Garmin 0104455 LICENSED NON-BROADCAST TRANSMITTER (TAS) AND TRAFFIC ALERT & COLLISION AVOIDANCE SYSTEM (TCAS) PROCESSOR MHz User Manual 190 00587 50

Garmin International Inc LICENSED NON-BROADCAST TRANSMITTER (TAS) AND TRAFFIC ALERT & COLLISION AVOIDANCE SYSTEM (TCAS) PROCESSOR MHz 190 00587 50

Users Manual

190-00587-50 January, 2012 Revision AGTS ProcessorInstallation ManualDRAFT
Page A GDR 66 Installation ManualRevision A 190-00587-50© Copyright 2012Garmin Ltd. or its subsidiariesAll Rights ReservedExcept as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.Garmin International, Inc.1200 E. 151st StreetOlathe, KS 66062 USATelephone: 913.397.8200Aviation Panel-Mount Technical Support Line (Toll Free) 1.888.606.5482www.garmin.comGarmin (Europe) Ltd.Liberty House, Bulls Copse RoadHounsdown Business ParkSouthampton, SO40 9RB U.K.+44/ (0) 870.8501241Garmin AT, Inc.2345 Turner Rd., SESalem, OR 97302 USATelephone: 503.581.8101RECORD OF REVISIONSRevision Revision Date DescriptionA 01/06/2012 Initial ReleaseDRAFT
GTS Processor Installation Manual Page i190-00587-50 Revision AINFORMATION SUBJECT TO EXPORT CONTROL LAWSThis 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) andwhich may not be exported, released, or disclosed to foreign nationals inside or outside of the United Stateswithout first obtaining an export license. The preceding statement is required to be included on any and allreproductions in whole or in part of this manual.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 DESCRIPTIONDOCUMENT PAGINATIONWARNINGRevision Page Number(s)Section Number Description of ChangeA All All Initial releaseSection Page RangeTable of Contents i – viiiSection 1 1-1 – 1-10Section 2 2-1 – 2-10Section 3 3-1 – 3-22Section 4 4-1 – 4-14Appendix A A-1 – A-4Appendix B B-1 – B-10DRAFT
Page ii GTS Processor Installation ManualRevision A 190-00587-50TABLE OF CONTENTSPARAGRAPH PAGESection 1 GENERAL DESCRIPTION .............................................................1-11.1 Introduction...................................................................................................................... 1-11.2 Equipment Description .................................................................................................... 1-11.2.1 GTS Processor Configuration Options.................................................................................1-21.3 Interface Summary...........................................................................................................1-21.4 Technical Specifications .................................................................................................. 1-21.4.1 Environmental Qualification Form.......................................................................................1-21.4.2 Physical Characteristics........................................................................................................1-31.4.3 General Specifications..........................................................................................................1-31.4.4 Power Requirements.............................................................................................................1-31.5 Certification ..................................................................................................................... 1-41.5.1 GTS Processor TSO/ETSO Compliance ..............................................................................1-41.5.2 GTS Processor TSO/ETSO Deviations ................................................................................1-51.6 Reference Documents ...................................................................................................... 1-81.7 Aviation Limited Warranty.............................................................................................. 1-9Section 2 INSTALLATION OVERVIEW........................................................2-12.1 Introduction...................................................................................................................... 2-12.1.1 Unit Configurations ..............................................................................................................2-12.1.2 Required Accessories ...........................................................................................................2-12.2 Installation Considerations .............................................................................................. 2-32.2.1 Antenna Considerations........................................................................................................2-32.3 Electrical Bonding ........................................................................................................... 2-32.4 Cabling and Wiring..........................................................................................................2-42.4.1 Coaxial Cable .......................................................................................................................2-42.5 Cooling Requirements ..................................................................................................... 2-92.6 Mounting Requirements ................................................................................................ 2-10Section 3 INSTALLATION PROCEDURE.....................................................3-13.1 Unpacking Unit................................................................................................................ 3-13.2 Wiring Harness Installation ............................................................................................. 3-13.3 Backshell and Configuration Module Assemblies........................................................... 3-33.4 GA 58 Antenna Installation ............................................................................................. 3-33.5 Sensor Systems Incorporated Low-Profile Antenna Installation..................................... 3-33.6 Unit Installation ............................................................................................................... 3-33.7 Downloading and Installing the GTS Processor Install Tool .......................................... 3-43.8 Downloading and Installing the GTS Assert Log Diagnosis Tool .................................. 3-63.9 Post Installation Configuration & Checkout.................................................................... 3-93.9.1 GTS Processor Configuration/Checkout for Different Installation Types ...........................3-93.9.2 Using the GTS Processor Install Tool ................................................................................3-103.9.3 Suppression Bus I/O Check................................................................................................3-163.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and Configuration...........3-173.9.5 Calibration/Self Test...........................................................................................................3-17DRAFT
GTS Processor Installation Manual Page iii190-00587-50 Revision APARAGRAPH PAGE3.9.6 Ramp Test and Return To Service Test..............................................................................3-203.9.7 Antenna Verification ..........................................................................................................3-223.10 Continued Airworthiness ............................................................................................. 3-23Section 4 SYSTEM INTERCONNECTS..........................................................4-14.1 GTS Processor Pin Function List..................................................................................... 4-14.1.1 P8001 (Digital) .....................................................................................................................4-14.1.2 P8002 (Analog/Discrete) ......................................................................................................4-34.1.3 P8003 (Power Supply)..........................................................................................................4-64.2 Power ............................................................................................................................... 4-74.2.1 Aircraft Power Functions......................................................................................................4-74.3 Serial Data........................................................................................................................ 4-84.3.1 RS-232..................................................................................................................................4-84.3.2 RS-422..................................................................................................................................4-84.3.3 ARINC 429...........................................................................................................................4-94.3.4 Ethernet.................................................................................................................................4-94.3.5 USB ....................................................................................................................................4-104.4 Configuration ................................................................................................................. 4-104.4.1 Configuration Module ........................................................................................................4-104.5 Analog/Discrete .............................................................................................................4-104.5.1 Heading Input .....................................................................................................................4-104.5.2 Inputs From Compass System/Directional Gyros ..............................................................4-114.5.3 Audio ..................................................................................................................................4-124.5.4 Active Low Discrete Inputs................................................................................................4-124.5.5 Active High Discrete Inputs ...............................................................................................4-134.5.6 Annunciator Output ............................................................................................................4-144.6 Mutual Suppression Bus ................................................................................................ 4-14Appendix A Outline and Installation Drawings .............................................A-1Appendix B Interconnect Examples ................................................................B-1DRAFT
Page iv GTS Processor Installation ManualRevision A 190-00587-50LIST OF FIGURESFIGURE PAGESection 1 GENERAL DESCRIPTION .............................................................1-1Section 2 INSTALLATION OVERVIEW........................................................2-1Figure 2-1 GTS Processor Installation with Top and Bottom Directional Antennas ........... 2-5Figure 2-2 GTS Processor Installation with Top Directional and Bottom Monopole Antennas.................................................................................................. 2-5Figure 2-3 GTS 855/GTS 825 Installation with Top Directional Antenna and No Bottom Antenna ...............................................................................................................2-6Figure 2-4 Heat Shrink Positioning ...................................................................................... 2-8Figure 2-5 GTS Processor Vertical Installation Rack (Garmin P/N 011-02572-00).......... 2-10Figure 2-6 GTS Processor Horizontal Installation Rack (Garmin P/N 115-00784-00) ..... 2-10Section 3 INSTALLATION PROCEDURE.....................................................3-1Figure 3-1 GTS Processor Install Tool – Installation ........................................................... 3-4Figure 3-2 GTS Processor Install Tool – Installation ........................................................... 3-5Figure 3-3 GTS Processor Install Tool – Installation ........................................................... 3-5Figure 3-4 GTS Processor Install Tool – Installation ........................................................... 3-5Figure 3-5 GTS Processor Install Tool – Installation ........................................................... 3-6Figure 3-6 GTS Processor Install Tool – Installation ........................................................... 3-6Figure 3-7 GTS Assert Log Diagnosis Tool – Installation.................................................. 3-7Figure 3-8 GTS Assert Log Diagnosis Tool – Installation ................................................... 3-7Figure 3-9 GTS Assert Log Diagnosis Tool – Installation.................................................. 3-8Figure 3-10 GTS Assert Log Diagnosis Tool – Installation................................................ 3-8Figure 3-11 GTS Assert Log Diagnosis Tool – Installation................................................ 3-8Figure 3-12 GTS Processor Install Tool – Normal Tab...................................................... 3-11Figure 3-13 GTS Processor Install Tool – Configuration Tab (GTS 825 and GTS 855)... 3-12Figure 3-14 GTS Processor Install Tool – Upload Tab ...................................................... 3-15Figure 3-15 GTS Processor Install Tool – Assert Tab........................................................ 3-16Figure 3-16 Self Test ..........................................................................................................3-19Figure 3-17 Ground Test Enable, GTS Processor Install Tool........................................... 3-20Figure 3-18 GND TEST Softkey ........................................................................................ 3-20Section 4 SYSTEM INTERCONNECTS..........................................................4-1Figure 4-1 View of J8001 connector from back of unit ....................................................... 4-1Figure 4-2 View of J8002 connector from back of unit ....................................................... 4-3Figure 4-3 View of J8003 connector from back of unit ....................................................... 4-6Appendix A Outline and Installation Drawings .............................................A-1Figure A-1 GTS Processor Vertical Outline Drawing......................................................... A-1Figure A-2 GTS Processor Vertical Installation Drawing.................................................. A-2Figure A-3 GTS Processor Horizontal Outline Drawing..................................................... A-3Figure A-4 GTS Processor Horizontal Installation Drawing............................................... A-4DRAFT
