-1 μs from bottom antenna) instead of 100 +/-5 μs.
TSO-C119c
1. Garmin was granted a deviation from RTCA DO-185B section 2.2.3.13.2.1.1 to not have the
ability to interface with FAA TSO-C119a compatible transponder units.
2. Garmin was granted a deviation from RTCA DO-185B section 2.2.4.4.2.2.b to use the
Enhanced Preamble Detection method of RTCA DO-260B Appendix I section I.4.1
3. Garmin was granted a deviation from RTCA DO-185B section 2.2.4.4.2.2.c to use the Baseline
Multi-sample bit and confidence declaration technique of RTCA DO-260B Appendix I section
I.4.2.3.1.
4. Garmin was granted a deviation from RTCA DO-185B section 2.2.6.7.2 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.
ETSO-C119c
1. Garmin was granted a deviation from ETSO-C119c to use EUROCAE ED-14F instead of
EUROCAE ED-14D as the standard for Environmental Conditions and Test Procedures for
Airborne Equipment.
2. Garmin was granted a deviation from RTCA DO-185B section 2.2.3.13.2.1.1 to not have the
ability to interface with FAA TSO-C119a compatible transponder units.
3. Garmin was granted a deviation from RTCA DO-185B section 2.2.4.4.2.2.b to use the
Enhanced Preamble Detection method of RTCA DO-260B Appendix I section I.4.1.
4. Garmin was granted a deviation from RTCA DO-185B section 2.2.4.4.2.2.c to use the Baseline
Multi-sample bit and confidence declaration technique of RTCA DO-260B Appendix I section
I.4.2.3.1.
5. Garmin was granted a deviation from RTCA DO-185B section 2.2.6.7.2 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.
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GTS Processor Installation Manual Page 1-7
190-00587-50 Revision A
TSO-C147
1. Garmin was granted a deviation from TSO-C147 section 1.c to use RTCA DO-160F, 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 2.2.3.9 and 2.2.4.5.4.2 following all the
applicable protocols for Mode-S surveillance interrogations in the NAS as stated in
RTCA DO-185B and RTCA DO-181D.
3. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the
Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement
of RTCA DO-197A section 2.2.3.2.1.
4. 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-185B section 2.2.3.8.1 instead of the “Mode C” format for
ATCRBS interrogations.
5. 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.
6. 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-185B section 2.2.3.12 (70 +/-1 μs
from top antenna and 90 +/-1 μs from bottom antenna) instead of 100 +/-5 μs.
ETSO-C147
1. Garmin was granted a deviation from ETSO-C147 section 3.1.2 to use EUROCAE ED-14F,
instead of EUROCAE ED-14D as the standard for Environmental Conditions and Test Procedures
for Airborne Equipment.
2. Garmin was granted a deviation from ETSO-C147 Appendix 1 section 1.6 to use selective Mode
S interrogations as specified by RTCA DO-185B section 2.2.3.9 and 2.2.4.5.4.2 following all the
applicable protocols for Mode-S surveillance interrogations in the NAS as stated in RTCA DO-
185B and RTCA DO-181D.
3. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the
Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement
of RTCA DO-197A section 2.2.3.2.1
4. 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-185B section 2.2.3.8.1 instead of the “Mode C” format for
ATCRBS interrogations.
5. 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.
6. 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-185B section 2.2.3.12 (70 +/-1 μs
from top antenna and 90 +/-1 μs from bottom antenna) instead of 100 +/-5 μs.
ETSO-C166a
1. Garmin was granted a deviation from ETSO-C166a, section 4.2 to allow not marking the unit
with the class information, which is instead provided in the installation and operation manual.
2. Garmin was granted a deviation from ETSO-C166a to use RTCA DO-260B instead of RTCA
DO-260A as the Minimum Performance Standard.
3. Garmin was granted a deviation from ETSO-C166a to use RTCA DO-160F instead of RTCA
DO-160E as the Environmental Standard.
4. Garmin was granted a deviation from RTCA DO-260B section 2.2.4.3.4.7.3.b to use the
Conservative and Brute Force error correction techniques specified by RTCA DO-260B section
2.2.4.4.3.1 instead of 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185B.
5. Garmin was granted a deviation from RTCA DO-260B section 2.2.4.5.b to use the Conservative
and Brute Force error correction techniques specified by RTCA DO-260B 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-185B.
Table 1-8 TSO/ETSO Deviations, Continued
DRAFT
Page 1-8 GTS Processor Installation Manual
Revision A 190-00587-50
1.6 Reference Documents
The following publications are sources of additional information for installing the GTS Processor. Before
installing the GTS Processor, the installer should read all referenced materials along with the manual.
Table 1-9 Reference Documents
Part Number Document
190-00313-11 Jackscrew Backshell Installation Instructions
190-00303-00 G1000 System Installation Manual
190-00587-51 GTS Processor System Maintenance Manual
190-00903-00 G1000 System Maintenace Manual LJ/VLJ
190-00907-00 G1000 System Maintenance Manual Standard Piston/Turboprop Aircraft
DRAFT
GTS Processor Installation Manual Page 1-9
190-00587-50 Revision A
1.7 Aviation Limited Warranty
All Garmin avionics products are warranted to be free from defects in materials or workmanship for: one
years from the date of purchase for new Remote-Mount and Panel-Mount products; one year from the date
of purchase for new portable products and any purchased newly-overhauled products; six months for
newly-overhauled products exchanged through a Garmin Authorized Service Center; and 90 days for
factory repaired or newly-overhauled products exchanged at Garmin in lieu of repair. Within the applicable
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 apply to: (i) cosmetic
damage, such as scratches, nicks and dents; (ii) consumable parts, such as batteries, unless product damage
has occurred due to a defect in materials or workmanship; (iii) damage caused by accident, abuse, misuse,
water, flood, fire, or other acts of nature or external causes; (iv) damage caused by service performed by
anyone who is not an authorized service provider of Garmin; or (v) damage to a product that has been
modified or altered without the written permission of Garmin. In addition, Garmin reserves the right to
refuse warranty claims against products or services that are obtained and/or used in contravention of the
laws of any country.
THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF
ALL OTHER WARRANTIES, WHETHER EXPRESS, 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 THE 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 (with a new or newly-overhauled replacement
product) the product 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.
Online Auction Purchases: Products purchased through online auctions are not eligible for warranty
coverage. 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.
International Purchases: A separate warranty may be provided by international distributors for devices
purchased outside the United States depending on the country. If applicable, this warranty is provided by
the local in-country distributor and this distributor provides local service for your device. Distributor
warranties are only valid in the area of intended distribution. Devices purchased in the United States or
Canada must be returned to the Garmin service center in the United Kingdom, the United States, Canada,
or Taiwan for service.
Garmin International, Inc. Garmin (Europe) Ltd.
1200 East 151st Street Liberty House, Bulls Copse Road
Olathe, Kansas 66062, U.S.A. Hounsdown Business Park
Phone:913/397.8200 Romsey, SO40 9RB, U.K.
FAX:913/397.0836 Phone:44/ (0) 870.8501241
FAX:44/ (0) 870.850125
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Revision A 190-00587-50
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GTS Processor Installation Manual Page 2-1
190-00587-50 Revision A
2 INSTALLATION OVERVIEW
2.1 Introduction
This section provides hardware equipment information for installing the GTS Processor and related
hardware. Installation of the GTS Processor 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 43.13-2B, where applicable, may be found useful for making retro-fit installations
that comply with FAA regulations.
2.1.1 Unit Configurations
The GTS Processor is available under the following part numbers:
2.1.2 Required Accessories
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 Processor and is required to install
the unit. Only one is required.
*Approved for use in RTCA DO-160F, Section 8, Category S, Curve C, Y, and L installations, as well as
RTCA DO-160F, Section 8, Category U, Curve G installations.
For a GTS Processor installation with a single GA 58 directional antenna (GTS 855/GTS 825 only), 8 TNC
connectors (not supplied), either straight or right angle, are required.
For a GTS Processor installation with dual GA 58 directional antennas (GTS 8000/GTS 855/GTS 825), 16
TNC connectors (not supplied), either straight or right angle, are required.
For a GTS Processor installation with a single GA 58 directional antenna and a monopole antenna (GTS
8000/GTS 855/GTS 825), 9 TNC connectors and 1 BNC connector (not supplied), either straight or right
angle, are required.
TNC 50 Ohm terminations (not supplied) are required for all unused antenna ports.
Table 2-1 Unit Configuration
Item
Applicable
LRU Software
Part Numbers
Applicable Custom
Logic Device
Part Numbers
Garmin P/N
GTS Processor, (011-02571-00)
All
006-B1244-0( )
through
006-B1244-2( )
except
006-B1244-00
through
006-B1244-03
006-C0081-2( ) 010-00962-00
NOTE
Table 2-2 Required Accessories
Installation Racks Garmin P/N
GTS Processor Vertical Installation Rack 011-02572-00*
GTS Processor Horizontal Installation Rack 115-00784-00*
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Page 2-2 GTS Processor Installation Manual
Revision A 190-00587-50
The GTS Processor is to be installed with a four-beam directional interrogation
antenna mounted to the top of the aircraft as described in the antenna installation
manual.
*010-10720-00 and 010-10720-02 include mounting screws and o-ring, unless specifically requested to exclude.
**Or Sensor Systems Incorporated part number S72-1735-24 (long TNC connectors) or S72-1735-26 (short TNC
connectors) that meet the requirements of Garmin part number 013-00276-0X or 013-00276-5X, respectively. Refer
to the manufacturer’s installation manual for installation instructions..
*Required for GTS Processor installations that do not have other means (such as a GDU XXXX
Configuration Module) to store GTS Processor configuration data. Contact Garmin for additional
guidance in determining applicability.
