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| 1 | Cover Letter(s) | September 01 2012 | ||||||
| 1 | Cover Letter(s) | September 01 2012 | ||||||
| 1 | External Photos | September 01 2012 / July 07 2012 | ||||||
| 1 | Cover Letter(s) | September 01 2012 | ||||||
| 1 | Internal Photos | September 01 2012 / July 07 2012 | ||||||
| 1 | ID Label/Location Info | September 01 2012 | ||||||
| 1 | RF Exposure Info | September 01 2012 | ||||||
| 1 | Cover Letter(s) | September 01 2012 | ||||||
| 1 | Cover Letter(s) | September 01 2012 | ||||||
| 1 | Test Report | September 01 2012 | ||||||
| 1 | Test Setup Photos | September 01 2012 / July 07 2012 | ||||||
| 1 | Parts List/Tune Up Info | September 01 2012 |
| 1 | Users Manual | Users Manual | 3.23 MiB | September 01 2012 / July 07 2012 |
GTS Processor Installation Manual 190-00587-50 January, 2012 Revision A DRAFT Copyright 2012 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited. Aviation Panel-Mount Technical Support Line (Toll Free) 1.888.606.5482 Garmin International, Inc. 1200 E. 151st Street Olathe, KS 66062 USA Telephone: 913.397.8200 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 A 01/06/2012 Initial Release Description Page A Revision A GDR 66 Installation Manual 190-00587-50 DRAFT 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. WARNING This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65. CURRENT REVISION DESCRIPTION Revision Page Number(s) Section Number A All All Initial release Description of Change DOCUMENT PAGINATION Section Table of Contents Section 1 Section 2 Section 3 Section 4 Appendix A Appendix B Page Range i viii 1-1 1-10 2-1 2-10 3-1 3-22 4-1 4-14 A-1 A-4 B-1 B-10 GTS Processor Installation Manual 190-00587-50 Page i Revision A DRAFT 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 Page ii Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 GTS Processor Installation Manual 190-00587-50 Page iii Revision A DRAFT 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 Page iv Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 GTS Processor Installation Manual 190-00587-50 Page v Revision A DRAFT 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 Page vi Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 GTS Processor Installation Manual 190-00587-50 Page vii Revision A DRAFT Page viii Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. NOTE 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. NOTE The GTS Processor is not to be installed in an aircraft with a TSO-C119a-only compatible transponder. NOTE 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 GTS Processor Installation Manual 190-00587-50 Page 1-1 Revision A DRAFT Refer to Table 1-1 for a list of compatible transponders. Table 1-1 Compatible Transponders Capable of GTX Transponder Model Receiving TCAS II Broadcast Data
(Required for GTS Processor) ADS-B Capable RTCA DO-185A/B Compatible Yes Yes(2) Yes(2) Yes(3) Yes(3) Yes(3) Yes(3) Yes(4) Yes GTX 330/330D GTX 330 ES/330D ES GTX 33/33D(1) GTX 33 ES/33D ES(1) GTX 328 GTX 3000 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. No No No No No Yes Yes No 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 GTS 855*
GTS 8000*
*Requires upgrade using GTX Processor TCAS I/TCAS II Enablement Process. See Section XXX for instructions. 011-02571-00 011-02571-00 011-02571-00 TSO-C147 TSO-C118 TSO-C119c X X X X X X 400 400 400 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 Page 1-2 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 1.4.2 Physical Characteristics Table 1-3 Physical Characteristics Characteristics GTS Processor Width w/out rack GTS Processor Height w/out rack GTS Processor Width with vertical rack GTS Processor Height with vertical rack GTS Processor Depth with vertical rack GTS Processor Width with horizontal rack GTS Processor Height with horizontal rack GTS Processor Depth with horizontal rack GTS Processor Depth w/Connector Kit GTS Processor Unit Weight w/out Connector Kit GTS Processor Unit Weight with Connector Kit w/Vertical Rack GTS Processor Unit Weight with Connector Kit w/Horizontal Rack Specifications 3.42 inches (86.9 mm) 6.25 inches (158.8 mm) 3.67 inches (93.1 mm) 6.74 inches (171.1 mm) 15.48 inches (396.7 mm) 6.42 inches (163.1 mm) 4.10 inches (104.1 mm) 14.79 inches (375.7 mm) 14.78 inches (375.4 mm) 11.30 lbs (5.13 kg) 12.65 lbs (5.74 kg) 13.25 lbs (6.01 kg) 1.4.3 General Specifications Table 1-4 contains general specifications. For detailed environmental specifications, see the Environmental Qualification Form. Characteristics Operating Temperature Range Humidity Altitude Range Software Compliance Hardware Compliance Environmental Compliance Table 1-4 General Specifications Specifications
-55C to +70C. 95% non-condensing
-1,500 ft to 55,000 ft RTCA/DO-178B level B RTCA/DO-254 Level B RTCA/DO-160F 1.4.4 Power Requirements Tables list the power requirements for the GTS Processor 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 GTS Processor Installation Manual 190-00587-50 Page 1-3 Revision A DRAFT 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. GTS Processor Configuration Table 1-7 TSO/ETSO Compliance 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 GTS 855 Traffic Alert and Collision Avoidance System (TCAS I) Airborne Equipment TSO-C118 ETSO-C118 GTS 825 Traffic Advisory System
(TAS) Airborne Equipment TSO-C147 ETSO-C147 Class A 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-B1244-0( ) through 006-B1244-2( ) except 006-B1244-00 through 006-B1244-03 All 006-B1224-0( ) through 006- B1224-2( ) except 006- B1224-00 through 006-B1224-03 All 006-B1224-0( ) through 006- B1224-2( ) except 006- B1224-00 through 006- B1224-03 All 006- B1224-0( ) through 006- B1224-2( ) except 006-B1224-00 through 006-B1224-03 006-C0081-2( ) 006-C0081-2( ) 006-C0081-2( ) 006-C0081-2( )
