T GTS Processor D R AF Installation Manual 190-00587-50 January, 2012 Revision A
© Copyright 2012 Garmin Ltd. or its subsidiaries All Rights Reserved T Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.
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TABLE OF CONTENTS PARAGRAPH PAGE Section 1 GENERAL DESCRIPTION .............................................................1-1 1.1 Introduction...................................................................................................................... 1-1 1.2 Equipment Description .................................................................................................... 1-1 1.2.1 GTS Processor Configuration Options ......................................................................
PARAGRAPH PAGE 3.9.6 Ramp Test and Return To Service Test..............................................................................3-20 3.9.7 Antenna Verification ..........................................................................................................3-22 3.10 Continued Airworthiness ............................................................................................. 3-23 Section 4 SYSTEM INTERCONNECTS..........................................................4-1 4.
LIST OF FIGURES FIGURE PAGE Section 1 GENERAL DESCRIPTION .............................................................1-1 Section 2 INSTALLATION OVERVIEW........................................................2-1 R AF T Figure 2-1 GTS Processor Installation with Top and Bottom Directional Antennas ........... 2-5 Figure 2-2 GTS Processor Installation with Top Directional and Bottom Monopole Antennas ..................................................................................................
FIGURE PAGE Appendix B Interconnect Examples ................................................................B-1 D R AF T Figure B-1 GTS Processor Interconnect Example Notes .....................................................B-1 Figure B-2 GTS Processor Interconnect Example................................................................B-2 Figure B-3 GTS Processor Garmin Integrated Flight Deck Interconnect Example .............
LIST OF TABLES TABLE PAGE Section 1 GENERAL DESCRIPTION .............................................................1-1 Compatible Transponders..................................................................................... 1-2 Configuration Options .......................................................................................... 1-2 Physical Characteristics........................................................................................ 1-3 General Specifications....................
TABLE Radar Altimeter ................................................................................................ 4-11 Inputs From Compass System/Directional Gyros ............................................ 4-11 Audio ................................................................................................................ 4-12 Active Low Discrete Inputs.............................................................................. 4-12 Active High Discrete Inputs ..............................
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1 GENERAL DESCRIPTION 1.1 Introduction This manual presents mechanical and electrical installation requirements for installing the GTS Processor as a Traffic Advisory System (TAS) (GTS 825), Traffic Collision Avoidance System (TCAS I) (GTS 855), and Traffic Collision Avoidance System (TCAS II) (GTS 8000). 1.
Refer to Table 1-1 for a list of compatible transponders. Table 1-1 Compatible Transponders GTX Transponder Model Capable of Receiving TCAS II Broadcast Data (Required for GTS Processor) ADS-B Capable RTCA DO-185A/B Compatible Yes(3) Yes(2) No Yes No GTX 330/330D (3) Yes GTX 33/33D(1) Yes(3) Yes(2) No GTX 33 ES/33D ES(1) Yes(3) Yes No No No Yes Yes Yes GTX 328 GTX 3000 (4) Yes T GTX 330 ES/330D ES R AF 1. Remote mounted transponders require a compatible controller.
1.4.2 Physical Characteristics Table 1-3 Physical Characteristics Characteristics Specifications 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.
1.5 Certification The conditions and tests required for TSO/ETSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO/ETSO standards. TSO/ ETSO articles must have separate approval for installation in an aircraft.
NOTE A statement identifying whether the installation is TSO-C166b/ETSO-C166a Class A1S/Type 1 Receiving Only or TSO-C166b/ETSO-C166a Class A1/Type 1 Receiving Only, per RTCA/DO-260B, should be included in the ship's log during Installation. † Installation of this Receiving Only class of equipment is intended only for those aircraft in which a 1090 MHz ADS-B transmit class of equipment, or other complementary ADS-B link transmit class of equipment (such as UAT), is already installed.
Table 1-8 TSO/ETSO Deviations, Continued 1. Garmin was granted a deviation from ETSO-C118 section 3.1.1 to use RTCA DO-197A, instead of RTCA DO-197 as the Minimum Performance Standard. 2. Garmin was granted a deviation from ETSO-C118 section 3.1.2 to use EUROCAE ED-14F, instead of EUROCAE ED-14D as the standard for Environmental Conditions and Test Procedures for Airborne Equipment. 4. Garmin was granted a deviation from RTCA DO-197A section 2.2.3.