Table 2-3 Connector Kits
Connector Kits Garmin P/N
GTS Processor Connector Kit 011-01360-00
GTS Connector Kit w/Config Module and USB Pigtail 011-01360-01
USB-B Pigtail (see GTS Configuration Options) 011-01782-00
Table 2-4 Optional Accessories
Optional Accessories Garmin P/N
Color Coded Heat Shrink Kit 011-02817-00
NOTE
Table 2-5 Antennas
Antennas Garmin P/N
GA 58 Directional Antenna, QMA (011-01346-00)
NOTE: Refer to 190-00587-00 GTS 8XX Installation Manual
for installation instructions
010-10720-00*
GA 58 Directional Antenna, TNC, (011-01346-02)
NOTE: Refer to 190-000587-20 GA 58 Installation Manual
for installation instructions.
010-10720-02*
Low Profile Directional Antenna 013-00276-XX**
Monopole Antenna 010-10160-00 or L-Band Monopole Antenna that
meets TSO-C74c
Table 2-6 Configuration Module
Configuration Module Garmin P/N
Configuration Module* 011-00979-20
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GTS Processor Installation Manual Page 2-3
190-00587-50 Revision A
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 Processor.
2.2.1 Antenna Considerations
Refer to GA 58 Installation Manual 190-00587-20 for antenna installation information.
For GTS 855/GTS 825 installations, either a monopole antenna or directional
antenna may be used if installing an optional bottom mounted antenna. For GTS
8000 installations, a bottom monopole or directional antenna is required. A
bottom directional antenna installation (recommended) gives the benefit of
intruder bearing visibility for targets that are shaded from the top directional
antenna. The target bearing accuracy may be degraded for bottom directional
antenna installations on aircraft with fixed gear.
2.2.1.1 TAS/TCAS Antenna Location
Refer to GA 58 Installation Manual 190-00587-20 for antenna installation information
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 Processor
equipment be electrically bonded.
Refer to GA 58 Installation Manual 190-00587-20 for antenna installation information.
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.
NOTE
DRAFT
Page 2-4 GTS Processor Installation Manual
Revision A 190-00587-50
2.4 Cabling and Wiring
The contacts used to facilitate the use of #18 AWG wire, if used 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.
When removing an expanded-diameter barrel contact, always cut off the
expanded-diameter barrel before using an extraction tool to remove the contact.
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.
All appliance to antenna coaxial cabling shall bundle top four channels as a group
and bottom four 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.
2.4.1 Coaxial Cable
The GTS Processor requires two 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.
TNC connectors and BNC connectors, required for building the coaxial cable
assemblies for some antenna options, are not provided.
2.4.1.1 GTS Processor Installations
For all GTS Processor installations, either a monopole antenna or directional
antenna (recommended) may be used if installing a bottom mounted antenna.
GTS 8000 installations require either a bottom-mounted directional
(recommended) or monopole antenna. A bottom antenna is optional for GTS 855/
GTS 825 installations, but a bottom directional antenna is recommended for best
performance. A bottom directional antenna installation gives the benefit of
intruder bearing visibility for targets that are shaded from the top directional
antenna. The target bearing accuracy may be degraded for bottom directional
antenna installations on aircraft with fixed gear.
A GTS Processor installation with both top and bottom mounted directional antennas uses one set of
coaxial cables for the four GTS Processor 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 Processor 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
NOTE
NOTE
NOTE
NOTE
DRAFT
GTS Processor Installation Manual Page 2-5
190-00587-50 Revision A
attenuation of 3.0dB at 1090MHz for a GA 58 directional antenna installations, and 2.5 dB for low-profile
directional antenna installations as shown in Figure 2-1.
Figure 2-1 GTS Processor Installation with Top and Bottom Directional Antennas
If a bottom mount monopole antenna is installed, a single coaxial cable must be used to connect the GTS
Processor bottom jack J1 BTM to the monopole antenna jack. The coaxial cable assembly shall not exceed
the maximum attenuation of 3.0dB at 1090MHz for a GA 58 directional antenna and 2.5 dB for a low
profile directional antenna as shown in Figure 2-2 and stated in Table 2-2. Each of the remaining GTS
Processor bottom jacks (J2 BTM, J3 BTM, J4 BTM) are to be terminated using a 50Ω TNC termination.
Figure 2-2 GTS Processor Installation with Top Directional and Bottom Monopole
Antennas
DRAFT
Page 2-6 GTS Processor Installation Manual
Revision A 190-00587-50
If no bottom mount antenna is installed, each of the GTS 855/GTS 825 bottom jacks (J1 BTM, J2 BTM, J3
BTM and J4 BTM) must be terminated with a 50Ω TNC termination shown in Figure 2-3.
Figure 2-3 GTS 855/GTS 825 Installation with Top Directional Antenna and No Bottom
Antenna
2.4.1.2 Fabrication of Coaxial Cable Assemblies
TNC connectors, required to build coaxial cable assemblies, are not provided.
Table 2-1 lists the recommended coaxial cable venders and the type of cable to be used for specific lengths
of coaxial cable. The maximum coaxial cable lengths are calculated from the maximum signal attenuation
at 1090 MHz for each coaxial cable type and an assumed loss figure of 0.035 dB per connector. The
maximum coaxial cable lengths in Table 2-1 are for reference only, and are defined as the end to end length
of a non-terminated coaxial cable. Actual cable lengths may vary depending on manufacturer
specifications for the maximum cable attenuation and the RF coaxial connector loss.
It is the installing agency’s responsibility to ensure that the coaxial cable assemblies meet the
manufacturer’s attenuation specifications as shown in Section 2-4 in order to comply with the system
installation standards.
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.
NOTE
NOTE
DRAFT
GTS Processor Installation Manual Page 2-7
190-00587-50 Revision A
*The “Max Terminated Cable Attenuation” values listed include the maximum attenuation of both the
maximum length of coaxial cable and two RF coaxial connectors at a frequency of 1090 MHz.
**Actual cable lengths may vary depending on manufacturer’s cable attenuation and connector
specifications.
Table 2-7 Recommended Coaxial Length
Max Terminated Cable Attenuation
(including connector loss)*
Max Cable
Attenuation
(dB/100ft)
ECS Type [1]
PIC Type [2]
MIL-C-17 Type [3]
RG Type [4]
Loss
of
0.5 dB
Loss
of
1.5 dB
Loss
of
2.0 dB
Loss
of
2.5 dB
Loss
of
3.0 dB
Max Coaxial Cable Lengths**
2' 2"
[0.66m]
7' 8"
[2.34m]
10' 7"
[3.23m]
13' 6"
[4.11m]
16' 5"
[5.00m] 17.2 M17/128-
RG400 RG-400
2' 3"
[0.69m]
8' 0"
[2.44m]
11' 0"
[3.35m]
14' 0"
[4.27m]
17' 0"
[5.18m] 16.7 S83204
2' 5"
[0.74m]
8' 6"
[2.59m]
11' 9"
[3.58m]
15' 0"
[4.57m]
18' 3"
[5.56m] 15.5 M17/60-
RG142 RG-142
3' 0"
[0.91m]
10' 7"
[3.23m]
14' 7"
[4.45m]
18' 7"
[5.66m]
22' 7"
[6.88m] 12.5 311901
3' 2"
[0.97m]
10' 11"
[3.33m]
15' 0"
[4.57m]
19' 2"
[5.84m]
23' 3"
[7.09m] 12.2 S44191
3' 3"
[0.99m]
11' 4"
[3.45m]
15' 6"
[4.72m]
19' 9"
[6.02m]
24' 0"
[7.32m] 11.8 S44193
4' 3"
[1.30m]
15' 0"
[4.57m]
20' 6"
[6.25m]
26' 2"
[7.98m]
31' 9"
[9.68m] 8.9 311601
5' 0"
[1.52m]
17' 9"
[5.41m]
24' 5"
[7.44m]
31' 0"
[9.45m]
37' 10"
[11.53m] 7.5 S67163
5' 1"
[1.55m]
18' 0"
[5.49m]
24' 8"
[7.52m]
31' 6"
[9.60m]
38' 3"
[11.66m] 7.4 311501
[1] Vendor: Electronic Cable Specialists
5300 W Franklin Drive, Franklin, WI 53132
Telephone: 800.327.9473 or 414.421.5300
Fax: 414.421.5301 Website: www.ecsdirect.com
[2] Vendor: PIC Wire and Cable
N53 W24747 S Corporate Circle, Sussex, WI 53089-0330
Telephone 800.742.3191 or 262.246.0500
Fax: 262.246.0450 Website: www.picwire.com
[3] See current issue of Qualified Products List, QPL-17.
[4] RG types are obsolete and are shown for reference only; replaced by M17 type numbers.
DRAFT
Page 2-8 GTS Processor Installation Manual
Revision A 190-00587-50
Coaxial cable "sets" are required for GTS Processor installations. Each coaxial cable "set", which consist
of 4 coaxial cable assemblies, must be length matched to the tolerances shown in Table 2-2.
*Ensure cables do not exceed the maximum lengths as stated in Table 2-1 unless supported by
manufacturers data for specific cables used.
It is recommended that a two inch piece of adhesive heat shrink tubing be installed
over all connector/cable interfaces. The heat shrink tubing should overlap the
connector body as much as practical without interfering with the coupling nut.
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.
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.
Figure 2-4 Heat Shrink Positioning
2.4.1.3 Coaxial Cable Assembly Repair and Rework
In the event that an individual coaxial cable assembly requires rework, the following rules apply:
Top or bottom GTS Processor to GA 58 (or other Garmin approved antenna) cables may be repaired with a
reduction in length of 2” maximum.
Refer to Table 2-1 for recommended maximum cable assembly lengths for cable assemblies fabricated by
the installer.
Table 2-8 Coaxial Cable Set Length Tolerance
Coaxial Cable Set
(consisting of four coaxial cable assemblies) Length Tolerance*
GTS Processor TOP to top directional antenna 2" of each other
GTS Processor BOTTOM to bottom directional antenna 2" of each other
NOTE
NOTE
NOTE
Connector
Body Ferrule Coaxial Cable
Heat shrink not to protrude past
this surface.