GTS Processor Installation Manual Page v190-00587-50 Revision AFIGURE PAGEAppendix B Interconnect Examples ................................................................B-1Figure B-1 GTS Processor Interconnect Example Notes .....................................................B-1Figure B-2 GTS Processor Interconnect Example................................................................B-2Figure B-3 GTS Processor Garmin Integrated Flight Deck Interconnect Example .............B-3Figure B-4 GTS Processor Field Approved (Retrofit) Garmin Integrated Flight Deck Interconnect Example ........................................................................................B-4Figure B-5 GTS Processor GNS 4XX/5XX/GMX 200 Interconnect Example....................B-5Figure B-6 GTS Processor GMA/HSI/Altimeter Interconnect Example .............................B-6Figure B-7 GTS Processor Dongle Cable (see Sections 3.7 and 3.8.6)................................B-7Figure B-8 GTS Processor Discrete Interconnect Example .................................................B-8Figure B-9 GTS Processor Configuration Module Interconnect Example...........................B-9Figure B-10 GTS Processor Dual Transponder Interconnect Example..............................B-10DRAFT
Page vi GTS Processor Installation ManualRevision A 190-00587-50LIST OF TABLESTABLE PAGESection 1 GENERAL DESCRIPTION .............................................................1-1Table 1-1 Compatible Transponders..................................................................................... 1-2Table 1-2 Configuration Options.......................................................................................... 1-2Table 1-3 Physical Characteristics........................................................................................ 1-3Table 1-4 General Specifications.......................................................................................... 1-3Table 1-5 Maximum Operation Current Draw ..................................................................... 1-3Table 1-6 Maximum Boot-Up Current Draw ....................................................................... 1-3Table 1-7 TSO/ETSO Compliance ....................................................................................... 1-4Table 1-8 TSO/ETSO Deviations ......................................................................................... 1-5Table 1-9 Reference Documents........................................................................................... 1-8Section 2 INSTALLATION OVERVIEW........................................................2-1Table 2-1 Unit Configuration ............................................................................................... 2-1Table 2-2 Required Accessories ........................................................................................... 2-1Table 2-3 Connector Kits...................................................................................................... 2-2Table 2-4 Optional Accessories............................................................................................ 2-2Table 2-5 Antennas............................................................................................................... 2-2Table 2-6 Configuration Module .......................................................................................... 2-2Table 2-7 Recommended Coaxial Length ............................................................................ 2-7Table 2-8 Coaxial Cable Set Length Tolerance.................................................................... 2-8Section 3 INSTALLATION PROCEDURE.....................................................3-1Table 3-1 Socket and Pin Contact Part Numbers ................................................................. 3-1Table 3-2 Socket Contact MIL SPEC M39029/5-115 Crimp Tooling................................. 3-1Table 3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling.... 3-2Table 3-4 Pin Socket Contacts GPN 336-00022-00 MIL SPEC M39029/63-368 and GPN 336-00023-00 Crimp Tooling....................................................................................... 3-2Table 3-5 Self Test.............................................................................................................. 3-19Section 4 SYSTEM INTERCONNECTS..........................................................4-1Table 4-1 P8001 Connector .................................................................................................. 4-1Table 4-2 P8002 Connector .................................................................................................. 4-3Table 4-3 P8002 Connector .................................................................................................. 4-6Table 4-4 Aircraft Power ...................................................................................................... 4-7Table 4-5 Remote Power ...................................................................................................... 4-7Table 4-6 Power On/Off Matrix ........................................................................................... 4-7Table 4-7 RS-232.................................................................................................................. 4-8Table 4-8 RS-422.................................................................................................................. 4-8Table 4-9 ARINC 429........................................................................................................... 4-9Table 4-10 Ethernet .............................................................................................................. 4-9Table 4-11 USB .................................................................................................................. 4-10Table 4-12 Configuration Module ...................................................................................... 4-10Table 4-13 26 Volt AC References..................................................................................... 4-10DRAFT
GTS Processor Installation Manual Page vii190-00587-50 Revision ATABLE PAGETable 4-14 Radar Altimeter ................................................................................................ 4-11Table 4-15 Inputs From Compass System/Directional Gyros ............................................ 4-11Table 4-16 Audio ................................................................................................................ 4-12Table 4-17 Active Low Discrete Inputs.............................................................................. 4-12Table 4-18 Active High Discrete Inputs ............................................................................. 4-13Table 4-19 Annunciator Output.......................................................................................... 4-14Table 4-20 Mutual Suppression Bus................................................................................... 4-14DRAFT
Page viii GTS Processor Installation ManualRevision A 190-00587-50DRAFT
GTS Processor Installation Manual Page 1-1190-00587-50 Revision A1 GENERAL DESCRIPTION1.1 IntroductionThis 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 DescriptionThe GTS Processor is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode S and Mode A/C transponders to provide Traffic Advisories and Resolution Advisories (GTS 8000 only) to the pilot. When installed in a system the GTS Processor can be configured as a TAS (GTS 825) or can be upgraded to a TCAS I (GTS 855) or TCAS II (GTS 8000) by purchasing an enablement card from Garmin. The GTS Processor meets the TSO/ETSO requirements for the configured traffic system function (TAS, TCAS I, or TCAS II). When installed with a 1090 MHz ADS-B transmit class of equipment the GTS Processor also utilizes passive surveillance. Traffic is displayed on an external MFD via ARINC 429 and/or Ethernet High Speed Data Bus (HSDB). An aural alert is also provided to inform the crew a traffic advisory (TA) or resolution advisory (RA) (GTS 8000 only) will be displayed.A top-mounted directional antenna is used to derive bearing of the intruder aircraft, which is displayed with relative altitude to own aircraft. Top antenna transmitted interrogations are directional, reducing the number of transponders that receive the interrogation, and thus reducing potential garble on the 1090 MHz band. For GTS 825 and GTS 855 installations, a bottom monopole or directional (highly recommended) antenna is optional. For GTS 8000 installations, a bottom monopole or directional (highly recommended) antenna is required. Bottom antenna transmit interrogations and broadcasts (GTS 8000 only) are omni directional, using a monopole antenna or a directional antenna. A bottom directional antenna installation gives the benefit of intruder bearing visibility for targets that are shaded from the top directional antenna. The target bearing accuracy may be degraded for bottom directional antenna installations on aircraft with fixed gear.GTS Processor installations, configured as a GTS 855 TCAS I or GTS 825 TAS, require a Garmin-approved transponder capable of receiving TCAS II broadcast data.GTS Processor installations, configured as a GTS 8000 TCAS II, require a GTX 3000 or other Garmin-approved RTCA DO-185A/B compatible transponder.The GTS Processor is not to be installed in an aircraft with a TSO-C119a-only compatible transponder.A co-installed mode S transponder should be connected to the mutual suppression bus, and meet the mutual suppression requirements of DO-181A or laterNOTENOTENOTENOTEDRAFT
Page 1-2 GTS Processor Installation ManualRevision A 190-00587-50Refer to Table 1-1 for a list of compatible transponders.1. Remote mounted transponders require a compatible controller. Contact Garmin for details.2. Factory update is required to allow ADS-B functionality.3. GTX Software version 6.11 or higher.4. GTX Software version 6.10 or higher.1.2.1 GTS Processor Configuration OptionsTable 1-2 lists the GTS Processor surveillance configuration options, enabled at the time of installation.*Requires upgrade using GTX Processor TCAS I/TCAS II Enablement Process. See Section XXX for instructions.1.3 Interface SummaryThe GTS Processor is designed as an open architecture system that uses typical ARINC 429, RS-232, and Ethernet communications interfaces.1.4 Technical Specifications1.4.1 Environmental Qualification FormIt 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 005-00630-02Table 1-1 Compatible TranspondersGTX Transponder ModelCapable of Receiving TCAS II Broadcast Data (Required for GTS Processor)ADS-B Capable RTCA DO-185A/B CompatibleGTX 330/330D Yes(3) Yes(2) NoGTX 330 ES/330D ES Yes(3) Yes NoGTX 33/33D(1) Yes(3) Yes(2) NoGTX 33 ES/33D ES(1) Yes(3) Yes NoGTX 328 Yes(4) No NoGTX 3000 Yes Yes YesTable 1-2 Configuration OptionsModel NumberGarmin Part NumberApplicable TSOTraffic Advisory System (TAS)Traffic Alert and Collision Avoidance System (TCAS I)Traffic Alert and Collision Avoidance System (TCAS II)1090 ES ADS-B ReceiverTransmit Power (Watts)GTS 825 011-02571-00 TSO-C147 X X 400GTS 855* 011-02571-00 TSO-C118 X X 400GTS 8000* 011-02571-00 TSO-C119c X X 400DRAFT
GTS Processor Installation Manual Page 1-3190-00587-50 Revision A1.4.2 Physical Characteristics1.4.3 General SpecificationsTable 1-4 contains general specifications. For detailed environmental specifications, see the Environmental Qualification Form.1.4.4 Power RequirementsTables list the power requirements for the GTS ProcessorTable 1-3 Physical CharacteristicsCharacteristics SpecificationsGTS Processor Width w/out rack 3.42 inches (86.9 mm)GTS Processor Height w/out rack 6.25 inches (158.8 mm)GTS Processor Width with vertical rack 3.67 inches (93.1 mm)GTS Processor Height with vertical rack 6.74 inches (171.1 mm)GTS Processor Depth with vertical rack 15.48 inches (396.7 mm)GTS Processor Width with horizontal rack 6.42 inches (163.1 mm)GTS Processor Height with horizontal rack 4.10 inches (104.1 mm)GTS Processor Depth with horizontal rack 14.79 inches (375.7 mm)GTS Processor Depth w/Connector Kit 14.78 inches (375.4 mm)GTS Processor Unit Weight w/out Connector Kit 11.30 lbs (5.13 kg)GTS Processor Unit Weight with Connector Kit w/Vertical Rack 12.65 lbs (5.74 kg)GTS Processor Unit Weight with Connector Kit w/Horizontal Rack 13.25 lbs (6.01 kg)Table 1-4 General SpecificationsCharacteristics SpecificationsOperating Temperature Range -55°C to +70°C. Humidity 95% non-condensingAltitude Range -1,500 ft to 55,000 ftSoftware Compliance RTCA/DO-178B level BHardware Compliance RTCA/DO-254 Level BEnvironmental Compliance RTCA/DO-160FTable 1-5 Maximum Operation Current DrawCharacteristics SpecificationsGTS Processor Power Consumption 2.5 A max operating at 28.0 Vdc5.0 A max operating at 14.0 VdcTable 1-6 Maximum Boot-Up Current DrawCharacteristics SpecificationsGTS Processor Boot-Up Current Draw 2.5 A at 28.0 Vdc for 700 ms5.0 A at 14.0 Vdc for 700 msDRAFT