Table 1-8 TSO/ETSO Deviations, Continued 1. Garmin was granted a deviation from TSO-C147 section 1.c to use RTCA DO-160F, instead of RTCA DO-160D as the standard for Environmental Conditions and Test Procedures for Airborne Equipment. 2. Garmin was granted a deviation from TSO-C147 Appendix 1 section 1.6 to use selective Mode S interrogations as specified by RTCA DO-185A section 2.2.3.9 and 2.2.4.5.4.
1.6 Reference Documents The following publications are sources of additional information for installing the GTS Processor. Before installing the GTS Processor, the installer should read all referenced materials along with the manual.
1.
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2 INSTALLATION OVERVIEW 2.1 Introduction This section provides hardware equipment information for installing the GTS Processor and related hardware. Installation of the GTS Processor should follow the aircraft TC or STC requirements. Cabling is fabricated by the installing agency to fit each particular aircraft. The guidance of FAA advisory circulars AC 43.13-1B and AC 43.13-2B, where applicable, may be found useful for making retro-fit installations that comply with FAA regulations. 2.1.
Table 2-3 Connector Kits Connector Kits Garmin P/N GTS Processor Connector Kit 011-01360-00 GTS Connector Kit w/Config Module and USB Pigtail 011-01360-01 USB-B Pigtail (see GTS Configuration Options) 011-01782-00 Table 2-4 Optional Accessories Optional Accessories Garmin P/N 011-02817-00 T Color Coded Heat Shrink Kit NOTE R AF The GTS Processor is to be installed with a four-beam directional interrogation antenna mounted to the top of the aircraft as described in the antenna installation manu
2.2 Installation Considerations Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GTS Processor. 2.2.1 Antenna Considerations Refer to GA 58 Installation Manual 190-00587-20 for antenna installation information. 2.2.1.1 TAS/TCAS Antenna Location T NOTE For GTS 855/GTS 825 installations, either a monopole antenna or directional antenna may be used if installing an optional bottom mounted antenna.
2.4 Cabling and Wiring The contacts used to facilitate the use of #18 AWG wire, if used for Aircraft Power and Aircraft Ground, have expanded-diameter barrels that extend out from the back of the standard D-sub connector body to accommodate the larger diameter wire. Appropriate heat shrink tubing should be utilized to provide sufficient insulation from surrounding contacts.
R AF T attenuation of 3.0dB at 1090MHz for a GA 58 directional antenna installations, and 2.5 dB for low-profile directional antenna installations as shown in Figure 2-1. D Figure 2-1 GTS Processor Installation with Top and Bottom Directional Antennas If a bottom mount monopole antenna is installed, a single coaxial cable must be used to connect the GTS Processor bottom jack J1 BTM to the monopole antenna jack. The coaxial cable assembly shall not exceed the maximum attenuation of 3.
R AF T If no bottom mount antenna is installed, each of the GTS 855/GTS 825 bottom jacks (J1 BTM, J2 BTM, J3 BTM and J4 BTM) must be terminated with a 50Ω TNC termination shown in Figure 2-3. Figure 2-3 GTS 855/GTS 825 Installation with Top Directional Antenna and No Bottom Antenna 2.4.1.2 Fabrication of Coaxial Cable Assemblies NOTE TNC connectors, required to build coaxial cable assemblies, are not provided.
Loss of 2.5 dB Loss of 3.0 dB RG Type [4] Loss of 2.0 dB PIC Type [2] Loss of 1.5 dB ECS Type [1] Loss of 0.5 dB Max Cable Attenuation (dB/100ft) Max Terminated Cable Attenuation (including connector loss)* MIL-C-17 Type [3] Table 2-7 Recommended Coaxial Length M17/128RG400 RG-400 M17/60RG142 RG-142 Max Coaxial Cable Lengths** 10' 7" [3.23m] 11' 0" [3.35m] 11' 9" [3.58m] 14' 7" [4.45m] 15' 0" [4.57m] 15' 6" [4.72m] 20' 6" [6.25m] 24' 5" [7.44m] 24' 8" [7.52m] 13' 6" [4.11m] 14' 0" [4.
Coaxial cable "sets" are required for GTS Processor installations. Each coaxial cable "set", which consist of 4 coaxial cable assemblies, must be length matched to the tolerances shown in Table 2-2.