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GTS Processor Installation Manual Page 2-9
190-00587-50 Revision A
2.5 Cooling Requirements
The GTS Processor meets all TSO requirements without external cooling, however the application of
forced air cooling to the rear air nozzle of the GTS Processor is highly recommended to provide beneficial
cooling the the unit. A 5/8” diameter air fitting for AIR is provided on the front of the GTS Processor for
the purpose of admitting cooling air if desired. If an external cooling hose is used, it should blow into the
AIR fitting. 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.
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2.6 Mounting Requirements
The GTS Processor can be mounted vertically or horizontally using the installation racks shown in Figures
2-5 & 2-6. Refer to Appendix A for outline and installation drawings.
Figure 2-5 GTS Processor Vertical Installation Rack (Garmin P/N 011-02572-00)
Figure 2-6 GTS Processor Horizontal Installation Rack (Garmin P/N 115-00784-00)
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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, and one 37-pin standard density connector. 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.
*Indicates plastic insertion/extraction tool
Table 3-1 Socket and Pin Contact Part Numbers
Manufacturer
78 Pin High Density D-Subminiature Connectors P8001 & P8002
37 Pin Standard Density D-Subminiature Connector P8003
19 Pin Circular Connector P651
High Density Pin (P8001
& P8002)
Standard Socket
(P8003)
18 AWG Socket
(P8003)
Garmin P/N 336-00021-00 336-00022-00 336-00023-00
Military P/N M39029/58-360 M39029/63-368 N/A
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 M22520/1-02 M81969/14-11*
Daniels AF8 TH1A M81969/14-11*
Tools Option 2
Military P/N M22520/2-01 M22520/2-02 M81969/14-11*
Daniels AFM8 K1S M81969/14-11*
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Note 1 - Indicates plastic insertion/extraction tool
Note 2 – Order by military part number
Note 1 - Indicates plastic insertion/extraction tool
Note 2 – Order by military part number
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.
Table 3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling
Manufacturer Hand Crimping
Tool Positioner Insertion/Extraction
Tool
Military P/N M22520/2-01 M22520/2-09 M81969/1-04
Daniels AFM8 K42 (Note 2)
Positronic 9507-0 9502-4 (Note 2)
ITT Cannon 995-0001-584 (Note 2) 274-7048-000 (Note 1)
Tyco-AMP 601966-1 601966-6 91067-1
Astro 615717 615725 (Note 2)
Amphenol (Note 2) (Note 2) (Note 2)
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)
18 AWG Socket Contact
GPN 336-00023-00
Positioner Insertion/Extraction
Tool 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 (Note 2) K774 (Note 2)
Positronic 9507-0 9502-5 (Note 2) 9502-11 (Note 2)
ITT Cannon 995-0001-584 995-0001-604 980-2000-426 (Note 1) N/A N/A
Tyco-AMP 601966-1 601966-5 91067-2 N/A N/A
ASTRO 615717 615724 (Note 2) NA N/A
Amphenol (Note 2) (Note 2) (Note 2) N/A N/A
NOTE
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3.3 Backshell and Configuration Module Assemblies
The GTS Processor 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 Jackscrew Configuration Module Installation Instructions (Garmin part number
190-00313-10) for configuration module assembly instructions.
3.4 GA 58 Antenna Installation
Refer to the GA 58 Installation Manual 190-00587-20 for installation instructions.
After antenna installation is complete, connect the four antenna cables ensuring each cable is connected to
the correct antenna connector. Each antenna connector and cable should have a matching color band.
3.5 Sensor Systems Incorporated Low-Profile Antenna Installation
Refer to manufacturers recommended installation instructions.
After antenna installation is complete, connect the four antenna cables ensuring each cable is connected to
the correct antenna connector. Each antenna connector and cable should have a matching color band.
3.6 Unit Installation
Refer to the applicable drawings in Appendix A Outline and Installation Drawings and Appendix B
Interconnect Example of this manual for GTS Processor unit installation.
GTS Processor units are not compatible with Garmin Integrated Flight Deck GDU
software versions prior to 9.14.
NOTE
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3.7 Downloading and Installing the GTS Processor Install Tool
GTS Processor Configuration, Ramp Test, and Return to Service tests are performed (on some
installations) using a computer (installed with Microsoft Windows XP or later) and the GTS Processor
Install Tool, Garmin part number 006-A0242-10. The GTS Processor Install Tool allows for configuration,
diagnostics, and upload of GTS Processor software. The tool is available for download from the Dealer
Resource Center portion of the Garmin website (www.garmin.com). See the “readme” file (included in
some versions) in the tool download for the latest GTS Processor Install Tool notes.
A USB-A plug to USB-B plug cable (not provided) is required to interface
between a computer USB-A receptacle and the GTS Processor USB-B receptacle
installed in the wiring harness. This Dongle Cable is required to use the GTS
Processor Install Tool, refer to Appendix B for interconnect drawing.
1. Go to the Dealer Resource section of www.garmin.com and save the “GTS Processor Install
Tool.zip” file from the website to the PC.
2. Apply power to the GTS Processor and connect the unit to a USB port on the PC.
3. If a pop-up window titled “Found New Hardware Wizard” appears on the PC, select ‘Cancel’ to
exit the wizard.
Figure 3-1 GTS Processor Install Tool – Installation
4. On the PC, locate the files “GTS Processor Install Tool.zip.” Extract the files from the zip file.
For computers with 32-bit Windows versions select the “Install Tool Installer 32-bit.msi” file.
For computers with 64-bit Windows versions select the “Install Tool Installer 64-bit.msi” file.
The installation will be canceled if the installation file and the operating system do
not match. On the PC, right click on ‘My Computer’ and select ‘Properties’ to
determine if the PC is operating on a 32-bit or a 64-bit version of Windows.
NOTE
NOTE
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5. On the PC, select ‘Next’ when prompted. Follow the wizard to setup the GTS Processor Install
Tool. (Examples shown assume a Windows XP operating system, the required steps may vary
with other Operating Systems.)
Figure 3-2 GTS Processor Install Tool – Installation
6. Select ‘Next’, when prompted or ‘Browse’, to select another folder.
Figure 3-3 GTS Processor Install Tool – Installation
7. Select ‘Next’, when prompted, to start the installation.
Figure 3-4 GTS Processor Install Tool – Installation
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8. Wait until the installation has completed.
Figure 3-5 GTS Processor Install Tool – Installation
9. When the installation has completed, the following screen will be displayed. Select ‘Close.’
Figure 3-6 GTS Processor Install Tool – Installation
3.8 Downloading and Installing the GTS Assert Log Diagnosis Tool
The GTS Assert Log Diagnosis Tool (006-A0244-00) is used with the GTS 8XX Assert Log to assist in the
diagnosis and resolution of asserts seen during the installation process and during post-installation flight
operation. This tool allows for viewing/storing of the GTS Assert Log using a computer (installed with
Microsoft Windows XP or later) and is available for download from the Dealers Resource Center portion
of the Garmin website (www.garmin.com). See the “readme” file in the tool download for the latest
installation/operation notes.
A USB-A plug to USB-B plug cable (not provided) is required to interface
between a computer USB-A receptacle and the GTS Processor USB-B receptacle
installed in the wiring harness. This Dongle Cable is required to use the GTS
Processor Install Tool, refer to Appendix B for interconnect drawing.
NOTE
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1. Go to the Dealer Resource section of www.garmin.com and save the “GTS Assert Log
Diagnosis Install Tool.zip” file from the website to the PC.
2. On the PC, locate the files “GTS Processor Install Tool.zip.” Extract the files from the zip file.
3. Select (double click) the “Assert_Log_Diagnosis.msi” file.
4. On the PC, select ‘Next’ when prompted. Follow the wizard to setup the GTS Processor Install
Tool. (Examples shown assume a Windows XP operating system, the required steps may vary
with other Operating Systems.)
Figure 3-7 GTS Assert Log Diagnosis Tool – Installation
5. Select ‘Next’, when prompted or ‘Browse’, to select another folder. If desired, click on the Disk
Cost button to view available storage drives and required disk space. Also a selection can be
made to control the tool’s availability to users of the PC.
Figure 3-8 GTS Assert Log Diagnosis Tool – Installation
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6. Select ‘Next’, when prompted to begin the installation.
Figure 3-9 GTS Assert Log Diagnosis Tool – Installation
7. The installation progress is displayed.
Figure 3-10 GTS Assert Log Diagnosis Tool – Installation
8. Verify that installation is successful, then select ‘Close’, to complete the installation.
Figure 3-11 GTS Assert Log Diagnosis Tool – Installation
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3.9 Post Installation Configuration & Checkout
The following actions must be performed after initial installation and after the equipment has been
removed/disconnected then reinstalled/reconnected :
1. GTS Processor Configuration (Section 3.8.2)
2. Suppression Bus I/O Check (Section 3.8.3)
3. CDTI (Cockpit Display of Traffic Information) Display
4. Setup and Configuration (Section 3.8.4)
5. Calibration/Self Test (Section 3.8.5)
6. Ramp Test and Return To Service Tests (Section 3.8.6)
7. Antenna Verification (Section 3.8.7)
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.
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.
3.9.1 GTS Processor Configuration/Checkout for Different Installation Types
Configuration instructions may differ according to the specifics of the installation. Refer to the following
subsections for specific instruction applicable to different installation types.
3.9.1.1 FAA Approved Garmin Integrated Flight Deck/GTS Processor Installation
When installed as part of a Garmin Integrated Flight Deck via the Garmin High Speed Data Bus (HSDB),
the GTS Processor must have FAA approved configuration data. Configuration data is loaded to the GTS
Processor from an aircraft-specific software loader card.
GDUs using SW prior to v11.10 require that the Ramp Test and Return to Service Tests are accomplished
using the GTS Processor Install Tool (Section 3.8.2). GDU SW v11.10 and newer allow the Ramp Test
and Return to Service Tests to be accomplished via the GDU (Section 3.8.6).