Page 1-4 GTS Processor Installation ManualRevision A 190-00587-501.5 CertificationThe 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 ComplianceWhen installed as a system, the GTS Processor, which includes a GA 58 (or other Garmin approved antenna), and a CDTI (Cockpit Display of Traffic Information) comprise what Garmin considers to be a minimum generic GTS Processor system installation. The GTS Processor lacks a display and by itself is an incomplete system and cannot completely meet the requirements of TSO-C119c/ETSO-C119c, TSO-C118/ETSO-C118 or TSO-C147/ETSO-C147.*Equipment is capable of TSO-C166b/ETSO-C166a Class A1S/Type 1 Receiving Only per RTCA/DO-260B when installed with a single antenna.*Equipment is capable of TSO-C166b/ETSO-C166a Class A1/Type 1 Receiving Only when installed with diversity antennas.*The Class level is dependent upon the installation.Table 1-7 TSO/ETSO ComplianceGTS Processor ConfigurationFunction TSO/ETSO CategoryApplicable LRU SW Part NumbersApplicable CLD Part NumbersGTS 8000Traffic Alert and Collision Avoidance System (TCAS II) Airborne EquipmentTSO-C119cETSO-C119cAll006-B1244-0( )through006-B1244-2( )except006-B1244-00through006-B1244-03006-C0081-2( )GTS 855Traffic Alert and Collision Avoidance System (TCAS I) Airborne EquipmentTSO-C118ETSO-C118All006-B1224-0( ) through 006- B1224-2( ) except006- B1224-00 through 006-B1224-03006-C0081-2( )GTS 825 Traffic Advisory System (TAS) Airborne EquipmentTSO-C147ETSO-C147 Class AAll006-B1224-0( ) through 006- B1224-2( ) except006- B1224-00 through 006- B1224-03006-C0081-2( )GTS 8000, GTS 855, and GTX 825Extended 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*All006- B1224-0( ) through 006- B1224-2( ) except006-B1224-00 through006-B1224-03006-C0081-2( )DRAFT
GTS Processor Installation Manual Page 1-5190-00587-50 Revision AA 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 DeviationsNOTETable 1-8 TSO/ETSO DeviationsTSO/ETSO DeviationTSO-C1181. 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 Standard2. Garmin was granted a deviation from TSO-C118 section a.(2) to use RTCA DO-160F, instead of RTCA DO-160B as the standard for Environmental Conditions and Test Procedures for Airborne Equipment. 3. Garmin was granted a deviation from TSO-C118 section a.(3)(i) to use RTCA DO-178B instead of RTCA DO-178A. 4. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement of RTCA DO-197A section 2.2.3.2.1.5. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.5 to use the “Mode C Only All-Call” format specified by RTCA DO-185B section 2.2.3.8.1 instead of the “Mode C” format for ATCRBS interrogations.6. Garmin was granted a deviation from RTCA DO-197A section 2.2.6 to use selective Mode S interrogations following all the applicable protocols for Mode-S surveillance interrogations in the NAS as stated in DO-185B and DO-181D. 7. Garmin was granted a deviation from RTCA DO-197A section 2.2.9.1 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.8. Garmin was granted a deviation from RTCA DO-197A section 2.2.11 to use the suppression pulse on the aircraft suppression bus specified by RTCA DO-185B section 2.2.3.12 (70 +/-1 µs from top antenna and 90 +/-1 µs from bottom antenna) instead of 100 +/-5 µs.DRAFT
Page 1-6 GTS Processor Installation ManualRevision A 190-00587-50Table 1-8 TSO/ETSO Deviations, ContinuedETSO-C1181. Garmin was granted a deviation from ETSO-C118 section 3.1.1 to use RTCA DO-197A, instead of RTCA DO-197 as the Minimum Performance Standard.2. Garmin was granted a deviation from ETSO-C118 section 3.1.2 to use EUROCAE ED-14F, instead of EUROCAE ED-14D as the standard for Environmental Conditions and Test Procedures for Airborne Equipment.3. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement of RTCA DO- 197A section 2.2.3.2.1.4. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.5 to use the “Mode C Only All-Call” format specified by RTCA DO-185B section 2.2.3.8.1 instead of the “Mode C” format for ATCRBS interrogations.5. Garmin was granted a deviation from RTCA DO-197A section 2.2.9.1 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.6. Garmin was granted a deviation from RTCA DO-197A section 2.2.11 to use the suppression pulse on the aircraft suppression bus specified by RTCA DO-185B section 2.2.3.12 (70 +/-1 μs from top antenna and 90 +/-1 μs from bottom antenna) instead of 100 +/-5 μs.TSO-C119c1. 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.4.13. Garmin was granted a deviation from RTCA DO-185B section 2.2.4.4.2.2.c to use the Baseline Multi-sample bit and confidence declaration technique of RTCA DO-260B Appendix I section I.4.2.3.1.4. Garmin was granted a deviation from RTCA DO-185B section 2.2.6.7.2 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.ETSO-C119c1. 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.DRAFT
GTS Processor Installation Manual Page 1-7190-00587-50 Revision ATSO-C1471. Garmin was granted a deviation from TSO-C147 section 1.c to use RTCA DO-160F, instead ofRTCA DO-160D as the standard for Environmental Conditions and Test Procedures for Airborne Equipment.2. Garmin was granted a deviation from TSO-C147 Appendix 1 section 1.6 to use selective Mode S interrogations as specified by RTCA DO-185A section 2.2.3.9 and 2.2.4.5.4.2 following all the applicable protocols for Mode-S surveillance interrogations in the NAS as stated in RTCA DO-185B and RTCA DO-181D.3. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.2.1 to use the Interrogations Spectrum requirement of RTCA DO-185B section 2.2.3.3 instead of the requirement of RTCA DO-197A section 2.2.3.2.1.4. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.5 to use the “Mode C Only All-Call” format specified by RTCA DO-185B section 2.2.3.8.1 instead of the “Mode C” format for ATCRBS interrogations.5. Garmin was granted a deviation from RTCA DO-197A section 2.2.9.1 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.6. Garmin was granted a deviation from RTCA DO-197A section 2.2.11 to use the suppression pulse on the aircraft suppression bus specified by RTCA DO-185B section 2.2.3.12 (70 +/-1 μs from top antenna and 90 +/-1 μs from bottom antenna) instead of 100 +/-5 μs.ETSO-C1471. 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 2.2.3.2.14. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.5 to use the “Mode C Only All-Call” format specified by RTCA DO-185B section 2.2.3.8.1 instead of the “Mode C” format for ATCRBS interrogations.5. Garmin was granted a deviation from RTCA DO-197A section 2.2.9.1 to realize the bearing estimation function using a direction finding antenna augmented by tracked correlated ADS-B data when such data is available and of sufficient integrity.6. Garmin was granted a deviation from RTCA DO-197A section 2.2.11 to use the suppression pulse on the aircraft suppression bus specified by RTCA DO-185B section 2.2.3.12 (70 +/-1 μs from top antenna and 90 +/-1 μs from bottom antenna) instead of 100 +/-5 μs.ETSO-C166a1. Garmin was granted a deviation from ETSO-C166a, section 4.2 to allow not marking the unit with the class information, which is instead provided in the installation and operation manual.2. Garmin was granted a deviation from ETSO-C166a to use RTCA DO-260B instead of RTCA DO-260A as the Minimum Performance Standard. 3. Garmin was granted a deviation from ETSO-C166a to use RTCA DO-160F instead of RTCA DO-160E as the Environmental Standard. 4. Garmin was granted a deviation from RTCA DO-260B section 2.2.4.3.4.7.3.b to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260B section 2.2.4.4.3.1 instead of 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185B. 5. Garmin was granted a deviation from RTCA DO-260B section 2.2.4.5.b to use the Conservative and Brute Force error correction techniques specified by RTCA DO-260B section 2.2.4.4.3.1 instead of section 2.2.4.4.2.2.d and Appendix A, Section 3 of RTCA DO-185B.Table 1-8 TSO/ETSO Deviations, ContinuedDRAFT
Page 1-8 GTS Processor Installation ManualRevision A 190-00587-501.6 Reference DocumentsThe following publications are sources of additional information for installing the GTS Processor. Before installing the GTS Processor, the installer should read all referenced materials along with the manual.Table 1-9 Reference DocumentsPart Number Document190-00313-11 Jackscrew Backshell Installation Instructions190-00303-00 G1000 System Installation Manual190-00587-51 GTS Processor System Maintenance Manual190-00903-00 G1000 System Maintenace Manual LJ/VLJ190-00907-00 G1000 System Maintenance Manual Standard Piston/Turboprop AircraftDRAFT
GTS Processor Installation Manual Page 1-9190-00587-50 Revision A1.7 Aviation Limited WarrantyAll Garmin avionics products are warranted to be free from defects in materials or workmanship for: one years from the date of purchase for new Remote-Mount and Panel-Mount products; one year from the date of purchase for new portable products and any purchased newly-overhauled products; six months for newly-overhauled products exchanged through a Garmin Authorized Service Center; and 90 days for factory repaired or newly-overhauled products exchanged at Garmin in lieu of repair. Within the applicable period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts or labor, provided that the customer shall be responsible for any transportation cost. This warranty does not apply to: (i) cosmetic damage, such as scratches, nicks and dents; (ii) consumable parts, such as batteries, unless product damage has occurred due to a defect in materials or workmanship; (iii) damage caused by accident, abuse, misuse, water, flood, fire, or other acts of nature or external causes; (iv) damage caused by service performed by anyone who is not an authorized service provider of Garmin; or (v) damage to a product that has been modified or altered without the written permission of Garmin. In addition, Garmin reserves the right to refuse warranty claims against products or services that are obtained and/or used in contravention of the laws of any country.THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES, WHETHER EXPRESS, IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE.IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE OR INABILITY TO USE THE PRODUCT OR FROM DEFECTS IN THE PRODUCT. SOME STATES DO NOT ALLOW THE EXCLUSION OF INCIDENTAL OR CONSEQUENTIAL DAMAGES, SO THE ABOVE LIMITATIONS MAY NOT APPLY TO YOU.Garmin retains the exclusive right to repair or replace (with a new or newly-overhauled replacement product) the product or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY.Online Auction Purchases: Products purchased through online auctions are not eligible for warranty coverage. Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an original or copy of the sales receipt from the original retailer is required. Garmin will not replace missing components from any package purchased through an online auction.International Purchases: A separate warranty may be provided by international distributors for devices purchased outside the United States depending on the country. If applicable, this warranty is provided by the local in-country distributor and this distributor provides local service for your device. Distributor warranties are only valid in the area of intended distribution. Devices purchased in the United States or Canada must be returned to the Garmin service center in the United Kingdom, the United States, Canada, or Taiwan for service. Garmin International, Inc. Garmin (Europe) Ltd.1200 East 151st Street Liberty House, Bulls Copse RoadOlathe, Kansas 66062, U.S.A. Hounsdown Business Park Phone:913/397.8200 Romsey, SO40 9RB, U.K.FAX:913/397.0836 Phone:44/ (0) 870.8501241 FAX:44/ (0) 870.850125DRAFT
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GTS Processor Installation Manual Page 2-1190-00587-50 Revision A2 INSTALLATION OVERVIEW2.1 IntroductionThis 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 ConfigurationsThe GTS Processor is available under the following part numbers: 2.1.2 Required AccessoriesRefer to the Dealer’s Only portion of www.garmin.com for instructions on determining what accessories are needed.Each of the following accessories are provided separately from the GTS Processor and is required to install the unit. Only one is required.*Approved for use in RTCA DO-160F, Section 8, Category S, Curve C, Y, and L installations, as well as RTCA DO-160F, Section 8, Category U, Curve G installations.For a GTS Processor installation with a single GA 58 directional antenna (GTS 855/GTS 825 only), 8 TNC connectors (not supplied), either straight or right angle, are required.For a GTS Processor installation with dual GA 58 directional antennas (GTS 8000/GTS 855/GTS 825), 16 TNC connectors (not supplied), either straight or right angle, are required.For a GTS Processor installation with a single GA 58 directional antenna and a monopole antenna (GTS 8000/GTS 855/GTS 825), 9 TNC connectors and 1 BNC connector (not supplied), either straight or right angle, are required.TNC 50 Ohm terminations (not supplied) are required for all unused antenna ports.Table 2-1 Unit ConfigurationItemApplicable LRU Software Part NumbersApplicable Custom Logic DevicePart NumbersGarmin P/NGTS Processor, (011-02571-00)All006-B1244-0( ) through 006-B1244-2( ) except006-B1244-00 through 006-B1244-03006-C0081-2( ) 010-00962-00NOTETable 2-2 Required AccessoriesInstallation Racks Garmin P/NGTS Processor Vertical Installation Rack 011-02572-00*GTS Processor Horizontal Installation Rack 115-00784-00*DRAFT