*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. Page 1-4 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT NOTE 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 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 s from top antenna and 90 +/-1 s from bottom antenna) instead of 100 +/-5 s. GTS Processor Installation Manual 190-00587-50 Page 1-5 Revision A DRAFT Table 1-8 TSO/ETSO Deviations, Continued 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 s from top antenna and 90 +/-1 s from bottom antenna) instead of 100 +/-5 s. 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. 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. ETSO-C118 TSO-C119c ETSO-C119c Page 1-6 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT Table 1-8 TSO/ETSO Deviations, Continued 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 s from top antenna and 90 +/-1 s from bottom antenna) instead of 100 +/-5 s. 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 s from top antenna and 90 +/-1 s from bottom antenna) instead of 100 +/-5 s. 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. TSO-C147 ETSO-C147 ETSO-C166a GTS Processor Installation Manual 190-00587-50 Page 1-7 Revision A DRAFT 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. Part Number 190-00313-11 190-00303-00 190-00587-51 190-00903-00 190-00907-00 Table 1-9 Reference Documents Document Jackscrew Backshell Installation Instructions G1000 System Installation Manual GTS Processor System Maintenance Manual G1000 System Maintenace Manual LJ/VLJ G1000 System Maintenance Manual Standard Piston/Turboprop Aircraft Page 1-8 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. 1200 East 151st Street Olathe, Kansas 66062, U.S.A. Phone:913/397.8200 FAX:913/397.0836 Garmin (Europe) Ltd. Liberty House, Bulls Copse Road Hounsdown Business Park Romsey, SO40 9RB, U.K. Phone:44/ (0) 870.8501241 FAX:44/ (0) 870.850125 GTS Processor Installation Manual 190-00587-50 Page 1-9 Revision A DRAFT This page intentionally left blank Page 1-10 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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:
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 2.1.2 Required Accessories NOTE Refer to the Dealers 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. Table 2-2 Required Accessories Installation Racks Garmin P/N 011-02572-00*
115-00784-00*
GTS Processor Vertical Installation Rack GTS Processor Horizontal Installation Rack
*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. GTS Processor Installation Manual 190-00587-50 Page 2-1 Revision A DRAFT Table 2-3 Connector Kits Connector Kits GTS Processor Connector Kit GTS Connector Kit w/Config Module and USB Pigtail USB-B Pigtail (see GTS Configuration Options) Table 2-4 Optional Accessories Optional Accessories Color Coded Heat Shrink Kit Garmin P/N 011-01360-00 011-01360-01 011-01782-00 Garmin P/N 011-02817-00 NOTE 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. Table 2-5 Antennas Antennas GA 58 Directional Antenna, QMA (011-01346-00) NOTE: Refer to 190-00587-00 GTS 8XX Installation Manual for installation instructions GA 58 Directional Antenna, TNC, (011-01346-02) NOTE: Refer to 190-000587-20 GA 58 Installation Manual for installation instructions. Low Profile Directional Antenna Monopole Antenna Garmin P/N 010-10720-00*
010-10720-02*
013-00276-XX**
010-10160-00 or L-Band Monopole Antenna that meets TSO-C74c
*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 manufacturers installation manual for installation instructions.. Table 2-6 Configuration Module Configuration Module Garmin P/N 011-00979-20 Configuration Module*
*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. Page 2-2 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. NOTE 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 aircrafts 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. GTS Processor Installation Manual 190-00587-50 Page 2-3 Revision A DRAFT 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. NOTE 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. NOTE 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. NOTE 2.4.1.1 GTS Processor Installations NOTE 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 Page 2-4 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 50 TNC termination. Figure 2-2 GTS Processor Installation with Top Directional and Bottom Monopole Antennas GTS Processor Installation Manual 190-00587-50 Page 2-5 Revision A DRAFT 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 50 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 NOTE 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 agencys responsibility to ensure that the coaxial cable assemblies meet the manufacturers attenuation specifications as shown in Section 2-4 in order to comply with the system installation standards. NOTE Any in-line or bulkhead penetrations must be evaluated separately. It is the installing agencys responsibility to show airworthiness of the installed fabricated or purchased coaxial cable assemblies. Page 2-6 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT Table 2-7 Recommended Coaxial Length Max Terminated Cable Attenuation
(including connector loss)*
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**
l e b a C x a M n o i t a u n e t t A
) t f 0 0 1 B d
2' 2"
[0.66m]
2' 3"
[0.69m]
2' 5"
[0.74m]
3' 0"
[0.91m]
3' 2"
[0.97m]
3' 3"
[0.99m]
4' 3"
[1.30m]
5' 0"
[1.52m]
5' 1"
7' 8"
[2.34m]
8' 0"
[2.44m]
8' 6"
[2.59m]
10' 7"
[3.23m]
10' 11"
[3.33m]
11' 4"
[3.45m]
15' 0"
[4.57m]
17' 9"
[5.41m]
18' 0"
[5.49m]
10' 7"
[3.23m]
11' 0"
[3.35m]
11' 9"
[3.58m]
14' 7"
[4.45m]
15' 0"
[4.57m]
15' 6"
[4.72m]
20' 6"
[6.25m]
24' 5"
[7.44m]
24' 8"
[7.52m]
13' 6"
[4.11m]
14' 0"
[4.27m]
15' 0"
[4.57m]
18' 7"
[5.66m]
19' 2"
[5.84m]
19' 9"
[6.02m]
26' 2"
[7.98m]
31' 0"
[9.45m]
31' 6"
[9.60m]
16' 5"
[5.00m]
17' 0"
[5.18m]
18' 3"
[5.56m]
22' 7"
[6.88m]
23' 3"
[7.09m]
24' 0"
[7.32m]
31' 9"
[9.68m]
37' 10"
[11.53m]
38' 3"
[1.55m]
[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
[11.66m]
17.2 16.7 15.5 12.5 12.2 11.8 8.9 7.5 7.4
2
e p y T C P I
3
e p y T 7 1
C
L M I
4
e p y T G R M17/128-
RG400 RG-400 M17/60-
RG142 RG-142 S83204 S44191 S44193 S67163
1
e p y T S C E 311901 311601 311501
[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.