For basic configuration information refer to the appropriate maintenance manual. For actual installation/
checkout, use only aircraft manufacturer approved or STC checkout procedures.
3.9.1.2 Field Approved (Retrofit) Garmin G500/600 Installation
For GTS Processor units in G500/600 installations, refer to the GTS Processor STC Install Manual,
(190-01279-00), for configuration procedures and instructions.
3.9.1.3 Field Approved (Retrofit) Garmin Integrated Flight Deck
Garmin Integrated Flight Deck refers to an installation with GIA 63/GIA 6XW integrated avionics units
and GDU 1XXX displays. GTS Processor units require an ARINC 429 connection to the transponder for
TCAS Equipage, but the transponder cannot be configured properly in the Garmin Integrated Flight Deck,
and therefore cannot be installed via Field Approval method. Refer to Figure B-5 for interconnect
example.
NOTE
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Please check the aircraft warranty status before installation and/or with the aircraft
manufacturer for guidance.
ADS-B receive functionality is not available in a Field Approved Garmin
Integrated Flight Deck installation.
3.9.1.4 Retrofitting a non-Garmin Integrated Flight Deck Installation such as a
GNS 4XX/5XX(W) or GTC 650/750 unit with a GTS Processor
Configuration, software uploading, and Ramp Test and Return to Service Tests are accomplished using the
GTS Processor Install Tool (Section 3.8.2).
Installations that are unable to electronically display the software part number of
the GTS Processor should affix a label on the GTS Processor LRU marked with
the software part number to meet the TSO marking requirements. For the
installer’s convenience, a label has been applied adjacent to the LRU serial
number tag.
3.9.1.5 Non-Garmin Installations with a GTS Processor
Configuration, software uploading, and Ramp Test and Return to Service Tests are accomplished using the
GTS Processor Install Tool (Section 3.8.2).
Installations that are unable to electronically display the software part number of
the GTS Processor should affix a label on the GTS Processor LRU marked with
the software part number to meet the TSO marking requirements. For the
installer’s convenience, a label has been applied adjacent to the LRU serial
number tag.
3.9.2 Using the GTS Processor Install Tool
The following tabs are accessible with the GTS Processor Install Tool. Changing tabs may cause the GTS
Processor unit to restart.
· Normal Tab – Reports System Faults, Status Flags, and Operating Status. Allows Ground
Test Mode to be Enabled or Disabled.
· Configuration Tab – Allows selection of installation options
· Upload Tab – Allows upload of software to GTS Processor unit
· Assert Tab – Generates the assert log which can be submitted to Garmin Technical Support
for troubleshooting.
NOTE
NOTE
NOTE
NOTE
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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. ‘Alpha Values’ phase measurement values for
the Top Antenna and Bottom Antenna (if a bottom directional antenna is installed) are found on the GTS
Processor Install Tool Normal tab, and are updated only after a self-test (Section 3.8.5) is run. These
antenna phase measurements are used to determine if the installation has adequate antenna ground planes.
Figure 3-12 GTS Processor Install Tool – Normal Tab
Normal Mode –
System Faults:
Red Bold text indicates that a fault is active.
Gray text indicates that there is no active fault.
(System Faults are described in the Calibration/Self-Test Section 3.8.5)
Status Flags:
Black Bold text indicates that a flag is set.
Gray text indicates that the flag is not set.
(Status Flags are described in the Calibration/Self-Test Section 3.8.5)
Ground Test:
Enabled
Disabled
(Ground Test is described in the Ramp Test and Return to Service Tests Section 3.8.6).
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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 3-13 GTS Processor Install Tool – Configuration Tab (GTS 825 and GTS 855)
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.
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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 KRA10A
King KRA405
Sperry AA100
Terra TRA3000/3500
GPS Position/Velocity/Time Source:
Note: At least one source required for ADS-B IN functionality.
PrimaryA429 RX Channels 1 - 6 or Disabled
SecondaryA429 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 Garmin GA58
Sensor Systems
Cable loss (dB) 0.2 – 4.0
Note: Cable loss information is described in Fabrication of Coaxial Cable
Assemblies Section 2.4.1.2.
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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 2.4.1.2.
Note: All A429 options have the ability to select High or Low speed.
Note: If an input is inactive, a will be displayed.
If an input is active, a will be displayed.
If an input is in an unknown state, a will be displayed.
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.
Discrete ‘gear-down’ Sense:
Indicate the type of gear down sense switch for the Gear Down and Locked* discrete input.
See Appendix B (Note 7) and Figure B-9 for Gear Down and Locked* discrete input.
Note: Discrete ‘gear-down’ sense is only enabled when ‘Retractable’ Gear/Wheel design is
configured.
ADSB TX Capable:
Indicate whether aircraft is equipped with ADS-B transmitter.
Squat ‘on-ground’ Sense:
Indicate type of sense switch.
Note: For helicopter installations without a squat switch, the traffic system status valid discrete
output can be wired to the air/ground discrete input to prevent the GTS from going to standby mode
during extended hover. For such installations, configure squat ‘on-ground’ sense to ‘open’.
Mode S ID (HEX):
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 Processor.
Revert Changes:
Select to show current GTS Processor settings.
An incorrect configuration will be reverted back to previous settings.
Note: Default is “disabled” for all inputs and outputs.
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Upload System Mode Tab
The Upload Tab displays version information for Boot Block, Region List, System, FPGA, Audio and
Magnetic Variation. Boot Block updating is not allowed. For other files, select the appropriate image files
and select upload.
Figure 3-14 GTS Processor Install Tool – Upload Tab
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Assert Tab
The Assert Tab gets and displays the contents of the assert log from the GTS. Select ‘Get Assert Log’ to
retrieve the assert log from the GTS and ‘Save Assert Log to File’ to save the received log to a text file.
Figure 3-15 GTS Processor Install Tool – Assert Tab
3.9.3 Suppression Bus I/O Check
Other equipment onboard the aircraft may transmit and receive in the same frequency band as the GTS
Processor (e.g. DME or transponder). Mutual Suppression is a synchronous pulse that is sent to other
equipment to suppress transmission of a competing transmitter/receiver for the duration of the pulse train
transmission. In order to limit mutual interference the GTS Processor transmission may be suppressed by
other onboard equipment, and other onboard equipment may be suppressed by the GTS Processor. This
will prevent a TA from being issued from an onboard transponder.
Perform a test of the GTS Processor Suppression Bus I/O by following these steps:
1. Ensure the GTS Processor is in Operate mode and the onboard transponder is in Airborne mode.
2. Verify there is no TA issued on or near own-aircraft position. If a TA occurs at own-aircraft
position, ensure the Suppression I/O (P8002 pin 48) is properly connected to the Suppression
I/O pin of the onboard transponder.
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3.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and
Configuration
For configuration of the displays, refer to their respective manuals.
· 500 Series Installation Manual (190-00181-02)
· GMX 200 Installation Manual
· (190-00607-04)
· GDU 620 Installation Manual
· (190-00601-04)
· GTS Processor System Maintenance Manual (190-00587-51)
· G1000 System Maintenance Manual LJ/VLJ (190-00903-00)
3.9.5 Calibration/Self Test
A self-test feature tests the (aural) alarm, attempts self calibration, and activates each 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.
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 Processor powered up and Standby indicated on the CDTI, cycle the GTS Processor to Self
Test. The self test feature of the GTS Processor tests the following internal parameters as well as performs
calibration of various components in the GTS Processor:
For helicopter installations without a squat switch, and wired as described in Note
6 of Appendix B, select standby mode on the CDTI and initiate the self test within
8 seconds before the unit changes back to operate mode.
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 3.8.2. Download the assert log and send to Garmin
for diagnosis per Assert Tab info in Section 3.8.2.
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. Download
the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. 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. Download the assert log and send to Garmin for
diagnosis per Assert Tab info in Section 3.8.2. If fault persists, return unit to Garmin for service.
NOTE
NOTE
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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 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 fault - Receive Frequency synthesizer is not locked. Cycle power and retry self test. If
fault persists, return unit to Garmin for service.
k) Receiver Cal 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. Download
the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If fault
persists, return unit to Garmin for service.
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 Cal 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.
Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If
fault persists, return unit to Garmin for service.
A transmitter self-calibration can only be performed after a successful receiver
self-calibration.
m) Baro Altitude 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) Temperature fault – Main board temperature or RF receiver temperature is greater than 100°
Celsius or less than -60° Celsius. Fault will persist until internal temperature returns to acceptable
range. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section
3.8.2.
o) TCAS Equipage 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.
p) Radio Altitude fault - Radio Altimeter has not remained active for five or more consecutive
updates within the first ten surveillance updates after power up or reset, or the radio altitude status
has been inactive for three or more consecutive seconds after the first ten seconds of operation.
Check wiring to source of radio altitude and ensure that source is operating. Fault will clear as
soon as valid radio altitude data is received.
NOTE
NOTE
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The self test feature also checks the following external parameters:
a) Mag Variation Available status – Magnetic variation data (difference between ‘True’ North and
Magnetic North) is available.
b) GPS Available status – GPS Position, Velocity and Time source is configured and valid data is
available. Otherwise source is not configured, data is not available or data is not valid.
c) Display #1 Active status – Traffic display #1 discrete input is active.
d) Display #2 Active status – Traffic display #2 discrete input is active.
e) Radio Altitude Available status – Radio altimeter source is configured, and valid data is available.
Otherwise source is not configured, data is not available, or data is not valid.
f) Mag Heading Available status – Magnetic heading source is configured, and valid data is
available. Otherwise source is not configured, data is not available, or data is not valid.
g) Airborne Self Test Allowed status – Self test while airborne is allowed if active, otherwise self test
can only be initiated on the ground.
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 3-16 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.
DRAFT
Page 3-20 GTS Processor Installation Manual
Revision A 190-00587-50
Audio annunciation shall be:
GTS 825 - “TAS system Passed” or “TAS system Failed”
GTS 855 - “TCAS I system Passed” or “TCAS I system Failed”
GTS 8000 - "TCAS II system Passed" or "TCAS II system Failed"
Any faults and flags are also displayed on the Normal Tab of the GTS Processor 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.
