Installation Manual

ManualsBrandsGarmin ManualsMarine RadarGTX 23 Marine RADAR

190-00906-01 June, 2014 Revision C

GTX 23

Transponder

Installation Manual

Summary of content (55 pages)

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GTX 23 Transponder Installation Manual 190-00906-01 June, 2014 Revision C
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© 2014 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.
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INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations ("EAR") issued by the United States Department of Commerce (15 CFR, Chapter VII, Subchapter C) and which may not be exported, released, or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual.
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CURRENT REVISION DESCRIPTION Revision Page Number(s) Section Number 1-5 1.7 1-8 1.9.2 Updated TSO/ETSO Deviations Table 1-6 1-9 1.10 Updated operating instructions info 2-1 2.2 Added new unit w/system rack part number 2-1 2.2.1 Added modular rack to equipment available table 2-2 2.2.2 Added modular rack mounting hardware info 2-5, 2-6 2.6, 2.6.1, & 2.6.
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Aviation Limited Warranty All Garmin avionics products are warranted to be free from defects in materials or workmanship for: two 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.
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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 1.3 ADS-B Capabilities .........................................................................................
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PARAGRAPH PAGE Appendix B SHIELD BLOCK INSTALLATION INSTRUCTIONS ..........B-1 B.1 Shield Block Installation Parts ........................................................................................B-1 B.2 Shield Termination Technique – Method A.1 (Standard)...............................................B-3 B.3 Shield Termination Technique - Method A.2 (Daisy Chain).........................................B-7 B.4 Shield Termination – Method B.1 (Quick Term)............................................
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LIST OF FIGURES FIGURE PAGE Section 1 GENERAL DESCRIPTION .............................................................1-1 Section 2 INSTALLATION OVERVIEW........................................................2-1 Figure 2-1. Antenna Installation Considerations ................................................................... 2-3 Figure 2-2. GTX 23 Stand-Alone Rack (115-00629-00)....................................................... 2-6 Figure 2-3. GTX 23 Modular Rack (115-00438-00) ...................
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LIST OF TABLES TABLE PAGE Section 1 GENERAL DESCRIPTION .............................................................1-1 Table 1-1 ADS-B Versions.................................................................................................... 1-2 Table 1-2 Physical Characteristics......................................................................................... 1-5 Table 1-3 General Specifications...........................................................................................
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1 GENERAL DESCRIPTION 1.1 Introduction This manual is intended to provide mechanical and electrical information for use in the planning and design of an installation of the GTX 23 into an aircraft. This manual is not a substitute for an approved airframe-specific maintenance manual, installation design drawing, or complete installation data package.
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1.3 ADS-B Capabilities The GTX 23 provides the capabilities of Automatic Dependent Surveillance-Broadcast (ADS-B) technology, which improves situational awareness and flight safety. With ADS-B capabilities, position, velocity, and heading information are automatically transmitted to other aircraft and ground stations. The current air traffic control system depends on a transponder request for pertinent aircraft information. ADS-B provides automatic transmission of aircraft information without a request.
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1.3.1.1 Installation Approval of Version 1 ADS-B Systems GTX 23 w/ES transponders running software versions v6.00 through v6.20 support Version 1 ADS-B Out functionality. According to AIR-130 Policy Memo ‘Approval for ADS-B Out Systems’, dated August 30, 2010, the FAA has suspended field approvals of Version 2 ADS-B Out equipment. At the time of this publication, there is currently no FAA policy addressing field approvals of Version 0 or Version 1 systems.
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1.5 Mutual Suppression Pulses Other equipment on board the aircraft may transmit in the same frequency band as the transponder. DME, TCAS, or another transponder are examples of equipment that operate in the same frequency band. Mutual suppression is a synchronous pulse that is sent to the other equipment to suppress transmission of a competing transmitter for the duration of the transmission.
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1.7 Technical Specifications 1.7.1 Physical Characteristics Table 1-2 Physical Characteristics Characteristic Specification Modular Rack Width 1.72 inches [44 mm] Modular Rack Height 6.30 inches [160 mm] Modular Rack Weight 0.4 lbs [0.18 kg] Stand-Alone Rack Width 1.78 Inches (45 mm) Stand-Alone Rack Height 6.92 Inches (176 mm) Stand-Alone Rack Weight 0.9 lbs. (0.41 kg) Depth Including Connectors (measured from front face of unit to rear of connector backshells) 11.