*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 manufacturers cable attenuation and connector specifications. GTS Processor Installation Manual 190-00587-50 Page 2-7 Revision A DRAFT 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. 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 GTS Processor BOTTOM to bottom directional antenna
*Ensure cables do not exceed the maximum lengths as stated in Table 2-1 unless supported by manufacturers data for specific cables used. 2" of each other 2" of each other NOTE 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. NOTE NOTE It is recommended that the nominal end to end coaxial cable (non-terminated) length for each set be recorded for the specific installation in the event that a particular coaxial cable assembly associated with an installed set should require replacement. Connector Body Ferrule Coaxial Cable Heat shrink not to protrude past this surface. 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. Page 2-8 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. GTS Processor Installation Manual 190-00587-50 Page 2-9 Revision A DRAFT 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) Page 2-10 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. Table 3-1 Socket and Pin Contact Part Numbers 78 Pin High Density D-Subminiature Connectors P8001 & P8002 37 Pin Standard Density D-Subminiature Connector P8003 19 Pin Circular Connector P651 Manufacturer High Density Pin (P8001
& P8002) Standard Socket
(P8003) 18 AWG Socket
(P8003) Garmin P/N Military P/N 336-00021-00 M39029/58-360 336-00022-00 M39029/63-368 336-00023-00 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 Daniels M22520/1-01 AF8 M22520/1-02 TH1A Tools Option 2 Military P/N M22520/2-01 M22520/2-02 Daniels AFM8
*Indicates plastic insertion/extraction tool K1S M81969/14-11*
M81969/14-11*
M81969/14-11*
M81969/14-11*
GTS Processor Installation Manual 190-00587-50 Page 3-1 Revision A DRAFT Table 3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling Insertion/Extraction Hand Crimping Manufacturer Tool Positioner Tool Military P/N Daniels Positronic ITT Cannon Tyco-AMP Astro Amphenol M22520/2-01 M22520/2-09 AFM8 9507-0 995-0001-584 601966-1 615717
(Note 2) K42 9502-4
(Note 2) 601966-6 615725
(Note 2) Note 1 - Indicates plastic insertion/extraction tool Note 2 Order by military part number M81969/1-04
(Note 2)
(Note 2) 274-7048-000 (Note 1) 91067-1
(Note 2)
(Note 2) Table 3-4 Pin Socket Contacts GPN 336-00022-00 MIL SPEC M39029/63-368 and Manufacturer Hand Crimping Tool GPN 336-00023-00 Crimp Tooling 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 Daniels Positronic ITT Cannon Tyco-AMP ASTRO Amphenol M22520/2-01 M22520/2-08 M81969/1-02 AFM8 9507-0 K13-1 9502-5
(Note 2)
(Note 2) 995-0001-584 995-0001-604 980-2000-426 (Note 1) 601966-1 615717
(Note 2) 601966-5 615724
(Note 2) 91067-2
(Note 2)
(Note 2) N/A K774 9502-11 N/A N/A NA N/A M81969/1-02
(Note 2)
(Note 2) N/A N/A N/A N/A Note 1 - Indicates plastic insertion/extraction tool Note 2 Order by military part number NOTE 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. Page 3-2 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. Garmins 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 GTS Processor Installation Manual 190-00587-50 Page 3-3 Revision A DRAFT 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. NOTE 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. NOTE 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. Page 3-4 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 GTS Processor Installation Manual 190-00587-50 Page 3-5 Revision A DRAFT 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. NOTE 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. Page 3-6 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 tools availability to users of the PC. Figure 3-8 GTS Assert Log Diagnosis Tool Installation GTS Processor Installation Manual 190-00587-50 Page 3-7 Revision A DRAFT 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 Page 3-8 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. NOTE Tests performed with a ramp tester should be performed away from buildings that may reflect the signal. Local air traffic control should be advised if the ramp tester has an altitude programmed into it that may cause interaction with other TCAS-equipped traffic. 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. GTS Processor Installation Manual 190-00587-50 Page 3-9 Revision A DRAFT Please check the aircraft warranty status before installation and/or with the aircraft manufacturer for guidance. NOTE ADS-B receive functionality is not available in a Field Approved Garmin Integrated Flight Deck installation. NOTE 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). NOTE 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 installers 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). NOTE 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 installers 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. Page 3-10 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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). GTS Processor Installation Manual 190-00587-50 Page 3-11 Revision A DRAFT 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. Page 3-12 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT Configuration Mode Barometric Altitude Source:
Note: At least one source must be selected (same altitude source used for the transponder). Primary Secondary COM A429 RX Channels 1 - 6 or Disabled A429 RX Channels 1 - 6 or Disabled RS-232 Ports 1 - 5 or Disabled Magnetic Heading Source (optional):
Primary Secondary A429 RX Channels 1 - 6 or Disabled A429 RX Channels 1 - 6 or Disabled Radio Altitude Source (optional):