Ensure that no Intruder appears at close range to own aircraft.
If the intruder appears at close range to own aircraft, verify that the mutual
suppression line is connected between GTS Processor and other L-band
equipment (transponder, DME, etc.).
3.9.6 Ramp Test and Return To Service Test
For helicopter installations with the traffic system status valid discrete output
wired to the air/ground discrete input, the ground test must be performed with the
squat 'on-ground' sense temporarily configured as 'ground'. After performing the
ground test, reconfigure the squat 'on-ground' sense to 'open'.
Garmin Integrated Flight Deck HSDB installations with GDU software versions
prior to 11.10 require the USB interface dongle cable (Appendix B) to allow use
of the GTS Processor Install Tool to simulate flight conditions such as altitude of
50,000 feet, gear up, etc (Section 3.8.2). Garmin Integrated Flight Deck HSDB
installations with GDU software versions 11.10 and newer can access the Ground
Test from the MFD to perform these tests. Consult Garmin for details.
For Garmin Integrated Flightdeck HSDB installations with GDU Software Versions prior to 11.10:
Activate ground test mode by clicking ‘Enable’ in the Ground Test field on the Normal Tab of the GTS
Processor Install Tool.
Figure 3-17 Ground Test Enable, GTS Processor Install Tool
For Garmin Integrated Flightdeck HSDB installations with GDU Software Versions 11.10 and
newer:
The Ground Test command is accessed from the MFD in normal mode while the aircraft is on the ground
by pressing the softkey sequence 3, 4, 4, 3. After pressing the softkeys in sequence, a 'GND TEST' softkey
appears, to allow the user to activate/deactivate the Ground Test. Press the 'GND TEST' softkey to begin
the procedure.
Figure 3-18 GND TEST Softkey
NOTE
NOTE
NOTE
DRAFT
GTS Processor Installation Manual Page 3-21
190-00587-50 Revision A
Ground Test Procedure:
The GTS Processor must be in Ground Test mode to select a scenario that will properly converge and
intercept the GTS Processor. The aircraft must be on the ground and the GTS Processor must be in Normal
System mode and in Standby, to enable Ground Test mode.
The GTS Processor will not accept the Ground Test command unless the unit is in
Standby and the squat switch indicates the aircraft is on the ground.
Configure Squat 'on-ground' sense as Open if no sense switch is installed. Leave
Air/Ground* discrete Open. Configuration of Gear/Wheel as 'Fixed' will cause
system to ignore the Gear Down and Locked* discrete input. See Appendix B
(Notes 6 and 7) and Figure B-9 for Air/Ground* and Gear Down And Locked*
discrete inputs.
The Ground Test simulates the GTS to be airborne at 50,000 ft with magnetic heading of 0°.
Use a ramp tester, such as a TIC TR220 or equivalent, to make the following setup and measurements to
verify GTS Processor operational and surveillance functionality.
1. Position the test set directional antenna with a clear line of sight to the GTS Processor antenna at
90 degrees.
2. With the GTS Processor powered up and in Standby mode (indicated on the CDTI), cycle the
GTS Processor to “Operate”.
3. Select the following scenario:
Intruder Type–ATCRBSIntruder Start Distance–10 NM
Intruder Start Altitude–50,000 ftVertical Speed–0 fpm
Velocity–360 Kts
4. Initiate the intruder scenario and verify that the following occurs:
a. 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. Verify that
only a single target is displayed in the expected quadrant.
b. 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.
c. The appropriate TA symbology (yellow filled circle with 00 displayed above) is
displayed, for GTS 855/GTS 825 installations an audio annunciation of "Traffic! 3
O'clock! Same Altitude! 3 Miles!" is issued, when the intruder approaches within 3
NM. For GTS 8000 installations, audio annunciations per DO-185B will be spoken
(Traffic! Traffic!).
When a GTS Processor is configured not to have a Radar Altimeter installed and
the gear is extended (in a retractable gear aircraft), the audio annunciation of
Traffic will be inhibited.
NOTE
NOTE
NOTE
DRAFT
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3.9.7 Antenna Verification
The GTS Processor must be in Ground Test mode to perform the antenna
verification. Refer to Section 3.8.6 for Ground Test mode information.
The first step in antenna verification is to verify auto-calibration operates without indicating a fault.
1. With the GTS Processor powered up and “Standby” indicated on the CDTI (Cockpit Display of
Traffic Information) cycle the GTS Processor to “Operate”. Each time the GTS Processor
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
ensure the antenna is properly connected and the GTS Processor is operational.
2. Position the test set directional antenna with a clear line of sight to the GTS Processor antenna.
3. Ensure that the transmitter or receiver (RX/TX) under test 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 Processor to the
normal operating mode.
9. Program a static intruder per the following scenario:
See ramp test set operators manual to set the following parameters
Intruder Start Distance–2 NM Intruder Start Altitude–50,000
Vertical Speed–0 fpm Velocity–0 Kts
10. Set the intruder type as ATCRBS.
11. Verify a target is annunciated on the GTS Processor 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.
14. Reengage the same intruder scenario as above.
15. Verify a target is annunciated on the GTS Processor TAS/TCAS display at the correct bearing
of approximately 90 degree azimuth at 2 NM and co-altitude.
NOTE
NOTE
DRAFT
GTS Processor Installation Manual Page 3-23
190-00587-50 Revision A
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 Processor 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 Processor 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 by verifying the
following:
· Connections are made to the proper channels and color-coded heat shrink is the same color
on both ends of cable
· TNC connectors are correctly installed on cables
· Correct antenna type is selected in the configuration
If multiple targets are displayed during the antenna tests, recheck the antenna
coaxial connections.
3.10 Continued Airworthiness
Maintenance of the GTS Processor is “on condition” only.
Antennas installed in lightning zone 1A of the aircraft require a cable check (verify the connectors are on
tight) following a lightning strike to the antenna.
It is the installer’s responsibility to properly document any Instructions for
Continued Airworthiness as may be required by the local aircraft certification
authorities.
NOTE
NOTE
DRAFT
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GTS Processor Installation Manual Page 4-1
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4 SYSTEM INTERCONNECTS
4.1 GTS Processor Pin Function List
4.1.1 P8001 (Digital)
Figure 4-1 View of J8001 connector from back of unit
Table 4-1 P8001 Connector
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
1 2 3 4 5 6 7 8 9 10 11121314151617181920
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39
40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
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Table 4-1 P8001 Connector, continued
Pin Pin Name I/O
36 ARINC 429 IN 4 B In
37 RS-422 IN A In
38 RS-422 IN B In
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 In
55 ETHERNET IN B In
56 SIGNAL GROUND --
57 RS-422 OUT A Out
58 RS-422 OUT B Out
59 SIGNAL GROUND --
60 CONFIG MODULE CLOCK Out
61 RESERVED --
62 RESERVED --
63 RESERVED --
64 RESERVED --
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)
Figure 4-2 View of J8002 connector from back of unit
Table 4-2 P8002 Connector
Pin Pin Name Applicable Model** I/O
1 SIGNAL GROUND --
2RA DISPLAY STATUS VALID* 1 GTS 8000 In
RESERVED GTS 855/GTS 825 --
3RA DISPLAY STATUS VALID* 2 GTS 8000 In
RESERVED GTS 855/GTS 825 --
4 RESERVED --
5 SIGNAL GROUND --
6 AIR/GROUND* In
7SPARE --
8 TRAFFIC DISPLAY 1 STATUS VALID* In
9 TRAFFIC DISPLAY 2 STATUS VALID* In
10 GEAR DOWN AND LOCKED* In
11 ADVISORY INHIBIT* 1 In
12 ADVISORY CANCEL* In
13 RESERVED --
14 SELF TEST INHIBIT PROGRAM* In
15 CLIMB INHIBIT* 1 GTS 8000 In
RESERVED GTS 855/GTS 825 --
16 CLIMB INHIBIT* 2 GTS 8000 In
RESERVED GTS 855/GTS 825 --
17 INCREASED CLIMB INHIBIT* 1 GTS 8000 In
RESERVED GTS 855/GTS 825 --
18 INCREASED CLIMB INHIBIT* 2 GTS 8000 In
RESERVED GTS 855/GTS 825 --
19 PERFORMANCE LIMIT* GTS 8000 In
RESERVED GTS 855/GTS 825 --
20 RESERVED --
21 SIGNAL GROUND --
22 RESERVED --
23 RESERVED --
24 RESERVED --
25 RESERVED --
26 RESERVED --
27 RESERVED --
28 RESERVED --
*Denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.
**Items in this column denote pin information specific to the listed model. Pin information applies to all models
(GTS 8000, GTS 855, and GTS 825) if blank.
1 2 3 4 5 6 7 8 9 10 11121314151617181920
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39
40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
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Revision A 190-00587-50
Table 4-2 P8002 Connector, continued
Pin Pin Name Applicable Model** I/O
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
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 ANNUN* 1 (CORRECTIVE RA)*** GTS 8000 Out
ANNUN* 1 (TA DISPLAY ENABLE)*** GTS 855/GTS 825 Out
51 ANNUN* 2 (PREVENTIVE RA)*** GTS 8000 Out
ANNUN* 2 (AURAL TA)*** GTS 855/GTS 825 Out
52 SPARE --
53 ANNUN* 3 (VISUAL TA) Out
54 TRAFFIC SYSTEM STATUS VALID* Out
55 RESERVED --
56 ADVISORY INHIBIT* 2 GTS 8000 In
RESERVED GTS 855/GTS 825 --
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 --
*Denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.
**Items in this column denote pin information specific to the listed model. Pin information applies to all models
(GTS 8000, GTS 855, and GTS 825) if blank.
***The Annunciator Outputs are configurable to perform the discrete output functions of ARINC 735 A/B.
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Table 4-2 P8002 Connector, continued
Pin Pin Name Applicable Model** I/O
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 --
*Denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.