2.5 Cooling Requirements The GTS Processor meets all TSO requirements without external cooling, however the application of forced air cooling to the rear air nozzle of the GTS Processor is highly recommended to provide beneficial cooling the the unit. A 5/8” diameter air fitting for AIR is provided on the front of the GTS Processor for the purpose of admitting cooling air if desired. If an external cooling hose is used, it should blow into the AIR fitting.
2.6 Mounting Requirements R AF T The GTS Processor can be mounted vertically or horizontally using the installation racks shown in Figures 2-5 & 2-6. Refer to Appendix A for outline and installation drawings.
3 INSTALLATION PROCEDURE 3.1 Unpacking Unit Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment. If the unit is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return the unit to Garmin until the carrier has authorized the claim. Retain the original shipping containers for storage.
Table 3-3 Pin Contact GPN 336-00021-00 MIL SPEC M39029/58-360 Crimp Tooling Hand Crimping Tool Positioner Insertion/Extraction Tool Military P/N M22520/2-01 M22520/2-09 M81969/1-04 Daniels AFM8 K42 (Note 2) Positronic 9507-0 9502-4 (Note 2) ITT Cannon 995-0001-584 (Note 2) 274-7048-000 (Note 1) Tyco-AMP 601966-1 601966-6 91067-1 Astro 615717 615725 (Note 2) Amphenol (Note 2) Note 1 - Indicates plastic insertion/extraction tool Note 2 – Order by military part number T Manufactu
3.3 Backshell and Configuration Module Assemblies The GTS Processor connector kits includes three Garmin backshell assemblies. The backshell assembly houses the configuration module, if applicable. Garmin’s backshell also gives the installer the ability to easily terminate shield grounds at the backshell housing. Refer to the Jackscrew Backshell Installation Instructions (Garmin part number 190-00313-11) for backshell assembly instructions.
3.7 Downloading and Installing the GTS Processor Install Tool GTS Processor Configuration, Ramp Test, and Return to Service tests are performed (on some installations) using a computer (installed with Microsoft Windows XP or later) and the GTS Processor Install Tool, Garmin part number 006-A0242-10. The GTS Processor Install Tool allows for configuration, diagnostics, and upload of GTS Processor software. The tool is available for download from the Dealer Resource Center portion of the Garmin website (www.
T 5. On the PC, select ‘Next’ when prompted. Follow the wizard to setup the GTS Processor Install Tool. (Examples shown assume a Windows XP operating system, the required steps may vary with other Operating Systems.) R AF Figure 3-2 GTS Processor Install Tool – Installation 6. Select ‘Next’, when prompted or ‘Browse’, to select another folder. D Figure 3-3 GTS Processor Install Tool – Installation 7. Select ‘Next’, when prompted, to start the installation.
T 8. Wait until the installation has completed. Figure 3-5 GTS Processor Install Tool – Installation R AF 9. When the installation has completed, the following screen will be displayed. Select ‘Close.’ Figure 3-6 GTS Processor Install Tool – Installation 3.
1. Go to the Dealer Resource section of www.garmin.com and save the “GTS Assert Log Diagnosis Install Tool.zip” file from the website to the PC. 2. On the PC, locate the files “GTS Processor Install Tool.zip.” Extract the files from the zip file. 3. Select (double click) the “Assert_Log_Diagnosis.msi” file. R AF T 4. On the PC, select ‘Next’ when prompted. Follow the wizard to setup the GTS Processor Install Tool.
T 6. Select ‘Next’, when prompted to begin the installation. R AF Figure 3-9 GTS Assert Log Diagnosis Tool – Installation 7. The installation progress is displayed. D Figure 3-10 GTS Assert Log Diagnosis Tool – Installation 8. Verify that installation is successful, then select ‘Close’, to complete the installation.
3.9 Post Installation Configuration & Checkout The following actions must be performed after initial installation and after the equipment has been removed/disconnected then reinstalled/reconnected : 1. GTS Processor Configuration (Section 3.8.2) 2. Suppression Bus I/O Check (Section 3.8.3) 3. CDTI (Cockpit Display of Traffic Information) Display 4. Setup and Configuration (Section 3.8.4) 5. Calibration/Self Test (Section 3.8.5) 7. Antenna Verification (Section 3.8.7) T 6.
NOTE Please check the aircraft warranty status before installation and/or with the aircraft manufacturer for guidance. NOTE ADS-B receive functionality is not available in a Field Approved Garmin Integrated Flight Deck installation. T 3.9.1.
