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GTXTM 330, GTXTM 330D TRANSPONDER INSTALLATION MANUAL

1. 01 2 98ed 6 Sed suonoeuuo seoi eg jenes 120uuooJ401u oee XLD 9 9 4 GARMIN GTX 330 ARINC 429 OUT 2 A ARINC 429 OUT 2 B ARINC 429 IN 1 A ARINC 429 IN 1 B RS 232 IN 1 ARINC 429 IN 2 A ARINC 429 IN 2 B ARINC 429 IN 3 A ARINC 429 IN 3 B ARINC 429 IN 4 A ARINC 429 IN 4 B 400 500 Series P4001 Unit 5501 5001 4 SEE NOTE 2 A 48 GPS ARINC 429 IN 1 A 28 49 GPS ARINC 429 IN 1 B Y Garmin Garmin Garmin GPS Receiver 400 Series 500 Series GPS 155 XL Unit Unit GNC 300 XL P4001 P5001 P101 32 A SEE NOTE 3 46 46 16 GPS ARINC 429 OUT A 35 47 47 15 GPS ARINC 429 OUT B X X Bendix King Bendix King GPS Receiver KLN 898 KLN 94 891 941 SEE NOTE 5 2 2 RS 232 OUT 22 Q e B amp D B amp D B amp D B amp D Bendix King Bendix King Air Data 2600 2601 2800 90004 003 481 KDC 481 Computer P201 P2811 P4811 D 2 5 15 11 27 5 U TRANSMITTER A 8 13 28 9 6 56 9 1 TRANSMITTER Electronic Flight EFS 40 50 53050 Information System 46528 26 SE STU N 47 LNAV TRANSMITTER A 29 y 20 LNAV TRANSMITTER B i B B RESERVED 49 y NOTES 1 ALL WIRES 24 AWG OR LARG
2. Piper MF oue 32260 Deosergation of Igne Change Installation of Garmin GTX 330 Mode S Transponder with Traffic Information System Capability Data Required 1 FAA Approved Airplane Flight Manual Supplement AFMS for Piper PA32 with Garmin GNS 430 VHF Communication Transceiver VOR ILS Receiver GPS Receiver or 2 FAA Approved Airplane Flight Manual Supplement AFMS for Piper PA32 with Garmin GNS 530 VHF Communication Transceiver VOR ILS Receiver GPS Receiver dated 11 21 2002 or later FAA Approved Revisions to 1 or 2 Limitations and Conditions Compatibility of this design change with previously approved modifications must be determined by the installer If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission Descriptive data pertaining to this design change are considered inadequate for duplication of other products This approval is limited to only the installation made in Piper model 32 260 Serial Number 32 7100002 This STC does not permit manufacturing of parts for multiple installations and lhe supporting which is the basis for approval Mall remain in until ene revolted or a termination dale ts olherwise established Ey tha Sbdininistrilor of the Yate nl apylicalion March 11 2002 Lele reissued Yule of SEANCE December 12
3. 6B 116 512 ll 3437 11710 8 00 203 2 GTX 330 Installation Manual 190 00207 02 Figure B 1 GTX 330 Outline Drawing Page B 1 Page B 2 blank Revision F APPENDIX B ASSEMBLY AND INSTALLATION DRAWINGS 211 60234 08 DO 2 PLACES 115 00294 00 A Po 2 TO TOP ANTENNA 211 63234 12 2 PLACES TO BOTTOM ANTENNA 330 00053 01 E DO 212 00022 00 D NUT SUPPLIED WITH CONNECTOR NOTES DD PART OF 011 00582 00 GTX 330 BACKPLATE ASSY 2 PART OF 011 00582 01 GTX 330D BACKPLATE ASSY 330 00185 62 3 PART OF 011 00583 00 CONNECTOR KIT 336 00021 00 AS REQ D FEED HARNESS WIRES THROUGH BACKSHELL 3 BEFORE INSERTION INTO CONNECTOR 5 SNAP NUTPLATE OVER BACKSHELL 6 APPLY THREAD LOCKING COMPOUND TO ALL THREADED FASTENERS 330 00220 37 GTX 330 Installation Manual 190 00207 02 125 00002 00 DE 336 00029 00 20 PLACES 212 00022 00 2 NUT SUPPLIED 2 WITH CONNECTOR 2 PLACES 125 00056 00 Figure B 2 GTX 330 Connector Rack Assembly Drawing Page B 3 Page B 4 blank Revision F APPENDIX B ASSEMBLY AND INSTALLATION DRAWINGS OPTION T STACK CUTOUT RACK INSTALLED FROM FRONT OF AIRCRAFT PANEL OPTION 2 RADIO CUTOUT RACK INSTALLED FROM FRONT OF AIRCRAFT PANEL OPTION 258 RADIO CUTOUT RACK INSTALLED FROM BACK OF AIRCRAFT PANEL
4. oti 4 6 Serial Data Electrical CharacterlStiCS ccccoonoonnncnccnnnononononanoccnnnnnnnnnnnanoconnnnnannnanos GTX 330 Installation Manual 190 00207 02 Page iii Revision F PARAGRAPH PAGE 5 POST INSTALLATION CONFIGURATION AND CHECKOUT PROCEDURE 5 Del TOPE T m 5 32 HH Hu 5 5 APPENDIX A CERTIFICATION DOCUMENTS OM om nu 1 A2 Continued 3 A 3 Environmental Qualification Forms GTX 330 Mode S Transponder A 5 APPENDIX ASSEMBLY AND INSTALLATION DRAWINGS APPENDIX C INTERCONNECT DRAWINGS Page iv GTX 330 Installation Manual Revision F 190 00207 02 LIST OF ILLUSTRATIONS FIGURE PAGE 2 1 Antenna Installation Considerations 2 1 Aal Rea collector o c d ont A 4 1 4 2 Dual GTX 330 Single Encoder Serial Input Connections Y III I I I I FF Fine 4 5 422 76126330 Software Update dida ent deed dio ta ruis 4 8 31 CG Front IE T UU TEE 5 1 A 1 GTX 330 Environmental Qualification Form sese eene nn FL FF A 6 GR 230 Outline Draw raid lana 1 B 2 GTX 330 Connector Rack Assembly Drawing E A
5. 4 select between Hex or Tail number press the CRSR key then 8 or 9 key to move to the correct selection 5 For entering either the address hex code or the US registration number press the CRSR key 1 time This highlights the address field GTX 330 Installation Manual Page 5 15 190 00207 02 Revision F 7 Enter the aircraft address using the number keys Press a key repeatedly to scroll through the digit alpha characters for that key 8 Press the CRSR key to select the next numeric entry field Enter the next character as stated in step 7 then move onto the next one repeating the process until the complete number is entered 9 When finished press the CRSR key to accept the number entry 10 Using the FUNC and or START STOP keys toggle through the pages to get off of then back onto the aircraft address page Verify that the address is correct The unit now contains a Mode 5 address and may be turned off To power the unit on in the normal mode press only the ON ALT or STBY key without holding the FUNC key or turn on with the avionics master switch MODE S ADDRESS AIRCRAFT REGISTRATION PAGE SELECTION DESCRIPTION US TAIL N Registration Number Hexadecimal code address MODE 5 ADDRESS FLIGHT ID PAGE 5 2 13 Mode S Aircraft Type Page Used for air to air communication with TCAS ec MODE 5 A C Type Page SELECTION DESCRIPTION AC TYPE UNKNOWN lt 15 5 Lb gt 15 5K
6. 4 5 1 Discrete Outputs Table 4 6 Discrete Outputs Pin Assignments PinName Pin Number _ ALTITUDE ALERT ANNUNCIATE EXTERNAL SUPPRESSION I O This output is considered active if either the voltage to ground is lt 1 9 V or the resistance to ground 15 lt 375 This output is considered inactive if the voltage to ground 15 11 33 Vdc 4 5 2 Discrete Inputs Table 4 7 Discrete Inputs Pin Assignments _________ Pin Number VO EXTERNAL IDENT SELECT EXTERNAL STANDBY SELECT SQUAT SWITCH IN TIS CONNECT SELECT AUDIO MUTE SELECT These inputs are considered active if either the voltage to ground is lt 1 9 V or the resistance to ground 15 lt 375 These inputs are considered inactive if the voltage to ground 15 11 33 Vdc EXTERNAL IDENT SELECT remote IDENT is a momentary input Refer to Figure C 4 for the squat switch interconnect and to Sections 5 2 10 and 5 2 15 for the squat switch configuration EXTERNAL STANDBY SELECT remote STANDBY is a momentary input used when two GTX 330 systems are installed in an aircraft Refer to Figures C 2 C 4 C 6 and C 7 for the EXTERNAL STANDBY SELECT interconnect and to Sections 5 2 15 for verifying external standby configuration When EXTERNAL STANDBY SELECT 15 grounded ARINC 429 OUT PORT 1 remains active while PORT 2 is inactive When TIS CONNECT SELECT is inactive Standby is displayed on the 400 500 Series units the GTX 33
7. Following is a suggested ICA for a Garmin GTX 330 unit installation Some of the checklist items do not apply in which case they should be marked N A Not Applicable INSTRUCTIONS FOR CONTINUED AIRWORTHINESS GARMIN GTX 330 1 Introduction Aircraft that has been altered Registration N number Make Model and Serial Number Content Scope Purpose and Arrangement This document identifies the Instructions for Continued Airworthiness for the modification of the above aircraft by installation of a Garmin GTX 330 Applicability Applies to aircraft altered by installation of the Garmin GTX 330 Definitions Abbreviations None N A Precautions None N A Units of Measurement None N A Referenced Publications Garmin GTX 330 Installation Manual P N 190 00207 02 Garmin GTX 330 Maintenance Manual P N 190 00207 05 Garmin STC STO1125WI Garmin GTX 330 Pilot s Guide P N 190 00207 00 Distribution This document should be a permanent aircraft record 2 Description of the Alteration Installation of the Garmin GTX 330 with interface to Encoding Altimeter or Blind Encoder Refer to Section 4 and Figures 4 1 and 4 2 of this manual for interconnect information Antenna installation removal and replacement should be in accordance with applicable provisions of AC 43 13 1B and AC 43 13 2A 3 Control Operation Information Refer to the GTX 330 Pilot s Guide 4 Servicing Information GTX 330 Installation Manual Page