**Items in this column denote pin information specific to the listed model. Pin information applies to all models
(GTS 8000, GTS 855, and GTS 825) if blank.
DRAFT
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Revision A 190-00587-50
4.1.3 P8003 (Power Supply)
Figure 4-3 View of J8003 connector from back of unit
Table 4-3 P8002 Connector
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 RESERVED --
8 RESERVED --
9 RESERVED --
10 RESERVED --
11 POWER GROUND --
12 RESERVED --
13 RESERVED --
14 POWER GROUND --
15 RESERVED --
16 RESERVED --
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 4.5.4 for signal
description.
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4.2 Power
4.2.1 Aircraft Power Functions
This section covers the power input requirements.
4.2.1.1 Aircraft Power
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.
4.2.1.2 Remote Power
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)
Table 4-4 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
POWER GROUND P8003 21 --
POWER GROUND P8003 22 --
POWER GROUND P8003 23 --
POWER GROUND P8003 24 --
Table 4-5 Remote Power
Pin Name Connector Pin I/O
TRAFFIC SYSTEM REMOTE POWER ON* P8003 18 In
TRAFFIC SYSTEM REMOTE POWER OFF P8003 36 In
Table 4-6 Power On/Off Matrix
Active Low Remote Power On (J8003
Pin 18)
Active High Remote Power Off
(J8003 Pin 36) Expected Unit State
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
DRAFT
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Revision A 190-00587-50
4.3 Serial Data
4.3.1 RS-232
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.
4.3.2 RS-422
The RS-422 channels conform to EIA standard RS-422.
Table 4-7 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
Table 4-8 RS-422
Pin Name Connector Pin I/O
RS-422 IN A P8001 37 In
RS-422 IN B P8001 38 In
RS-422 OUT A P8001 57 Out
RS-422 OUT B P8001 58 Out
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4.3.3 ARINC 429
The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5
standard ARINC 429 receivers.
4.3.4 Ethernet
This Ethernet based HSDB (High Speed Data Bus) meets the hardware aspects of IEEE standard 802.3 for
10 base T Ethernet communications.
Table 4-9 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
Table 4-10 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
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4.3.5 USB
**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.
4.4 Configuration
4.4.1 Configuration Module
**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection.
4.5 Analog/Discrete
4.5.1 Heading Input
4.5.1.1 26 Volt AC References
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
Table 4-11 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 --
Table 4-12 Configuration Module
Pin Name Connector Pin I/O
CONFIG MODULE GROUND P8001 1 --
CONFIG MODULE POWER OUT** P8001 21 --
CONFIG MODULE DATA** P8001 40 I/O
CONFIG MODULE CLOCK** P8001 60 I/O
Table 4-13 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
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4.5.1.2 Radar Altimeter
Provides altitude information during approach. Input voltage range is 0 to 30Vdc. Compatible with Radar
Altimeters listed in section 3.5.2.4.
4.5.2 Inputs From Compass System/Directional Gyros
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: >10 kΩ
Resolution: ± 0.1° or better
Accuracy: ± 2°
Both the active high Heading Valid discrete and the active low Heading Valid*
discrete inputs to the GTS Processor must be valid for heading information to be
used by the GTS Processor system.
If the Compass System/Directional Gyro provides an active high Heading Valid discrete output, wire to the
GTS Processor active high Heading Valid discrete input, otherwise wire the GTS Processor active high
Heading Valid discrete input to the circuit breaker output (14 Vdc or 28 Vdc) for the Compass System/
Directional Gyro.
If the Compass System/Directional Gyro provides an active low Heading Valid* discrete output, wire to
the GTS Processor active low Heading Valid* discrete input, otherwise wire the GTS Processor active low
Heading Valid* discrete input to Ground.
Table 4-14 Radar Altimeter
Pin Name Connector Pin I/O
ANALOG RADAR ALTIMETER HI P8002 71 In
ANALOG RADAR ALTIMETER LO P8002 72 In
Table 4-15 Inputs From Compass System/Directional Gyros
Pin Name Connector Pin I/O
HEADING X P8002 41 In
HEADING LO (GROUND) P8002 42 --
HEADING Y HI P8002 44 In
HEADING Y LO (GROUND) P8002 45 --
HEADING Z HI (GROUND) P8002 60 In
HEADING Z LO (GROUND) P8002 61 --
NOTE
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4.5.3 Audio
Alert Audio shield should only be connected to ground on the Audio Panel end.
4.5.4 Active Low Discrete Inputs
*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
**Items in this column denote pin information specific to the listed model. Pin information applies to all
models (GTS 8000/ GTS 855, and GTS 825) if blank
Table 4-16 Audio
Pin Name Connector Pin I/O
ALERT AUDIO OUT HI P8002 58 Out
ALERT AUDIO OUT LO P8002 59 Out
NOTE
Table 4-17 Active Low Discrete Inputs
Pin Name Applicable
Model**
Connector Pin I/O
RA DISPLAY STATUS VALID* 1 GTS 8000 P8002 2 In
RA DISPLAY STATUS VALID* 2 GTS 8000 P8002 3 In
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
ADVISORY INHIBIT* 1 P8002 11 In
ADVISORY CANCEL* P8002 12 In
SELF TEST INHIBIT PROGRAM* P8002 14 In
CLIMB INHIBIT* 1 GTS 8000
P8002 15 In
RESERVED GTS 855/
GTS 825
CLIMB INHIBIT* 2 GTS 8000
P8002 16 In
RESERVED GTS 855/
GTS 825
INCREASED CLIMB INHIBIT* 1 GTS 8000
P8002 17 In
RESERVED GTS 855/
GTS 825
INCREASED CLIMB INHIBIT* 2 GTS 8000
P8002 18 In
RESERVED GTS 855/
GTS 825
PERFORMANCE LIMIT* GTS 8000 P8002 19 In
RESERVED GTS 855/
GTS 825
HEADING VALID* P8002 69 In
SELF TEST INITIALIZE SELECT* P8002 74 In
TRAFFIC OPERATE/STANDBY* P8002 75 In
DRAFT
GTS Processor Installation Manual Page 4-13
190-00587-50 Revision A
The ‘sense’ of the AIR/GROUND* and the GEAR DOWN AND LOCKED*
Active Low Discrete Inputs are configurable using the GTS Processor Install
Tool.
Two discrete inputs (CLIMB INHIBIT* 1 and CLIMB INHIBIT* 2) have been provided to indicate that
the aircraft cannot climb at the rate of 1500 feet per minute. The 1500 fpm climb limit condition should be
assumed whenever CLIMB INHIBIT* 1 OR CLIMB INHIBIT* 2 are active.
Two discrete inputs (INCREASED CLIMB INHIBIT* 1 and INCREASED CLIMB INHIBIT* 2) have
been provided to indicate that the aircraft cannot climb at the rate of 2500 feet per minute. The 2500 fpm
climb limit condition should be assumed whenever INCREASED CLIMB INHIBIT* 1 OR INCREASED
CLIMB INHIBIT* 2 are active.
Connect ADVISORY INHIBIT* 1 to the audio inhibit output from a higher priority audio source, such as
TAWS.
ADVISORY CANCEL*, SELF TEST INITIALIZE SELECT*, and TRAFFIC OPERATE/STANDBY*
inputs are driven with pulsed signals. When the switch is activated, these inputs provide the following
functionality:
· ADVISORY CANCEL* cancels the audio for the currently playing aural alert (if any). This input
can be connected to a Traffic Advisory acknowledge momentary switch to mute TA audio.
· SELF TEST INITIALIZE SELECT* initiates the Self Test function. In normal operating mode,
transitions to the active state on this line toggles the intruder altitude filter between UNR (+9,900 ft
to -9,900 ft), ABV (+9000 ft to -2700 ft), NRM (+2700 ft to -2700 ft), and BLW (+2700 ft to
-9000 ft).
· TRAFFIC OPERATE/STANDBY* toggles between Operate and Standby modes.
4.5.5 Active High Discrete Inputs
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.
NOTE
Table 4-18 Active High Discrete Inputs
Pin Name Connector Pin I/O
HEADING VALID P8002 68 In
ANALOG RADAR ALTIMETER VALID P8002 76 In
DRAFT
Page 4-14 GTS Processor Installation Manual
Revision A 190-00587-50
4.5.6 Annunciator Output
*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.
**Items in this column denote pin information specific to the listed model. Pin information applies to all
models (GTS 8000, GTS 855, and GTS 825) if blank
***GTS 855/GTS 825: VISUAL TA stays active throughout a TA, and during a self test. GTS 8000:
VISUAL TA, CORRECTIVE RA, and PREVENTIVE RA stay active during their respective state, and
only one can be active at a time. VISUAL TA is active during a self test.
4.6 Mutual Suppression Bus
Mutual Suppression Input/Output bus compliant with ARINC 735A/B 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.
Table 4-19 Annunciator Output
Pin Name Applicable
Model**
Connector Pin I/O
ANNUN* 1 (CORRECTIVE RA) GTS 8000
P8002 50 Out
ANNUN* 1 (TA DISPLAY ENABLE) GTS 855/
GTS 825
ANNUN* 2 (PREVENTIVE RA) GTS 8000
P8002 51 Out
ANNUN* 2 (AURAL TA) GTS 855/
GTS 825
ANNUN* 3 (VISUAL TA)*** P8002 53 Out
TRAFFIC SYSTEM STATUS VALID* P8002 54 Out
Table 4-20 Mutual Suppression Bus
Pin Name Connector Pin I/O
EXTERNAL SUPPRESSION I/O P8002 48 I/O
DRAFT
GTS Processor Installation Manual Page A-1
190-00587-50 Revision A
APPENDIX A Outline and Installation Drawings
Figure A-1 GTS Processor Vertical Outline Drawing
1.99 50.5
6.74
171.1
13.49 342.5
CENTER OF GRAVITY
TBD
GRAVITY
TBD
CENTER OF
.625
15.88
7.00
177.8 4.375
111.13
3.32 84.23.67 93.1
.18 4.4
CENTER OF GRAVITY
TBD
GRAVITY
TBD
CENTER OF
6X NOTE 3
GRAVITY
TBD
CENTER OF
GRAVITY
TBD
CENTER OF
NOTES:
DIMENSIONS: INCHES [mm]
1.