A429 Analog A429 RX Channels 1 - 6 or Disabled 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 COM A429 TX Channels 1 - 6 or Disabled 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. A429 RX Channels 1 - 6 or Disabled Primary RX 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 Cable loss (dB) Garmin GA58 Sensor Systems 0.2 4.0 Note: Cable loss information is described in Fabrication of Coaxial Cable Assemblies Section 2.4.1.2. GTS Processor Installation Manual 190-00587-50 Page 3-13 Revision A DRAFT 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 If an input is active, a If an input is in an unknown state, a will be displayed. will be displayed. 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. Page 3-14 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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 GTS Processor Installation Manual 190-00587-50 Page 3-15 Revision A DRAFT 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. Page 3-16 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 3.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and Configuration For configuration of the displays, refer to their respective manuals.
(190-00607-04) 500 Series Installation Manual (190-00181-02) GMX 200 Installation Manual GDU 620 Installation Manual GTS Processor System Maintenance Manual (190-00587-51) G1000 System Maintenance Manual LJ/VLJ (190-00903-00)
(190-00601-04) 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. NOTE Self tests may be performed indoors but signal multi-path from building walls may be a factor. If problems are experienced, self tests should be performed outside away from buildings, and where local traffic is not a factor. With the GTS 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:
NOTE 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 0s or Fs ). 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. GTS Processor Installation Manual 190-00587-50 Page 3-17 Revision A DRAFT 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. 1030 MHz fault - Transmit Frequency synthesizer is not locked. Cycle power and retry self test. If fault persists, return unit to Garmin for service. 1090 MHz fault - Receive Frequency synthesizer is not locked. Cycle power and retry self test. If fault persists, return unit to Garmin for service. i) j) 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. NOTE Receiver self-calibration is performed prior to the transmitter self-calibration. In the event that a receiver calibration fault occurs, a transmitter self-calibration will not be performed. l) Transmitter 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. NOTE 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. Page 3-18 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. GTS Processor Installation Manual 190-00587-50 Page 3-19 Revision A DRAFT 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. NOTE 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 NOTE 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'. NOTE 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 Page 3-20 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. NOTE 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. NOTE 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 TypeATCRBSIntruder Start Distance10 NM Intruder Start Altitude50,000 ftVertical Speed0 fpm Velocity360 Kts Initiate the intruder scenario and verify that the following occurs:
4. 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!). NOTE 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. GTS Processor Installation Manual 190-00587-50 Page 3-21 Revision A DRAFT 3.9.7 Antenna Verification NOTE 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:
NOTE See ramp test set operators manual to set the following parameters Intruder Start Altitude50,000 Velocity0 Kts Intruder Start Distance2 NM Vertical Speed0 fpm 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. Page 3-22 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 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. NOTE 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. NOTE It is the installers responsibility to properly document any Instructions for Continued Airworthiness as may be required by the local aircraft certification authorities. GTS Processor Installation Manual 190-00587-50 Page 3-23 Revision A DRAFT This page intenionally left blank Page 3-24 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 4 SYSTEM INTERCONNECTS 4.1 GTS Processor Pin Function List 4.1.1 P8001 (Digital) 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Figure 4-1 View of J8001 connector from back of unit Table 4-1 P8001 Connector Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 Pin Name CONFIG MODULE GROUND RS-232 OUT 1 RS-232 IN 1 SIGNAL GROUND RS-232 OUT 2 RS-232 IN 2 SIGNAL GROUND RS-232 OUT 3 RS-232 IN 3 SIGNAL GROUND RS-232 OUT 4 RS-232 IN 4 SIGNAL GROUND ARINC 429 OUT 1 A ARINC 429 OUT 1 B ARINC 429 IN 1 A ARINC 429 IN 1 B SIGNAL GROUND GPS PPS 1 IN SIGNAL GROUND CONFIG MODULE POWER OUT SIGNAL GROUND ARINC 429 OUT 2 A ARINC 429 OUT 2 B ARINC 429 IN 2 A ARINC 429 IN 2 B SIGNAL GROUND ARINC 429 OUT 3 A ARINC 429 OUT 3 B ARINC 429 IN 3 A ARINC 429 IN 3 B SIGNAL GROUND ARINC 429 OUT 4 A ARINC 429 OUT 4 B ARINC 429 IN 4 A I/O
Out In
Out In
Out In
Out In
Out Out In In
In
Out
Out Out In In
Out Out In In
Out Out In GTS Processor Installation Manual 190-00587-50 Page 4-1 Revision A DRAFT Table 4-1 P8001 Connector, continued Pin 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 Pin Name ARINC 429 IN 4 B RS-422 IN A RS-422 IN B SIGNAL GROUND CONFIG MODULE DATA SIGNAL GROUND ARINC 429 OUT 5 A ARINC 429 OUT 5 B ARINC 429 IN 5 A ARINC 429 IN 5 B SIGNAL GROUND ARINC 429 OUT 6 A ARINC 429 OUT 6 B ARINC 429 IN 6 A ARINC 429 IN 6 B SIGNAL GROUND ETHERNET OUT A ETHERNET OUT B ETHERNET IN A ETHERNET IN B SIGNAL GROUND RS-422 OUT A RS-422 OUT B SIGNAL GROUND CONFIG MODULE CLOCK RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED SPARE SPARE SPARE SPARE GPS PPS IN 2 HI GPS PPS IN 2 LO USB VBUS POWER USB DATA HI USB DATA LO USB GROUND I/O In In In
I/O
Out Out In In
Out Out In In
Out Out In In
Out Out
Out
In In In I/O I/O
