GTX 330, GTX 330D TRANSPONDER INSTALLATION MANUAL TM TM â GARMIN International, Inc. 1200 E.
© Copyright 2002 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.
TABLE OF CONTENTS To be supplied GTX 330 Installation Manual 190-00207-02 Page i Rev 1
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1. GENERAL DESCRIPTION 1.1 INTRODUCTION This manual describes the physical, mechanical, and electrical characteristics and the installation requirements for the GTX 330 Mode S Transponder and GTX 330D Diversity Mode S Transponder. In this manual, the term GTX 330 applies to both transponders unless otherwise stated. Information pertaining to the maintenance, alignment, and procurement of replacement parts is found in the GTX 330 Maintenance Manual, P/N 190-00207-05.
• Serial altitude or GPS groundspeed input. • Serial altitude output. • Mode S with Extended Squitter, Comm A and Comm B protocol. • Temperature, Altitude Hold, Density Altitude and the ability to enter flight ID or tail numbers. • Digitally recorded voice and discrete warning annunciator activated by Altitude Hold when limits are exceeded. • Diversity: GTX 330 is available with or without the Diversity feature. 1.4 GTX 330 TECHNICAL SPECIFICATIONS 1.4.
1.4.2 Physical Characteristics of the GTX 330 SPECIFICATION CHARACTERISTIC Bezel Height 1.65 inches (42 mm) Bezel Width 6.25 inches (159 mm) Rack Height (Dimple to Dimple) 1.68 inches (43 mm) Rack Width 6.30 inches (160 mm) Depth Behind Panel with Connectors (measured from face of aircraft panel to rear of connector backshells) GTX 330 Unit Weight 11.25 inches (286 mm) GTX 330 Rack Weight (Installed with rack and connectors) 4.2 lbs. (1.9 kg) 3.4 lbs. (1.5 kg) 1.4.
1.4.5 Additional Equipment Required • Antenna Sealant - Use antenna manufacturer’s instructions, install according to FAA AC 43.13-2A. • Cables - The installer will supply all system cables including circuit breakers. Cable requirements and fabrication is detailed in Section 2 of this manual. • Hardware - #6 Flat Head Screw (6 ea.) and #6-32 Self-Locking Nut (6 ea.). Hardware required to mount installation rack is not provided.
1.7 LIMITED WARRANTY GARMIN warrants this product to be free from defects in materials and manufacture for one year from the date of purchase. 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. The customer is, however, responsible for any transportation costs. This warranty does not cover failures due to abuse, misuse, accident or unauthorized alteration or repairs.
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2. INSTALLATION 2.1 INTRODUCTION This section provides the necessary information for installing the GTX 330 Mode S Transponder, and where required, optional accessories. Installation of the GTX 330 will differ according to equipment location and other factors. Cabling will be fabricated by the installing agency to fit these various requirements. Appendix B contains interconnect wiring diagrams, mounting dimensions, and information pertaining to installation.
NOTE If the antenna is being installed on a composite aircraft, ground planes must sometimes be added. Conductive wire mesh, radials, or thin aluminum sheets embedded in the composite material provide the proper ground plane allowing the antenna pattern (gain) to be maximized for optimum transponder performance. 2.3.2 Antenna Installation Install the antenna according to the antenna manufacturer’s instructions and FAA AC 43.13-2A. 2.3.
2.3.4 Antenna Cable Installation When routing antenna cables, observe the following precautions: • All cable routing should be kept as short as possible and as direct as possible. • Avoid sharp bends. • Avoid routing cables near power sources (e.g., 400 Hz generators, trim motors, etc.) or near power for fluorescent lighting. • Avoid routing cable near ADF antenna cable (allow at least a 12-inch separation).
2.4 COOLING AIR The GTX 330 meets all TSO requirements without forced air-cooling. (The application of forced air cooling to the rear air nozzle of the GTX 330 provides beneficial cooling to the unit. The GTX 330 is designed to dissipate its internal heat without the need of blowing air inside the unit.) The GTX 330 was designed to handle a constant 450 PRF, with short periods of 1200 PRF. Rate limit is set at 1200 PRF.