8. GTK 330 3300 TRANSPONDER INSTALLATION MANUAL GTX330 a Garmin Ltd its subsidiaries 190 00207 02 Revision F March 2004 Copyright 2002 2004 Garmin Ltd its subsidiaries Rights Reserved Except as expressly provided herein no part of this manual may be reproduced copied transmitted disseminated downloaded or stored in any storage medium for any purpose without the express prior written consent of Garmin Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto 15 strictly prohibited Garmin International Inc 1200 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 Aviation Panel Mount Technical Support Line Toll Free 1 888 606 5482 WWW garmin com Garmin Europe Ltd Unit 5 The Quadrangle Abbey Park Industrial Estate Romsey 5051 9DL U K Telephone 44 1794 5 19944 RECORD OF REVISIONS B 5 02 ___ UpgradetoSW3 03 7 20932 D 8 4 03 Added Figure 4 9 330 327 w Dual Display 21954 10 22 03 Added TIS TCAD combo and SW connector 22929 0
9. density altitude DALT pressure altitude PALT current barometric pressure BARO and vertical speed VSPD can be viewed If ADC W ALT or FADC W ALT format selected 5 2 18 ARINC 429 Channels Pages The GTX 330 receives one of the following sets of ARINC 429 ARINC 429 CHANNELS 1 and 2 data on either ARINC 429 receivers 1 2 or 3 The labels chosen when selected in ARINC 429 INPUT Section 5 2 8 The received data may be at either LOW or HIGH speed The ARINC 429 CHANNELS 3 and 4 default 15 LOW The transmit data labels and their rate are as follows Page 5 18 GTX 330 Installation Manual Revision F 190 00207 02 AHRS COMPUTER AHRS LABEL DATA TRUE HEADING degrees MAGNETIC HEADING degrees VERTICAL RATE feet min AIR DATA COMPUTER ADC PRESSURE ALTITUDE in feet set to 29 92 Hg 1013 25 mb EFIS DISPLAY SYSTEM EF AD SELECTED COURSE degrees PRESSURE ALTITUDE in feet set to 29 92 Hg 1013 25 mb JOYSTICK LON TRUE HEADING MAGNETIC HEADING degrees GPS NAVIGATION SYSTEM GPS LABEL DATA 312 GROUND SPEED knots If ADC W ALT or EF AD W ALT format selected GTX 330 Installation Manual Page 5 19 190 00207 02 Revision F This page intentionally left blank Page 5 20 GTX 330 Installation Manual Revision F 190 00207 02 APPENDIX CERTIFICATION DOCUMENTS A 1 STC Order number 8300 10 FSAW 98 04B FSAW 98 04B AMENDED provides Fli
10. 5 2 12 Mode S Address Entry Pages It is VERY important to enter the Mode 5 address correctly in the GTX 330 Aircraft Registration or Flight ID Number Page When the unit 1s turned on for the first time or an invalid address 1s recognized the unit prompts the user to enter a valid aircraft address MODE 5 Address A C Reg Page Once the aircraft address 1s entered the unit remains on 1n the same mode as before Flight ID can be entered in TSO Class 2A units P N 010 00230 and 010 00293 MODE 5 Address Flight ID Page For first time turn on proceed to step 5 Otherwise begin at step 1 with the unit turned off 1 Toenter the configuration pages press and hold the FUNC key while powering on the unit 2 Power the unit on by pressing the ON ALT or STBY key while holding the FUNC key or turn on with the avionics master switch The unit performs a self test routine and displays a Jump to Diagnostics page 3 Press the FUNC key repeatedly to toggle through the pages until you come to the address entry page or for a shortcut select the Aircraft Configuration Menu page see para 5 2 1 and then toggle the FUNC key three times a The page that appears is either as ADDRESS HEX b Oras ADDRESS US TAIL N It is not necessary for the installer to convert the aircraft registration number N number for US registry aircraft to a Hex address The GTX 330 converts the registration number to hexadecimal automatically
11. MESSAGE 0 9 Selected audio tones and messages 0 Toggles a continuous tone on and off 1 Attention Tone precedes voice messages to attract the pilot s attention 2 Leaving Altitude when altitude monitor 15 active and the altitude deviation 15 exceeded 3 Traffic when a TIS traffic alert 15 received similar to a Traffic Advisory in TCAS terms 4 Timer Expired when the countdown timer expires 5 Traffic Not Available when TIS service 1s not available or out of range of an operating TIS Mode 5 site 6 through 9 are not used at this time ALTITUDE MONITOR Off tone or message COUNT DOWN TIMER Off tone or message PAGE CHANGE Enables Disables Altitude Monitor sub page when altitude deviation is exceeded 5 2 3 Traffic Information Page TRAFFIC MESSAGES TRAFFIC INFORMATION Page Sets the Traffic Messages to either Tone or Message Traffic Information Service TIS provides notification of close proximity traffic GTX 330 Installation Manual Page 5 7 190 00207 02 Revision F 5 2 4 Display Mode DISPLAY MODE DISPLAY MODE Page SELECTION DESCRIPTION AUTO Automatic DEFAULT Display automatically changes between Positive mode during the day and Negative mode at night depending on ambient light level received by the photocell NGTV Negative Display always has light characters on a black background regardless of ambient lighting PSTV Positive Di
12. RS 232 OUTPUT Altitude Source SELECTION DESCRIPTION DEFAULT for channel 2 No unit is connected to output of this channel ICARUS ALT DEFAULT for channel 1 RS 232 serial altitude from an Icarus Instruments 3000 REMOTE RS 232 serial output remote data Reserved for future use REMOTE TIS RS 232 serial output remote data with TIS 5 2 10 Operation Configuration Pages VS RATE Vertical Speed Rate First CONFIGURATION Page This field 15 the typical vertical speed for climb descent of the aircraft The settable number determines the rate of climb the GTX 330 assumes as liftoff for starting the flight timer and operational functions The range is 100 feet per minute to 9999 feet per minute and is set to 500 fpm at the factory GTX 330 Installation Manual Page 5 13 190 00207 02 Revision F FORMAT Format This field determines how the pressure altitude is shown on the GTX 330 display SELECTION DESCRIPTION FLIGHT LVL DEFAULT The pressure altitude 1s displayed in hundreds of feet For Flight Level example a pressure altitude of 12 300 feet is displayed as FL 123 FEET Pressure altitude 1s displayed in feet METERS Pressure altitude is displayed in meters VFR ID VFR Transponder Code This field 15 the four digit code that 18 selected when the user presses the GTX 330 VFR key In the United States 1200 15 the VFR code for any altitude The default 15 set to 1200 ALTITUDE A
13. e Serial altitude input Reduces wire count vs parallel wire gray code altimeter interface e Software update input e Supports Comm A and Comm B protocol e Temperature Altitude Hold and Density Altitude e Digitally recorded voice and discrete warning annunciator activated by Altitude Hold when limits are exceeded e Diversity GTX 330 15 available with or without the diversity feature The GTX 330 supports the following list of Binary Data Selector BDS registers e BDS 0 0 Air Initiated Comm B AICB BDS 1 0 Data Link Capability Report e BDS 1 7 Common Usage Ground Initiated Comm B GICB Capability Report e BDS 1 8 Mode S Specific Services GICB Capability Report e BDS 1 9 Mode S Specific Services GICB Capability Report e BDS 1 D Mode 5 Specific Services Protocols MSP Capability Report BDS 2 0 Aircraft Identification BDS register information 15 presented for the installation agency to understand the functionality of the GTX 330 and make a determination that the unit complies with the requirements of their civil aviation authorities No further wiring or configuration programming is required for the unit Note that BDS 3 0 15 only required for transponders compatible with ACAS TCAS II The GTX 330 does not support BDS 3 0 GTX 330 Installation Manual Page 1 3 190 00207 02 Revision F 1 6 Technical Specifications The following table presents general environmental specifications For deta
14. 330 IS IN REMOTE THE PILOT TO SELECT AND DESELECT ALTITUDE TRAFFIC ALERT AUDIO STANDBY ALTITUDE DATA IS NOT TRANSMITTED OVER ARINC 429 OUTPUT 2 LINES A SWITCHED INPUT MAY ALSO BE USED BUT THE AUDIO PANEL SHOULD ORDER TO PROVIDE ALTITUDE TO THE OTHER GPS UNIT CONTINUOUSLY CONNECT THE BE PLACARDED IF AN ADF OR DME INPUT IS USED FOR EXAMPLE RS 232 OUTPUT TO THE SECOND 400 500 SERIES UNIT THE ONE NOT USED FOR TIS Figure C 8 GTX 330 Interconnect Wiring Diagram Aircraft with TIS and TCAD TCAS GTX 330 Installation Manual Page C 15 Page C 16 blank 190 00207 02 Revision F
15. 330 Installation Manual Revision F 190 00207 02 MIN Minimum Auto Only Sets the minimum brightness of the display The higher the number the brighter the minimum brightness Display minimum brightness has a range of 0 zero to 99 with the default set to 8 It is prudent to verify that display lighting characteristics match those of other equipment in the panel under night lighting conditions BKLT SRCE Backlight Source SELECTION DESCRIPTION PHOTO Photocell 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 ighti Backlight level tracks a 28 volt DC aircraft lighting bus Backlight level tracks a 5 volt DC aircraft lighting bus If a lighting bus any selection other than PHOTO 1s selected and the lighting bus control is turned to its minimum daytime setting the display brightness tracks the GTX 330 photocell SLOPE Auto Only Sets the sensitivity of the display brightness to changes in the input level The higher the number the brighter the display for a given increase 1 the input level This field has a range of 0 zero to 99 with the default set to 50 OFFSET Auto Only Adjusts the lighting level up or down for any given input level This field has a range of 0 zero to 99 and is set to 50 at the factory This may also be used to match lighting curves with other equipment 1 the p