Page 4-2 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 4.1.2 P8002 (Analog/Discrete) 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Figure 4-2 View of J8002 connector from back of unit Table 4-2 P8002 Connector Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 Pin Name SIGNAL GROUND RA DISPLAY STATUS VALID* 1 RESERVED RA DISPLAY STATUS VALID* 2 RESERVED RESERVED SIGNAL GROUND AIR/GROUND*
SPARE TRAFFIC DISPLAY 1 STATUS VALID*
TRAFFIC DISPLAY 2 STATUS VALID*
GEAR DOWN AND LOCKED*
ADVISORY INHIBIT* 1 ADVISORY CANCEL*
RESERVED SELF TEST INHIBIT PROGRAM*
CLIMB INHIBIT* 1 RESERVED CLIMB INHIBIT* 2 RESERVED INCREASED CLIMB INHIBIT* 1 RESERVED INCREASED CLIMB INHIBIT* 2 RESERVED PERFORMANCE LIMIT*
RESERVED RESERVED SIGNAL GROUND RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED Applicable Model**
GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 I/O
In
In
In
In In In In In
In In
In
In
In
In
*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. GTS Processor Installation Manual 190-00587-50 Page 4-3 Revision A DRAFT Table 4-2 P8002 Connector, continued Pin 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 Pin Name RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED SIGNAL GROUND SIGNAL GROUND HEADING X HI HEADING X LO (GROUND) SIGNAL GROUND HEADING Y HI HEADING Y LO (GROUND) SIGNAL GROUND SPARE EXTERNAL SUPPRESSION I/O SIGNAL GROUND ANNUN* 1 (CORRECTIVE RA)***
ANNUN* 1 (TA DISPLAY ENABLE)***
ANNUN* 2 (PREVENTIVE RA)***
ANNUN* 2 (AURAL TA)***
SPARE ANNUN* 3 (VISUAL TA) TRAFFIC SYSTEM STATUS VALID*
RESERVED ADVISORY INHIBIT* 2 RESERVED SIGNAL GROUND ALERT AUDIO OUT HI ALERT AUDIO OUT LO HEADING Z HI (GROUND) HEADING Z LO (GROUND) SIGNAL GROUND 26 VAC HEADING REF HI 26 VAC HEADING REF LO SIGNAL GROUND SPARE SPARE HEADING VALID HEADING VALID*
SIGNAL GROUND Applicable Model**
GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 GTS 8000 GTS 855/GTS 825 I/O
In
In
I/O
Out Out Out Out
Out Out
In
Out Out In
In In
In In
*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. Page 4-4 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT Table 4-2 P8002 Connector, continued Pin 71 72 73 74 75 76 77 78 Pin Name ANALOG RADAR ALTIMETER HI ANALOG RADAR ALTIMETER LO SIGNAL GROUND SELF TEST INITIALIZE SELECT*
TRAFFIC OPERATE/STANDBY*
ANALOG RADAR ALTIMETER VALID SPARE SIGNAL GROUND Applicable Model**
I/O In In
In In In
*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. GTS Processor Installation Manual 190-00587-50 Page 4-5 Revision A DRAFT 4.1.3 P8003 (Power Supply) Figure 4-3 View of J8003 connector from back of unit Table 4-3 P8002 Connector Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 Pin Name POWER GROUND AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 POWER GROUND RESERVED RESERVED RESERVED RESERVED POWER GROUND RESERVED RESERVED POWER GROUND RESERVED RESERVED POWER GROUND TRAFFIC SYSTEM REMOTE POWER ON*
POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND TRAFFIC SYSTEM REMOTE POWER OFF POWER GROUND I/O
In In In In
In
In
An asterisk (*) following a signal name denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description. Page 4-6 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 4.2 Power 4.2.1 Aircraft Power Functions This section covers the power input requirements. 4.2.1.1 Aircraft Power Table 4-4 Aircraft Power Connector Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 POWER GROUND POWER GROUND POWER GROUND POWER GROUND 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. P8003 P8003 P8003 P8003 P8003 P8003 P8003 P8003 Pin 2 3 4 5 21 22 23 24 I/O In In In In
Connector P8003 P8003 Pin 18 36 I/O In In 4.2.1.2 Remote Power Table 4-5 Remote Power Pin Name TRAFFIC SYSTEM REMOTE POWER ON*
TRAFFIC SYSTEM REMOTE POWER OFF 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 4-6 Power On/Off Matrix Active Low Remote Power On (J8003 Pin 18) State Inactive Active Inactive Active Level Vin > 8 VDC or Open Vin < 3VDC or Gnd Vin > 8 VDC or Open Vin < 3VDC or Gnd State Inactive Inactive Active Active Active High Remote Power Off
(J8003 Pin 36) Level Expected Unit State Vin < 3VDC or Open Vin < 3VDC or Open Vin > 8 VDC Vin > 8 VDC OFF ON OFF OFF GTS Processor Installation Manual 190-00587-50 Page 4-7 Revision A DRAFT 4.3 Serial Data 4.3.1 RS-232 Table 4-7 RS-232 Connector Pin Name RS-232 OUT 1 RS-232 IN 1 RS-232 OUT 2 RS-232 IN 2 RS-232 OUT 3 RS-232 IN 3 RS-232 OUT 4 RS-232 IN 4 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. P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 I/O Out In Out In Out In Out In Pin 2 3 5 6 8 9 11 12 4.3.2 RS-422 Table 4-8 RS-422 Pin Name RS-422 IN A RS-422 IN B RS-422 OUT A RS-422 OUT B The RS-422 channels conform to EIA standard RS-422. Connector P8001 P8001 P8001 P8001 Pin 37 38 57 58 I/O In In Out Out Page 4-8 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 4.3.3 ARINC 429 Table 4-9 ARINC 429 Connector Pin Name ARINC 429 OUT 1 A ARINC 429 OUT 1 B ARINC 429 IN 1 A ARINC 429 IN 1 B ARINC 429 OUT 2 A ARINC 429 OUT 2 B ARINC 429 IN 2 A ARINC 429 IN 2 B ARINC 429 OUT 3 A ARINC 429 OUT 3 B ARINC 429 IN 3 A ARINC 429 IN 3 B ARINC 429 OUT 4 A ARINC 429 OUT 4 B ARINC 429 IN 4 A ARINC 429 IN 4 B ARINC 429 OUT 5 A ARINC 429 OUT 5 B ARINC 429 IN 5 A ARINC 429 IN 5 B ARINC 429 OUT 6 A ARINC 429 OUT 6 B ARINC 429 IN 6 A ARINC 429 IN 6 B The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers. P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 Pin 14 15 16 17 23 24 25 26 28 29 30 31 33 34 35 36 42 43 44 45 47 48 49 50 I/O Out Out In In Out Out In In Out Out In In Out Out In In Out Out In In Out Out In In 4.3.4 Ethernet Table 4-10 Ethernet Pin Name ETHERNET OUT A ETHERNET OUT B EHTERNET IN A ETHERNET IN B This Ethernet based HSDB (High Speed Data Bus) meets the hardware aspects of IEEE standard 802.3 for 10 base T Ethernet communications. P8001 P8001 P8001 P8001 Pin 52 53 54 55 I/O Out Out In In Connector GTS Processor Installation Manual 190-00587-50 Page 4-9 Revision A DRAFT 4.3.5 USB Table 4-11 USB Pin Name USB VBUS POWER**
USB DATA HI**
USB DATA LO**
USB GROUND
**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection. USB TYPE B RECEPTACLE P8001 P8001 P8001 P8001 I/O In I/O I/O
Pin 75 76 77 78 Connector 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 Table 4-12 Configuration Module Pin Name CONFIG MODULE GROUND CONFIG MODULE POWER OUT**