R AF T Normal System Mode Tab The Normal Tab displays various faults, flags, and operational information. When the Normal Tab is selected, the unit is commanded to Normal System Mode. ‘Alpha Values’ phase measurement values for the Top Antenna and Bottom Antenna (if a bottom directional antenna is installed) are found on the GTS Processor Install Tool Normal tab, and are updated only after a self-test (Section 3.8.5) is run.
R AF T Configuration System Mode Tab The Configuration Tab displays configuration data and allows the installer to change the installation configuration. When the Configuration Tab is selected, the unit is commanded to Configuration System Mode. Figure 3-13 GTS Processor Install Tool – Configuration Tab (GTS 825 and GTS 855) D The Configuration Tab displays installation configuration options. Changes made in the Configuration Tab are not immediately committed to the GTS.
Configuration Mode – Barometric Altitude Source: Note: At least one source must be selected (same altitude source used for the transponder).
Bottom Antenna: Model None Monopole Garmin GA58 Sensor Systems Cable loss (dB) 0.2 – 4.0 Note: Cable loss information is described in Fabrication of Coaxial Cable Assemblies Section 2.4.1.2. Note: All A429 options have the ability to select High or Low speed. T 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. R AF Volume Level: Allows audio volume level selection from 0 to -63 dB in 0.
R AF T Upload System Mode Tab The Upload Tab displays version information for Boot Block, Region List, System, FPGA, Audio and Magnetic Variation. Boot Block updating is not allowed. For other files, select the appropriate image files and select upload.
R AF T Assert Tab The Assert Tab gets and displays the contents of the assert log from the GTS. Select ‘Get Assert Log’ to retrieve the assert log from the GTS and ‘Save Assert Log to File’ to save the received log to a text file. Figure 3-15 GTS Processor Install Tool – Assert Tab 3.9.3 Suppression Bus I/O Check Other equipment onboard the aircraft may transmit and receive in the same frequency band as the GTS Processor (e.g. DME or transponder).
3.9.4 CDTI (Cockpit Display of Traffic Information) Display Setup and Configuration For configuration of the displays, refer to their respective manuals. 500 Series Installation Manual (190-00181-02) GMX 200 Installation Manual (190-00607-04) GDU 620 Installation Manual (190-00601-04) GTS Processor System Maintenance Manual (190-00587-51) G1000 System Maintenance Manual LJ/VLJ (190-00903-00) 3.9.
T g) Whisper Shout fault – Transmitted power is out of tolerance. Check cable loss configuration, antenna installation and all cable connections and retry self test. If fault persists, return unit to Garmin for service. h) Transmit Power fault - One of the internal transmitter power source voltages are out of range. Fault will persist until power is cycled. Check aircraft power supply. If fault persists, return unit to Garmin for service. i) 1030 MHz fault - Transmit Frequency synthesizer is not locked.
The self test feature also checks the following external parameters: R AF T 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.
Audio annunciation shall be: GTS 825 - “TAS system Passed” or “TAS system Failed” GTS 855 - “TCAS I system Passed” or “TCAS I system Failed” GTS 8000 - "TCAS II system Passed" or "TCAS II system Failed" Any faults and flags are also displayed on the Normal Tab of the GTS Processor Install Tool. Faults that occur will be colored in red and flags will be colored in black. If self test fails, refer to the diagnostics data to determine a cause. Ensure that no Intruder appears at close range to own aircraft.
Ground Test Procedure: The GTS Processor must be in Ground Test mode to select a scenario that will properly converge and intercept the GTS Processor. The aircraft must be on the ground and the GTS Processor must be in Normal System mode and in Standby, to enable Ground Test mode. NOTE The GTS Processor will not accept the Ground Test command unless the unit is in Standby and the squat switch indicates the aircraft is on the ground.
3.9.7 Antenna Verification NOTE The GTS Processor must be in Ground Test mode to perform the antenna verification. Refer to Section 3.8.6 for Ground Test mode information. The first step in antenna verification is to verify auto-calibration operates without indicating a fault. T 1. With the GTS Processor powered up and “Standby” indicated on the CDTI (Cockpit Display of Traffic Information) cycle the GTS Processor to “Operate”.