16. 429 OUT 1 B 34 y vd gt 49 DR 3 TIS CONNECT SELECT 46 lt 11 EXTERNAL STANDBY SELECT 13 RS 232 IN 2 24 lt e PS 15 D A SAN SEE NOTE 6 La O 1 AUDIO OUT LO 16 7 o H 5 TRANSPONDER 2 V GARMIN P5001 yr QA ub gt 48 P3271 gt 49 4 Y 11 EXTERNAL STANDBY SELECT 13 lt RS 232 IN 2 24 lt e UD Q gt 31 U gt 52 GARMIN AND GARMIN W TIS FORMATS ARE AVAILABLE ARINC 429 PORT 1 IN UNITS WITH SW 3 03 AND ABOVE UNLIKE PORT 2 ARINC 429 OUT PORT 1 REMAINS ACTIVE WHEN EXTERNAL STANDBY SELECT IS GROUNDED THE AUDIO PANEL WIRING CONFIGURATION SHOWN DOES NOT ALLOW THE PILOT TO SELECT AND DESELECT ALTITUDE TRAFFIC ALERT AUDIO A SWITCHED INPUT MAY ALSO BE USED BUT THE AUDIO PANEL SHOULD BE PLACARDED IF AN ADF OR DME INPUT IS USED FOR EXAMPLE GARMIN 400 500 Series Unit 2 GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE E GARMIN GMA 540 Audio Panel ALT WRN IN SEE NOTE 6 ALT WRN RETURN Figure C 7 GTX 330 GTX 327 Interconnect Wiring Diagram Dual Display Connections Page C 13 Page C 14 blank Revision F APPENDIX C INTERCONNECT DRAWINGS P3301 400 500 Series P4001 Unit 41 P5001 ARINC 429 IN 32 Le cu e A 46 GPS ARINC 429 OUT A ARINC 429 IN 1 B 55 5 47 GPS ARINC 429 O
17. E 3 B 3 GTX 330 Recommended Panel Cutout Dimensions esses B 5 Cal GTX 330 Typical Interconnect Wiring Diagram ea 1 2 Dual TXP Interconnect Wiring Diagram Encoding Altitude C 3 C 3 GTX 330 Interconnect Wiring Diagram Altitude And Temperature Connections C 5 4 GTX 330 Interconnect Wiring Diagram Discrete And Audio Connections uusussse C 7 C 5 GTX 330 Interconnect Wiring Diagram Serial Devices 1 C 9 C 6 Dual GTX 330 Interconnect Wiring Diagram Dual Display C 11 C 7 GTX 330 327 Interconnect Wiring Diagram Dual Display Connections C 13 C 8 GTX 330 Interconnect Wiring Diagram Aircraft With TIS and C 15 LIST OF TABLES TABLE PAGE Sal Pin Contact Part Numbers ont Y 3 3 2 Recommended Crimp I 60lSs ie i DNO d dne MEE 3 del P3350 4 1 Airera Power Pin ASSISDITIe ia 4 3 4 5 Airera nt Antina Pit ASSIP nmehls sio E OD NG 4 3 4 4 Temperature Probe PIn RON NO US 4 3 45 Ercoded Altitude PA AA te t M 4 4 4 6 Discrete Outputs Pin ASSiOnMENls ui
18. Lb or ROTOR MAX AIRSPEED UNKNOWN lt 75 kt lt 150 kt lt 300 kt or 7300 kt AIRCRAFT TYPE Sets the AIRCRAFT TYPE Message to ROTOR to a weight of less than 15 500 pounds more than or equal to 15 500 pounds or unknown weight Defaults to less than 15 500 pounds MAXIMUM AIRSPEED Sets the AIRCRAFT AIRSPEED Message to a speed of less than or equal to 75 knots between 75 knots and 150 knots between 150 knots and 300 knots more than 300 knots or unknown airspeed Defaults to less than or equal to 150 knots Enter the aircraft s maximum cruising true airspeed capability Page 5 16 GTX 330 Installation Manual Revision F 190 00207 02 5 2 14 Gray Code Input GRAY CODE GRAY CODE INPUT Page This field shows the status 1 ground 0 open of each of the ten gray code altitude inputs This information may aid in installation troubleshooting This page 15 not used in systems that contain serial altitude input DECODED ALTITUDE This field displays the gray code altitude input in feet Verify that it 1s the correct altitude 5 2 15 External Switch State Page IDENT EXTERNAL SWITCH Page This field displays the state of the EXTERNAL IDENT discrete input The box 15 filled when EXTERNAL IDENT 15 grounded STANDBY This field displays the state of the EXTERNAL STANDBY discrete input The box is filled when EXTERNAL STANDBY is grounded If EXTERNAL STANDBY is active during power up the w
19. page CONTRAST LEVEL ADJUSTMENT This 15 a slider bar graph control Use the 8 key to move the graph to the left decreasing the numbers and contrast level Use the 9 key to move it to the right increasing the numbers and contrast level In manual contrast mode this 1s a direct adjustment of the display contrast In automatic contrast mode this adjusts the offset to the automatically compensated contrast with the default set to an offset of 50 5 2 8 ARINC 429 Configuration Pages EUG 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 OFS desired function s The ARINC 429 IN 1 INPUT allows ARINC 429 INPUT Second Page automated start and stop of the flight timer and places the transponder in ground GND mode upon landing The same input data source cannot be selected for multiple input channels 1 through 3 ADLP 5 included for future use SPEED Channel 1 3 SELECTION DESCRIPTION Standard low speed ARINC 429 nominally 12 5 kilobits per second High High speed ARINC 429 nominally 100 kilobits per second DATA Channel 1 4 through AHRS Attitude and heading information 3 EF AD NO ALT Selected course heading temperature joystick waypoint and speed information EF AD W ALT Selected course heading temperature joystick waypoint and speed information plus altitude da
20. the word IDENT appears in the upper left corner of the display Sets the transponder code to the pre programmed VFR code selected in Configuration Mode Set to 1200 at the factory Pressing the VFR key again restores the previous identification code Changes the page shown on the right side of the display Display data includes Pressure Altitude Flight Time Altitude Monitor Count Up and Count Down timers In the Configuration Mode steps through the function pages e START Starts and stops the Altitude Monitor Count Up Count Down and Flight timers STOP CRSR CLR In configuration mode steps through functions in reverse Initiates entry of the starting time for the Count Down timer and cancels transponder code entry Selects changeable fields in Configuration Mode Resets the Count Up Count Down and Flight timers Cancels the previous keypress during code selection and Count Down entry Used in Configuration Mode Page 5 2 Revision F GTX 330 Installation Manual 190 00207 02 8 Reduces Contrast and Display Brightness when the respective fields are displayed and enters the number eight into the Count Down timer Used in Configuration Mode e 9 Increases Contrast and Display Brightness when the respective fields are displayed and enters the number nine into the Count Down timer Used in Configuration Mode 5 1 2 Code Selection Code selection 15 done with eight keys 0 7 pro
21. was increased to DO 160C Helicopter Test Curve N as follows 0 1 inches pk pk double amplitude from 5Hz to 17Hz and 1 5g pk from 17Hz to 500Hz GTX330 GTX33 Environmental Qualification Form 005 00131 03 Page 3 of 3 Rev C Figure A 1 GTX 330 Environmental Qualification Form Sheet 2 of 2 GTX 330 Installation Manual Page A 7 190 00207 02 Revision F This page intentionally left blank Page 8 GTX 330 Installation Manual Revision F 190 00207 02 APPENDIX B ASSEMBLY AND INSTALLATION DRAWINGS i o 9 f gt 6 30 160 0 6 25 158 8 3 20 81 31 BER 9 4 90 124 5 9 91 251 6 11 04 280 4 r Un 11 25 285 8 88 22 4 SN 9 O E 1 68 42 51 1 68 41 91 _ M N 47 2 2 y
22. 0 logs onto TIS service when a momentary ground is applied to P3301 46 When TIS is active a momentary ground logs off of TIS service Refer to Figures C 1 C 4 C 6 and C 8 for TIS CONNECT SELECT connections and to Sections 5 2 2 and 5 2 3 for TIS configuration An AUDIO MUTE SELECT mute switch may be used to control TIS audio alerts TIS Traffic Mute must be clearly marked with MUTE ON MUTE OFF or TIS Audio ON Audio OFF labels The muting feature may be enabled through a Multi Function display In order to prevent inadvertent muting the status of muting must default to Mute off upon each power cycle Refer to Figures C 1 C 4 and C 8 for AUDIO MUTE SELECT connections and to Sections 5 2 2 and 5 2 3 for AUDIO configuration Page 4 6 GTX 330 Installation Manual Revision F 190 00207 02 4 6 Serial Data Electrical Characteristics The GTX 330 can be configured to include GPS Airdata AHRS EFIS Airdata and ADLP ARINC 429 inputs functioning as an ARINC 429 data concentrator Since the Garmin 400 500 Series products have only two ARINC 429 input ports the GTX 330 manages support for several equipment interfaces The GTX 330 has four ARINC 429 input ports making it capable of taking altitude air data heading EFIS selected course and possible future features and then concentrating it on the ARINC 429 OUT 2 port This line 1s then wired to an ARINC 429 input port on the 400 500 Series products TIS data 1s included on the same high sp