Page 2-2 GTS Processor Installation ManualRevision A 190-00587-50The GTS Processor is to be installed with a four-beam directional interrogation antenna mounted to the top of the aircraft as described in the antenna installation manual.*010-10720-00 and 010-10720-02 include mounting screws and o-ring, unless specifically requested to exclude.**Or Sensor Systems Incorporated part number S72-1735-24 (long TNC connectors) or S72-1735-26 (short TNC connectors) that meet the requirements of Garmin part number 013-00276-0X or 013-00276-5X, respectively. Refer to the manufacturer’s installation manual for installation instructions..*Required for GTS Processor installations that do not have other means (such as a GDU XXXX Configuration Module) to store GTS Processor configuration data. Contact Garmin for additional guidance in determining applicability.Table 2-3 Connector KitsConnector Kits Garmin P/NGTS Processor Connector Kit 011-01360-00GTS Connector Kit w/Config Module and USB Pigtail 011-01360-01USB-B Pigtail (see GTS Configuration Options) 011-01782-00Table 2-4 Optional AccessoriesOptional Accessories Garmin P/NColor Coded Heat Shrink Kit 011-02817-00NOTETable 2-5 AntennasAntennas Garmin P/NGA 58 Directional Antenna, QMA (011-01346-00) NOTE: Refer to 190-00587-00 GTS 8XX Installation Manual for installation instructions010-10720-00*GA 58 Directional Antenna, TNC, (011-01346-02) NOTE: Refer to 190-000587-20 GA 58 Installation Manual for installation instructions.010-10720-02*Low Profile Directional Antenna 013-00276-XX**Monopole Antenna 010-10160-00 or L-Band Monopole Antenna that meets TSO-C74cTable 2-6 Configuration ModuleConfiguration Module Garmin P/NConfiguration Module* 011-00979-20DRAFT
GTS Processor Installation Manual Page 2-3190-00587-50 Revision A2.2 Installation ConsiderationsFabrication 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 ConsiderationsRefer to GA 58 Installation Manual 190-00587-20 for antenna installation information.For GTS 855/GTS 825 installations, either a monopole antenna or directional antenna may be used if installing an optional bottom mounted antenna. For GTS 8000 installations, a bottom monopole or directional antenna is required. A bottom directional antenna installation (recommended) gives the benefit of intruder bearing visibility for targets that are shaded from the top directional antenna. The target bearing accuracy may be degraded for bottom directional antenna installations on aircraft with fixed gear.2.2.1.1 TAS/TCAS Antenna LocationRefer to GA 58 Installation Manual 190-00587-20 for antenna installation information2.3 Electrical BondingElectrical equipment, supporting brackets, and racks should be electrically bonded to the aircraft’s main structure. Refer to SAE ARP 1870 section 5 when surface preparation is required to achieve electrical bond. The electrical bond should achieve direct current (DC) resistance less than or equal to 2.5 milliohms to local structure to where the equipment is mounted. Compliance should be verified by inspection using a calibrated milliohm meter. An equivalent OEM procedure may also be substituted. There may be OEM-specific reasons for electrically isolating equipment or having a higher bond resistance. These reasons should be rationalized upon installation approval. In general, Garmin recommends that all GTS Processor equipment be electrically bonded.Refer to GA 58 Installation Manual 190-00587-20 for antenna installation information.For composite aircraft, the antenna baseplate must be electrically bonded to the common ground of other installed equipment for lightning purposes. This can be achieved through the antenna mounting screws.NOTEDRAFT
Page 2-4 GTS Processor Installation ManualRevision A 190-00587-502.4 Cabling and WiringThe contacts used to facilitate the use of #18 AWG wire, if used for Aircraft Power and Aircraft Ground, have expanded-diameter barrels that extend out from the back of the standard D-sub connector body to accommodate the larger diameter wire. Appropriate heat shrink tubing should be utilized to provide sufficient insulation from surrounding contacts. When removing an expanded-diameter barrel contact, always cut off the expanded-diameter barrel before using an extraction tool to remove the contact.Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference. Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and routing near aircraft control cables.All appliance to antenna coaxial cabling shall bundle top four channels as a group and bottom four channels as a group to prevent incorrect wiring between top and bottom channels.A visual inspection shall be performed to verify that all coaxial cables are connected properly, before attempting to operate the equipment.2.4.1 Coaxial CableThe GTS Processor requires two sets of coaxial cable assemblies when a directional GA 58 antenna (or other Garmin approved antenna) is used for both top and bottom. Each set consists of four coaxial cable assemblies. Each set of four cables must be assembled using the same type of coaxial cable in order to meet phase and attenuation matching requirements. In order for the system to operate in compliance with manufacturer specifications, the coaxial cable assemblies must not exceed the attenuation specifications as stated in this document. This section explains in further detail the coaxial cable and termination requirements.TNC connectors and BNC connectors, required for building the coaxial cable assemblies for some antenna options, are not provided.2.4.1.1 GTS Processor InstallationsFor 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 NOTENOTENOTENOTEDRAFT
GTS Processor Installation Manual Page 2-5190-00587-50 Revision Aattenuation 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 AntennasIf a bottom mount monopole antenna is installed, a single coaxial cable must be used to connect the GTS Processor bottom jack J1 BTM to the monopole antenna jack. The coaxial cable assembly shall not exceed the maximum attenuation of 3.0dB at 1090MHz for a GA 58 directional antenna and 2.5 dB for a low profile directional antenna as shown in Figure 2-2 and stated in Table 2-2. Each of the remaining GTS Processor bottom jacks (J2 BTM, J3 BTM, J4 BTM) are to be terminated using a 50Ω TNC termination. Figure 2-2 GTS Processor Installation with Top Directional and Bottom Monopole AntennasDRAFT
Page 2-6 GTS Processor Installation ManualRevision A 190-00587-50If no bottom mount antenna is installed, each of the GTS 855/GTS 825 bottom jacks (J1 BTM, J2 BTM, J3 BTM and J4 BTM) must be terminated with a 50Ω TNC termination shown in Figure 2-3.Figure 2-3 GTS 855/GTS 825 Installation with Top Directional Antenna and No Bottom Antenna2.4.1.2 Fabrication of Coaxial Cable AssembliesTNC connectors, required to build coaxial cable assemblies, are not provided.Table 2-1 lists the recommended coaxial cable venders and the type of cable to be used for specific lengths of coaxial cable. The maximum coaxial cable lengths are calculated from the maximum signal attenuation at 1090 MHz for each coaxial cable type and an assumed loss figure of 0.035 dB per connector. The maximum coaxial cable lengths in Table 2-1 are for reference only, and are defined as the end to end length of a non-terminated coaxial cable. Actual cable lengths may vary depending on manufacturer specifications for the maximum cable attenuation and the RF coaxial connector loss. It is the installing agency’s responsibility to ensure that the coaxial cable assemblies meet the manufacturer’s attenuation specifications as shown in Section 2-4 in order to comply with the system installation standards.Any in-line or bulkhead penetrations must be evaluated separately. It is the installing agency’s responsibility to show airworthiness of the installed fabricated or purchased coaxial cable assemblies.NOTENOTEDRAFT
GTS Processor Installation Manual Page 2-7190-00587-50 Revision A*The “Max Terminated Cable Attenuation” values listed include the maximum attenuation of both the maximum length of coaxial cable and two RF coaxial connectors at a frequency of 1090 MHz.**Actual cable lengths may vary depending on manufacturer’s cable attenuation and connector specifications.Table 2-7 Recommended Coaxial LengthMax Terminated Cable Attenuation(including connector loss)*Max Cable Attenuation(dB/100ft)ECS Type [1]PIC Type [2]MIL-C-17 Type [3]RG Type [4]Loss of 0.5 dBLoss of 1.5 dBLoss of 2.0 dBLoss of 2.5 dBLoss of 3.0 dBMax Coaxial Cable Lengths**2' 2"[0.66m]7' 8"[2.34m]10' 7"[3.23m]13' 6"[4.11m]16' 5"[5.00m] 17.2 M17/128-RG400 RG-4002' 3"[0.69m]8' 0"[2.44m]11' 0"[3.35m]14' 0"[4.27m]17' 0"[5.18m] 16.7 S832042' 5"[0.74m]8' 6"[2.59m]11' 9"[3.58m]15' 0"[4.57m]18' 3"[5.56m] 15.5 M17/60-RG142 RG-1423' 0"[0.91m]10' 7"[3.23m]14' 7"[4.45m]18' 7"[5.66m]22' 7"[6.88m] 12.5 3119013' 2"[0.97m]10' 11"[3.33m]15' 0"[4.57m]19' 2"[5.84m]23' 3"[7.09m] 12.2 S441913' 3"[0.99m]11' 4"[3.45m]15' 6"[4.72m]19' 9"[6.02m]24' 0"[7.32m] 11.8 S441934' 3"[1.30m]15' 0"[4.57m]20' 6"[6.25m]26' 2"[7.98m]31' 9"[9.68m] 8.9 3116015' 0"[1.52m]17' 9"[5.41m]24' 5"[7.44m]31' 0"[9.45m]37' 10"[11.53m] 7.5 S671635' 1"[1.55m]18' 0"[5.49m]24' 8"[7.52m]31' 6"[9.60m]38' 3"[11.66m] 7.4 311501[1] Vendor: Electronic Cable Specialists 5300 W Franklin Drive, Franklin, WI 53132 Telephone: 800.327.9473 or 414.421.5300 Fax: 414.421.5301 Website: www.ecsdirect.com[2] Vendor: PIC Wire and Cable N53 W24747 S Corporate Circle, Sussex, WI 53089-0330 Telephone 800.742.3191 or 262.246.0500 Fax: 262.246.0450 Website: www.picwire.com[3] See current issue of Qualified Products List, QPL-17.[4] RG types are obsolete and are shown for reference only; replaced by M17 type numbers.DRAFT
Page 2-8 GTS Processor Installation ManualRevision A 190-00587-50Coaxial cable "sets" are required for GTS Processor installations. Each coaxial cable "set", which consist of 4 coaxial cable assemblies, must be length matched to the tolerances shown in Table 2-2.*Ensure cables do not exceed the maximum lengths as stated in Table 2-1 unless supported by manufacturers data for specific cables used.It is recommended that a two inch piece of adhesive heat shrink tubing be installed over all connector/cable interfaces. The heat shrink tubing should overlap the connector body as much as practical without interfering with the coupling nut.It is recommended that a color band be placed on both ends of each cable to match the color marking designating the mating jack connector. It is recommended that the nominal end to end coaxial cable (non-terminated) length for each set be recorded for the specific installation in the event that a particular coaxial cable assembly associated with an installed set should require replacement.Figure 2-4 Heat Shrink Positioning2.4.1.3 Coaxial Cable Assembly Repair and ReworkIn the event that an individual coaxial cable assembly requires rework, the following rules apply:Top or bottom GTS Processor to GA 58 (or other Garmin approved antenna) cables may be repaired with a reduction in length of 2” maximum.Refer to Table 2-1 for recommended maximum cable assembly lengths for cable assemblies fabricated by the installer.Table 2-8 Coaxial Cable Set Length ToleranceCoaxial Cable Set(consisting of four coaxial cable assemblies) Length Tolerance*GTS Processor TOP to top directional antenna 2" of each otherGTS Processor BOTTOM to bottom directional antenna 2" of each otherNOTENOTENOTEConnectorBody Ferrule Coaxial CableHeat shrink not to protrude past this surface.DRAFT
GTS Processor Installation Manual Page 2-9190-00587-50 Revision A2.5 Cooling RequirementsThe 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.DRAFT
Page 2-10 GTS Processor Installation ManualRevision A 190-00587-502.6 Mounting RequirementsThe 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)DRAFT
GTS Processor Installation Manual Page 3-1190-00587-50 Revision A3 INSTALLATION PROCEDURE3.1 Unpacking UnitCarefully 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 InstallationAllow adequate space for installation of cables and connectors. The installer shall supply and fabricate all of the cables. All electrical connections are made through two 78-pin high-density D subminiature connectors, and one 37-pin standard density connector. Section 4 defines the electrical characteristics of all input and output signals. Required connectors and associated hardware are supplied with the connector kit.See Appendix B for examples of interconnect wiring diagrams. Construct the actual harness in accordance with aircraft manufacturer authorized interconnect standards.*Indicates plastic insertion/extraction toolTable 3-1 Socket and Pin Contact Part NumbersManufacturer78 Pin High Density D-Subminiature Connectors P8001 & P800237 Pin Standard Density D-Subminiature Connector P800319 Pin Circular Connector P651High Density Pin (P8001 & P8002)Standard Socket(P8003)18 AWG Socket(P8003)Garmin P/N 336-00021-00 336-00022-00 336-00023-00Military P/N M39029/58-360 M39029/63-368 N/ATable 3-2 Socket Contact MIL SPEC M39029/5-115 Crimp ToolingManufacturer Hand Crimping Tool Positioner Insertion/Extraction ToolTools Option 1Military P/N M22520/1-01 M22520/1-02 M81969/14-11*Daniels AF8 TH1A M81969/14-11*Tools Option 2Military P/N M22520/2-01 M22520/2-02 M81969/14-11*Daniels AFM8 K1S M81969/14-11*DRAFT