3. INSTALLATION PROCEDURE 3.1 ANTENNA INSTALLATION 3.1.1 Antenna Installation Install the antenna according to the antenna manufacturer’s instructions and FAA AC 43.13-2A. 3.1.2 Antenna Cable Connectors The antenna cable requires a BNC connector at the antenna and a male BNC “Blindmate” connector (P/N 330-00053-01, supplied with GTX 330 backplate assembly, 011-00582-00/01 at the transponder. Follow BNC connector manufacturer instructions for assembly of the BNC connector. 3.
3.4 POST INSTALLATION CHECKOUT CAUTION Be sure to check all aircraft control movements before flight is attempted to insure that the wiring harness does not touch any moving part. Verify proper operation of the transponder during a flight test under VFR conditions. Page 3-2 Rev.
Figure 3-1 GTX 330 OUTLINE DRAWING GTX 330 Installation Manual 190-00207-02 Page 3-5 (Page 3-6 blank) Rev 1
Figure 3-2 GTX 330 CONNECTOR/RACK ASSEMBLY DRAWING GTX 330 Installation Manual 190-00207-02 Page 3-7 (Page 3-8 blank) Rev 1
Figure 3-3 GTX 330 RECOMMENDED PANEL CUTOUT DIMENSIONS GTX 330 Installation Manual 190-00207-02 Page 3-9 (Page 3-10 blank) Rev 1
4. SYSTEM INTERCONNECTS 4.1 PIN FUNCTION LIST 4.1.1 J3301 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.
Connector P3301, continued Pin Pin Name I/O 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 ARINC 429 OUT 1 B ARINC 429 IN 1 B ARINC 429 IN 2 B ARINC 429 OUT 1 A TEMPERATURE PROBE 1 OUT TEMPERATURE PROBE 1 IN RESERVED TEMPERATURE PROBE 2 OUT AIRCRAFT POWER AIRCRAFT GROUND TEMPERATURE PROBE 2 IN 14 V/5 V LIGHTING BUS HI TIS CONNECT SELECT* RESERVED ARINC 429 IN 4 A ARINC 429 IN 4 B ALTITUDE COMMON (GROUND) RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERV
4.2 Power and Lighting Function Power Input requirements and Lighting Bus input are listed in the following tables. The power-input pins accept 11-33 VDC. Switched Power Out is a power source available for devices such as a remote digital altitude encoder. 4.2.1 Aircraft Power PIN NAME AIRCRAFT POWER AIRCRAFT POWER SWITCHED POWER OUT AIRCRAFT GROUND AIRCRAFT GROUND CONNECTOR/PIN P3301 21 P3301 42 P3301 62 P3301 27 P3301 43 I/O In In Out --- Table 4-2. Aircraft Power Pin Assignments 4.2.
4.4 Altitude Function Altitude inputs are considered active if either the voltage to ground is < 1.9 V or the resistance to ground is < 375 Ω. These inputs are considered inactive if the voltage to ground is 11-33 VDC. NOTE The GTX 330 contains internal altitude code line isolation diodes to prevent the unit from pulling the encoder lines to ground when the transponder is turned off.
4.6 Serial Data Electrical Characteristics Pin Name RS 232 OUT 1 RS 232 IN 1 RS 232 OUT 2 RS 232 IN 2 Connector P3301 P3301 P3301 P3301 Pin 23 22 23 24 I/O Out In Out In Table 4-7. RS 232 Pin Assignments The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ± 5 V when driving a standard RS-232 load. Refer to Figure 4-2 on page 4-7 for the RS-232 serial data interconnect. Refer to sections 5.2.9. and 5.2.16.
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Figure 4-1 GTX 330 INTERCONNECT WIRING DIAGRAM GTX 330 Installation Manual 190-00207-02 Page 4-5 (Page 4-6 blank) Rev 1
Figure 4-2 DUAL TXP INTERCONNECT WIRING DIAGRAM, ENCODING ALTITUDE CONNECTIONS GTX 330 Installation Manual 190-00207-02 Page 4-7 (Page 4-8 blank) Rev 1
5. POST INSTALLATION CONFIGURATION AND CHECKOUT PROCEDURE 5.1 OPERATION NOTE The coverage you can expect from the GTX 330 is limited to line of sight. Low altitude or antenna shielding by the aircraft itself may result in reduced range. Range can be improved by climbing to a higher altitude. It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes. Figure 5-1.