23. 1 OR TO PANEL DIMMING BUS 14 V 5 V LIGHTING BUS HI 45 m P4001 P5001 ARINC 429 IN 1 A 32 ARINC 429 IN 1 B 35 lt x x x ARINC 429 OUT 2 A 30 A ENEE A 48 ARINC 429 OUT 2 B 28 Y z 49 X SEE NOTE 6 1 46 lt 11 EXTERNAL SUPPRESSION 1 0 51 gt SEE NOTE 7 P4001 ALTITUDE D4 t ALTITUDE A1 2 F lt mE ALTITUDE A2 4 48 ALTITUDE A4 5 49 ALTITUDE B1 7 5 x ALTITUDE B2 9 FROM ALTITUDE ENCODER 11 ALTITUDE 10 e OR ENCODING ALTIMETER ALTITUDE C1 8 ALTITUDE C2 m ALTITUDE C4 6 L ALTITUDE COMMON GROUND 50 AUDIO MUTE SELECT 47 FROM TAWS OR WIND SHEAR RADAR SYSTEM SEE NOTE 8 E AUDIO OUT 15 YTT ol AUDIO OUT LO 16 32 P3302 SEE NOTE 9 CN BOTTOM Y GTX 330D ONLY T SEE ote CN TOP TOP ANTENNA Y XPDR ANTENNA GTX 330 Installation Manual 190 00207 02 GARMIN 400 500 Series Unit 42 GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE E GARMIN 340 Audio Panel SEE NOTE 10 ALT WRN IN ALT WRN RETURN NOTES 1 2 10 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED ABSOLUTE MAXIMUM SOURCE CURRENT FROM THE SWITCHED POWER OUTPUT IS 1 5 AMPS 13 75 VDC INPUT TO THE GTX 330 AVIONICS MASTER ON SELECT P3301 1 WHEN TIED TO AIRCRAFT POWER INPUT P3301 2
24. 1 OR 42 PROVIDES AUTOMATIC UNIT POWER UP WHEN POWER IS APPLIED THE UNIT WILL POWER UP IN THE LAST MODE SELECTED ARINC 429 IN 1 P3301 32 AND 35 INPUT ALLOWS AUTOMATED START AND STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND GND MODE UPON LANDING IF EXTERNAL STBY SELECT IS CONNECTED IN THIS CONFIGURATION USE AIRINC 429 OUT 1 A AND 1 B PINS 37 AND 34 RATHER THAN AIRINC 429 OUT 2 A AND 2 B PINS 30 AND 28 SHOWN ALTITUDE DATA WILL NOT BE TRANSMITTED OVER AIRINC 429 PORT 2 TO THE 400 500 SERIES UNIT WHEN EXTERNAL STBY SELECT IS GROUNDED WHEN TIS IS USED IN THE AIRCRAFT DO NOT CONNECT ANOTHER TRAFFIC SYSTEM TO THE SAME 400 500 SERIES UNIT REFER TO FIGURE C 8 EXTERNAL SUPPRESSION 1 0 P3301 31 SENDS AND ACCEPTS POSITIVE GOING SUPPRESSION PULSES TO FROM ANOTHER TRANSPONDER DME THE AUDIO MUTE SELECT INPUT P3301 47 MUTES ALL GTX 330 AUDIO WHEN OTHER SYSTEMS ARE OUTPUTTING HIGHER PRIORITY AUDIO WARNINGS TO PARAGRAPH 4 5 2 FOR A DESCRIPTION OF A PILOT CONTROLLED AUDIO MUTE SELECT SWITCH ROUTE THE ANTENNA CABLE S AS FAR AS PRACTICAL FROM ANY HARNESS BUNDLE IN NO CASE SHOULD THE ANTENNA CABLE S LACED INTO A HARNESS BUNDLE MAXIMUM COAXIAL CABLE LOSS IS 1 5 dB AT 1090 MHz THE AUDIO PANEL WIRING CONFIGURATION SHOWN DOES NOT ALLOW THE PILOT TO SELECT AND DESELECT ALTITUDE TRAFFIC ALERT AUDIO A SWITCHED INPUT MAY ALSO BE USED BUT THE AUDIO PANEL SHOULD BE PLACARDED IF AN ADF OR DME INPU
25. 2002 Yate amended of the Sbdininistrablor Signature FAA Program Manager Wichita Aircraft Certification Office Title roc a A a ____ ______________ alteration of this certificate is punishable by a fine of not exceeding 1 000 or imprisonment not exceeding 3 years or both FAA Form B110 2 10 68 PAGE 1 of 2 PAGES This certificate may be transferred in accordance with FAR 21 47 Page A 2 GTX 330 Installation Manual Revision F 190 00207 02 2 Continued Airworthiness Other than for regulatory periodic functional checks maintenance of the GTX 330 15 condition only Refer to the GTX 330 Maintenance Manual Garmin P N 190 00207 05 Periodic maintenance of the GTX 330 1s not required This section provides assistance to the installing agency in preparing Instructions for Continued Airworthiness ICA in response to Bulletin Number HBAW 98 18 Checklist for Instructions for Continued Airworthiness for Major Alterations Approved Under the Field Approval Process effective 10 7 98 Aviation Authority approved installers are hereby granted permission to reference appropriate service instructions and excerpts from this Installation Manual to accomplish the Instructions for Continued Airworthiness This permission does not construe suitability of the documents It is the applicant s responsibility to determine the suitability of the documents for the ICA
26. 21 5301 WWW ecsdirect com MIL C 17 types See current issue of Qualified Products List QPL 17 RG types See current issue of Qualified Products List QPL 17 GTX 330 Installation Manual 190 00207 02 Page 2 3 Revision F 2 6 Cooling Air The GTX 330 meets all applicable TSO requirements without forced air cooling The application of forced air cooling to the rear air nozzle of the GTX 330 1s highly recommended to provide beneficial cooling to the unit The GTX 330 was designed to handle a constant interrogation of 450 Pulse Repetition Frequency PRF per second with short periods of 1200 PRF Rate limit 1s set at 1200 PRF A typical radar site would interrogate the transponder once every 5 to 10 seconds for approximately 100 milliseconds at a 400 PRF rate In very high traffic areas with multiple ground stations and 5 traffic it is possible to have long term PRF rates above 450 PRF 2 7 GTX 330 Installation Avoid installing the unit near heat sources If this is not possible insure that additional cooling 1s provided Allow adequate space for installation of cables and connectors The installer will supply and fabricate all of the cables All wiring must be in accordance with FAA 43 13 18 and AC 43 13 2A l Assemble the connector rack kit according to Figure B 2 Install the rack assembly according to the dimensions given in Figure 1 and paragraph 1 6 2 Physical Characteristics Mounting bra
27. 3 26 04 Upgrade to SW 3 05 25218 Page A GTX 330 Installation Manual Revision F 190 00207 02 This manual 15 written for software version 3 05 The software version and information in this document is subject to change without notice 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 A violation of the EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to 1 000 000 under Section 2410 of the Export Administration Act of 1979 Include this notice with any reproduced portion of this document 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 NOTE Throughout this document references made to GTX 330 shall egually apply to the GTX 330D except where specifically noted GTX 330 Installation Manual Page i 190 00207 02 Revision F This page intentionally left blank Page
28. 45 RS 232 OUT HI RS 232 OUT LO GARMIN 400 500 Series Unit 2 GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE E GARMIN GMA 340 Audio Panel SEE NOTE 5 ALT WRN IN ALT WRN RETURN Figure C 6 Dual GTX 330 Interconnect Wiring Diagram Dual Display Connections Page C 11 Page C 12 blank Revision F APPENDIX C INTERCONNECT DRAWINGS GARMIN 400 500 Series Unit 1 GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE E GARMIN 45 RS 232 OUT HI RS 232 OUT LO NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 ARINC 429 IN 1 P3301 32 AND 35 INPUT ALLOWS AUTOMATED START AND STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND GND MODE UPON LANDING 3 WHEN TIS 15 USED IN THE AIRCRAFT DO NOT CONNECT ANOTHER TRAFFIC SYSTEM TO THE SAME 400 500 SERIES UNIT REFER TO FIGURE C 8 4 FOR THE REMAINDER OF GTX 327 CONNECTIONS REFER GTX 327 TRANSPONDER INSTALLATION MANUAL P N 190 00187 02 GTX 330 Installation Manual 190 00207 02 P3301 P4001 P5001 ARINC 429 IN 1 A 32 A ND 46 ARINC 429 IN 1 B 35 lt 47 ARINC 429 OUT 1 A 37 5 NE A O A 48 ARINC
29. 5 3 In Flight Loss of Cooling 4 5 4 Not Applicable Cooling Air is Not Required but is HiGHLY RECOMMENDED Altitude 4 6 1 Decompression 4 6 2 Overpressure 4 6 3 Issued 07 29 97 Temperature Variation 5 0 Equipment tested to Category B Issued 07 29 97 Humidity 6 0 Equipment tested to Category A Issued 07 29 97 GTX330 GTX33 Environmental Qualification Form 005 00131 03 Page 2 of 3 Rev C Figure A 1 GTX 330 Environmental Qualification Form Sheet 1 of 2 Page A 6 GTX 330 Installation Manual Revision F 190 00207 02 Operational Shocks amp Crash Safety 7 0 Equipment tested to Category B Sustained Crash Safety 72 Equipment tested for Random Orientation Issued 07 29 97 8 0 Equipment tested to Test Curves B2 and M Change No 1 Issued 12 14 2000 See Note 1 Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Power Input 16 0 Equipment tested to Categories B Z Change No 2 Issued 6 12 2001 Voltage Spike Equipment tested to Category A Issued 07 29 97 Audio Frequency Conducted 18 0 Equipment tested to Categories Z Susceptibility Power Inputs Change No 2 Issued 6 12 2001 Issued 07 29 97 Radiated and Conducted Change No 1 Issued 12 14 2000 Energy Issued 07 29 97 Susceptibility Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Issued 07 29 97 Notes and Remarks l Vibration Test Curve M