Page 3-2 GTS Processor Installation ManualRevision A 190-00587-50Note 1 - Indicates plastic insertion/extraction toolNote 2 – Order by military part numberNote 1 - Indicates plastic insertion/extraction toolNote 2 – Order by military part number1. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.2. Extracting a contact used for #18 AWG requires that the wire barrel be cut off from the contact. It may also be necessary to push the pin out from the face of the connector when using and extractor due to the absence of the wire. A new contact must be used when reassembling the connector. Table 3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp ToolingManufacturer Hand Crimping Tool Positioner Insertion/ExtractionToolMilitary P/N M22520/2-01 M22520/2-09 M81969/1-04Daniels AFM8 K42 (Note 2)Positronic 9507-0 9502-4 (Note 2)ITT Cannon 995-0001-584 (Note 2) 274-7048-000 (Note 1)Tyco-AMP 601966-1 601966-6 91067-1Astro 615717 615725 (Note 2)Amphenol (Note 2) (Note 2) (Note 2)Table 3-4 Pin Socket Contacts GPN 336-00022-00 MIL SPEC M39029/63-368 and GPN 336-00023-00 Crimp ToolingManufacturerHand CrimpingTool22 AWG Socket Contact GPN 336-00022-00 (M39029/63-368)18 AWG Socket Contact GPN 336-00023-00Positioner Insertion/Extraction Tool Positioner Insertion/Extraction ToolMilitary P/N M22520/2-01 M22520/2-08 M81969/1-02 N/A M81969/1-02Daniels AFM8 K13-1 (Note 2) K774 (Note 2)Positronic 9507-0 9502-5 (Note 2) 9502-11 (Note 2)ITT Cannon 995-0001-584 995-0001-604 980-2000-426 (Note 1) N/A N/ATyco-AMP 601966-1 601966-5 91067-2 N/A N/AASTRO 615717 615724 (Note 2) NA N/AAmphenol (Note 2) (Note 2) (Note 2) N/A N/ANOTEDRAFT
GTS Processor Installation Manual Page 3-3190-00587-50 Revision A3.3 Backshell and Configuration Module AssembliesThe GTS Processor connector kits includes three Garmin backshell assemblies. The backshell assembly houses the configuration module, if applicable. Garmin’s backshell also gives the installer the ability to easily terminate shield grounds at the backshell housing.Refer to the Jackscrew Backshell Installation Instructions (Garmin part number 190-00313-11) for backshell assembly instructions.Refer to the Jackscrew Configuration Module Installation Instructions (Garmin part number 190-00313-10) for configuration module assembly instructions.3.4 GA 58 Antenna InstallationRefer 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 InstallationRefer 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 InstallationRefer 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.NOTEDRAFT
Page 3-4 GTS Processor Installation ManualRevision A 190-00587-503.7 Downloading and Installing the GTS Processor Install ToolGTS Processor Configuration, Ramp Test, and Return to Service tests are performed (on some installations) using a computer (installed with Microsoft Windows XP or later) and the GTS Processor Install Tool, Garmin part number 006-A0242-10. The GTS Processor Install Tool allows for configuration, diagnostics, and upload of GTS Processor software. The tool is available for download from the Dealer Resource Center portion of the Garmin website (www.garmin.com). See the “readme” file (included in some versions) in the tool download for the latest GTS Processor Install Tool notes.A USB-A plug to USB-B plug cable (not provided) is required to interface between a computer USB-A receptacle and the GTS Processor USB-B receptacle installed in the wiring harness. This Dongle Cable is required to use the GTS Processor Install Tool, refer to Appendix B for interconnect drawing.1. Go to the Dealer Resource section of www.garmin.com and save the “GTS Processor Install Tool.zip” file from the website to the PC.2. Apply power to the GTS Processor and connect the unit to a USB port on the PC.3. If a pop-up window titled “Found New Hardware Wizard” appears on the PC, select ‘Cancel’ to exit the wizard.Figure 3-1 GTS Processor Install Tool – Installation4. On the PC, locate the files “GTS Processor Install Tool.zip.” Extract the files from the zip file.For computers with 32-bit Windows versions select the “Install Tool Installer 32-bit.msi” file.For computers with 64-bit Windows versions select the “Install Tool Installer 64-bit.msi” file.The installation will be canceled if the installation file and the operating system do not match. On the PC, right click on ‘My Computer’ and select ‘Properties’ to determine if the PC is operating on a 32-bit or a 64-bit version of Windows.NOTENOTEDRAFT
GTS Processor Installation Manual Page 3-5190-00587-50 Revision A5. 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 – Installation6. Select ‘Next’, when prompted or ‘Browse’, to select another folder.Figure 3-3 GTS Processor Install Tool – Installation7. Select ‘Next’, when prompted, to start the installation.Figure 3-4 GTS Processor Install Tool – InstallationDRAFT
Page 3-6 GTS Processor Installation ManualRevision A 190-00587-508. Wait until the installation has completed.Figure 3-5 GTS Processor Install Tool – Installation9. When the installation has completed, the following screen will be displayed. Select ‘Close.’Figure 3-6 GTS Processor Install Tool – Installation3.8 Downloading and Installing the GTS Assert Log Diagnosis ToolThe GTS Assert Log Diagnosis Tool (006-A0244-00) is used with the GTS 8XX Assert Log to assist in the diagnosis and resolution of asserts seen during the installation process and during post-installation flight operation. This tool allows for viewing/storing of the GTS Assert Log using a computer (installed with Microsoft Windows XP or later) and is available for download from the Dealers Resource Center portion of the Garmin website (www.garmin.com). See the “readme” file in the tool download for the latest installation/operation notes. A USB-A plug to USB-B plug cable (not provided) is required to interface between a computer USB-A receptacle and the GTS Processor USB-B receptacle installed in the wiring harness. This Dongle Cable is required to use the GTS Processor Install Tool, refer to Appendix B for interconnect drawing.NOTEDRAFT
GTS Processor Installation Manual Page 3-7190-00587-50 Revision A1. 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 – Installation5. Select ‘Next’, when prompted or ‘Browse’, to select another folder. If desired, click on the Disk Cost button to view available storage drives and required disk space. Also a selection can be made to control the tool’s availability to users of the PC.Figure 3-8 GTS Assert Log Diagnosis Tool – InstallationDRAFT
Page 3-8 GTS Processor Installation ManualRevision A 190-00587-506. Select ‘Next’, when prompted to begin the installation.Figure 3-9 GTS Assert Log Diagnosis Tool – Installation7. The installation progress is displayed.Figure 3-10 GTS Assert Log Diagnosis Tool – Installation8. Verify that installation is successful, then select ‘Close’, to complete the installation.Figure 3-11 GTS Assert Log Diagnosis Tool – InstallationDRAFT
GTS Processor Installation Manual Page 3-9190-00587-50 Revision A3.9 Post Installation Configuration & Checkout The following actions must be performed after initial installation and after the equipment has been removed/disconnected then reinstalled/reconnected :1. GTS Processor Configuration (Section 3.8.2)2. Suppression Bus I/O Check (Section 3.8.3)3. CDTI (Cockpit Display of Traffic Information) Display 4. Setup and Configuration (Section 3.8.4)5. Calibration/Self Test (Section 3.8.5)6. Ramp Test and Return To Service Tests (Section 3.8.6)7. Antenna Verification (Section 3.8.7)Before beginning the installation calibration, the installer must perform a visual inspection to verify the coaxial cables are installed correctly based upon the system and antenna configuration.Tests performed with a ramp tester should be performed away from buildings that may reflect the signal. Local air traffic control should be advised if the ramp tester has an altitude programmed into it that may cause interaction with other TCAS-equipped traffic.3.9.1 GTS Processor Configuration/Checkout for Different Installation TypesConfiguration 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 InstallationWhen 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 InstallationFor 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 DeckGarmin 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. NOTEDRAFT
Page 3-10 GTS Processor Installation ManualRevision A 190-00587-50Please check the aircraft warranty status before installation and/or with the aircraft manufacturer for guidance.ADS-B receive functionality is not available in a Field Approved Garmin Integrated Flight Deck installation.3.9.1.4 Retrofitting a non-Garmin Integrated Flight Deck Installation such as a GNS 4XX/5XX(W) or GTC 650/750 unit with a GTS ProcessorConfiguration, software uploading, and Ramp Test and Return to Service Tests are accomplished using the GTS Processor Install Tool (Section 3.8.2).Installations that are unable to electronically display the software part number of the GTS Processor should affix a label on the GTS Processor LRU marked with the software part number to meet the TSO marking requirements. For the installer’s convenience, a label has been applied adjacent to the LRU serial number tag.3.9.1.5 Non-Garmin Installations with a GTS ProcessorConfiguration, software uploading, and Ramp Test and Return to Service Tests are accomplished using the GTS Processor Install Tool (Section 3.8.2).Installations that are unable to electronically display the software part number of the GTS Processor should affix a label on the GTS Processor LRU marked with the software part number to meet the TSO marking requirements. For the installer’s convenience, a label has been applied adjacent to the LRU serial number tag.3.9.2 Using the GTS Processor Install Tool The following tabs are accessible with the GTS Processor Install Tool. Changing tabs may cause the GTS Processor unit to restart.· Normal Tab – Reports System Faults, Status Flags, and Operating Status. Allows GroundTest 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 Supportfor troubleshooting.NOTENOTENOTENOTEDRAFT
GTS Processor Installation Manual Page 3-11190-00587-50 Revision ANormal System Mode TabThe 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 TabNormal 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:EnabledDisabled(Ground Test is described in the Ramp Test and Return to Service Tests Section 3.8.6).DRAFT
Page 3-12 GTS Processor Installation ManualRevision A 190-00587-50Configuration System Mode TabThe 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.DRAFT
GTS Processor Installation Manual Page 3-13190-00587-50 Revision AConfiguration Mode – Barometric Altitude Source:Note: At least one source must be selected (same altitude source used for the transponder).Primary A429 RX Channels 1 - 6 or DisabledSecondary A429 RX Channels 1 - 6 or DisabledCOM RS-232 Ports 1 - 5 or DisabledMagnetic Heading Source (optional): Primary A429 RX Channels 1 - 6 or DisabledSecondary A429 RX Channels 1 - 6 or DisabledRadio Altitude Source (optional): A429 A429 RX Channels 1 - 6 or DisabledAnalog DisabledARINC 552 ARINC 552A Bonzer MK10XCollins ALT50Collins ALT55King KRA10 King KRA10AKing KRA405 Sperry AA100Terra TRA3000/3500GPS Position/Velocity/Time Source:Note: At least one source required for ADS-B IN functionality. PrimaryA429 RX Channels 1 - 6 or DisabledSecondaryA429 RX Channels 1 - 6 or DisabledTraffic Display Destination: Note: At least one source is required.Primary A429 TX Channels 1 - 6 or DisabledCOM RS-232 Ports 1 - 5 or DisabledTransponder 1 & 2 Communication: Note: At least Transponder 1 RX and TX required for GTS 820 and GTS 850. Primary should be configured for channels wired to Transponder 1. Secondary should be configured for channels wired to Transponder 2 in a dual transponder installation. Primary RX A429 RX Channels 1 - 6 or DisabledPrimary TX A429 TX Channels 1 - 6 or DisabledSecondary RX A429 RX Channels 1 - 6 or DisabledSecondary TX A429 TX Channels 1 - 6 or DisabledTop Antenna: Model Garmin GA58Sensor SystemsCable loss (dB) 0.2 – 4.0Note: Cable loss information is described in Fabrication of Coaxial Cable Assemblies Section 2.4.1.2.DRAFT
Page 3-14 GTS Processor Installation ManualRevision A 190-00587-50Bottom Antenna: Model None MonopoleGarmin GA58Sensor SystemsCable loss (dB) 0.2 – 4.0Note: Cable loss information is described in Fabrication of Coaxial Cable Assemblies Section 2.4.1.2.Note: All A429 options have the ability to select High or Low speed.Note: If an input is inactive, a will be displayed.If an input is active, a will be displayed.If an input is in an unknown state, a will be displayed.Volume Level:Allows audio volume level selection from 0 to -63 dB in 0.5 dB increments.Maximum audio output is at least 80 mW into a 600 Ohm load. (6.93 Vrms) Voice Gender:Enter voice preference selection.Gear/Wheel:Enter type of aircraft gear design.Discrete ‘gear-down’ Sense:Indicate the type of gear down sense switch for the Gear Down and Locked* discrete input. See Appendix B (Note 7) and Figure B-9 for Gear Down and Locked* discrete input. Note: Discrete ‘gear-down’ sense is only enabled when ‘Retractable’ Gear/Wheel design is configured.ADSB TX Capable:Indicate whether aircraft is equipped with ADS-B transmitter.Squat ‘on-ground’ Sense:Indicate type of sense switch.Note: For helicopter installations without a squat switch, the traffic system status valid discrete output can be wired to the air/ground discrete input to prevent the GTS from going to standby mode during extended hover. For such installations, configure squat ‘on-ground’ sense to ‘open’.Mode S ID (HEX): Enter Mode S transponder ID (must match the Mode S ID used by the transponder).Set Active:Must select Set Active to enable the settings on the GTS Processor.Revert Changes:Select to show current GTS Processor settings. An incorrect configuration will be reverted back to previous settings.Note: Default is “disabled” for all inputs and outputs.DRAFT
GTS Processor Installation Manual Page 3-15190-00587-50 Revision AUpload System Mode TabThe 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 TabDRAFT