16. Toggle intruder traffic to standby or off. 17. Reposition ramp test set and directional antenna to an aft position of 180 degrees. 18. Reengage the same intruder scenario as above. 19. Verify a target is annunciated on the GTS Processor TAS/TCAS display at the correct bearing of approximately 180 degree azimuth at 2 NM and co-altitude. 20. Toggle intruder traffic to standby or off. 21. Reposition ramp test set and directional antenna to a port position of 270 degrees. T 22.
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4 SYSTEM INTERCONNECTS 4.1 GTS Processor Pin Function List 4.1.
Table 4-1 P8001 Connector, continued Pin Name I/O 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 ARINC 429 IN 4 B RS-422 IN A RS-422 IN B SIGNAL GROUND CONFIG MODULE DATA SIGNAL GROUND ARINC 429 OUT 5 A ARINC 429 OUT 5 B ARINC 429 IN 5 A ARINC 429 IN 5 B SIGNAL GROUND ARINC 429 OUT 6 A ARINC 429 OUT 6 B ARINC 429 IN 6 A ARINC 429 IN 6 B SIGNAL GROUND ETHERNET OUT A ETHERNET OUT B ETHERNET IN A ETHERNET IN B SIGNAL GROUND RS
4.1.
Pin Name 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED SIGNAL GROUND SIGNAL GROUND HEADING X HI HEADING X LO (GROUND) SIGNAL GROUND HEADING Y HI HEADING Y LO (GROUND) SIGNAL GROUND SPARE EXTERNAL SUPPRESSION I/O SIGNAL GROUND ANNUN* 1 (CORRECTIVE RA)*** ANNUN* 1 (TA DISPLAY ENABLE)*** ANNUN* 2 (PREVENTIVE RA)*** ANNUN* 2 (AURAL TA)*** SPARE ANNUN* 3 (VISUAL TA) TRAFFIC SYSTEM STATUS VALID* RESERVED A
Table 4-2 P8002 Connector, continued Applicable Model** Pin Pin Name 71 72 73 74 75 76 77 78 ANALOG RADAR ALTIMETER HI ANALOG RADAR ALTIMETER LO SIGNAL GROUND SELF TEST INITIALIZE SELECT* TRAFFIC OPERATE/STANDBY* ANALOG RADAR ALTIMETER VALID SPARE SIGNAL GROUND I/O In In -In In In --- D R AF T *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.
4.1.
4.2 Power 4.2.1 Aircraft Power Functions This section covers the power input requirements. 4.2.1.1 Aircraft Power Table 4-4 Aircraft Power Pin Name Pin I/O P8003 P8003 P8003 P8003 P8003 P8003 P8003 P8003 2 3 4 5 21 22 23 24 In In In In ----- T AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 POWER GROUND POWER GROUND POWER GROUND POWER GROUND Connector R AF Pins 2 and 3 are internally connected to form AIRCRAFT POWER 1.
4.3 Serial Data 4.3.1 RS-232 Table 4-7 RS-232 Connector Pin I/O P8001 P8001 P8001 P8001 P8001 P8001 P8001 P8001 2 3 5 6 8 9 11 12 Out In Out In Out In Out In T Pin Name RS-232 OUT 1 RS-232 IN 1 RS-232 OUT 2 RS-232 IN 2 RS-232 OUT 3 RS-232 IN 3 RS-232 OUT 4 RS-232 IN 4 The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5V when driving a standard RS-232 load. R AF 4.3.
4.3.
4.3.5 USB Table 4-11 USB Pin Name Connector Pin I/O USB VBUS POWER** P8001 75 In USB DATA HI** P8001 76 I/O USB DATA LO** P8001 77 I/O USB GROUND P8001 78 -**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. 4.4 Configuration 4.4.1 Configuration Module T This interface is used for unit configuration and software uploads. Conforms to the Universal Serial Bus Version 1.
4.5.1.2 Radar Altimeter Table 4-14 Radar Altimeter Pin Name ANALOG RADAR ALTIMETER HI ANALOG RADAR ALTIMETER LO Connector Pin I/O P8002 P8002 71 72 In In Provides altitude information during approach. Input voltage range is 0 to 30Vdc. Compatible with Radar Altimeters listed in section 3.5.2.4. 4.5.
4.5.3 Audio Table 4-16 Audio Pin Name Connector Pin I/O P8002 P8002 58 59 Out Out ALERT AUDIO OUT HI ALERT AUDIO OUT LO NOTE Alert Audio shield should only be connected to ground on the Audio Panel end. T 4.5.