NOTE Any time the function switch is in the ON or ALT position the transponder becomes an active part of the Air Traffic Control Radar Beacon System (ATCRBS). The transponder also responds to interrogations from TCAS equipped aircraft. • IDENT Pressing the IDENT key activates the Special Position Identification (SPI) Pulse for 18 seconds, identifying the transponder return from others on an air traffic controller’s screen.
• Important Codes: 1200 The VFR code for any altitude in the US (Refer to ICAO standards elsewhere) 7000 The VFR code commonly used in Europe (Refer to ICAO standards) 7500 Hijack code (Aircraft is subject to unlawful interference) 7600 Loss of communications 7700 Emergency 7777 Military interceptor operations (Never squawk this code) 0000 Military use (Not enterable) Avoid selecting code 7500 and all codes in the 7600-7777 range. These codes trigger special indicators in automated facilities.
5.2 CONFIGURATION PAGES Holding down the FUNC key and pressing the ON key provides access to the configuration pages. The FUNC key sequences forward through the configuration pages. The START/STOP button reverses through the pages, stopping at the Menu page. The CRSR key will highlight selectable fields on each page. When a field is highlighted, numeric data entry will be performed with the 0 – 9 keys and list selections will be performed with the 8 or 9 keys. Press the CRSR key to accept changes.
5.2.1 Configuration Menu Page CONFIGURATION MENU Page CONFIGURATION MENU The JUMP TO menu page provides the capability to select a configuration mode starting page without having to step through all of the pages. Select the desired section with the CRSR key and sequence through with the 8 and 9 keys. Jump to the selection by pressing the CRSR key again with the desired selection highlighted.
5.2.4 DISPLAY MODE PAGE DISPLAY MODE Page DISPLAY MODE Selection AUTO (Automatic) NGTV (Negative) PSTV (Positive) Description DEFAULT. The display will automatically change between Positive mode (during the day) and Negative mode (at night), depending on the ambient light level received by the photocell. The display will always be light characters on a black background, regardless of ambient lighting. The display will always be black characters on a light background, regardless of ambient lighting.
BKLT SRCE (Backlight Source) Selection PHOTO (Photocell) 14V 28V 5V Description DEFAULT. Backlight level is determined by the ambient light level as measured by the photocell on the GTX 330. Backlight level tracks a 14 volt DC aircraft lighting bus. Backlight level tracks a 28 volt DC aircraft lighting bus. Backlight level tracks a 5 volt DC aircraft lighting bus.
RSP TIME (Response Time) Sets the speed with which the brightness responds to ambient light changes (only for AUTO key lighting mode). The higher the number, the slower the key lighting responds. This field has a range of 3 to 7, and is set to 4 at the factory. MIN (Minimum) Sets the minimum brightness of the key lighting. The higher the number, the brighter the minimum brightness. Key lighting minimum brightness has a range of 0 (zero) to 99, and is set to 8 at the factory.
5.2.8 ARINC 429 CONFIGURATION Pages ARINC 429 INPUT ARINC 429 INPUT (First) Page The ARINC 429 INPUT Pages configure the ARINC 429 input ports. Each port can be configured independently for the desired function(s). ARINC 429 INPUT (Second) Page SPEED Selection Low High Description Standard low-speed ARINC 429 (nominally 12.5 kilobits per second). High-speed ARINC 429 (nominally 100 kilobits per second).
5.2.10 OPERATION CONFIGURATION PAGES VS RATE (Vertical Speed Rate) First CONFIGURATION Page This field is the typical vertical speed for climb/descent of the aircraft. This number determines when a climb or descent arrow is displayed on the PRESSURE ALT page of the GTX 330. The range is 0 (zero) feet per minute to 9999 feet per minute. It is set to 500 fpm at the factory. FORMAT (Altitude Format) This field determines how the pressure altitude will be shown on the GTX 330 display.