Page 3-16 GTS Processor Installation ManualRevision A 190-00587-50Assert TabThe 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 Tab3.9.3 Suppression Bus I/O CheckOther 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.DRAFT
GTS Processor Installation Manual Page 3-17190-00587-50 Revision A3.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and ConfigurationFor configuration of the displays, refer to their respective manuals.· 500 Series Installation Manual (190-00181-02)· GMX 200 Installation Manual· (190-00607-04)· GDU 620 Installation Manual· (190-00601-04)· GTS Processor System Maintenance Manual (190-00587-51)· G1000 System Maintenance Manual LJ/VLJ (190-00903-00)3.9.5 Calibration/Self TestA self-test feature tests the (aural) alarm, attempts self calibration, and activates each display element in a pre-determined sequential pattern to allow visual verification that display outputs issued by the digital processor can be correctly interpreted by the pilot.Self tests may be performed indoors but signal multi-path from building walls may be a factor. If problems are experienced, self tests should be performed outside away from buildings, and where local traffic is not a factor.With the GTS Processor powered up and Standby indicated on the CDTI, cycle the GTS Processor to Self Test. The self test feature of the GTS Processor tests the following internal parameters as well as performs calibration of various components in the GTS Processor:For helicopter installations without a squat switch, and wired as described in Note 6 of Appendix B, select standby mode on the CDTI and initiate the self test within 8 seconds before the unit changes back to operate mode.a) Calibration Data fault – Stored factory calibration parameters are invalid. Return unit to Garmin for service.b) Configuration Data fault – Stored system configuration parameters are invalid or Mode S address is invalid (All 0’s or F’s ). Fault will persist until configuration is corrected. Attempt configuration per the Configuration Section 3.8.2. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2.c) FPGA fault – Check of the FPGA image failed. Fault will persist until valid FPGA image is loaded. If upload of FPGA image was recently attempted, retry the upload. Otherwise, return unit to Garmin for service. d) ROM fault – Internal non-volatile memory failure, or invalid data image detected. If upload of audio image or IGRF magnetic field image was recently attempted, retry the upload. Otherwise return unit to Garmin for service.e) Execution fault – CPU execution fault has occurred. Cycle power and retry self test. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If fault persists, return unit to Garmin for service.f) Electrical fault – One of the internal electrical voltages are out of range. Fault will persist until power is cycled. Check aircraft power supply. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If fault persists, return unit to Garmin for service.NOTENOTEDRAFT
Page 3-18 GTS Processor Installation ManualRevision A 190-00587-50g) Whisper Shout fault – Transmitted power is out of tolerance. Check cable loss configuration, antenna installation and all cable connections and retry self test. If fault persists, return unit to Garmin for service.h) Transmit Power fault - One of the internal transmitter power source voltages are out of range. Fault will persist until power is cycled. Check aircraft power supply. If fault persists, return unit to Garmin for service.i) 1030 MHz fault - Transmit Frequency synthesizer is not locked. Cycle power and retry self test. If fault persists, return unit to Garmin for service.j) 1090 MHz fault - Receive Frequency synthesizer is not locked. Cycle power and retry self test. If fault persists, return unit to Garmin for service.k) Receiver Cal fault. Check antenna installation and all cable connections and retry self test. Ensure that self test occurs in area free of buildings and large objects that can reflect signals. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If fault persists, return unit to Garmin for service.Receiver self-calibration is performed prior to the transmitter self-calibration. In the event that a receiver calibration fault occurs, a transmitter self-calibration will not be performed. l) Transmitter Cal fault. Check antenna installation and all cable connections and retry self test. Ensure that self test occurs in area free of buildings and large objects that can reflect signals. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2. If fault persists, return unit to Garmin for service.A transmitter self-calibration can only be performed after a successful receiver self-calibration.m) Baro Altitude fault – Own ship barometric altitude calculation is invalid or has timed out. Check wiring to source of barometric altitude and ensure that source is operating. Fault will clear as soon as valid barometric altitude data is received. n) Temperature fault – Main board temperature or RF receiver temperature is greater than 100° Celsius or less than -60° Celsius. Fault will persist until internal temperature returns to acceptable range. Download the assert log and send to Garmin for diagnosis per Assert Tab info in Section 3.8.2.o) TCAS Equipage fault – TCAS Equipage data is not being received or has timed out for 800ms. Check wiring to TCAS Equipage data source and ensure that source is operating. Fault will clear as soon as valid TCAS Equipage data is received.p) Radio Altitude fault - Radio Altimeter has not remained active for five or more consecutive updates within the first ten surveillance updates after power up or reset, or the radio altitude status has been inactive for three or more consecutive seconds after the first ten seconds of operation. Check wiring to source of radio altitude and ensure that source is operating. Fault will clear as soon as valid radio altitude data is received. NOTENOTEDRAFT
GTS Processor Installation Manual Page 3-19190-00587-50 Revision AThe 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 TestTable 3-5 Self TestIntruder #1 (transmitted in intruder number field) 2.0 NMVertical Rate = Climbing, relative altitude = –200 feetTA, Bearing = –90 degreesIntruder #2 (transmitted in intruder number field)3.625 NMVertical Rate = Descending, relative altitude = –1,000 feetProx Traffic, Bearing = +33.75 degreesIntruder #3 (transmitted in intruder number field)3.625 NMNo vertical rate, relative altitude = +1,000 feetOther traffic, bearing = –33.75 degrees.DRAFT
Page 3-20 GTS Processor Installation ManualRevision A 190-00587-50Audio annunciation shall be:GTS 825 - “TAS system Passed” or “TAS system Failed”GTS 855 - “TCAS I system Passed” or “TCAS I system Failed”GTS 8000 - "TCAS II system Passed" or "TCAS II system Failed"Any faults and flags are also displayed on the Normal Tab of the GTS Processor Install Tool. Faults that occur will be colored in red and flags will be colored in black. If self test fails, refer to the diagnostics data to determine a cause.Ensure that no Intruder appears at close range to own aircraft. If the intruder appears at close range to own aircraft, verify that the mutual suppression line is connected between GTS Processor and other L-band equipment (transponder, DME, etc.).3.9.6 Ramp Test and Return To Service TestFor helicopter installations with the traffic system status valid discrete output wired to the air/ground discrete input, the ground test must be performed with the squat 'on-ground' sense temporarily configured as 'ground'. After performing the ground test, reconfigure the squat 'on-ground' sense to 'open'.Garmin Integrated Flight Deck HSDB installations with GDU software versions prior to 11.10 require the USB interface dongle cable (Appendix B) to allow use of the GTS Processor Install Tool to simulate flight conditions such as altitude of 50,000 feet, gear up, etc (Section 3.8.2). Garmin Integrated Flight Deck HSDB installations with GDU software versions 11.10 and newer can access the Ground Test from the MFD to perform these tests. Consult Garmin for details.For Garmin Integrated Flightdeck HSDB installations with GDU Software Versions prior to 11.10:Activate ground test mode by clicking ‘Enable’ in the Ground Test field on the Normal Tab of the GTS Processor Install Tool. Figure 3-17 Ground Test Enable, GTS Processor Install ToolFor 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 SoftkeyNOTENOTENOTEDRAFT
GTS Processor Installation Manual Page 3-21190-00587-50 Revision AGround Test Procedure:The GTS Processor must be in Ground Test mode to select a scenario that will properly converge and intercept the GTS Processor. The aircraft must be on the ground and the GTS Processor must be in Normal System mode and in Standby, to enable Ground Test mode. The GTS Processor will not accept the Ground Test command unless the unit is in Standby and the squat switch indicates the aircraft is on the ground.Configure Squat 'on-ground' sense as Open if no sense switch is installed. Leave Air/Ground* discrete Open. Configuration of Gear/Wheel as 'Fixed' will cause system to ignore the Gear Down and Locked* discrete input. See Appendix B (Notes 6 and 7) and Figure B-9 for Air/Ground* and Gear Down And Locked* discrete inputs.The Ground Test simulates the GTS to be airborne at 50,000 ft with magnetic heading of 0°.Use a ramp tester, such as a TIC TR220 or equivalent, to make the following setup and measurements to verify GTS Processor operational and surveillance functionality.1. Position the test set directional antenna with a clear line of sight to the GTS Processor antenna at 90 degrees. 2. With the GTS Processor powered up and in Standby mode (indicated on the CDTI), cycle the GTS Processor to “Operate”.3. Select the following scenario:Intruder Type–ATCRBSIntruder Start Distance–10 NMIntruder Start Altitude–50,000 ftVertical Speed–0 fpmVelocity–360 Kts4. Initiate the intruder scenario and verify that the following occurs:a. Traffic should be acquired at approximately 10 NM at 90 degree bearing and co-altitude. Observe intruder closes on own aircraft at a rate of .1 NM/sec. Verify that only a single target is displayed in the expected quadrant.b. The intruder should transition from Other Traffic (displayed as an open diamond with 00 displayed above), to proximate traffic (displayed as a filled white diamond with 00 displayed above), to a Traffic Advisory (TA) alarm.c. The appropriate TA symbology (yellow filled circle with 00 displayed above) is displayed, for GTS 855/GTS 825 installations an audio annunciation of "Traffic! 3 O'clock! Same Altitude! 3 Miles!" is issued, when the intruder approaches within 3 NM. For GTS 8000 installations, audio annunciations per DO-185B will be spoken (Traffic! Traffic!).When a GTS Processor is configured not to have a Radar Altimeter installed and the gear is extended (in a retractable gear aircraft), the audio annunciation of Traffic will be inhibited.NOTENOTENOTEDRAFT
Page 3-22 GTS Processor Installation ManualRevision A 190-00587-503.9.7 Antenna VerificationThe GTS Processor must be in Ground Test mode to perform the antenna verification. Refer to Section 3.8.6 for Ground Test mode information.The first step in antenna verification is to verify auto-calibration operates without indicating a fault. 1. With the GTS Processor powered up and “Standby” indicated on the CDTI (Cockpit Display of Traffic Information) cycle the GTS Processor to “Operate”. Each time the GTS Processor transitions between these modes, a self test of the antenna circuit is initialized. If the antenna connection is not correct the CDTI will display “Failure” indicating it will be necessary to recheck the antenna coaxial connections. If the CDTI displays “Operate” without indicating a fault, proceed to the next step of antenna verification.Using a ramp tester, such as a TIC TR220 or equivalent, make the following set up and measurements to ensure the antenna is properly connected and the GTS Processor is operational. 2. Position the test set directional antenna with a clear line of sight to the GTS Processor antenna. 3. Ensure that the transmitter or receiver (RX/TX) under test is significantly closer to the ramp tester than another operating RX/TX, or erroneous and inaccurate results may occur. All four quadrants (forward, starboard, aft, and port) will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the CDTI. 4. Using the ramp tester, select the proper antenna gain and distance to aircraft. 5. Position ramp test set at 0 degrees. 6. Turn the test set on. 7. Connect the directional antenna to the ramp test set. 8. Set the multifunction test set to perform “TCAS” testing. Configure the GTS Processor to the normal operating mode.9. Program a static intruder per the following scenario:See ramp test set operators manual to set the following parametersIntruder Start Distance–2 NM Intruder Start Altitude–50,000Vertical Speed–0 fpm Velocity–0 Kts10. 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. NOTENOTEDRAFT
GTS Processor Installation Manual Page 3-23190-00587-50 Revision A16. 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 off25. .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 coloron both ends of cable· TNC connectors are correctly installed on cables· Correct antenna type is selected in the configurationIf multiple targets are displayed during the antenna tests, recheck the antenna coaxial connections.3.10 Continued AirworthinessMaintenance of the GTS Processor is “on condition” only.Antennas installed in lightning zone 1A of the aircraft require a cable check (verify the connectors are on tight) following a lightning strike to the antenna.It is the installer’s responsibility to properly document any Instructions for Continued Airworthiness as may be required by the local aircraft certification authorities.NOTENOTEDRAFT