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.
2.
MOUNTING HOLE FOR FOR #8 PANHEAD SCREW.
3.
DRAFT
GTS Processor Installation Manual Page A-2
190-00587-50 Revision A
APPENDIX A Outline and Installation Drawings
Figure A-2 GTS Processor Vertical Installation Drawing
CONNECTOR KITCONNECTOR KIT
011-01360-00 (UNSEALED)011-01360-00 (UNSEALED)
OROR
011-01360-10 (SEALED)011-01360-10 (SEALED)
GTS PROCESSOR UNITGTS PROCESSOR UNIT
011-02571-00011-02571-00
GTS PROCESSOR VERTICAL RACKGTS PROCESSOR VERTICAL RACK
011-02572-00011-02572-00
011-01855-04011-01855-04
(2 PLACES)(2 PLACES)
NOTE 1NOTE 1
011-01855-03011-01855-03
NOTE 1NOTE 1
330-00502-37 (UNSEALED)330-00502-37 (UNSEALED)
OROR
330-00853-37 (SEALED)330-00853-37 (SEALED)
330-00366-78 (UNSEALED)330-00366-78 (UNSEALED)
OROR
330-00776-78 (SEALED)330-00776-78 (SEALED)
(2 PLACES)(2 PLACES)
NOTES:NOTES:
1. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS1. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS
DRAFT
GTS Processor Installation Manual Page A-3
190-00587-50 Revision A
APPENDIX A Outline and Installation Drawings
Figure A-3 GTS Processor Horizontal Outline Drawing
1.99 50.5
3.48 88.3
HEIGHT
WITHOUT FEET
4.10
104.1
HEIGHT
WITH FEET
12.80 325.1
CENTER OF GRAVITY
TBD
OF GRAVITY
TBD
CENTER
OF GRAVITY
TBD
CENTER
CENTER OF GRAVITY
TBD
1.59 40.3 9.73
247.0
2.40 61.0 8.10
205.7
.46
11.7
2.75 69.9
2.75 69.9
6.42
163.1
OF GRAVITY
TBD
CENTER
CENTER OF GRAVITY
TBD
6X NOTE 3
NOTES:
DIMENSIONS: INCHES [mm]
1.
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.
2.
MOUNTING HOLE FOR #8 PANHEAD OR SOCKET HEAD
3.
CAP SCREW. RECOMMENDED LENGTH .750 INCHES MINIMUM.
MOUNTING FEET MAY BE REMOVED WHEN DESIRED FOR INSTALLATION.
4.
SEE FIGURE A-?? FOR DETAILS OF REUSE OF SCREWS AND MOUNTING HOLES
IN A FOOTLESS INSTALLATION.
DRAFT
GTS Processor Installation Manual Page A-4
190-00587-50 Revision A
APPENDIX A Outline and Installation Drawings
Figure A-4 GTS Processor Horizontal Installation Drawing
GTS PROCESSOR UNIT
011-02571-00
GTS PROCESSOR HORIZONTAL RACK
115-00784-00
SCREWS AND HOLES FOR REUSE
WHEN INSTALLING RACK WITH FEET REMOVED
(SEE NOTE 1)
SCREWS AND HOLES FOR REUSE
WHEN INSTALLING RACK WITH FEET REMOVED
(SEE NOTE 1)
011-01855-03
NOTE 2
011-01855-04
(2 PLACES)
NOTE 2
330-00366-78 (UNSEALED)
OR
330-00776-78 (SEALED)
(2 PLACES)
330-00502-37 (UNSEALED)
OR
330-00853-37 (SEALED)
CONNECTOR KIT
011-01360-00 (UNSEALED)
OR
011-01360-10 (SEALED)
NOTES:
RACK MAY BE INSTALLED WITH MOUNTING FEET ATTACHED, OR AFTER REMOVAL OF MOUNTING FEET.
1.
TO INSTALL RACK WITHOUT MOUNTING FEET, REMOVE FEET AND REUSE SCREWS (QUANTITY 6) IN THE
EXTREME FRONT COUNTERSUNK MOUNTING HOLES (3 PLACES) AND THE EXTREME BACK COUNTERSUNK
MOUNTING HOLES (3 PLACES).
2. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS.
DRAFT
GTS Processor Installation Manual Page B-1
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-1 GTS Processor Interconnect Example Notes
THE GTS PROCESSOR SUPPRESSION I/O PULSES MAY NOT BE COMPATIBLE WITH ALL MODELS OF TRANSPONDERS AND DME UNITS THAT HAVE OUTPUT-ONLY SUPPRESSION, AND
CAN BE DAMAGED BY THE GTS PROCESSOR MUTUAL SUPPRESSION OUTPUT. FOR TRANSPONDERS AND DME UNITS THAT HAVE OUTPUT-ONLY SUPPRESSION, AN IN-LINE DIODE
MUST BE INSTALLED BETWEEN THE GTS PROCESSOR SUPPRESSION I/O (CATHODE) AND THE OUTPUT-ONLY SUPPRESSION LINE.
PROCESSOR A GTX 3000, OR OTHER
RTCA DO-185A/B GARMIN-APPROVED COMPATIBLE TRANSPONDER, IS REQUIRED FOR ALL GTS 8000 INSTALLATIONS.
GTS 8000 INSTALLATIONS REQUIRE ARINC 429 IN/OUT CONNECTIONS TO A GTX 3000, OR OTHER RTCA DO-185A/B GARMIN-APPROVED COMPATIBLE TRANSPONDER. GTX 3000 BARO
ALTITUDE AND TCAS EQUIPAGE DATA ARE PRESENT ON A SINGLE ARINC 429 INTERFACE.
13. IF INSTALLED, THE USB PIGTAIL MUST BE WIRED DIRECTLY TO THE DSUB CONNECTOR. ALL USB EXTENSION CABLES MUST BE DISCONNECTED DURING FLIGHT.
FOR GTS 8000 INTERCONNECTION TO A GTX 3000, TX/XT INTERFACE MUST BE WIRED AS FOLLOWS: FROM GTX 3000 ARINC 429 OUTPUT CHANNEL 4 TO APPROPRIATELY CONFIGURED
GTS 8000 ARINC INPUT, AND FROM APPROPRIATELY CONFIGURED GTS 8000 ARINC OUTPUT TO GTX 3000 ARINC 429 INPUT CHANNEL 8.
DRAFT
GTS Processor Installation Manual Page B-2
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-2 GTS Processor Interconnect Example
GTS PROCESSOR
BOTTOM ANTENNA IS OPTIONAL FOR GTS 855 AND GTS 825 INSTALLATIONS. BOTTOM ANTENNA IS REQUIRED FOR GTS 8000 INSTALLATIONS.
DRAFT
GTS Processor Installation Manual Page B-3
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-3 GTS Processor Garmin Integrated Flight Deck Interconnect Example
Garmin
52
53
ETHERNET OUT A
ETHERNET OUT B
Garmin
GDL 69/69A
27 ETHERNET IN 2 A
196P1008P
26 ETHERNET IN 2 B
54
55
ETHERNET IN A
ETHERNET IN B
29
28
ETHERNET OUT 2 A
ETHERNET OUT 2 B
Garmin
GTX 33(D) w/ES
31 EXT SUPPRESSION I/O
P3301
48
SUPPRESSION I/O
P8002
UAT
DME
EXT SUPPRESSION I/O
EXT SUPPRESSION I/O
SS
S
S
S
S
Garmin
GIA 63(W) #1
1P604
751AURAL TA ALERT*
3811TA INHIBIT* 1 ANNUNCIATE* 15
DISCRETE* 1
Garmin
GMA 1347
P3471
19
39
UNSWITCHED AUDIO IN 1 HI
UNSWITCHED AUDIO IN LO
58
59
AUDIO ALERT OUT HI
AUDIO ALERT OUT LO
S
SS
S S
Garmin
GIA 63(W) #2
2P604
7
38 ANNUNCIATE* 15
DISCRETE* 1
S
S
ALERT AUDIO SHIELD SHOULD ONLY BE CONNECTED
TO GROUND ON THE AUDIO PANEL END.
Garmin
Garmin
GIA 63/63W
8 MAIN ARINC 429 IN 3 A
P603
9 MAIN ARINC 429 IN 3 B
74
75
MAIN ARINC 429 OUT 3 B
MAIN ARINC 429 OUT 3 A
S
S
S
S
14
15
16
17
ARINC 429 OUT 1 A
ARINC 429 OUT 1 B
ARINC 429 IN 1 A
ARINC 429 IN 1 B
Garmin
P8001
NOTE 11
REFER TO NOTE 12
FOR FAA APPROVED GARMIN INTEGRATED FLIGHT DECK/GTS PROCESSOR INSTALLATIONS (SEE SECTION 3.8.1.1):
APPLIES TO GTS PROCESSOR.
CONNECT THE HSDB INTERFACE. DO NOT CONNECT THE ARINC INTERFACE.
USB CONNECTION REQUIRED FOR GDU SW PRIOR TO V11.10.
SUPPRESSION I/O, ANALOG AUDIO ALERT OUTPUTS, AND TA INHIBIT DISCRETE INPUTS ARE NEEDED FOR ALL INSTALLATIONS.
REQUIRES FAA APPROVED CONFIGURATION DATA LOADED FROM AN AIRCRAFT SPECIFIC LOADER CARD.