30. A 3 190 00207 02 Revision F 10 11 12 13 14 15 16 Maintenance Instructions Maintenance of the GTX 330 15 condition only Periodic maintenance 15 not required Refer to the GTX 330 Maintenance Manual Troubleshooting Information Refer to the GTX 330 Maintenance Manual 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 Diagrams Refer to Section 3 and Section 4 of this manual Special Inspection Requirements N A Application of Protective Treatments N A Data Relative to Structural Fasteners Antenna installation removal and replacement should be in accordance with applicable provisions of AC 43 13 1B and AC 43 13 2A Also refer to Section 2 of this manual Special Tools N A This Section is for Commuter Category Aircraft Only A Electrical loads Refer to Section 1 3 of this manual B Methods of balancing flight controls N A C Identification of primary and secondary structures N A D Special repair methods applicable to the airplane Antenna installation removal and replacement should be in accordance with applicable provisions of AC 43 13 1B and 43 13 2 Overhaul Period No additional overhaul time limitations Airworthiness Limitation Section N A Revision To revise this ICA a letter must be submitted t
31. ARINC 429 lines 15 received in the second 400 500 Series unit via ARINC 429 CHANNEL 2 while the GTX 330 15 active No data 15 received over ARINC 429 CHANNEL 2 while the GTX 330 is in remote standby Remote standby 15 usually used as part of a dual transponder installation Page 4 8 GTX 330 Installation Manual Revision F 190 00207 02 4 6 4 ARINC 429 Input Output The ARINC 429 Output 2 port J3301 pins 30 and 28 15 at a high impedance when in remote standby therefore not active When two GTX 3305 are installed the two ARINC 429 Output 2 ports may be hard wired together since the EXTERNAL STANDBY SELECT input 15 active for only one of the two GTX 3305 at any given time The GTX 330 ARINC 429 Output 1 port is active when J3301 pin 13 15 grounded EXTERNAL STANDBY SELECT remote STANDBY In installations having a transponder combination of GTX 330 GTX 327 or GTX 330 other transponder the GARMIN and GARMIN W TIS formats from the ARINC 429 Output 1 port J3301 pins 34 and 37 are available if the GTX 330 has SW 3 03 and above Table 4 9 ARINC 429 Pin Assignments ll PinName PinNumber VO __ The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers Refer to Figures C 1 C 5 C 6 C 7 and C 8 for the ARINC 429 serial data interconnect and Sections 5 2 8 and 5 2 18 for ARINC 429 serial data configuration GTX 330 Installation Manual Page 4 9 190 00207 02
32. ER UNLESS OTHERWISE NOTED 2 THE GARMIN FORMAT ON ARINC 429 OUT 2 IS A DATA CONCENTRATOR OUTPUT THAT COMBINES DATA FROM GTX 330 DATA INPUTS THE GARMIN W TIS FORMAT ADDS TIS TRAFFIC DATA ON THE SAME HIGH SPEED ARINC 429 BUS 3 ARINC 429 IN 1 P3301 32 AND 35 OR RS 232 IN 1 P3301 22 INPUT ALLOWS AUTOMATED START AND STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND GND MODE UPON LANDING 4 LOWER CASE PIN DESIGNATORS ARE SHOWN AS UNDERLINED UPPER CASE LETTERS 5 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY WHEN TIS IS USED IN THE AIRCRAFT DO NOT CONNECT ANOTHER TRAFFIC SYSTEM TO THE SAME 400 500 SERIES UNIT REFER TO FIGURE C 8 XIGNAddV SONIMVuUG LOANNOOYSALNI INTERCONNECT DRAWINGS APPENDIX C NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 ARINC 429 IN 1 P3301 32 AND 35 INPUT ALLOWS AUTOMATED START AND STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND GND MODE UPON LANDING 5 WHEN TIS IS USED IN THE AIRCRAFT DO NOT CONNECT ANOTHER TRAFFIC SYSTEM TO THE SAME 400 500 SERIES UNIT GTX 330 Installation Manual 190 00207 02 REFER TO FIG
33. Encoder Serial Input Connections For complete dual installations containing two encoders it is best to connect one encoder to each transponder 4 4 4 Altimeter Selection Priority The installer must be aware of the GTX 330 priority for selecting encoded altimeter interconnections The GTX 330 searches in this sequence for altitude and stops when it finds a valid pressure altitude input Only approved devices may provide altitude to the GTX 330 in accordance with 14 CFR Part 91 217 In addition all altitude reporting devices installed in the aircraft must meet certification requirements of 14 CFR Part 91 413 The installer must select an altitude reporting device that 1s a certified altitude source for the particular aircraft Altitude reporting equipment order of precedence 1 ARINC 429 Air Data Computer label 203 if configured W ALT 25 2 ARINC 429 EFIS label 203 if configured W ALT 25 3 RS 232 Fuel Air Data Computer if configured W ALT 25 4 Parallel wire Gray Code input 100 5 Shadin Altitude Serializer Encoder 1007 25 6 Icarus Altitude Serializer Encoder 100 25 It is the installing agency s responsibility to determine that the installed encoder is compatible with the selected altitude reporting criteria either 100 25 Refer to Section 5 2 8 and 5 2 9 for the altitude data reporting configuration GTX 330 Installation Manual Page 4 5 190 00207 02 Revision F 4 5 Discrete Functions
34. Equipment Unit P N 011 00455 T 20 Erba Sel 011 00455 D 30 011 00455 P 50 Notes See Paragraph 1 6 3 for part number and complete TSO classification and description versions of the 011 00455 are class 2A except 40 50 which are class 1A and obsolete GTX 330 Installation Manual Page A 5 190 00207 02 Revision F GTX330 GTX33 Environmental Qualification Form Nomenclature GTX330 GTX33 Airborne Air Traffic Control Radar Beacon System Mode Select ATCRBS Mode S Transponder Equipment TSO JTSO Number TSO C112 JTSO 2C112a Type Model Part Number TSO Class GTX33 Non Diversity Part Number 010 00267 Includes 011 00779 Class 2A1 121 010 GTX33D Diversity Part Number 010 00294 Includes 011 00779 Class 2A1 121 011 GTX330 Non Diversity Part Number 010 00230 Includes 011 00455 Class 2A1 121 010 GTX330D Diversity Part Number 010 00293 Includes 011 00455 Class 2A1 121 011 Manufacturer s Specification And Or Other Applicable Specification 004 00099 00 Manufacturer Garmin Ltd or its subsidiaries Address 1200 East 151 Street Olathe Kansas 66062 U S A DO 160D RTCA DO 160D Conditions Section and Description of Conducted Tests Date of Issue Temperature and Altitude 4 0 Equipment tested to Categories A2B2F 1 Ground Survival Low Operating Low 4 5 1 Ground Survival High Short Time Operating High 4 5 2 Operating Temperature High 4
35. LERT DEVIATION Altitude Format This field determines the amount of altitude difference from selected altitude to generate an altitude alert deviation It is set to 200 feet the minimum altitude at the factory SQUAT SWITCH The squat switch field may be set to either YES or NO Second CONFIGURATION Page Selecting YES in this field sets the GTX 330 to use the squat switch to determine lift off Selecting NO sets the GTX 330 to use Automated Airborne Determination from other sources DELAY TIME This 15 the number of seconds the aircraft must be on the ground before the AUTO STANDBY feature automatically switches to standby mode when the airborne source 15 the squat switch It has a range of 0 zero seconds to 99 seconds with the default set to 24 seconds AUTO FLIGHT TIMER Available choices are MAN CLEAR and ACCUM Selecting CLEAR resets flight time to zero and starts the flight timer when lift off is sensed Manual selection DEFAULT Flight timer START STOP is controlled manually by the pilot Automated flight timer START STOP resets to zero at every lift off Automated flight timer START STOP accumulates meaning it continues counting up at lift off Page 5 14 GTX 330 Installation Manual Revision F 190 00207 02 5 2 11 Temperature SENSOR INSTALLED TEMPERATURE Page Sets the Sensor to YES or NO Default is NO UNITS Sets the units to degrees Fahrenheit or Centigrade Default 15 degrees C
36. ONLY MAXIMUM AIRCRAFT PANEL THICKNESS IS 125 INCH 3 2 mm GTX 330 Installation Manual 190 00207 02 6 30 160 0 68 42 7 05 1 3 75 19 1 4 2 51 63 8 6 30 160 0 X 1 60 40 6 05 1 3 Spe 2 45 62 2 2 98 75 8 6 18 157 0 NOTES 1 DIMENSIONS INCH mm 2 IF THE FRONT LIP OF THE MOUNTING RACK 5 BEHIND THE SURFACE OF THE AIRCRAFT PANEL THE UNIT CONNECTORS MAY NOT FULLY ENGAGE Figure B 3 GTX 330 Recommended Panel Cutout Dimensions Page B 5 Page B 6 blank Revision F APPENDIX C INTERCONNECT DRAWINGS GARMIN 400 500 Series Unit 1 GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE E P3301 XPDR CIRCUIT BREAKER 22 AWG AIRCRAFT POWER 1 21 5A 11 33 AIRCRAFT POWER 22 AIRCRAFT POWER 1 42 XPDR CIRCUIT BREAKER 422 AWG AIRCRAFT POWER 2 56 OPTIONAL ALTERNATE 11 33 VDC AIRCRAFT POWER 22 AWG AIRCRAFT POWER 2 22 POWER GROUND 27 22 POWER GROUND s 22 SWITCHED POWER OUT 62 PELS SEE NOTE 2 AVIONICS MASTER ON SELECT 1 SEE NOTE 3 28 V LIGHTING BUS HI
37. P Interconnect Wiring Diagram Encoding Altitude Connections GTX 330 Installation Manual Page C 3 Page C 4 blank 190 00207 02 Revision F 0 20200 061 enue A uonejpejsu Q0 XLO GARMIN 550 Bendix King Trans Cal Ameri King Encoding imerer 5501 130A SSD120 AK 350 or Blind Encoder ALTITUDE 04 11 1 1 1 04 ALTITUDE A1 2 2 2 2 A1 ALTITUDE A2 4 5 5 5 A2 ALTITUDE A4 5 4 4 4 4 ALTITUDE B1 7 2 5 5 1 ALTITUDE B2 9 9 9 9 B2 ALTITUDE B4 10 10 10 10 B4 ALTITUDE C1 8 11 11 11 1 ALTITUDE C2 5 15 15 15 2 ALTITUDE C4 6 12 12 12 C4 ALTITUDE COMMON GROUND 50 6 6 6 COMMON XIGNAddV SONIMV4ad LOANNOOYSALNI Altitude Serializer Garmin Shadin Shadin or Fuel Air Da 45 8800T 9000T F ADC 200 SEE NOTE 3 9200T F ADC 2000 P5 RS 232 IN 2 24 Q E 1 7 6 RS 232 OUT EE 5 15 9 5 252 OUT LO GPS Receiver Garmin Garmin Garmin 400 Series 500 Series GPS 155 XL Unit Unit GNC 300 XL P4001 P5001 P101 RS 232 OUT 2 25 E 57 57 17 RS 232 IN Y Y Current Sensing Temperature Probe CURRENT TEMPERATURE PROBE OUT 41 A A IN CURRENT TEMPERATURE PROBE IN 44 J J OUT suonoeuuo pue epni