CONFIG MODULE DATA**
CONFIG MODULE CLOCK**
**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection. 4.5 Analog/Discrete P8001 P8001 P8001 P8001 Connector 4.5.1 Heading Input 4.5.1.1 26 Volt AC References Table 4-13 26 Volt AC References Pin Name 26 VAC HEADING REF HI 26 VAC HEADING REF LO Used to sample AC inputs. This signal must be the same phase and frequency as the indicator being driven. P8002 P8002 Connector Pin 1 21 40 60 I/O
I/O I/O Pin 63 64 I/O In In Frequency:
Voltage:
Input Impedance:
400 Hz 10%
22.6 Vrms to 28.6 Vrms
>10 k Page 4-10 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT 4.5.1.2 Radar Altimeter Table 4-14 Radar Altimeter Pin Name ANALOG RADAR ALTIMETER HI ANALOG RADAR ALTIMETER LO Provides altitude information during approach. Input voltage range is 0 to 30Vdc. Compatible with Radar Altimeters listed in section 3.5.2.4. Connector P8002 P8002 Pin 71 72 I/O In In 4.5.2 Inputs From Compass System/Directional Gyros Table 4-15 Inputs From Compass System/Directional Gyros Connector Pin Name HEADING X HEADING LO (GROUND) HEADING Y HI HEADING Y LO (GROUND) HEADING Z HI (GROUND) HEADING Z LO (GROUND) 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. P8002 P8002 P8002 P8002 P8002 P8002 Pin 41 42 44 45 60 61 I/O In
In
In
Frequency:
Voltage:
Input Impedance:
Resolution:
Accuracy:
400Hz 10%
11.8 Vrms nominal, 13.0 Vrms maximum
>10 k 0.1 or better 2 NOTE 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. GTS Processor Installation Manual 190-00587-50 Page 4-11 Revision A DRAFT 4.5.3 Audio Pin Name ALERT AUDIO OUT HI ALERT AUDIO OUT LO Table 4-16 Audio NOTE Connector P8002 P8002 Pin 58 59 I/O Out Out Alert Audio shield should only be connected to ground on the Audio Panel end. 4.5.4 Active Low Discrete Inputs Table 4-17 Active Low Discrete Inputs Pin Name RA DISPLAY STATUS VALID* 1 RA DISPLAY STATUS VALID* 2 AIR/GROUND*
TRAFFIC DISPLAY 1 STATUS VALID*
TRAFFIC DISPLAY 2 STATUS VALID*
GEAR DOWN AND LOCKED*
ADVISORY INHIBIT* 1 ADVISORY CANCEL*
SELF TEST INHIBIT PROGRAM*
CLIMB INHIBIT* 1 RESERVED CLIMB INHIBIT* 2 RESERVED INCREASED CLIMB INHIBIT* 1 RESERVED INCREASED CLIMB INHIBIT* 2 RESERVED PERFORMANCE LIMIT*
RESERVED Connector Pin I/O P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 P8002 2 3 6 8 9 10 11 12 14 15 16 17 18 19 In In In In In In In In In In In In In In Applicable Model**
GTS 8000 GTS 8000 GTS 8000 GTS 855/
GTS 825 GTS 8000 GTS 855/
GTS 825 GTS 8000 GTS 855/
GTS 825 GTS 8000 GTS 855/
GTS 825 GTS 8000 GTS 855/
GTS 825 HEADING VALID*
SELF TEST INITIALIZE SELECT*
TRAFFIC OPERATE/STANDBY*
*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 P8002 P8002 P8002 69 74 75 In In In Page 4-12 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT NOTE 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 Table 4-18 Active High Discrete Inputs Pin Name HEADING VALID ANALOG RADAR ALTIMETER VALID 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. Connector P8002 P8002 Pin 68 76 I/O In In GTS Processor Installation Manual 190-00587-50 Page 4-13 Revision A DRAFT 4.5.6 Annunciator Output Pin Name ANNUN* 1 (CORRECTIVE RA) ANNUN* 1 (TA DISPLAY ENABLE) ANNUN* 2 (PREVENTIVE RA) ANNUN* 2 (AURAL TA) Table 4-19 Annunciator Output Applicable Model**
GTS 8000 GTS 855/
GTS 825 GTS 8000 GTS 855/
GTS 825 Connector Pin I/O P8002 P8002 50 51 Out Out 53 54 P8002 P8002 ANNUN* 3 (VISUAL TA)***
TRAFFIC SYSTEM STATUS VALID*
*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 Out Out Table 4-20 Mutual Suppression Bus I/O Pin Name I/O EXTERNAL SUPPRESSION I/O 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. Connector Pin 48 P8002 Page 4-14 Revision A GTS Processor Installation Manual 190-00587-50 DRAFT APPENDIX A Outline and Installation Drawings 1.99 50.5 TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY 3.67 93.1 NOTES:
1. 2. 3. DIMENSIONS: INCHES [mm]
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. MOUNTING HOLE FOR FOR #8 PANHEAD SCREW. GTS Processor Installation Manual 190-00587-50 TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY 13.49 342.5 6.74 171.1 6X NOTE 3 3.32 84.2
.18 4.4
.625 15.88 7.00 177.8 4.375 111.13 Figure A-1 GTS Processor Vertical Outline Drawing Page A-1 Revision A DRAFT APPENDIX A Outline and Installation Drawings GTS PROCESSOR UNIT GTS PROCESSOR UNIT 011-02571-00 011-02571-00 CONNECTOR KIT CONNECTOR KIT 011-01360-00 (UNSEALED) 011-01360-00 (UNSEALED) OROR 011-01360-10 (SEALED) 011-01360-10 (SEALED) 011-01855-04 011-01855-04
(2 PLACES)
(2 PLACES) NOTE 1 NOTE 1 011-01855-03 011-01855-03 NOTE 1 NOTE 1 330-00366-78 (UNSEALED) 330-00366-78 (UNSEALED) OROR 330-00776-78 (SEALED) 330-00776-78 (SEALED)
(2 PLACES)
(2 PLACES) 330-00502-37 (UNSEALED) 330-00502-37 (UNSEALED) OROR 330-00853-37 (SEALED) 330-00853-37 (SEALED) NOTES:
NOTES:
1. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS 1. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS GTS PROCESSOR VERTICAL RACK GTS PROCESSOR VERTICAL RACK 011-02572-00 011-02572-00 GTS Processor Installation Manual 190-00587-50 Figure A-2 GTS Processor Vertical Installation Drawing Page A-2 Revision A DRAFT APPENDIX A Outline and Installation Drawings 1.99 50.5 TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY DIMENSIONS: INCHES [mm]
DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. MOUNTING HOLE FOR #8 PANHEAD OR SOCKET HEAD MOUNTING FEET MAY BE REMOVED WHEN DESIRED FOR INSTALLATION. NOTES:
1. 2. 3. CAP SCREW. RECOMMENDED LENGTH .750 INCHES MINIMUM. 4. SEE FIGURE A-?? FOR DETAILS OF REUSE OF SCREWS AND MOUNTING HOLES IN A FOOTLESS INSTALLATION. TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY 12.80 325.1 6X NOTE 3 TBD CENTER OF GRAVITY 3.48 88.3 HEIGHT WITHOUT FEET 4.10 104.1 HEIGHT WITH FEET 6.42 163.1 2.75 69.9 2.75 69.9