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Table 1-3 General Specifications Characteristic Specification External Suppression Output Output: minimum is +18V (for 300 ohm load) and maximum of +23V (for 2000 ohm load) Audio Output 4.04 Vrms to 7.85 Vrms into a 500 ohm load 1.7.3 Power Requirements Table 1-4 Power Requirements Characteristic Specification Input Voltage 14/28 Vdc See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages.
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1.9.
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1.9.2 TSO/ETSO Deviations Table 1-6 TSO/ETSO Deviations TSO/ETSO Deviation 1. Garmin was granted a deviation from TSO-C112 to use RTCA DO-178B instead of RTCA DO-178A. 2. Garmin was granted a deviation from TSO-C112 to use RTCA DO-160D instead of RTCA DO-160B. TSO-C112 3. Garmin was granted a deviation from TSO-C112 to use RTCA DO-181C instead of RTCA DO-181. 4. Garmin was granted a deviation from DO-160D, section 20.3.d. 5. Garmin was granted a deviation from DO-181C section 2.2.16.2.6.
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1.10 Operating Instructions The GTX 23 is a remote-mount LRU with no user controls or indicators. All user interface is accomplished through a compatible display device. Although different displays will handle the transponder interface differently, all will typically have the following user inputs: Mode Selection: 1. Standby Mode: In Standby Mode, the GTX 23 will not reply to interrogations. 2.
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2 INSTALLATION OVERVIEW 2.1 Introduction This section provides hardware equipment information for installing the GTX 23 Mode S transponder, related hardware, and optional accessories. Installation of the GTX 23 should follow the data detailed in this manual. 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.
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2.2.2 Additional Equipment Required The following installation accessories are required but not provided: • • • • Cables – The installer will supply all system cables including circuit breakers. Cable requirements and fabrication is detailed in Section 3 of this manual. Hardware – #6-32 x 100° Flathead SS Screw [(MS24693, AN507R or other approved fastener) (4 ea.)] for horizontal mounting of the remote stand-alone rack.
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2.3 Installation Considerations 2.3.1 Preservation of Previous Systems It is the installer’s responsibility to preserve the essential characteristic of the aircraft being modified with this equipment to be in accordance with the aircraft manufacturer’s original design. This includes the preservation of multiple power buses, which reduces the probability of interrupting power to essential instruments and avionics. 2.3.
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2.4 Cabling and Wiring Refer to the interconnect examples in Appendix C for wire gauge guidance. 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.
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2.4.1 Cable Routing Considerations After the cable assemblies are made and wiring installed to the rack back plate, route wiring bundle as appropriate. Use cable ties to secure the cable assemblies and coax to provide strain relief for the cable assemblies. When routing cables, observe the following precautions: • All cable routing should be kept as short and as direct as practical. • Avoid sharp bends to prevent insulation from being breached.
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Figure 2-2. GTX 23 Stand-Alone Rack (115-00629-00) Figure 2-3. GTX 23 Modular Rack (115-00438-00) 190-00906-01 Rev.
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Figure 2-4. GTX 23 Stand-Alone Rack, Suggested Mounting Locations 190-00906-01 Rev.
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3 INSTALLATION PROCEDURE 3.1 Unpacking Unit Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment. If the unit is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return the unit to Garmin until the carrier has authorized the claim. Retain the original shipping containers for storage.
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Table 3-2 Recommended Crimp Tools (High Density) 18-20 AWG Manufacturer (note 1) Hand Crimping Tool Positioner 22-28 AWG Insertion/ Extraction Tool Positioner Insertion/ Extraction Tool (note 2) Military P/N M22520/2-01 N/A M81969/1-04 M22520/2-09 M81969/1-04 Positronic 9507-0 9502-11 M81969/1-04 9502-4 M81969/1-04 AMP 601966-1 N/A 91067-1 601966-6 91067-1 Daniels AFM8 K774 M81969/1-04 K42 M81969/1-04 Astro 615717 N/A M81969/1-04 615725 M81969/1-04 1) Non-Garmin part num
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3.7 Final Installation For final installation and assembly, refer to the outline and installation drawings shown in Appendix D of this manual. a. Assemble the connector backshell as described in Appendix B. b. Attach the connector to the rear plate using the screws provided in the connector kit. c. Mount the unit rack to a mounting location that considers the mounting requirements in Section 2.6. d. Assemble the rear plate into the GTX 23 unit rack using screws provided with the rear plate. e.