38. Revision F This page intentionally left blank Page 4 10 GTX 330 Installation Manual Revision F 190 00207 02 5 POST INSTALLATION CONFIGURATION CHECKOUT PROCEDURE Perhaps the most important factor in the GTX 330 transponder configuration and checkout is the Mode S address entry Refer to Section 5 2 12 for Mode S address entry pages 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 If the unit detects an internal failure mode the word FAIL 15 displayed on the screen Make sure an approved device 15 installed for reporting altitude in accordance with 14 CFR Part 91 217 Refer to Section 4 4 4 for altimeter data selection priority 5 1 Operation 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 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 GTX 330 Front Pane The GTX 330 should be turned off before starting aircraft engine s GTX 330 Installation Manual 190 00207 02 Page 5 1 Revision F 5 1 1 Function Selector Switches The function selection s
39. T IS USED FOR EXAMPLE Figure C 1 GTX 330 Typical Interconnect Wiring Diagram Page C 1 Page C 2 blank Revision F APPENDIX C INTERCONNECT DRAWINGS GARMIN Encoding Altimeter GUA 39 90 1 or Blind Encoder P3301 SEE NOTE 2 ALTITUDE D4 11 D4 ALTITUDE A1 2 lt gt A1 ALTITUDE A2 4 A2 ALTITUDE A4 5 lt A4 ALTITUDE B1 7 B1 ALTITUDE B2 9 lt gt B2 ALTITUDE B4 10 lt BA ALTITUDE C1 8 P C1 ALTITUDE C2 3 lt 62 ALTITUDE C4 6 gt SWITCHED POWER OUTPUT 62 TRANSPONDER 2 COMMON EXTERNAL STANDBY SELECT 13 s V SEE NOTE 3 TRANSPONDER 1 POWER INPUT GARMIN GIA 550 NOTED P5501 SEE NOTE 2 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED a 4 2 THE GTX 330 CONTAINS INTERNAL ALTITUDE CODE LINE ISOLATION DIODES EXISTING INSTALLATIONS WITH DIODES ALTITUDE A2 A INSTALLED IN THE WIRE HARNESS MAY BE USED AS IS ALTITUDE A4 5 cures gt WITHOUT REMOVING THE DIODES ALTITUDE 2 9 gt 3 FOR ENCODER POWER INPUT USE DIODES OF AT LEAST ALTITUDE B4 10 3 AMP 50 VOLTS REVERSE RATING ALTITUDE C1 8 ALTITUDE C2 3 ALTITUDE C4 6 SWITCHED POWER OUTPUT 62 EXTERNAL STANDBY SELECT 13 Figure C 2 Dual TX
40. UCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY To obtain warranty service contact your local Garmin Authorized Service Center For assistance in locating a Service Center near you call Garmin Customer Service at one of the numbers shown below Products sold through online auctions are not eligible for rebates or other special offers from Garmin 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 Garmin International Inc Garmin Europe Ltd 1200 East 151 Street Unit 5 The Quadrangle Abbey Park Industrial Estate Olathe Kansas 66062 U S A Romsey 5051 9DL U K Phone 913 397 8200 Phone 44 1794 519944 FAX 913 397 0836 FAX 44 1794 519222 Page 1 8 GTX 330 Installation Manual Revision F 190 00207 02 2 INSTALLATION OVERVIEW 2 1 Introduction This section provides the necessary information for installing the GTX 330 Mode 5 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 Sections 3 and 4 contain interconnect wiring diagrams mounting dimensions and information pertaining to installation E
41. URE C 8 P3301 ARINC 429 IN 1 A 32 ETE A ARINC 429 IN 1 B 35 z 9 ARINC 429 OUT 2 A 30 A Na a ARINC 429 OUT 2 B 28 E UAWN SEE NOTE 5 TIS CONNECT SELECT 46 EXTERNAL STANDBY SELECT 13 a EN RS 232 IN 2 24 o AUDIO OUT HI 15 A Pa N AUDIO OUT LO 16 Oy V TRANSPONDER 2 GARMIN SEE NOTE 4 i GTX 350 2 a TRANSPONDER 1 ARINC 429 IN 1 A 32 A REE ARINC 429 IN 1 B 55 Y y ry r ARINC 429 OUT 2 50 A gt ARINC 429 OUT 2 B 28 z Y 9 5 TIS CONNECT SELECT 46 EXTERNAL STANDBY SELECT 13 y RS 232 IN 2 24 Q AUDIO OUT HI 15 A A AUDIO OUT LO 16 uU U THE GTX 550 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 THE AUDIO PANEL WIRING CONFIGURATION SHOWN DOES NOT ALLOW THE PILOT TO SELECT AND DESELECT ALTITUDE TRAFFIC ALERT AUDIO A SWITCHED INPUT MAY ALSO BE USED BUT THE AUDIO PANEL SHOULD BE PLACARDED IF AN ADF OR DME INPUT IS USED FOR EXAMPLE P4001 P5001 46 47 48 49 11 PS P4001 P5001 46 47 48 49 11 CER 51 52 GARMIN 400 500 Series Unit 1 GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE E GARMIN
42. UT B ARINC 429 OUT 1 A 37 aes As 48 GPS ARINC 429 IN 1 A ARINC 429 OUT 1 B 34 tre 49 GPS ARINC 429 IN 1 B TIS CONNECT SELECT 46 lt 11 ANNUNCIATE E 400 500 Series P4001 Unit 42 P5001 ARINC 429 OUT 2 30 ENANA O gt 48 GPS ARINC 429 IN 1 A ARINC 429 OUT 2 B 28 y gt 49 GPS ARINC 429 IN 1 B RS 232 OUT 2 25 Q IE gt 57 RS 232 IN AUDIO MUTE SELECT 47 FROM TAWS OR WIND SHEAR RADAR SYSTEM SEE NOTE 5 34 Audio Panel SEE NOTE 6 AUDIO OUT HI 15 A es gt 31 ALT WRN IN AUDIO OUT LO 16 H tre 32 ALT WRN RETURN NOTES 1 ARINC 429 IN 1 P3301 32 AND 35 INPUT ALLOWS AUTOMATED START 4 USE ARINC 429 ONLY IF SINGLE INSTALLATION NO REMOTE STBY STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND GND MODE USE RS 232 IF DUAL TRANSPONDER INSTALLATION USING REMOTE STBY UPON LANDING NEUEM 5 THE AUDIO MUTE SELECT INPUT P3301 47 MUTES ALL GTX 330 AUDIO WHEN 2 WHEN TIS IS INSTALLED IN THE AIRCRAFT TIS MAY TRANSMIT DATA ON ARINC OTHER SYSTEMS ARE OUTPUTTING HIGHER PRIORITY AUDIO WARNINGS REFER 429 OUTPUT 1 WHILE OTHER DATA MAY BE TRANSMITTED VIA ARINC 429 TO PARAGRAPH 4 5 2 FOR A DESCRIPTION OF A PILOT CONTROLLED AUDIO OUTPUT 2 THE OTHER TRAFFIC SYSTEM CAN THEN BE CONNECTED TO THE MUTE SELECT SWITCH SECOND 400 500 SERIES UNIT SEE SECTIONS 4 AND 5 FOR CONFIGURATION 6 THE AUDIO PANEL WIRING CONFIGURATION SHOWN DOES NOT ALLOW 3 IN DUAL TRANSPONDER INSTALLATIONS WHEN THE PRIMARY GTX
43. ach installation shall be accomplished to meet the requirements of FAA AC 43 13 1B and AC 43 13 2A 2 2 Unpacking and Inspecting Equipment Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment If the unit is damaged notify the carrier and file a claim To justify a claim save the original shipping container and all packing materials Do not return the unit to Garmin until the carrier has authorized the claim Retain the original shipping containers for storage If the original containers are not available a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement 2 3 Antenna Installation 2 3 1 Location Considerations Place optional diversity antenna on top of aircraft 1 Place main antenna on bottom of aircraft Figure 2 1 Antenna Installation Considerations A The antenna s Garmin P N 010 10160 00 should be mounted away from major protrusions such as engine s propeller s and antenna masts It should also be as far as practical from landing gear doors access doors or other openings that could effect its radiation pattern GTX 330 Installation Manual Page 2 1 190 00207 02 Revision F B The main antenna should be mounted vertically on the bottom of the aircraft The optional second diversity antenna should be mounted vertically on top of the aircraft Horiz
44. aft See Figure 4 3 for software update connections GIX 550 P3301 XPDR CIRCUIT BREAKER 22 AWG AIRCRAFT POWER 1 21 5A 11 33 VDC AIRCRAFT POWER 22 AWG AIRCRAFT POWER 1 42 TEST MODE SELECT 18 1 1 P POWER GROUND 27 5 2 POWER GROUND 45 RS 232 IN 1 22 5 5 RS 232 OUT 1 25 2 2 9 D SUB CONNECTOR TO PC S COM PORT Figure 4 3 GTX 330 Software Update Connections 4 6 3 Aircraft with Both TIS and TCAS TCAD Installed Refer to Figure C 8 for wiring connections If redundant traffic systems are desired in the aircraft such as TIS and TCAD TCAS both systems cannot be connected to the same 400 500 Series unit to display traffic simultaneously In a multiple traffic system multiple 400 500 Series unit installation connect ARINC 429 CHANNEL 1 from the GTX 330 to only one of the 400 500 Series units and ARINC 429 CHANNEL 2 to the other 400 500 Series unit Connect the TIS CONNECT SELECT line from the GTX 330 to the 400 500 Series unit receiving TIS data The TCAD TCAS system may now be connected to the second 400 500 Series unit Refer to Section 5 for configuration Configure ARINC 429 output CHANNEL 1 for GARMIN W TIS and ARINC 429 output CHANNEL 2 for GARMIN TIS 15 then enabled over CHANNEL 1 when the GTX 330 15 connected to a Garmin 400 500 Series unit through the ARINC 429 wiring configured input data that is concentrated through the GTX 330 via