5.2.11 TEMPERATURE PAGE SENSOR INSTALLED TEMPERATURE Page Sets the Sensor to YES or NO. Default is NO. UNITS Sets the units to degrees Fahrenheit or Centigrade. Default is degrees F. 5.2.12 MODE S Address Entry Pages Aircraft Registration or Flight ID Number Pages NOTE It is VERY important to enter the Mode S address correctly in the GTX 330. During production of a GTX 330 the unit is initially set with an address of 0. The software recognizes this as an invalid address.
MODE S Aircraft Type Page MODE S (A/C Type) Page Selection AC TYPE MAX AIRSPEED ACQ SQUITTER INHIBITED Description ROTOR, >15.5K Lb, <15.5K Lb, or UNKNOWN. <75 Kts, <150 Kts, <300 Kts, >300 Kts, or UNKNOWN. YES OR NO. AIRCRAFT TYPE Sets the AIRCRAFT TYPE Message to ROTOR, to a weight of Less Than 15,500 pounds, More Than 15,500 pounds, or Unknown weight. Defaults to Less Than or equal to 15,500 pounds.
5.2.14 EXTERNAL SWITCH STATE Page IDENT EXTERNAL SWITCH Page This field displays the state of the EXTERNAL IDENT discrete input. The box is filled when EXTERNAL IDENT is grounded. STANDBY This field displays the state of the EXTERNAL STANDBY discrete input. The box is filled when EXTERNAL STANDBY is grounded. SQUAT This field displays the state of the SQUAT SWITCH input. The box is filled when the SQUAT SWITCH input is active (the aircraft is on the ground as configured on the SETUP 2 page). 5.2.
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APPENDIX A A.1 CERTIFICATION DOCUMENTS Continued Airworthiness Other than for regulatory periodic functional checks, maintenance of the GTX 330 is “on condition” only. Refer to the GTX 330 Maintenance Manual, (Garmin P/N 190-00207-05). Periodic maintenance of the GTX 330 is not required.
5. Maintenance Instructions Maintenance of the GTX 330 is ‘on condition’ only. Periodic maintenance is not required. Refer to the GTX 330 Maintenance Manual. 6. Troubleshooting Information Refer to the GTX 330 Maintenance Manual. 7. Removal and Replacement Information Refer to section 2 of this manual. If the unit is removed and reinstalled, a functional check of the equipment should be conducted in accordance with section 5 of this manual. 8. Diagrams Refer to section 3 and section 4 of this manual.
Implementation and Record Keeping For major alterations performed in accordance with FAA field approval policy, the owner/operator operating under Part 91 is responsible for ensuring that the ICA is made part of the applicable section 91.409 inspection program for their aircraft. This is accomplished when a maintenance entry is made in the aircraft’s maintenance record in accordance with section 43.9. This entry records the major alteration and identifies the original ICA location (e.g.
A.2 ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE: GTX 330 Airborne ATC/Mode S Transponder Equipment TYPE/MODEL/PART NO.: 010-00230–( ), which includes 011-00455–( ) TSO/JTSO COMPLIANCE: TSO – C112 Class 2A, and TSO - C74c Class 1A MANUFACTURER'S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: 004-00099-00 Minimum Performance Specification MANUFACTURER: GARMIN INTERNATIONAL ADDRESS: 1200 E 151st St, Olathe, Kansas 66062 Conditions Temperature and Altitude RTCA DO-160D Section 4.
Conditions Section Description of Conducted Tests Explosion 9.0 Equipment identified as Category X, no test required Waterproofness 10.0 Equipment identified as Category X, no test required Fluids Susceptibility 11.0 Equipment identified as Category X, no test required Sand and Dust 12.0 Equipment identified as Category X, no test required Fungus 13.0 Equipment identified as Category X, no test required Salt Spray 14.
APPENDIX B STC PERMISSION Consistent with N8110.69 or Order 8110.4, Aviation Authority approved installers are hereby granted permission to use STC #(xxxxxxxxx) data to modify aircraft. GTX 330 Installation Manual 190-00207-02 Page B1 Rev.
To be supplied Page B2 Rev.