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GTS Processor Installation Manual Page 4-1190-00587-50 Revision A4 SYSTEM INTERCONNECTS4.1 GTS Processor Pin Function List4.1.1 P8001 (Digital)Figure 4-1 View of J8001 connector from back of unitTable 4-1 P8001 ConnectorPin Pin Name I/O1 CONFIG MODULE GROUND --2 RS-232 OUT 1 Out3 RS-232 IN 1 In4 SIGNAL GROUND --5 RS-232 OUT 2 Out6 RS-232 IN 2 In7 SIGNAL GROUND --8 RS-232 OUT 3 Out9 RS-232 IN 3 In10 SIGNAL GROUND --11 RS-232 OUT 4 Out12 RS-232 IN 4 In13 SIGNAL GROUND --14 ARINC 429 OUT 1 A Out15 ARINC 429 OUT 1 B Out16 ARINC 429 IN 1 A In17 ARINC 429 IN 1 B In18 SIGNAL GROUND --19 GPS PPS 1 IN In20 SIGNAL GROUND --21 CONFIG MODULE POWER OUT Out22 SIGNAL GROUND --23 ARINC 429 OUT 2 A Out24 ARINC 429 OUT 2 B Out25 ARINC 429 IN 2 A In26 ARINC 429 IN 2 B In27 SIGNAL GROUND --28 ARINC 429 OUT 3 A Out29 ARINC 429 OUT 3 B Out30 ARINC 429 IN 3 A In31 ARINC 429 IN 3 B In32 SIGNAL GROUND --33 ARINC 429 OUT 4 A Out34 ARINC 429 OUT 4 B Out35 ARINC 429 IN 4 A In1 2 3 4 5 6 7 8 9 10 1112131415161718192021 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 3940 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 5960 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78DRAFT
Page 4-2 GTS Processor Installation ManualRevision A 190-00587-50Table 4-1 P8001 Connector, continuedPin Pin Name I/O36 ARINC 429 IN 4 B In37 RS-422 IN A In38 RS-422 IN B In39 SIGNAL GROUND --40 CONFIG MODULE DATA I/O41 SIGNAL GROUND --42 ARINC 429 OUT 5 A Out43 ARINC 429 OUT 5 B Out44 ARINC 429 IN 5 A In45 ARINC 429 IN 5 B In46 SIGNAL GROUND --47 ARINC 429 OUT 6 A Out48 ARINC 429 OUT 6 B Out49 ARINC 429 IN 6 A In50 ARINC 429 IN 6 B In51 SIGNAL GROUND --52 ETHERNET OUT A Out53 ETHERNET OUT B Out54 ETHERNET IN A In55 ETHERNET IN B In56 SIGNAL GROUND --57 RS-422 OUT A Out58 RS-422 OUT B Out59 SIGNAL GROUND --60 CONFIG MODULE CLOCK Out61 RESERVED --62 RESERVED --63 RESERVED --64 RESERVED --65 RESERVED --66 RESERVED --67 RESERVED --68 RESERVED --69 SPARE --70 SPARE --71 SPARE --72 SPARE --73 GPS PPS IN 2 HI In74 GPS PPS IN 2 LO In75 USB VBUS POWER In76 USB DATA HI I/O77 USB DATA LO I/O78 USB GROUND --DRAFT
GTS Processor Installation Manual Page 4-3190-00587-50 Revision A4.1.2 P8002 (Analog/Discrete)Figure 4-2 View of J8002 connector from back of unitTable 4-2 P8002 ConnectorPin Pin Name Applicable Model** I/O1 SIGNAL GROUND --2RA DISPLAY STATUS VALID* 1 GTS 8000 InRESERVED GTS 855/GTS 825 --3RA DISPLAY STATUS VALID* 2 GTS 8000 InRESERVED GTS 855/GTS 825 --4 RESERVED --5 SIGNAL GROUND --6 AIR/GROUND* In7SPARE --8 TRAFFIC DISPLAY 1 STATUS VALID* In9 TRAFFIC DISPLAY 2 STATUS VALID* In10 GEAR DOWN AND LOCKED* In11 ADVISORY INHIBIT* 1 In12 ADVISORY CANCEL* In13 RESERVED --14 SELF TEST INHIBIT PROGRAM* In15 CLIMB INHIBIT* 1 GTS 8000 InRESERVED GTS 855/GTS 825 --16 CLIMB INHIBIT* 2 GTS 8000 InRESERVED GTS 855/GTS 825 --17 INCREASED CLIMB INHIBIT* 1 GTS 8000 InRESERVED GTS 855/GTS 825 --18 INCREASED CLIMB INHIBIT* 2 GTS 8000 InRESERVED GTS 855/GTS 825 --19 PERFORMANCE LIMIT* GTS 8000 InRESERVED GTS 855/GTS 825 --20 RESERVED --21 SIGNAL GROUND --22 RESERVED --23 RESERVED --24 RESERVED --25 RESERVED --26 RESERVED --27 RESERVED --28 RESERVED --*Denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.**Items in this column denote pin information specific to the listed model. Pin information applies to all models (GTS 8000, GTS 855, and GTS 825) if blank.1 2 3 4 5 6 7 8 9 10 1112131415161718192021 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 3940 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 5960 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78DRAFT
Page 4-4 GTS Processor Installation ManualRevision A 190-00587-50Table 4-2 P8002 Connector, continuedPin Pin Name Applicable Model** I/O29 RESERVED --30 RESERVED --31 RESERVED --32 RESERVED --33 RESERVED --34 RESERVED --35 RESERVED --36 RESERVED --37 RESERVED --38 RESERVED --39 SIGNAL GROUND --40 SIGNAL GROUND --41 HEADING X HI In42 HEADING X LO (GROUND) --43 SIGNAL GROUND --44 HEADING Y HI In45 HEADING Y LO (GROUND) --46 SIGNAL GROUND --47 SPARE --48 EXTERNAL SUPPRESSION I/O I/O49 SIGNAL GROUND --50 ANNUN* 1 (CORRECTIVE RA)*** GTS 8000 OutANNUN* 1 (TA DISPLAY ENABLE)*** GTS 855/GTS 825 Out51 ANNUN* 2 (PREVENTIVE RA)*** GTS 8000 OutANNUN* 2 (AURAL TA)*** GTS 855/GTS 825 Out52 SPARE --53 ANNUN* 3 (VISUAL TA) Out54 TRAFFIC SYSTEM STATUS VALID* Out55 RESERVED --56 ADVISORY INHIBIT* 2 GTS 8000 InRESERVED GTS 855/GTS 825 --57 SIGNAL GROUND --58 ALERT AUDIO OUT HI Out59 ALERT AUDIO OUT LO Out60 HEADING Z HI (GROUND) In61 HEADING Z LO (GROUND) --62 SIGNAL GROUND --63 26 VAC HEADING REF HI In64 26 VAC HEADING REF LO In65 SIGNAL GROUND --66 SPARE --67 SPARE --68 HEADING VALID In69 HEADING VALID* In70 SIGNAL GROUND --*Denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.**Items in this column denote pin information specific to the listed model. Pin information applies to all models (GTS 8000, GTS 855, and GTS 825) if blank.***The Annunciator Outputs are configurable to perform the discrete output functions of ARINC 735 A/B.DRAFT
GTS Processor Installation Manual Page 4-5190-00587-50 Revision ATable 4-2 P8002 Connector, continuedPin Pin Name Applicable Model** I/O71 ANALOG RADAR ALTIMETER HI In72 ANALOG RADAR ALTIMETER LO In73 SIGNAL GROUND --74 SELF TEST INITIALIZE SELECT* In75 TRAFFIC OPERATE/STANDBY* In76 ANALOG RADAR ALTIMETER VALID In77 SPARE --78 SIGNAL GROUND --*Denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.**Items in this column denote pin information specific to the listed model. Pin information applies to all models (GTS 8000, GTS 855, and GTS 825) if blank.DRAFT
Page 4-6 GTS Processor Installation ManualRevision A 190-00587-504.1.3 P8003 (Power Supply)Figure 4-3 View of J8003 connector from back of unitTable 4-3 P8002 ConnectorPin Pin Name I/O1 POWER GROUND --2 AIRCRAFT POWER 1 In3 AIRCRAFT POWER 1 In4 AIRCRAFT POWER 2 In5 AIRCRAFT POWER 2 In6 POWER GROUND --7 RESERVED --8 RESERVED --9 RESERVED --10 RESERVED --11 POWER GROUND --12 RESERVED --13 RESERVED --14 POWER GROUND --15 RESERVED --16 RESERVED --17 POWER GROUND --18 TRAFFIC SYSTEM REMOTE POWER ON* In19 POWER GROUND --20 POWER GROUND --21 POWER GROUND --22 POWER GROUND --23 POWER GROUND --24 POWER GROUND --25 POWER GROUND --26 POWER GROUND --27 POWER GROUND --28 POWER GROUND --29 POWER GROUND --30 POWER GROUND --31 POWER GROUND --32 POWER GROUND --33 POWER GROUND --34 POWER GROUND --35 POWER GROUND --36 TRAFFIC SYSTEM REMOTE POWER OFF In37 POWER GROUND --An asterisk (*) following a signal name denotes that the signal is Active Low. Refer to Section 4.5.4 for signal description.DRAFT
GTS Processor Installation Manual Page 4-7190-00587-50 Revision A4.2 Power4.2.1 Aircraft Power FunctionsThis section covers the power input requirements.4.2.1.1 Aircraft PowerPins 2 and 3 are internally connected to form AIRCRAFT POWER 1. Pins 4 and 5 are internally connected to form AIRCRAFT POWER 2. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are “diode ORed” to provide aircraft power redundancy.4.2.1.2 Remote PowerAn 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 OFFACTIVE: Vin > 8 VDC (Unit OFF)INACTIVE: Vin < 3 VDC or floating (Unit ON)Table 4-4 Aircraft PowerPin Name Connector Pin I/OAIRCRAFT POWER 1 P8003 2 InAIRCRAFT POWER 1 P8003 3 InAIRCRAFT POWER 2 P8003 4 InAIRCRAFT POWER 2 P8003 5 InPOWER GROUND P8003 21 --POWER GROUND P8003 22 --POWER GROUND P8003 23 --POWER GROUND P8003 24 --Table 4-5 Remote PowerPin Name Connector Pin I/OTRAFFIC SYSTEM REMOTE POWER ON* P8003 18 InTRAFFIC SYSTEM REMOTE POWER OFF P8003 36 InTable 4-6 Power On/Off MatrixActive Low Remote Power On (J8003 Pin 18)Active High Remote Power Off(J8003 Pin 36) Expected Unit StateState Level State LevelInactive Vin > 8 VDC or Open Inactive Vin < 3VDC or Open OFFActive Vin < 3VDC or Gnd Inactive Vin < 3VDC or Open ONInactive Vin > 8 VDC or Open Active Vin > 8 VDC OFFActive Vin < 3VDC or Gnd Active Vin > 8 VDC OFFDRAFT
Page 4-8 GTS Processor Installation ManualRevision A 190-00587-504.3 Serial Data4.3.1 RS-232The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5V when driving a standard RS-232 load.4.3.2 RS-422The RS-422 channels conform to EIA standard RS-422.Table 4-7 RS-232 Pin Name Connector Pin I/ORS-232 OUT 1 P8001 2 OutRS-232 IN 1 P8001 3 InRS-232 OUT 2 P8001 5 OutRS-232 IN 2 P8001 6 InRS-232 OUT 3 P8001 8 OutRS-232 IN 3 P8001 9 InRS-232 OUT 4 P8001 11 OutRS-232 IN 4 P8001 12 InTable 4-8 RS-422Pin Name Connector Pin I/ORS-422 IN A P8001 37 InRS-422 IN B P8001 38 InRS-422 OUT A P8001 57 OutRS-422 OUT B P8001 58 OutDRAFT
GTS Processor Installation Manual Page 4-9190-00587-50 Revision A4.3.3 ARINC 429The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers.4.3.4 EthernetThis Ethernet based HSDB (High Speed Data Bus) meets the hardware aspects of IEEE standard 802.3 for 10 base T Ethernet communications.Table 4-9 ARINC 429Pin Name Connector Pin I/OARINC 429 OUT 1 A P8001 14 OutARINC 429 OUT 1 B P8001 15 OutARINC 429 IN 1 A P8001 16 InARINC 429 IN 1 B P8001 17 InARINC 429 OUT 2 A P8001 23 OutARINC 429 OUT 2 B P8001 24 OutARINC 429 IN 2 A P8001 25 InARINC 429 IN 2 B P8001 26 InARINC 429 OUT 3 A P8001 28 OutARINC 429 OUT 3 B P8001 29 OutARINC 429 IN 3 A P8001 30 InARINC 429 IN 3 B P8001 31 InARINC 429 OUT 4 A P8001 33 OutARINC 429 OUT 4 B P8001 34 OutARINC 429 IN 4 A P8001 35 InARINC 429 IN 4 B P8001 36 InARINC 429 OUT 5 A P8001 42 OutARINC 429 OUT 5 B P8001 43 OutARINC 429 IN 5 A P8001 44 InARINC 429 IN 5 B P8001 45 InARINC 429 OUT 6 A P8001 47 OutARINC 429 OUT 6 B P8001 48 OutARINC 429 IN 6 A P8001 49 InARINC 429 IN 6 B P8001 50 InTable 4-10 EthernetPin Name Connector Pin I/OETHERNET OUT A P8001 52 OutETHERNET OUT B P8001 53 OutEHTERNET IN A P8001 54 InETHERNET IN B P8001 55 InDRAFT
Page 4-10 GTS Processor Installation ManualRevision A 190-00587-504.3.5 USB**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection. USB TYPE B RECEPTACLE pigtail cable must be wired directly to P8001 to minimize lightning exposure.This interface is used for unit configuration and software uploads. Conforms to the Universal Serial Bus Version 1.1 standard for a “full-speed” device.4.4 Configuration4.4.1 Configuration Module**Signals have ESD (Electrostatic Discharge) protection, but not lightning protection. 4.5 Analog/Discrete4.5.1 Heading Input4.5.1.1 26 Volt AC ReferencesUsed to sample AC inputs.This signal must be the same phase and frequency as the indicator being driven.Frequency: 400 Hz ± 10%Voltage: 22.6 Vrms to 28.6 VrmsInput Impedance: >10 kΩTable 4-11 USBPin Name Connector Pin I/OUSB VBUS POWER** P8001 75 InUSB DATA HI** P8001 76 I/OUSB DATA LO** P8001 77 I/OUSB GROUND P8001 78 --Table 4-12 Configuration ModulePin Name Connector Pin I/OCONFIG MODULE GROUND P8001 1 --CONFIG MODULE POWER OUT** P8001 21 --CONFIG MODULE DATA** P8001 40 I/OCONFIG MODULE CLOCK** P8001 60 I/OTable 4-13 26 Volt AC ReferencesPin Name Connector Pin I/O26 VAC HEADING REF HI P8002 63 In26 VAC HEADING REF LO P8002 64 InDRAFT
GTS Processor Installation Manual Page 4-11190-00587-50 Revision A4.5.1.2 Radar AltimeterProvides altitude information during approach. Input voltage range is 0 to 30Vdc. Compatible with Radar Altimeters listed in section 3.5.2.4.4.5.2 Inputs From Compass System/Directional GyrosInputs heading information from a directional gyro.3-wire synchro magnetic heading input, with HEADING Z grounded. Index reference is 0° as specified by ARINC 407.Frequency: 400Hz ± 10%Voltage: 11.8 Vrms nominal, 13.0 Vrms maximumInput Impedance: >10 kΩResolution: ± 0.1° or betterAccuracy: ± 2°Both the active high Heading Valid discrete and the active low Heading Valid* discrete inputs to the GTS Processor must be valid for heading information to be used by the GTS Processor system. If the Compass System/Directional Gyro provides an active high Heading Valid discrete output, wire to the GTS Processor active high Heading Valid discrete input, otherwise wire the GTS Processor active high Heading Valid discrete input to the circuit breaker output (14 Vdc or 28 Vdc) for the Compass System/Directional Gyro. If the Compass System/Directional Gyro provides an active low Heading Valid* discrete output, wire to the GTS Processor active low Heading Valid* discrete input, otherwise wire the GTS Processor active low Heading Valid* discrete input to Ground. Table 4-14 Radar AltimeterPin Name Connector Pin I/OANALOG RADAR ALTIMETER HI P8002 71 InANALOG RADAR ALTIMETER LO P8002 72 InTable 4-15 Inputs From Compass System/Directional GyrosPin Name Connector Pin I/OHEADING X P8002 41 InHEADING LO (GROUND) P8002 42 --HEADING Y HI P8002 44 InHEADING Y LO (GROUND) P8002 45 --HEADING Z HI (GROUND) P8002 60 InHEADING Z LO (GROUND) P8002 61 --NOTEDRAFT
Page 4-12 GTS Processor Installation ManualRevision A 190-00587-504.5.3 AudioAlert Audio shield should only be connected to ground on the Audio Panel end.4.5.4 Active Low Discrete Inputs*Denotes that the signal is Active Low.ACTIVE: 0 V ≤ Vin ≤ 3.5 V, or Rin ≤ 375 ohmsINACTIVE: 8 V ≤ Vin ≤ 36 V, or Rin ≥ 100k ohmsSource 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 blankTable 4-16 AudioPin Name Connector Pin I/OALERT AUDIO OUT HI P8002 58 OutALERT AUDIO OUT LO P8002 59 OutNOTETable 4-17 Active Low Discrete InputsPin Name Applicable Model**Connector Pin I/ORA DISPLAY STATUS VALID* 1 GTS 8000 P8002 2 InRA DISPLAY STATUS VALID* 2 GTS 8000 P8002 3 InAIR/GROUND* P8002 6 InTRAFFIC DISPLAY 1 STATUS VALID* P8002 8 InTRAFFIC DISPLAY 2 STATUS VALID* P8002 9 InGEAR DOWN AND LOCKED* P8002 10 InADVISORY INHIBIT* 1 P8002 11 InADVISORY CANCEL* P8002 12 InSELF TEST INHIBIT PROGRAM* P8002 14 InCLIMB INHIBIT* 1 GTS 8000P8002 15 InRESERVED GTS 855/GTS 825CLIMB INHIBIT* 2 GTS 8000P8002 16 InRESERVED GTS 855/GTS 825INCREASED CLIMB INHIBIT* 1 GTS 8000P8002 17 InRESERVED GTS 855/GTS 825INCREASED CLIMB INHIBIT* 2 GTS 8000P8002 18 InRESERVED GTS 855/GTS 825PERFORMANCE LIMIT* GTS 8000 P8002 19 InRESERVED GTS 855/GTS 825HEADING VALID* P8002 69 InSELF TEST INITIALIZE SELECT* P8002 74 InTRAFFIC OPERATE/STANDBY* P8002 75 InDRAFT