NOTE The ‘sense’ of the AIR/GROUND* and the GEAR DOWN AND LOCKED* Active Low Discrete Inputs are configurable using the GTS Processor Install Tool. Two discrete inputs (CLIMB INHIBIT* 1 and CLIMB INHIBIT* 2) have been provided to indicate that the aircraft cannot climb at the rate of 1500 feet per minute. The 1500 fpm climb limit condition should be assumed whenever CLIMB INHIBIT* 1 OR CLIMB INHIBIT* 2 are active.
4.5.6 Annunciator Output Table 4-19 Annunciator Output Applicable Model** ANNUN* 1 (CORRECTIVE RA) ANNUN* 1 (TA DISPLAY ENABLE) ANNUN* 2 (PREVENTIVE RA) ANNUN* 2 (AURAL TA) ANNUN* 3 (VISUAL TA)*** TRAFFIC SYSTEM STATUS VALID* GTS 8000 GTS 855/ GTS 825 GTS 8000 GTS 855/ GTS 825 Connector Pin I/O P8002 50 Out P8002 51 Out P8002 P8002 53 54 Out Out T Pin Name R AF *Denotes that the signal is Active Low. ACTIVE: 0 V ≤ Vout ≤ 0.
APPENDIX A Outline and Installation Drawings R AF T 1.99 50.5 TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY 6.74 171.1 TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY 13.49 342.5 TBD CENTER OF GRAVITY 6X NOTE 3 TBD CENTER OF GRAVITY D 3.67 93.1 3.32 84.2 NOTES: 1. DIMENSIONS: INCHES [mm] 2. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. 3. MOUNTING HOLE FOR FOR #8 PANHEAD SCREW. .625 15.88 GTS Processor Installation Manual 190-00587-50 .18 4.4 7.00 177.8 4.375 111.
GTS PROCESSOR UNIT 011-02571-00 R AF T APPENDIX A Outline and Installation Drawings CONNECTOR KIT 011-01360-00 (UNSEALED) OR 011-01360-10 (SEALED) 011-01855-03 NOTE 1 330-00366-78 (UNSEALED) OR 330-00776-78 (SEALED) (2 PLACES) 330-00502-37 (UNSEALED) OR 330-00853-37 (SEALED) D 011-01855-04 (2 PLACES) NOTE 1 GTS PROCESSOR VERTICAL RACK 011-02572-00 NOTES: 1.
APPENDIX A Outline and Installation Drawings TBD CENTER OF GRAVITY TBD CENTER OF GRAVITY R AF TBD CENTER OF GRAVITY T 1.99 50.5 3.48 88.3 HEIGHT WITHOUT FEET 4.10 104.1 HEIGHT WITH FEET TBD CENTER OF GRAVITY 12.80 325.1 TBD CENTER OF GRAVITY NOTES: 1. DIMENSIONS: INCHES [mm] 2. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY. 3. MOUNTING HOLE FOR #8 PANHEAD OR SOCKET HEAD CAP SCREW. RECOMMENDED LENGTH .750 INCHES MINIMUM. 4. MOUNTING FEET MAY BE REMOVED WHEN DESIRED FOR INSTALLATION.
APPENDIX A Outline and Installation Drawings D R AF NOTES: 1. RACK MAY BE INSTALLED WITH MOUNTING FEET ATTACHED, OR AFTER REMOVAL OF MOUNTING FEET. 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.
R AF T APPENDIX B Interconnect Examples D 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.
APPENDIX B Interconnect Examples R AF T GTS PROCESSOR D BOTTOM ANTENNA IS OPTIONAL FOR GTS 855 AND GTS 825 INSTALLATIONS. BOTTOM ANTENNA IS REQUIRED FOR GTS 8000 INSTALLATIONS.