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3.8.3 Performance (Ramp) Test CAUTION If the unit is removed from the aircraft and operated, always connect J2302 to an antenna or a 50 Ω, 5-Watt load. The GTX 23 transmits Mode S acquisition squitters about once per second whether interrogations are received or not.
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4 SYSTEM INTERCONNECTS 4.1 Pin Function List 4.1.1 P2301 21 20 42 19 41 62 18 40 61 17 39 60 16 38 59 15 37 58 14 36 57 13 35 56 12 34 55 11 33 54 10 32 53 9 31 52 8 30 51 50 7 29 49 6 28 48 5 4 27 26 47 3 25 46 2 24 1 23 22 44 Figure 4-1.
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Table 4-1 P2301 Pin Assignments Pin Pin Name I/O 31 MUTUAL SUPPRESSION I/O I/O 32 NOT USED -- 33 NOT USED -- 34 ARINC 429 OUT 1 B 35 NOT USED 36 NOT USED 37 ARINC 429 OUT 1 A 38 NOT USED -- 39 POWER GROUND -- 40 NOT USED -- 41 NOT USED -- 42 AIRCRAFT POWER 1 In 43 RS-232 GROUND -- 44 NOT USED -- 45 NOT USED In 46 TIS CONNECT SELECT* In 47 NOT USED -- 48 NOT USED -- 49 NOT USED -- 50 RS-232 GROUND 2 -- 51 NOT USED -- 52 NOT USED -- 53 NOT USED
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4.1.2 Aircraft Power Power input requirements are listed in the following tables. The power input pins accept 14/28 Vdc. Refer to Figure C-1 and C-2 for power interconnections. Table 4-2 Aircraft Power Pin Name Connector Pin I/O AIRCRAFT POWER 1 P2301 21 In AIRCRAFT POWER 1 P2301 42 In AIRCRAFT POWER 2 P2301 56 In AIRCRAFT POWER 2 P2301 60 In POWER GROUND P2301 39 -- POWER GROUND P2301 58 -- 4.2 Discrete Functions 4.2.
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4.2.2 Discrete Inputs Sink current is internally limited to 200 uA max for a grounded input EXTERNAL IDENT SELECT (remote IDENT) is a momentary input. When grounded, it activates the IDENT pulse for 18 seconds in Mode A replies. EXTERNAL STANDBY SELECT (remote STANDBY) is not a momentary input. When EXTERNAL STANDBY SELECT is grounded, the GTX 23 operates in standby mode. In this mode, the transponder will not squitter or reply to interrogations. TIS CONNECT SELECT is a momentary input.
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4.3 Serial Data Electrical Characteristics 4.3.1 RS-232 Input/Output RS-232 input #1 is used to receive pressure altitude control commands. RS-232 output #1 provides unit status and TIS data. RS-232 #1 input and output are also used for software upgrades. For installations that enable ADS-B, RS-232 input #2 should be connected to a GNS 400W/500W-series WAAS enabled unit or a GTN 6XX/7XX series unit. This connection provides the GTX 23 with GPS data for ADS-B. The RS-232 output #2 is unused on the GTX 23.
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4.4 RS-232 Input/Output, Software Update Connections GTX 23 software is updated using the RS-232 #1 interface. When wiring the RS-232 #1 interface to the rest of the system, it may be useful to splice in a pigtail connector that could be plugged into a laptop computer. Also when wiring, consider that the GTX 23 must be turned on (during software update) and the other avionic equipment attached to the RS-232 #1 interface (e.g. GSU or GDU) must be turned off.
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APPENDIX A CONSTRUCTION AND VALIDATION OF STRUCTURES A.1 Static Test Loading This appendix includes information necessary for testing load-carrying capabilities of equipment mounting structures, such as shelves, mounting plates and mounting brackets, used to mount the GTX 23 remote mounting racks. Baggage compartments and cabins or cockpit floors are good mounting platforms providing the floor attachments meet the strength requirements.
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7. Examine the support structure carefully. If there has been damage or permanent deformation, the structure is not suitable and must be replaced with one that is strong enough to withstand the test loads. Examine all aircraft stringers, bulkheads and skin surfaces, which may have direct or indirect contact with the fabricated shelf.