.46 11.7 GTS Processor Installation Manual 190-00587-50 1.59 40.3 2.40 61.0 9.73 247.0 8.10 205.7 Figure A-3 GTS Processor Horizontal Outline Drawing Page A-3 Revision A DRAFT APPENDIX A Outline and Installation Drawings GTS PROCESSOR UNIT 011-02571-00 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. SCREWS AND HOLES FOR REUSE WHEN INSTALLING RACK WITH FEET REMOVED
(SEE NOTE 1) GTS PROCESSOR HORIZONTAL RACK 115-00784-00 SCREWS AND HOLES FOR REUSE WHEN INSTALLING RACK WITH FEET REMOVED
(SEE NOTE 1) Figure A-4 GTS Processor Horizontal Installation Drawing Page A-4 Revision A 330-00366-78 (UNSEALED) OR 330-00776-78 (SEALED)
(2 PLACES) 011-01855-03 NOTE 2 011-01855-04
(2 PLACES) NOTE 2 GTS Processor Installation Manual 190-00587-50 330-00502-37 (UNSEALED) OR 330-00853-37 (SEALED) CONNECTOR KIT 011-01360-00 (UNSEALED) OR 011-01360-10 (SEALED) DRAFT APPENDIX B Interconnect Examples 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. 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. RTCA DO-185A/B GARMIN-APPROVED COMPATIBLE TRANSPONDER, IS REQUIRED FOR ALL GTS 8000 INSTALLATIONS. PROCESSOR A GTX 3000, OR OTHER 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. 13. IF INSTALLED, THE USB PIGTAIL MUST BE WIRED DIRECTLY TO THE DSUB CONNECTOR. ALL USB EXTENSION CABLES MUST BE DISCONNECTED DURING FLIGHT. GTS Processor Installation Manual 190-00587-50 Figure B-1 GTS Processor Interconnect Example Notes Page B-1 Revision A DRAFT APPENDIX B Interconnect Examples GTS PROCESSOR BOTTOM ANTENNA IS OPTIONAL FOR GTS 855 AND GTS 825 INSTALLATIONS. BOTTOM ANTENNA IS REQUIRED FOR GTS 8000 INSTALLATIONS. GTS Processor Installation Manual 190-00587-50 Figure B-2 GTS Processor Interconnect Example Page B-2 Revision A DRAFT APPENDIX B Interconnect Examples Garmin GTS PROCESSOR ETHERNET OUT A ETHERNET OUT B ETHERNET IN A ETHERNET IN B Garmin GTS PROCESSOR ARINC 429 OUT 1 A ARINC 429 OUT 1 B ARINC 429 IN 1 A ARINC 429 IN 1 B Garmin GTS PROCESSOR USB VBUS POWER USB DATA HI USB DATA LO USB GROUND 1008P 52 53 54 55 P8001 14 15 16 17 P8001 75 76 77 78 S S S S Garmin GDL 69/69A ETHERNET IN 2 A ETHERNET IN 2 B ETHERNET OUT 2 A ETHERNET OUT 2 B 196P 27 26 29 28 Garmin GIA 63/63W P603 8 9 MAIN ARINC 429 IN 3 A MAIN ARINC 429 IN 3 B 74 75 MAIN ARINC 429 OUT 3 B MAIN ARINC 429 OUT 3 A S S S Garmin GTS PROCESSOR P8002 SUPPRESSION I/O 48 REFER TO NOTE 12 P3301 Garmin GTX 33(D) w/ES NOTE 11 31 EXT SUPPRESSION I/O S S S S S S S S S UAT EXT SUPPRESSION I/O DME EXT SUPPRESSION I/O S S Garmin GIA 63(W) #1 1P604 7 DISCRETE* 1 38 ANNUNCIATE* 15 Garmin GIA 63(W) #2 2P604 7 DISCRETE* 1 38 ANNUNCIATE* 15 Garmin GMA 1347 P3471 19 39 UNSWITCHED AUDIO IN 1 HI UNSWITCHED AUDIO IN LO USB TYPE B RECEPTACLE RED GREEN WHITE BLACK 1 3 2 4 VBUS D+
D-
GND SHELL SHIELD AURAL TA ALERT*
51 TA INHIBIT* 1 11 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. 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. REQUIRES FAA APPROVED CONFIGURATION DATA LOADED FROM AN AIRCRAFT SPECIFIC LOADER CARD. SUPPRESSION I/O, ANALOG AUDIO ALERT OUTPUTS, AND TA INHIBIT DISCRETE INPUTS ARE NEEDED FOR ALL INSTALLATIONS. AUDIO ALERT OUT HI AUDIO ALERT OUT LO 58 59 ALERT AUDIO SHIELD SHOULD ONLY BE CONNECTED TO GROUND ON THE AUDIO PANEL END. GTS Processor Installation Manual 190-00587-50 Figure B-3 GTS Processor Garmin Integrated Flight Deck Interconnect Example Page B-3 Revision A DRAFT APPENDIX B Interconnect Examples E L U D O M G F N O C I D N G C C V A T A D K L C 1 4 3 2 W 3 6 A G I I I S C N O V A D E T A R G E T N I 3 0 6 P 2 D N U O R G L A N G S I A 4 N B 4 N I I I C N R A C N R A I 8 4 0 1 1 1 S U B V D N G
D
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, I I I A G T N E R E F F D T C E L E S Y A M R E L L A T S N D E T S L E S O H T N A H T S L E N N A H C C N R A E S O H T H C T A M T S U M D E S U S L E N N A H C I I
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, I D E T O N E S W R E H T O S S E L N U 1 S U B R E W O P T F A R C R A D N A R E K A E R B 1 S A T I 2 S U B R E W O P T F A R C R A D N A R E K A E R B 1 S A T I 8 E T O N O T R E F E R 1 0 0 8 P I G N T R E L A C F F A R T R O S S E C O R P S T G I M E T S Y S 1 2 0 4 0 6 1 T U O R E W O P E L U D O M G F N O C D N U O R G E L U D O M G F N O C I I K C O L C E L U D O M G F N O C A T A D E L U D O M G F N O C I I S S S S 3 1 4 1 5 1 A 1 T U O 9 2 4 C N R A B 1 T U O 9 2 4 C N R A D N U O R G L A N G S I I I 2 2 6 1 7 1 D N U O R G L A N G S I A 1 N B 1 N I I 9 2 4 C N R A 9 2 4 C N R A I I 6 7 7 7 8 7 5 7 R E W O P S U B V B S U I O L A T A D B S U D N U O R G B S U H A T A D B S U 2 0 0 8 P 4 7 5 7
T C E L E S E Z L A T N I I I I T S E T F L E S
Y B D N A T S E T A R E P O C F F A R T I 1 1 1 I
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0 1
D E K C O L D N A N W O D R A E G 8 5 9 5 I O L T U O T R E L A O D U A H T U O T R E L A O D U A I I 3 0 0 8 P 2 R E W O P T F A R C R A I 3 R E W O P T F A R C R A I 4 R E W O P T F A R C R A I 5 R E W O P T F A R C R A I 1 2 D N U O R G R E W O P 2 2 D N U O R G R E W O P 3 2 D N U O R G R E W O P 4 2 D N U O R G R E W O P GTS Processor Installation Manual 190-00587-50 Figure B-4 GTS Processor Field Approved (Retrofit) Garmin Integrated Flight Deck Interconnect Example Page B-4 Revision A DRAFT APPENDIX B Interconnect Examples GTS PROCESSOR GTS PROCESSOR GTS Processor Installation Manual 190-00587-50 Figure B-5 GTS Processor GNS 4XX/5XX/GMX 200 Interconnect Example Page B-5 Revision A DRAFT APPENDIX B Interconnect Examples 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 THESE CONNECTIONS NOT REQUIRED FOR GTX 3000 INSTALLATION 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 GTS Processor Installation Manual 190-00587-50 Figure B-6 GTS Processor GMA/HSI/Altimeter Interconnect Example Page B-6 Revision A DRAFT APPENDIX B Interconnect Examples GTS PROCESSOR 4 P8001 USB TYPE B RECEPTACLE USB VBUS POWER USB DATA HI USB DATA LO USB GROUND 75 76 77 78 28 AWG 28 AWG s RED GRN WHT BLK 1 3 2 4 SHELL VBUS D+
D-