45. aircraft avionics master bus can turn the unit on Provision is made for unit software upgrade by means of RS 232 data through rear connector pins If an optional connector 15 placed in the aircraft transponder removal and reinstallation for SW upgrade 15 not required The software can be changed while the unit is still mounted inside the aircraft GTX 330 Installation Manual Page 1 1 190 00207 02 Revision F CAUTION The GTX 330 lens 15 coated with a special anti reflective coating which is very sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings 1 3 TIS System Capabilities The GTX 330 also provides uplink information such as Traffic Information Service TIS TIS is a ground based service providing relative location of all ATCRBS Mode A and Mode C transponder equipped aircraft within a specified service volume The TIS ground sensor uses real time track reports to generate traffic notification TIS provides a graphic display of traffic advisory information in the cockpit for non TCAS equipped aircraft Advisory traffic information 15 available to aircraft equipped with a Mode 5 data link such as the Garmin GTX 330 transponder Advisory traffic information may be displayed on a Garmin 400 500 Series unit surveill
46. al 190 00207 02 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 6 2 SQUAT SWITCH IN P3301 17 INPUT ALLOWS AUTOMATED START AND STOP OF FLIGHT TIMER AND PLACES THE TRANSPONDER IN GROUND MODE UPON LANDINC LOGIC IS SET VIA A CONFIGURATION PAGE 5 EXTERNAL SUPPRESSION 1 0 P3301 31 SENDS AND ACCEPTS POSITIVE GOING SUPPRESSION PULSES TO FROM ANOTHER TRANSPONDER DME 8 4 EXTERNAL STANDBY SELECT P3301 13 WHEN TIED TO GROUND WILL PLACE THAT UNIT IN STANDBY MODE TYPICALLY USED IN DUAL INSTALLATIONS 5 MOMENTARY CONNECTION OF EXTERNAL IDENT SELECT P3301 12 TO GROUND WILL CAUSE THE GTX 550 TO TRANSMIT IDENT PULSES 52 ALT WRN RETURN D WHEN TIS 15 USED IN THE AIRCRAFT DO NOT CONNECT ANOTHER TRAFFIC SYSTEM TO THE SAME 400 500 SERIES UNIT REFER TO FIGURE C 8 THE AUDIO MUTE SELECT INPUT P3301 47 MUTES ALL GTX 330 AUDIO WHEN OTHER SYSTEMS ARE OUTPUTTING HIGHER PRIORITY AUDIO WARNINGS REFER TO PARAGRAPH 4 5 2 FOR A DESCRIPTION OF A PILOT CONTROLLED AUDIO MUTE SELECT SWITCH THE AUDIO PANEL WIRING CONFIGURATION SHOWN DOES NOT ALLOW THE PILOT TO SELECT AND DESELECT ALTITUDE TRAFFIC ALERT AUDIO A SWITCHED INPUT MAY ALSO BE USED BUT THE AUDIO PANEL SHOULD BE PLACARDED IF AN ADF OR DME INPUT IS USED Figure C 4 GTX 330 Interconnect Wiring Diagram Discrete and Audio Connections Page C 7 Page C 8 blank Revision F c0 L0700 061 enue A uonejpejsu Q0 XLO 4
47. ance data includes all transponder equipped aircraft within the coverage volume Aircraft without an operating transponder are invisible to TIS TIS displays traffic within seven nautical miles from 3000 feet below to 3500 feet above the requesting aircraft The pilot sees the location relative direction and altitude of other aircraft 1 4 Mutual Suppression Pulses Other equipment on board the aircraft may transmit in the same frequency band as the transponder such as DME or another transponder Mutual suppression 15 a synchronous pulse that 1s sent to the other equipment to suppress transmission of a competing transmitter for the duration of the pulse train transmission The transponder transmission may be suppressed by an external source and other equipment on board may be suppressed by the transponder This feature 15 designed to limit mutual interference 1 5 Interface Summary The GTX 330 provides the following interface connections via the rear connector e 10 encoding altimeter inputs e External IDENT input e External STBY input useful for dual transponder installations e External suppression pulse input e Switched power output of up to 1 5 amps for digital altitude encoder power e Aircraft power input 11 to 33 volts e Aircraft dimming bus input voltage Page 1 2 GTX 330 Installation Manual Revision F 190 00207 02 e Aircraft master switch turn on option e Serial altitude or GPS groundspeed input
48. anel 5 2 6 Key Lighting Page The key lighting mode 15 always the same as the display backlight mode so the mode must be changed on the Display KEY LIGHTING Page Backlight configuration page If the lighting mode is AUTO then the key lighting parameters can be edited on this page KEY Key Lighting SELECTION DESCRIPTION AUTO Automatic Key lighting is automatically controlled based on the parameters entered on this configuration page MAN Manual Key lighting is controlled manually by the pilot on the GTX 330 DISPLAY page GTX 330 Installation Manual Page 5 9 190 00207 02 Revision F LVL Level Shows the current level of key lighting based on the lighting input source lighting bus voltage or the ambient light if the source is PHOTO and the settings on this configuration page This field has a range of 0 zero to 999 but 1s not a user entered field display only 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 0 to 7 and is set to 4 at the factory MIN Minimum Auto Only 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 It is prudent to verify that key lighting characteristic
49. ckets are not supplied due to the wide range of mounting configurations available Suitable mounting brackets may be fabricated from sheet metal or angle stock To insure a sturdy mount rear support for the unit must be provided 2 Looking at the bottom of the transponder make sure the front lobe of the locking mechanism 15 in a vertical position This can be accomplished by using a 3 32 Allen wrench through the face plate 3 Slide the unit into the rack until the front lobe of the unit touches the rack 4 Turn the Allen wrench clockwise until unit 1s secured in the rack Continue turning until tight Do not overtighten the screw 5 Toremove the unit from the rack turn the 3 32 Allen wrench counterclockwise until it disengages from the rack Page 2 4 GTX 330 Installation Manual Revision F 190 00207 02 3 INSTALLATION PROCEDURE 3 1 Antenna Installation Install the antenna according to the antenna manufacturer s instructions and FAA AC 43 13 1B and AC 43 13 2A The antenna cable requires a BNC plug connector on both ends Follow BNC connector manufacturer instructions for assembly of the BNC connector 3 2 Electrical Connections electrical connections except for the antenna s and shield ground are made through a single 62 pin D subminiature connector see Figure 4 1 The card edge connector may be used to terminate shield grounds to the GTX 330 back plate Table 4 1 lists the electrical connections of all input an
50. d output signals See Appendix C for interconnect wiring diagrams and cable requirements for each signal Required connector and associated hardware are supplied in the connector kit P N 011 00583 00 CAUTION Check wiring connections for errors before inserting the GTX 330 into the rack Incorrect wiring could cause internal component damage Table 3 1 Pin Contact Part Numbers 62 pin D Subminiature connector P3301 16 AWG 18 AWG Power Only Power Only Garmin P N 336 00044 01 336 00044 00 336 00044 02 336 00021 00 Military P N Table 3 2 Recommended Crimp Tools 15 108 20 AWG 2228AWG _____ Hand Crimping Tool Positioner Insertion Positioner Insertion Extraction Tool Extraction note 2 Tool Military P N M22520 2 01 M81969 1 04 M22520 2 09 M81969 1 04 9502 11 M81969 1 04 9502 3 M81969 1 04 739 601966 1 91067 1 601966 6 91067 1 8 M81969 1 04 K42 M81969 1 04 615717 M81969 1 04 615725 M81969 1 04 GTX 330 Installation Manual Page 3 1 190 00207 02 Revision F 1 Non Garmin part numbers shown not maintained by Garmin and consequently are subject to change without notice 2 Extracting the 16 18 and 20 contact requires that the expanded 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 an extractor due to the absence of the wire A new contact must be used when reassembling the connector 3 3 P
51. de changes GTX 330 Installation Manual Page 5 3 190 00207 02 Revision F 5 1 3 Function Display PRESSURE ALT Displays the altitude data supplied to the GTX 330 in feet hundreds of feet 1 e flight level or meters depending on configuration FLIGHT TIME Displays the Flight Time controlled by the START STOP key or by one of four airborne sources squat switch GPS ground speed recognition airdata airspeed recognition or altitude increase as configured during installation The timer begins when the GTX 330 determines that the aircraft is airborne ALTITUDE MONITOR Controlled by START STOP key Activates a voice alarm and warning annunciator when altitude limit is exceeded OAT DALT Displayed when the GTX 330 is configured with temperature input Displays Outside Air Temperature and Density Altitude COUNT UP TIMER Controlled by START STOP and CLR keys COUNT DOWN TIMER Controlled by START STOP CLR and CRSR keys The initial Count Down time 15 entered with the 0 9 keys CONTRAST This page 15 only displayed if manual contrast mode 15 selected in Configuration Mode Contrast 15 controlled by the 8 and 9 keys DISPLAY This page 15 only displayed if manual backlighting mode 15 selected in Configuration Mode Backlighting 15 controlled by the 8 and 9 keys Page 5 4 GTX 330 Installation Manual Revision F 190 00207 02 5 2 Configuration Pages The configuration descriptions given in this section reflect softwar