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APPENDIX B SHIELD BLOCK INSTALLATION INSTRUCTIONS B.1 Shield Block Installation Parts CAUTION Disclaimer: This instruction manual assumes skill and knowledge of aircraft harness fabrication techniques. DO NOT PERFORM THIS INSTALLATION IF YOU ARE UNQUALIFIED. Tables B-1 & B-2 list parts needed to install a Shield Block in a D-Sub connector. The Item Numbers listed in Tables B-1 & B-2 coincide with the Item Numbers in Figure B-1.
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NOTE In Figure B-1, “AR” denotes quantity “As Required” for the particular installation. 18 Figure B-1 Shield Block Installation (78 pin example) 190-00906-01 Rev.
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B.2 Shield Termination Technique – Method A.1 (Standard) NOTE For the following steps please refer to Figure B-l. 1. Attach the Shield Block(s) (Item 2) to the backshell (Item 1) by inserting the flathead screws (Item 3) through the holes on the Shield Block and threading into the tapped holes on the backshell (Item 1) (see Figure B-1). Figure B-2 Method A.
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3. Connect a Flat Braid (Item 6) to the shield exposed through the window of the prepared cable assembly (Item 4) from step 2. The Flat Braid should go out the front of the termination towards the connector. It is not permitted to exit the rear of the termination and loop back towards the connector (Figure B-2). Make this connection using an approved shield termination technique. NOTE FAA AC 43.
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Secondary Method: Solder a Flat Braid (Item 6) to the shield exposed through the window of the prepared cable assembly (Item 4). Ensure a solid electrical connection through the use of acceptable soldering practices. Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire. Slide a minimum 0.75 inches of Teflon heat shrinkable tubing (Item 5) onto the prepared wire assembly and shrink using a heat gun.
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6. Insert newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams. 7. Cut the Flat Braid (Item 6) to a length that, with the addition of a ring terminal, will reach one of the tapped holes of the Shield Block (Item 2) (Figure B-1). An appropriate amount of excess length without looping should be given to the Flat Braid (Item 6) to allow it to freely move with the wire bundle.
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B.3 Shield Termination Technique - Method A.2 (Daisy Chain) In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal (Figure B-4). All other restrictions and instructions for the shield termination technique set forth for Method A.1 are still applicable. NOTE The maximum length of the combined braids should be approximately 4 inches. Figure B-4 Method A.
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At the end of the shielded cable (Item 4), strip “Quick Term Min” to “Quick Term Max” (Table B-4) length of the jacket to expose the shield. Next trim the shield so that at most 0.35 inches remains extending beyond the insulating jacket. Fold this remaining shield back over the jacket. Connect a Flat Braid (Item 6) to the folded back shield of the prepared cable assembly. The flat braid should go out the front of the termination towards the connector.
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Table B-4 Shielded Cable Preparations – (Quick Term) Backshell Size Number of Pins Std/HD Quick Term Min (inches) Quick Term Max (inches) Quick Term Float (inches) 1 9/15 1.25 2.25 1.75 2 15/26 1.5 2.5 2.0 3 25/44 1.5 2.5 2.0 4 37/62 1.5 2.5 2.0 5 50/78 1.5 2.5 2.0 B.5 Shield Termination-Method B.
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B.6 Daisy Chain between Methods A and B In rare situations where more braids need to be terminated for a connector than three per ring terminal and a mixture of Methods A and B have been used, it is allowable to daisy chain a maximum of two shields together from a Method A termination to a Method B (Figure B-7). All other restrictions and instructions for the shield termination technique set forth for Method A and B are still applicable.
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Figure B-8 D-Sub Spliced Signal Wire illustration 190-00906-01 Rev.
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APPENDIX C INTERCONNECT DRAWINGS (Example Only) GTX 23 P2301 XPDR CIRCUIT BREAKER 21 42 39 XPDR CIRCUIT BREAKER 56 60 58 EXTERNAL IDENT SELECT 12 MUTUAL SUPPRESSION I/O 31 RS-232 OUT 1 23 18 RS-232 IN 1 22 19 RS-232 OUT 3 RS-232 GROUND 43 40 SIGNAL GROUND SEE NOTE 3 GSU 73 P731 RS-232 IN 3 NOTES: 1. USE 22 AWG WIRE FOR AIRCRAFT POWER AND AIRCRAFT GROUND. ALL OTHER WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED. 2.