GND SHIELD 5 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 MANUFACTURERS REQUIREMENTS. s 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. GTS Processor Installation Manual 190-00587-50 Figure B-7 GTS Processor Dongle Cable (see Sections 3.7 and 3.8.6) Page B-7 Revision A DRAFT APPENDIX B Interconnect Examples D I L A V N I 1 Y A L P S D A R I D I L A V 1 Y A L P S D A R I D I L A V N I 2 Y A L P S D A R I D I L A V 2 Y A L P S D A R I D I L A V 1 Y A L P S D A R I D I L A V 2 Y A L P S D A R I 2 3
) Y L N O 0 0 0 8 S T G
1
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2
D I L A V S U T A T S Y A L P S D A R I
L E C N A C Y R O S V D A I R O S S E C O R P S T G GTS Processor Installation Manual 190-00587-50
T R E L A A T L A U S V 3
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N U N N A Figure B-8 GTS Processor Discrete Interconnect Example Page B-8 Revision A DRAFT APPENDIX B Interconnect Examples GARMIN GTS PROCESSOR GTS Processor Installation Manual 190-00587-50 Figure B-9 GTS Processor Configuration Module Interconnect Example Page B-9 Revision A DRAFT APPENDIX B Interconnect Examples GTS 820/850 4 P8001 ARINC 429 OUT 3 A ARINC 429 OUT 3 B ARINC 429 IN 3 A ARINC 429 IN 3 B 28 29 30 31 TRANSPONDER 1 TRANSPONDER 2 TO DME/UAT ARINC 429 OUT 2 A ARINC 429 OUT 2 B ARINC 429 IN 2 A ARINC 429 IN 2 B 23 24 25 26 s s EXTERNAL SUPPRESSION I/O 48 P8002 NOTES:
GTX 33/33D 330/330D P3301 GTX 327/32/
320A P3271 GTX 328 P3281 GARMIN TRANSPONDER #2 33 36 30 28 13 31
33 36 30 28 ARINC 429 IN 2 A ARINC 429 IN 2 B ARINC 429 OUT 2 A ARINC 429 OUT 2 B EXTERNAL STANDBY SELECT 17 31 EXTERNAL SUPPRESSION I/O GTX 33/33D 330/330D P3301 GTX 327/32/
320A P3271 GTX 328 P3281 GARMIN TRANSPONDER #1 33 36 30 28 13 31
33 36 30 28 ARINC 429 IN 2 A ARINC 429 IN 2 B ARINC 429 OUT 2 A ARINC 429 OUT 2 B EXTERNAL STANDBY SELECT 17 31 EXTERNAL SUPPRESSION I/O s s s s 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. s 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. 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 330S AT ANY GIVEN TIME. 7. IF ONLY ONE TRANSPONDER IS INSTALLED, CONNECT AS SHOWN FOR TRANSPONDER #1. 8. THE GTS PROCESSOR IS NOT TO BE INSTALLED IN AN AIRCRAFT WITH A TSO-C119a-ONLY COMPATIBLE TRANSPONDER. GTS Processor Installation Manual 190-00587-50 Figure B-10 GTS Processor Dual Transponder Interconnect Example Page B-10 Revision A DRAFT
| frequency | equipment class | purpose | ||
|---|---|---|---|---|
| 1 | 2012-01-09 | 1030 ~ 1030 | TNB - Licensed Non-Broadcast Station Transmitter | Original Equipment |
| app s | Applicant Information | |||||
|---|---|---|---|---|---|---|
| 1 | Effective |
2012-01-09
|
||||
| 1 | Applicant's complete, legal business name |
Garmin International Inc
|
||||
| 1 | FCC Registration Number (FRN) |
0005088588
|
||||
| 1 | Physical Address |
1200 E. 151st. Street
|
||||
| 1 |
Olathe, Kansas 66062
|
|||||
| 1 |
United States
|
|||||
| app s | TCB Information | |||||
| 1 | TCB Application Email Address |
T******@TIMCOENGR.COM
|
||||
| 1 | TCB Scope |
B3: Maritime & Aviation Radio Services equipment in 47 CFR parts 80 & 87
|
||||
| app s | FCC ID | |||||
| 1 | Grantee Code |
IPH
|
||||
| 1 | Equipment Product Code |
0104455
|
||||
| app s | Person at the applicant's address to receive grant or for contact | |||||
| 1 | Name |
D******** K******
|
||||
| 1 | Title |
Manager Environmental and Regulatory Affairs
|
||||
| 1 | Telephone Number |
91344********
|
||||
| 1 | Fax Number |
913 3********
|
||||
| 1 |
d******@garmin.com
|
|||||
| app s | Technical Contact | |||||
| n/a | ||||||
| app s | Non Technical Contact | |||||
| n/a | ||||||
| app s | Confidentiality (long or short term) | |||||
| 1 | Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | Yes | ||||
| 1 | Long-Term Confidentiality Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | Yes | ||||
| 1 | If so, specify the short-term confidentiality release date (MM/DD/YYYY format) | 07/07/2012 | ||||
| if no date is supplied, the release date will be set to 45 calendar days past the date of grant. | ||||||
| app s | Cognitive Radio & Software Defined Radio, Class, etc | |||||
| 1 | Is this application for software defined/cognitive radio authorization? | No | ||||
| 1 | Equipment Class | TNB - Licensed Non-Broadcast Station Transmitter | ||||
| 1 | Description of product as it is marketed: (NOTE: This text will appear below the equipment class on the grant) | LICENSED NON-BROADCAST TRANSMITTER (TAS) AND TRAFFIC ALERT & COLLISION AVOIDANCE SYSTEM (TCAS) PROCESSOR MHz | ||||
| 1 | Related OET KnowledgeDataBase Inquiry: Is there a KDB inquiry associated with this application? | No | ||||
| 1 | Modular Equipment Type | Does not apply | ||||
| 1 | Purpose / Application is for | Original Equipment | ||||
| 1 | Composite Equipment: Is the equipment in this application a composite device subject to an additional equipment authorization? | No | ||||
| 1 | Related Equipment: Is the equipment in this application part of a system that operates with, or is marketed with, another device that requires an equipment authorization? | No | ||||
| 1 | Is there an equipment authorization waiver associated with this application? | No | ||||
| 1 | If there is an equipment authorization waiver associated with this application, has the associated waiver been approved and all information uploaded? | No | ||||
| app s | Test Firm Name and Contact Information | |||||
| 1 | Firm Name |
Rogers Labs, Inc.
|
||||
| 1 | Name |
S******** R****
|
||||
| 1 | Telephone Number |
913-8********
|
||||
| 1 | Fax Number |
913-8********
|
||||
| 1 |
r******@micoks.net
|
|||||
| Equipment Specifications | |||||||||||||||||||||||||||||||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
| Line | Rule Parts | Grant Notes | Lower Frequency | Upper Frequency | Power Output | Tolerance | Emission Designator | Microprocessor Number | |||||||||||||||||||||||||||||||||
| 1 | 1 | 87 | 1030.00000000 | 1030.00000000 | 374.0000000 | 1.0000000000 ppm | 18M7V1D | ||||||||||||||||||||||||||||||||||
some individual PII (Personally Identifiable Information) available on the public forms may be redacted, original source may include additional details
This product uses the FCC Data API but is not endorsed or certified by the FCC