GTS Processor Installation Manual Page 4-13190-00587-50 Revision AThe ‘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 InputsACTIVE: 8 V ≤ Vin ≤ 36 VINACTIVE: 0 V ≤ Vin ≤ 3.5 V, or Rin ≥ 100k ohmsSink current is internally limited to approximately 1 mA typical for an input connected to +28VDC.NOTETable 4-18 Active High Discrete InputsPin Name Connector Pin I/OHEADING VALID P8002 68 InANALOG RADAR ALTIMETER VALID P8002 76 InDRAFT
Page 4-14 GTS Processor Installation ManualRevision A 190-00587-504.5.6 Annunciator Output*Denotes that the signal is Active Low.ACTIVE: 0 V ≤ Vout ≤ 0.5 V or Rout ≤ 10 ohms, sinking up to 500 mAINACTIVE: 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 BusMutual Suppression Input/Output bus compliant with ARINC 735A/B Attachment 8, with the exception that the maximum applied DC steady state voltage is +30.3V. Suppression I/O signal is pulsed under normal operation.Table 4-19 Annunciator OutputPin Name Applicable Model**Connector Pin I/OANNUN* 1 (CORRECTIVE RA) GTS 8000P8002 50 OutANNUN* 1 (TA DISPLAY ENABLE) GTS 855/GTS 825ANNUN* 2 (PREVENTIVE RA) GTS 8000P8002 51 OutANNUN* 2 (AURAL TA) GTS 855/GTS 825ANNUN* 3 (VISUAL TA)*** P8002 53 OutTRAFFIC SYSTEM STATUS VALID* P8002 54 OutTable 4-20 Mutual Suppression BusPin Name Connector Pin I/OEXTERNAL SUPPRESSION I/O P8002 48 I/ODRAFT
GTS Processor Installation Manual Page A-1190-00587-50 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-1 GTS Processor Vertical Outline Drawing1.99 50.56.74171.113.49 342.5CENTER OF GRAVITYTBDGRAVITYTBDCENTER OF.62515.887.00177.8 4.375111.133.32 84.23.67 93.1.18 4.4CENTER OF GRAVITYTBDGRAVITYTBDCENTER OF6X NOTE 3GRAVITYTBDCENTER OFGRAVITYTBDCENTER OFNOTES:DIMENSIONS: INCHES [mm]1.DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.2.MOUNTING HOLE FOR FOR #8 PANHEAD SCREW.3.DRAFT
GTS Processor Installation Manual Page A-2190-00587-50 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-2 GTS Processor Vertical Installation DrawingCONNECTOR KITCONNECTOR KIT011-01360-00 (UNSEALED)011-01360-00 (UNSEALED)OROR011-01360-10 (SEALED)011-01360-10 (SEALED)GTS PROCESSOR UNITGTS PROCESSOR UNIT011-02571-00011-02571-00GTS PROCESSOR VERTICAL RACKGTS PROCESSOR VERTICAL RACK011-02572-00011-02572-00011-01855-04011-01855-04(2 PLACES)(2 PLACES)NOTE 1NOTE 1011-01855-03011-01855-03NOTE 1NOTE 1330-00502-37 (UNSEALED)330-00502-37 (UNSEALED)OROR330-00853-37 (SEALED)330-00853-37 (SEALED)330-00366-78 (UNSEALED)330-00366-78 (UNSEALED)OROR330-00776-78 (SEALED)330-00776-78 (SEALED)(2 PLACES)(2 PLACES)NOTES:NOTES:1. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS1. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTSDRAFT
GTS Processor Installation Manual Page A-3190-00587-50 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-3 GTS Processor Horizontal Outline Drawing1.99 50.53.48 88.3HEIGHTWITHOUT FEET4.10104.1HEIGHTWITH FEET12.80 325.1CENTER OF GRAVITYTBDOF GRAVITYTBDCENTEROF GRAVITYTBDCENTERCENTER OF GRAVITYTBD1.59 40.3 9.73247.02.40 61.0 8.10205.7.4611.72.75 69.92.75 69.96.42163.1OF GRAVITYTBDCENTERCENTER OF GRAVITYTBD6X NOTE 3NOTES:DIMENSIONS: INCHES [mm]1.DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.2.MOUNTING HOLE FOR #8 PANHEAD OR SOCKET HEAD3. CAP SCREW. RECOMMENDED LENGTH .750 INCHES MINIMUM.MOUNTING FEET MAY BE REMOVED WHEN DESIRED FOR INSTALLATION.4. SEE FIGURE A-?? FOR DETAILS OF REUSE OF SCREWS AND MOUNTING HOLES IN A FOOTLESS INSTALLATION.DRAFT
GTS Processor Installation Manual Page A-4190-00587-50 Revision AAPPENDIX A Outline and Installation DrawingsFigure A-4 GTS Processor Horizontal Installation DrawingGTS PROCESSOR UNIT011-02571-00GTS PROCESSOR HORIZONTAL RACK115-00784-00SCREWS AND HOLES FOR REUSEWHEN INSTALLING RACK WITH FEET REMOVED(SEE NOTE 1)SCREWS AND HOLES FOR REUSEWHEN INSTALLING RACK WITH FEET REMOVED(SEE NOTE 1)011-01855-03NOTE 2011-01855-04(2 PLACES)NOTE 2330-00366-78 (UNSEALED)OR330-00776-78 (SEALED)(2 PLACES)330-00502-37 (UNSEALED)OR330-00853-37 (SEALED)CONNECTOR KIT011-01360-00 (UNSEALED)OR011-01360-10 (SEALED)NOTES:RACK MAY BE INSTALLED WITH MOUNTING FEET ATTACHED, OR AFTER REMOVAL OF MOUNTING FEET.1. TO INSTALL RACK WITHOUT MOUNTING FEET, REMOVE FEET AND REUSE SCREWS (QUANTITY 6) IN THE EXTREME FRONT COUNTERSUNK MOUNTING HOLES (3 PLACES) AND THE EXTREME BACK COUNTERSUNK MOUNTING HOLES (3 PLACES).2. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS.DRAFT
GTS Processor Installation Manual Page B-1190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-1 GTS Processor Interconnect Example Notes THE GTS PROCESSOR SUPPRESSION I/O PULSES MAY NOT BE COMPATIBLE WITH ALL MODELS OF TRANSPONDERS AND DME UNITS THAT HAVE OUTPUT-ONLY SUPPRESSION, AND CAN BE DAMAGED BY THE GTS PROCESSOR MUTUAL SUPPRESSION OUTPUT. FOR TRANSPONDERS AND DME UNITS THAT HAVE OUTPUT-ONLY SUPPRESSION, AN IN-LINE DIODE MUST BE INSTALLED BETWEEN THE GTS PROCESSOR SUPPRESSION I/O (CATHODE) AND THE OUTPUT-ONLY SUPPRESSION LINE.PROCESSOR A GTX 3000, OR OTHER RTCA DO-185A/B GARMIN-APPROVED COMPATIBLE TRANSPONDER, IS REQUIRED FOR ALL GTS 8000 INSTALLATIONS.GTS 8000 INSTALLATIONS REQUIRE ARINC 429 IN/OUT CONNECTIONS TO A GTX 3000, OR OTHER RTCA DO-185A/B GARMIN-APPROVED COMPATIBLE TRANSPONDER. GTX 3000 BARO ALTITUDE AND TCAS EQUIPAGE DATA ARE PRESENT ON A SINGLE ARINC 429 INTERFACE.13. IF INSTALLED, THE USB PIGTAIL MUST BE WIRED DIRECTLY TO THE DSUB CONNECTOR. ALL USB EXTENSION CABLES MUST BE DISCONNECTED DURING FLIGHT.FOR GTS 8000 INTERCONNECTION TO A GTX 3000, TX/XT INTERFACE MUST BE WIRED AS FOLLOWS: FROM GTX 3000 ARINC 429 OUTPUT CHANNEL 4 TO APPROPRIATELY CONFIGURED GTS 8000 ARINC INPUT, AND FROM APPROPRIATELY CONFIGURED GTS 8000 ARINC OUTPUT TO GTX 3000 ARINC 429 INPUT CHANNEL 8.DRAFT
GTS Processor Installation Manual Page B-2190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-2 GTS Processor Interconnect Example GTS PROCESSORBOTTOM ANTENNA IS OPTIONAL FOR GTS 855 AND GTS 825 INSTALLATIONS. BOTTOM ANTENNA IS REQUIRED FOR GTS 8000 INSTALLATIONS.DRAFT
GTS Processor Installation Manual Page B-3190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-3 GTS Processor Garmin Integrated Flight Deck Interconnect ExampleGarmin5253ETHERNET OUT AETHERNET OUT BGarminGDL 69/69A27 ETHERNET IN 2 A196P1008P26 ETHERNET IN 2 B5455ETHERNET IN AETHERNET IN B2928ETHERNET OUT 2 AETHERNET OUT 2 BGarminGTX 33(D) w/ES31 EXT SUPPRESSION I/OP330148SUPPRESSION I/OP8002UATDMEEXT SUPPRESSION I/OEXT SUPPRESSION I/OSSSSSSGarminGIA 63(W) #11P604751AURAL TA ALERT*3811TA INHIBIT* 1 ANNUNCIATE* 15DISCRETE* 1GarminGMA 1347P34711939UNSWITCHED AUDIO IN 1 HIUNSWITCHED AUDIO IN LO5859AUDIO ALERT OUT HIAUDIO ALERT OUT LOSSSS SGarminGIA 63(W) #22P604738 ANNUNCIATE* 15DISCRETE* 1SSALERT AUDIO SHIELD SHOULD ONLY BE CONNECTED TO GROUND ON THE AUDIO PANEL END.GarminGarminGIA 63/63W8 MAIN ARINC 429 IN 3 AP6039 MAIN ARINC 429 IN 3 B7475MAIN ARINC 429 OUT 3 BMAIN ARINC 429 OUT 3 ASSSS14151617ARINC 429 OUT 1 AARINC 429 OUT 1 BARINC 429 IN 1 AARINC 429 IN 1 BGarminP8001NOTE 11REFER TO NOTE 12FOR FAA APPROVED GARMIN INTEGRATED FLIGHT DECK/GTS PROCESSOR INSTALLATIONS (SEE SECTION 3.8.1.1):APPLIES TO GTS PROCESSOR.CONNECT THE HSDB INTERFACE. DO NOT CONNECT THE ARINC INTERFACE.USB CONNECTION REQUIRED FOR GDU SW PRIOR TO V11.10.SUPPRESSION I/O, ANALOG AUDIO ALERT OUTPUTS, AND TA INHIBIT DISCRETE INPUTS ARE NEEDED FOR ALL INSTALLATIONS.REQUIRES FAA APPROVED CONFIGURATION DATA LOADED FROM AN AIRCRAFT SPECIFIC LOADER CARD.Garmin7576USB VBUS POWERUSB DATA HIUSB TYPE BRECEPTACLE1 VBUSP80013D+7778USB DATA LOUSB GROUND24D-GNDSSHELLREDGREENWHITEBLACKSHIELDNOTE: USB TYPE B RECEPTACLE PIGTAIL MUST BE WIRED DIRECTLY TOP8001 TO MINIMIZE LIGHTNING EXPOSURE. USB EXTENSION CABLESMUST BE DISCONNECTED FROM THE PIGTAIL WHILE FLYING.GTS PROCESSORGTS PROCESSORGTS PROCESSORGTS PROCESSORDRAFT
GTS Processor Installation Manual Page B-4190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-4 GTS Processor Field Approved (Retrofit) Garmin Integrated Flight Deck Interconnect ExampleGTS PROCESSORTRAFFIC ALERTING SYSTEMP8001P8002P8003SIGNAL GROUND 13ARINC 429 OUT 1 A 14ARINC 429 OUT 1 B 15SIGNAL GROUND 22ARINC 429 IN 1 A 16ARINC 429 IN 1 B 17CONFIG MODULE GROUND 1CONFIG MODULE POWER OUT 21CONFIG MODULE DATA 40CONFIG MODULE CLOCK 60USB VBUS POWER 75USB DATA HI 76USB DATA LO 77USB GROUND 78SELF TEST INITIALIZE SELECT* 74TRAFFIC OPERATE/STANDBY* 75AUDIO ALERT OUT HI 58AUDIO ALERT OUT LO 59TA INHIBIT* 1 11AIRCRAFT POWER 2POWER GROUND 21POWER GROUND 23POWER GROUND 22POWER GROUND 24GMA x347AUDIO PANELP3471SS19 UNSWITCHED AUDIO IN 1 HI39 UNSWITCHED AUDIO IN LOGIA 63WINTEGRATED AVIONICS2P60438 ANNUN* 15 (TA INHIBIT* 1)36 ANNUN* 13 (TAS SELF TEST*)37 ANNUN* 14 (TAS STBY/OPR*)CONFIG MODULE1 GND4 VCC3 DATA2 CLKGIA 63WINTEGRATED AVIONICS2P60351 SIGNAL GROUND71 ARINC OUT 1A70 ARINC OUT 1B11 ARINC IN 4B10 ARINC IN 4A48 SIGNAL GROUNDSSSSAIR/GROUND* 6 AIR/GROUND (SQUAT SWITCH), OPTIONAL CONNECTIONGEAR DOWN AND LOCKED* 10 GEAR DOWN AND LOCKED, OPTIONAL CONNECTIONUSB TYPE B RECEPTACLE1 VBUS3 D+2 D-4 GNDSSHELL SHIELDTAS 1 BREAKER AND AIRCRAFT POWER BUS 1TAS 1 BREAKER AND AIRCRAFT POWER BUS 2REFER TO NOTE 8AIRCRAFT POWER 3AIRCRAFT POWER 4AIRCRAFT POWER 5INSTALLER MAY SELECT DIFFERENT GIA ARINC CHANNELS THAN THOSE LISTED, CHANNELS USED MUST MATCH THOSE USED IN CONFIGURATION (SECTION 3.9)IN CERTAIN INSTALLATIONS, THE UNSWITCHED AUDIO PORT MAY ALREADY BE CONFIGURED FOR USE BY ANOTHER SYSTEM. IF ANOTHER SYSTEM IS USING THE 'UNSWITCHED AUDIO IN 1' OUTPUT, THE INSTALLER MUST VERIFY THERE IS NO INTERFERENCE WITH THE OTHER SYSTEM. A DIFFERENT GMA OUTPUT PORT (IF AVAILABLE) MAY BE CONFIGURED TO RECEIVE TAS AUDIOUNLESS OTHERWISE NOTED, ALL CONNECTIONS SHOWN ARE REQUIRED DRAFT
GTS Processor Installation Manual Page B-5190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-5 GTS Processor GNS 4XX/5XX/GMX 200 Interconnect Example GTS PROCESSOR GTS PROCESSORDRAFT
GTS Processor Installation Manual Page B-6190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-6 GTS Processor GMA/HSI/Altimeter Interconnect ExampleWHEN 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 POWERTHESE CONNECTIONS NOT REQUIRED FOR GTX 3000 INSTALLATION GTS PROCESSOR GTX 330 ES/GTX 3000 GTS PROCESSOR}FOR GTX 3000, BARO OUT AND NTA COUNT INFO ARE OUTPUT ON A SINGLE ARINC CHANNEL DRAFT
GTS Processor Installation Manual Page B-7190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-7 GTS Processor Dongle Cable (see Sections 3.7 and 3.8.6)USB VBUS POWERUSB DATA HIUSB DATA LOUSB GROUNDREDGRNWHTBLK75767778GTS PROCESSORP8001VBUSD+D-GND1324USB TYPE BRECEPTACLESHIELDSHELLsNOTES:1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.2. GROUND DESIGNATIONS: SHIELD BLOCK GROUND AIRFRAME GROUND3. AT THE GTS PROCESSOR, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS OR CONNECTOR BACKSHELL WITH AS SHORT A CONDUCTOR AS PRACTICAL FOLLOWING ANY EQUIPMENT MANUFACTURER’S REQUIREMENTS.4. USB TYPE B RECEPTACLE PIGTAIL (P/N 011-01782-00) MUST BE WIRED DIRECTLY TO P8001 TO MINIMIZE LIGHTNING EXPOSURE.5. THE USB PIGTAIL SHIELD DRAIN USES 28 AWG WIRE.s428 AWG28 AWG5DRAFT
GTS Processor Installation Manual Page B-8190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-8 GTS Processor Discrete Interconnect ExampleGTS PROCESSORANNUN* 3 VISUAL TA ALERT*ANNUN* 2 AURAL TA ANNUN* 1 (CORRECTIVE AURAL* RA - GTS 8000 / TA DISPLAY ENABLE* - GTS 855/GTS 825)ADVISORY CANCEL*RA DISPLAY STATUS VALID* 2 (GTS 8000 ONLY) 3RA DISPLAY 2 VALID RA DISPLAY 2 INVALID RA DISPLAY 2 VALID RA DISPLAY STATUS VALID* 1 (GTS 8000 ONLY) 2RA DISPLAY 1 VALID RA DISPLAY 1 INVALID RA DISPLAY 1 VALID DRAFT
GTS Processor Installation Manual Page B-9190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-9 GTS Processor Configuration Module Interconnect ExampleGTS PROCESSOR GARMINDRAFT
GTS Processor Installation Manual Page B-10190-00587-50 Revision AAPPENDIX B Interconnect ExamplesFigure B-10 GTS Processor Dual Transponder Interconnect ExampleGTS 820/850ARINC 429 OUT 2 AARINC 429 OUT 2 B2324P8001GARMINTRANSPONDER #1ARINC 429 IN 2 AARINC 429 IN 2 B333631P3301sNOTES:1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED.2. GROUND DESIGNATIONS: SHIELD BLOCK GROUND AIRFRAME GROUND3. AT THE GTS 8XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0 ". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL. 4. CONFIGURE THE ARINC 429 BUS SPEED TO MATCH THE GTS PROCESSOR OUTPUT SPEED.5. REFER TO GARMIN TRANSPONDER INSTALLATION MANUAL FOR ADDITIONAL INSTALLATION DETAILS.7. IF ONLY ONE TRANSPONDER IS INSTALLED, CONNECT AS SHOWN FOR TRANSPONDER #1.sEXTERNAL SUPPRESSION I/O 48 EXTERNAL SUPPRESSION I/OARINC 429 IN 2 AARINC 429 IN 2 B2526ARINC 429 OUT 2 AARINC 429 OUT 2 B3028sP8002ss4GTX 33/33D330/330D333631P32813028GTX 328----17P3271----GTX 327/32/320AGARMINTRANSPONDER #2ARINC 429 IN 2 AARINC 429 IN 2 B333631P3301EXTERNAL SUPPRESSION I/OARINC 429 OUT 2 AARINC 429 OUT 2 B3028ssGTX 33/33D330/330D333631P32813028GTX 328----17P3271----GTX 327/32/320A13 EXTERNAL STANDBY SELECT13 EXTERNAL STANDBY SELECTTRANSPONDER 2TRANSPONDER 1TO DME/UATARINC 429 OUT 3 AARINC 429 OUT 3 B2829ARINC 429 IN 3 AARINC 429 IN 3 B30316. THE GTX 330 ARINC 429 OUT 2 PORT IS HIGH-IMPEDANCE WHEN THE EXTERNAL STANDBY SELECT INPUT IS GROUNDED. THIS ALLOWS ARINC 429 OUTPUTS FROM DUAL GTX 330 UNITS TO BE HARD-WIRED TOGETHER SINCE THE EXTERNAL STANDBY SELECT INPUT WILL BE ACTIVE FOR ONE OF THE TWO GTX 330’S AT ANY GIVEN TIME.8. THE GTS PROCESSOR IS NOT TO BE INSTALLED IN AN AIRCRAFT WITH A TSO-C119a-ONLY COMPATIBLE TRANSPONDER.DRAFT

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