APPENDIX B Interconnect Examples ETHERNET OUT A Garmin GDL 69/69A P8001 P691 52 27 ETHERNET IN 2 A ETHERNET OUT B 53 26 ETHERNET IN 2 B ETHERNET IN A 54 29 ETHERNET OUT 2 A ETHERNET IN B 55 28 ETHERNET OUT 2 B S S Garmin GTS PROCESSOR Garmin GIA 63/63W P603 ARINC 429 OUT 1 A 14 8 MAIN ARINC 429 IN 3 A ARINC 429 OUT 1 B 15 9 MAIN ARINC 429 IN 3 B SUPPRESSION I/O P8002 P3301 S S ARINC 429 IN 1 A 16 74 MAIN ARINC 429 OUT 3 B 17 75 MAIN ARINC 429 OUT 3 A RED 75 76
GTS Processor Installation Manual 190-00587-50 11 6 10 58 59 TA INHIBIT* 1 AIR/GROUND* GEAR DOWN AND LOCKED* AUDIO ALERT OUT HI AUDIO ALERT OUT LO 2 3 4 5 21 22 23 24 AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT POWER POWER GROUND POWER GROUND POWER GROUND POWER GROUND P8003 74 75 P8002 75 76 77 78 22 16 17 SELF TEST INITIALIZE SELECT* TRAFFIC OPERATE/STANDBY* USB VBUS POWER USB DATA HI USB DATA LO USB GROUND S S INSTALLER MAY SELECT DIFFERENT GIA ARINC CHANNELS THAN THOSE LIST
T APPENDIX B Interconnect Examples GTS PROCESSOR D R AF GTS PROCESSOR GTS Processor Installation Manual 190-00587-50 Figure B-5 GTS Processor GNS 4XX/5XX/GMX 200 Interconnect Example Page B-5 Revision A
APPENDIX B Interconnect Examples GTS PROCESSOR GTX 330 ES/GTX 3000 D R AF THESE CONNECTIONS NOT REQUIRED FOR GTX 3000 INSTALLATION FOR GTX 3000, BARO OUT AND NTA COUNT INFO ARE OUTPUT ON A SINGLE ARINC CHANNEL T } GTS PROCESSOR WHEN INSTALLING A RADAR ALTIMETER THAT DOES NOT HAVE AN ACTIVE HIGH ANALOG FLAG OUTPUT, THE GTS 8XX ANALOG RADAR ALTIMETER VALID INPUT (PIN 76) SHOULD BE CONNNECTED TO AIRCRAFT POWER GTS Processor Installation Manual 190-00587-50 Figure B-6 GTS Processor GMA/HSI/Altimeter
APPENDIX B Interconnect Examples T GTS PROCESSOR 4 P8001 75 76 77 78 RED GRN WHT BLK R AF USB VBUS POWER USB DATA HI USB DATA LO USB GROUND 28 AWG 28 AWG s 1 3 2 4 SHELL USB TYPE B RECEPTACLE VBUS D+ DGND SHIELD 5 NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT THE GTS PROCESSOR, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0 ".
GTS Processor Installation Manual 190-00587-50 RA DISPLAY 1 VALID 3 RA DISPLAY STATUS VALID* 2 (GTS 8000 ONLY) ANNUN* 3 VISUAL TA ALERT* ANNUN* 2 AURAL TA ANNUN* 1 (CORRECTIVE AURAL* RA - GTS 8000 / TA DISPLAY ENABLE* - GTS 855/GTS 825) ADVISORY CANCEL* 2 RA DISPLAY STATUS VALID* 1 (GTS 8000 ONLY) RA DISPLAY 2 VALID RA DISPLAY 2 INVALID RA DISPLAY 1 VALID RA DISPLAY 1 INVALID T RA DISPLAY 2 VALID R AF D GTS PROCESSOR APPENDIX B Interconnect Examples Figure B-8 GTS Processor Discrete Interc
R AF T APPENDIX B Interconnect Examples D GARMIN GTS PROCESSOR GTS Processor Installation Manual 190-00587-50 Figure B-9 GTS Processor Configuration Module Interconnect Example Page B-9 Revision A
APPENDIX B Interconnect Examples GTS 820/850 GTX GTX 33/33D 327/32/ 330/330D 320A P3301 P3271 4 ARINC 429 OUT 3 A ARINC 429 OUT 3 B 28 29 ARINC 429 IN 3 A ARINC 429 IN 3 B 30 31 GARMIN TRANSPONDER #2 P3281 T P8001 GTX 328 s s 33 36 --- 33 36 ARINC 429 IN 2 A ARINC 429 IN 2 B 30 28 --- 30 28 ARINC 429 OUT 2 A ARINC 429 OUT 2 B 13 17 R AF 31 EXTERNAL STANDBY SELECT 31 EXTERNAL SUPPRESSION I/O GTX 328 GARMIN TRANSPONDER #1 TRANSPONDER 1 ARINC 429 OUT 2 A ARINC 429 OUT 2 B 23 24