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APPENDIX C INTERCONNECT DRAWINGS (EXAMPLE ONLY) GTX 23 GNS 430W/530W P2301 RS-232 IN 2 24 RS-232 GROUND 2 50 P4001/5001 58 OR GTX 23 P2301 GPS RS-232 OUT 2 GTN 6XX/7XX P1001 RS-232 IN 2 24 8 RS-232 OUT 1 RS-232 GROUND 2 50 46 RS-232 GROUND 1 NOTES: 1. IF THE INSTALLATION DOES NOT INTEND TO TRANSMIT ADS-B INFORMATION, THEN NONE OF THE CONNECTIONS ON THIS PAGE ARE NECESSARY.
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APPENDIX C Interconnect Drawings (Example Only) GTX 23 P2301 GNS 4XX/5XX P4001/5001 ARINC 429 OUT 2 A 30 50 ARINC IN 2A ARINC 429 OUT 2 B 28 51 ARINC IN 2B TIS CONNECT SELECT 46 11 ANNUNCIATE E NOTES: 1. THE CONNECTIONS ON THIS PAGE ARE OPTIONAL. THE GDU 37X WILL DISPLAY TIS DATA. THESE CONNECTIONS ENABLE TIS TO BE DISPLAYED ON A GNS 4XXW/5XXW-SERIES UNIT. 2. IF TIS WILL BE DISPLAYED ON A GNS, THE GNS MUST BE CONFIGURED FOR THIS SETUP. PLEASE SEE THE FOLLOWING CONFIGURATION GUIDANCE. 3.
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APPENDIX D OUTLINE AND INSTALLATION DRAWINGS 175.7 6.92 164.9 6.49 90 3.6 CENTER OF GRAVITY 135 5.3 CENTER OF GRAVITY 23 .9 CENTER OF GRAVITY 246.0 9.69 290.0 11.42 48.7 1.92 158.8 6.25 4X 4.8 .19 29.0 1.14 45.3 1.78 8.2 .
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APPENDIX D OUTLINE AND INSTALLATION DRAWINGS 115-00629-00 211-63234-11 (2 PLACES) 330-00185-62 011-00950-03 NOTE 3 CONNECTOR KIT 011-01012-01 011-01169-01 NOTE 3 211-60234-08 (2 PLACES) 330-00053-01 (BNC) OR 330-00053-02 (TNC) BACKPLATE ASSEMBLY 011-00582-XX 125-00002-00 212-00022-00 NUT SUPPLIED WITH 330-00053-XX NOTES: 1. IF REMOVED, APPLY 291-00023-02 THREAD LOCKING COMPOUND TO ALL THREADED FASTENERS BEFORE REINSTALLATION. 2.
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APPENDIX D OUTLINE AND INSTALLATION DRAWINGS 6X NOTE 3 184.4 7.26 160.0 6.30 81 3.2 CENTER OF GRAVITY 124 4.9 CENTER OF GRAVITY 244.8 9.64 273.6 10.77 288.8 11.37 9.91±0.25 .390±.010 43.6 1.72 6X NOTE 3 (BOTH SIDES) 12.19±0.25 .480±.010 TYP. NOTES: 1. DIMENSIONS: INCHES [mm] 2. DIMENSIONS SHOWN ARE FOR REFERENCE ONLY. 3. MOUNTING HOLES FOR #6 FLAT HEAD 100° CSK SCREW (18 PLACS). 9.58±0.25 .377±.010 85.09±0.25 3.350±.
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APPENDIX D OUTLINE AND INSTALLATION DRAWINGS 115-00438-00 MINIMUM EIGHT 6-32 100˚ COUNTER-SUNK FLATHEAD SCREWS REQUIRED (2 PER POSITION) 211-63234-11 (2 PLACES) 330-00185-62 011-00950-03 NOTE 3 211-60234-08 (2 PLACES) BACKPLATE ASSEMBLY 011-00582-XX CONNECTOR KIT 011-01012-01 011-01169-01 NOTE 3 330-00053-01 (BNC) OR 330-00053-02 (TNC) 125-00002-00 212-00022-00 NUT SUPPLIED WITH 330-00053-XX NOTES: 1.