Garmin
75
76
USB VBUS POWER
USB DATA HI
USB TYPE B
RECEPTACLE
1 VBUS
P8001
3D+
77
78
USB DATA LO
USB GROUND
2
4
D-
GND
S
SHELL
RED
GREEN
WHITE
BLACK
SHIELD
NOTE: USB TYPE B RECEPTACLE PIGTAIL MUST BE WIRED DIRECTLY TO
P8001 TO MINIMIZE LIGHTNING EXPOSURE. USB EXTENSION CABLES
MUST BE DISCONNECTED FROM THE PIGTAIL WHILE FLYING.
GTS PROCESSOR
GTS PROCESSOR
GTS PROCESSOR
GTS PROCESSOR
DRAFT
GTS Processor Installation Manual Page B-4
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-4 GTS Processor Field Approved (Retrofit) Garmin Integrated Flight Deck Interconnect Example
GTS PROCESSOR
TRAFFIC ALERTING
SYSTEM
P8001
P8002
P8003
SIGNAL GROUND 13
ARINC 429 OUT 1 A 14
ARINC 429 OUT 1 B 15
SIGNAL GROUND 22
ARINC 429 IN 1 A 16
ARINC 429 IN 1 B 17
CONFIG MODULE GROUND 1
CONFIG MODULE POWER OUT 21
CONFIG MODULE DATA 40
CONFIG MODULE CLOCK 60
USB VBUS POWER 75
USB DATA HI 76
USB DATA LO 77
USB GROUND 78
SELF TEST INITIALIZE SELECT* 74
TRAFFIC OPERATE/STANDBY* 75
AUDIO ALERT OUT HI 58
AUDIO ALERT OUT LO 59
TA INHIBIT* 1 11
AIRCRAFT POWER 2
POWER GROUND 21
POWER GROUND 23
POWER GROUND 22
POWER GROUND 24
GMA x347
AUDIO PANEL
P3471
S
S
19 UNSWITCHED AUDIO IN 1 HI
39 UNSWITCHED AUDIO IN LO
GIA 63W
INTEGRATED AVIONICS
2P604
38 ANNUN* 15 (TA INHIBIT* 1)
36 ANNUN* 13 (TAS SELF TEST*)
37 ANNUN* 14 (TAS STBY/OPR*)
CONFIG MODULE
1 GND
4 VCC
3 DATA
2 CLK
GIA 63W
INTEGRATED AVIONICS
2P603
51 SIGNAL GROUND
71 ARINC OUT 1A
70 ARINC OUT 1B
11 ARINC IN 4B
10 ARINC IN 4A
48 SIGNAL GROUND
S
S
S
S
AIR/GROUND* 6 AIR/GROUND (SQUAT SWITCH), OPTIONAL CONNECTION
GEAR DOWN AND LOCKED* 10 GEAR DOWN AND LOCKED, OPTIONAL CONNECTION
USB TYPE B RECEPTACLE
1 VBUS
3 D+
2 D-
4 GND
S
SHELL SHIELD
TAS 1 BREAKER AND AIRCRAFT POWER BUS 1
TAS 1 BREAKER AND AIRCRAFT POWER BUS 2
REFER TO NOTE 8
AIRCRAFT POWER 3
AIRCRAFT POWER 4
AIRCRAFT POWER 5
INSTALLER MAY SELECT DIFFERENT GIA
ARINC CHANNELS THAN THOSE LISTED,
CHANNELS USED MUST MATCH THOSE
USED IN CONFIGURATION (SECTION 3.9)
IN CERTAIN INSTALLATIONS, THE UNSWITCHED AUDIO PORT MAY ALREADY BE
CONFIGURED FOR USE BY ANOTHER SYSTEM. IF ANOTHER SYSTEM IS USING THE
'UNSWITCHED AUDIO IN 1' OUTPUT, THE INSTALLER MUST VERIFY THERE IS NO
INTERFERENCE WITH THE OTHER SYSTEM. A DIFFERENT GMA OUTPUT PORT (IF
AVAILABLE) MAY BE CONFIGURED TO RECEIVE TAS AUDIO
UNLESS OTHERWISE NOTED, ALL CONNECTIONS SHOWN ARE REQUIRED
DRAFT
GTS Processor Installation Manual Page B-5
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-5 GTS Processor GNS 4XX/5XX/GMX 200 Interconnect Example
GTS PROCESSOR GTS PROCESSOR
DRAFT
GTS Processor Installation Manual Page B-6
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-6 GTS Processor GMA/HSI/Altimeter Interconnect Example
WHEN INSTALLING A RADAR ALTIMETER THAT DOES NOT HAVE AN ACTIVE HIGH ANALOG
FLAG OUTPUT, THE GTS 8XX ANALOG RADAR ALTIMETER VALID INPUT (PIN 76) SHOULD BE
CONNNECTED TO AIRCRAFT POWER
THESE CONNECTIONS NOT REQUIRED FOR GTX 3000 INSTALLATION
GTS PROCESSOR GTX 330 ES/GTX 3000 GTS PROCESSOR
}
FOR GTX 3000, BARO OUT AND NTA
COUNT INFO ARE OUTPUT ON A
SINGLE ARINC CHANNEL
DRAFT
GTS Processor Installation Manual Page B-7
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-7 GTS Processor Dongle Cable (see Sections 3.7 and 3.8.6)
USB VBUS POWER
USB DATA HI
USB DATA LO
USB GROUND
RED
GRN
WHT
BLK
75
76
77
78
GTS PROCESSOR
P8001
VBUS
D+
D-
GND
1
3
2
4
USB TYPE B
RECEPTACLE
SHIELDSHELL
s
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: SHIELD BLOCK GROUND AIRFRAME GROUND
3. AT THE GTS PROCESSOR, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS
THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS OR CONNECTOR BACKSHELL WITH AS SHORT
A CONDUCTOR AS PRACTICAL FOLLOWING ANY EQUIPMENT MANUFACTURER’S REQUIREMENTS.
4. USB TYPE B RECEPTACLE PIGTAIL (P/N 011-01782-00) MUST BE WIRED DIRECTLY TO P8001 TO MINIMIZE LIGHTNING
EXPOSURE.
5. THE USB PIGTAIL SHIELD DRAIN USES 28 AWG WIRE.
s
4
28 AWG
28 AWG
5
DRAFT
GTS Processor Installation Manual Page B-8
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-8 GTS Processor Discrete Interconnect Example
GTS PROCESSOR
ANNUN* 3 VISUAL TA ALERT*
ANNUN* 2 AURAL TA
ANNUN* 1 (CORRECTIVE AURAL* RA - GTS 8000 / TA DISPLAY ENABLE* - GTS 855/GTS 825)
ADVISORY CANCEL*
RA DISPLAY STATUS VALID* 2 (GTS 8000 ONLY) 3RA DISPLAY 2 VALID
RA DISPLAY 2 INVALID
RA DISPLAY 2 VALID
RA DISPLAY STATUS VALID* 1 (GTS 8000 ONLY) 2RA DISPLAY 1 VALID
RA DISPLAY 1 INVALID
RA DISPLAY 1 VALID
DRAFT
GTS Processor Installation Manual Page B-9
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-9 GTS Processor Configuration Module Interconnect Example
GTS PROCESSOR
GARMIN
DRAFT
GTS Processor Installation Manual Page B-10
190-00587-50 Revision A
APPENDIX B Interconnect Examples
Figure B-10 GTS Processor Dual Transponder Interconnect Example
GTS 820/850
ARINC 429 OUT 2 A
ARINC 429 OUT 2 B
23
24
P8001
GARMIN
TRANSPONDER #1
ARINC 429 IN 2 A
ARINC 429 IN 2 B
33
36
31
P3301
s
NOTES:
1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.
2. GROUND DESIGNATIONS: SHIELD BLOCK GROUND AIRFRAME GROUND
3. AT THE GTS 8XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS
THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL.
4. CONFIGURE THE ARINC 429 BUS SPEED TO MATCH THE GTS PROCESSOR OUTPUT SPEED.
5. REFER TO GARMIN TRANSPONDER INSTALLATION MANUAL FOR ADDITIONAL INSTALLATION DETAILS.
7. IF ONLY ONE TRANSPONDER IS INSTALLED, CONNECT AS SHOWN FOR TRANSPONDER #1.
s
EXTERNAL SUPPRESSION I/O 48 EXTERNAL SUPPRESSION I/O
ARINC 429 IN 2 A
ARINC 429 IN 2 B
25
26
ARINC 429 OUT 2 A
ARINC 429 OUT 2 B
30
28
s
P8002
s
s
4
GTX
33/33D
330/330D
33
36
31
P3281
30
28
GTX
328
--
--
17
P3271
--
--
GTX
327/32/
320A
GARMIN
TRANSPONDER #2
ARINC 429 IN 2 A
ARINC 429 IN 2 B
33
36
31
P3301
EXTERNAL SUPPRESSION I/O
ARINC 429 OUT 2 A
ARINC 429 OUT 2 B
30
28
s
s
GTX
33/33D
330/330D
33
36
31
P3281
30
28
GTX
328
--
--
17
P3271
--
--
GTX
327/32/
320A
13 EXTERNAL STANDBY SELECT
13 EXTERNAL STANDBY SELECT
TRANSPONDER 2
TRANSPONDER 1
TO DME/UAT
ARINC 429 OUT 3 A
ARINC 429 OUT 3 B
28
29
ARINC 429 IN 3 A
ARINC 429 IN 3 B
30
31
6. THE GTX 330 ARINC 429 OUT 2 PORT IS HIGH-IMPEDANCE WHEN THE EXTERNAL STANDBY SELECT INPUT IS
GROUNDED. THIS ALLOWS ARINC 429 OUTPUTS FROM DUAL GTX 330 UNITS TO BE HARD-WIRED TOGETHER SINCE THE
EXTERNAL STANDBY SELECT INPUT WILL BE ACTIVE FOR ONE OF THE TWO GTX 330’S AT ANY GIVEN TIME.
8. THE GTS PROCESSOR IS NOT TO BE INSTALLED IN AN AIRCRAFT WITH A TSO-C119a-ONLY COMPATIBLE TRANSPONDER.
DRAFT