52. e version 3 05 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 key reverses through the pages stopping at the Menu page The CRSR key highlights selectable fields on each page When a field 15 highlighted the 0 9 keys enter numeric data and the 8 9 keys move through list selections Press the CRSR key to accept changes When a field is highlighted pressing the FUNC key moves to the next configuration page without saving the changes Changes made through the configuration pages are stored in EEPROM memory To exit the configuration pages turn the power off Then turn on again without holding the FUNC key for normal operation The configuration page sequence is as follows menu categories are listed in parentheses Menu Audio and Messages 1 Audio and Messages 2 Traffic Messages Display Mode Display Backlight Key Backlight Contrast ARINC 429 Input 1 First I O Configuration page ARINC 429 Input 2 Second I O Configuration page ARINC 429 Output 5 232 Input Output Operation Configuration 1 First Aircraft Configuration page Operation Configuration 2 Second Aircraft Configuration page Temperature Aircraft Address Flight ID Aircraft Type Gray Code Input External Switch State Analog Input RS 232 Input Display ARINC 429 Input Display 71 ARINC 429 Input Disp
53. eed ARINC 429 bus Airborne Data Link Processor ADLP is reserved for future data link applications ADLP requires an ARINC 429 input and output The ADLP interface allows the Mode 5 data link transponder to function as a modem An ADLP performs functions requiring sending and or receiving data from ground sensors via Mode S interrogations and replies NOTE The GTX 330 15 currently FAA approved to display TIS traffic information on Garmin 400 500 Series products only 4 6 1 RS 232 Input Output Table 4 8 RS 232 Pin Assignments PinName I O _ 5 232 IN 1 RS 232 OUT 2 RS 232 IN 2 The RS 232 outputs conform to Standard RS 232C with an output voltage swing of at least 5 V when driving a standard RS 232 load Refer to Figures 4 3 C 3 C 5 and 8 for the RS 232 serial data interconnect and to Sections 5 2 9 and 5 2 17 for RS 232 serial data configuration GTX 330 Installation Manual Page 4 7 190 00207 02 Revision F 4 6 2 RS 232 Input Output Software Update Connections An optional RS 232 serial data connector may be installed in the aircraft for future software upgrades negating the need to remove the transponder from the panel The connector can be mounted anywhere convenient for access such as under the instrument panel on a remote avionics shelf or in the instrument panel itself Be sure to label the connector for Software Update Do not include the Test Mode Select switch in the aircr
54. ental Type Certificate STC pertaining to and valid for the subject antenna installation 3 Contact the FAA Aircraft Certification Office in the appropriate Region and request identification of FAA Designated Engineering Representatives DERs who are authorized to prepare and approve the required antenna installation engineering data 4 Obtain FAA Advisory Circular AC 183C and select and contact a DER from the roster of individuals identified thereunder 5 Contact an aviation industry organization such as the Aircraft Electronics Association and request their assistance Page 2 2 GTX 330 Installation Manual Revision F 190 00207 02 2 5 Cabling and Wiring Use AWG 24 or larger wire for all connections unless otherwise specified by the aircraft manufacturer or Garmin The standard pin contacts supplied in the connector kit are compatible with up to AWG 22 wire In cases where some installations have more than one unit sharing a common circuit breaker sizing and wire gauge is based on aircraft circuit breaker layout length of wiring current draw of units and internal unit protection characteristics Do not attempt to combine more than one unit on the same circuit breaker unless it 15 specified on aircraft manufacturer approved drawings In some cases a larger gauge wire such as AWG 18 or 16 may be needed for power connections If using 16 or 18 barrel contacts ensure that no two contacts are mounted directly adjacent to eac
55. f aircraft to determine that the aircraft installation conditions are within the TSO standards TSO 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 For GTX 330 TSO compliance and STC see Appendix A For antenna TSO compliance refer to antenna manufacturer s literature Page 1 6 GTX 330 Installation Manual Revision F 190 00207 02 1 8 Aircraft Station Licensing Requirements The Telecommunications Act of 1996 effective February 8 1996 provides the FCC discretion to eliminate radio station license requirements for aircraft and ships The GTX 330 installation must comply with current transmitter licensing requirements To find out the specific details on whether a particular installation is exempt from licensing please visit the FCC web site http wireless fec gov aviation If an aircraft license 15 required make application for a license on FCC form 404 Application for Aircraft Radio Station License The FCC also has a fax on demand service to provide forms by fax The GTX 330 owner accepts all responsibility for obtaining the proper licensing before using the transponder CAUTION The UHF transmitter in this equipment is guaranteed to meet federal communications commission acceptance over the operating temperature range Modifications not expressly approved by Garmin could invalidate the license and ma
56. ght Standards Service AFS policy concerning follow on field approvals of Traffic Alert Advisory Systems such as the Garmin GTX 330 Mode S and GTX 330D Diversity Mode S Transponder systems installed and operated under the provisions of 14 CFR Part 91 or Part 135 Certain models of traffic display devices have been awarded Supplemental Type Certificates STC in certain makes and models of aircraft As such the appropriate STC approved data can be used as the basis for follow on FAA field approval on FAA Form 337 When an installing agency submits installation data for approval that 15 based on previously approved data the installation of the device can be field approved with the attendant Aircraft Flight Manual Supplement AFMS signed by the Airworthiness Aviation Safety Inspector ASI Refer to the GTX 330 330D SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT P N 190 00207 06 GTX 330 Installation Manual Page A 1 190 00207 02 Revision F United States of America Department nf Transportation Federal Abiation Administration Supplemental Type Certificate PD t STO1125WI certificate Lo Garmin International 1200 E 151 Street Olathe KS 66062 that the change in the design for the following product with the Canclations and therefor as specified hereon meets the airworthiness reguirements of Part of the Civil Air Regulations Original Ddod 2 A3SO
57. h as an EDMO P N 655 PROBE or Davtron P N C307PS Connect the red wire to pin 41 and the black wire to pin 44 The GTX 330 1s not configurable for different types of temperature sensors The temperature input specification is 1 microamp per degree Kelvin 1 wA K Refer to Figure C 3 for the temperature probe interconnect and to Section 5 2 11 for probe configuration GTX 330 Installation Manual Page 4 3 190 00207 02 Revision F 4 4 Altitude Functions Parallel gray code altitude inputs are considered active if either the voltage to ground is 1 9 V or the resistance to ground is lt 375 O These inputs are considered inactive if the voltage to ground is 11 33 Vdc Refer to Figures C 2 and C 3 for parallel gray code and Figure C 3 for serial data altitude interconnections Carefully check encoder input lines for correct connection after wiring 1s complete The GTX 330 contains internal altitude code line isolation diodes to prevent the unit from pulling the encoder lines to ground when the transponder 15 turned off For altimeters that can be connected in both serial data and parallel gray code format such as the Garmin GAE 43 Garmin P N 013 00066 00 select one or the other but not both wiring connections Among the surveillance items the Mode S transponder will transmit to the ground stations and other aircraft are altitude reporting in 25 increments with the proper encoder In order to report altitude 25 foot increments
58. h other This minimizes the risk of contacts touching and shorting to adjacent pins or to ground 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 When routing antenna cables observe the following precautions All cable routing should be kept as short and direct as possible e 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 The following table lists examples of the recommended antenna cable vendors and the type of cable to be used for specific lengths of cable Any cable meeting specifications is acceptable for the installation The maximum coaxial cable attenuation at 1090 MHz must not exceed 1 5 dB In the diversity installation the cable characteristics must be the same to within 0 1 dB Top and bottom cables of the same length should have approximately the same characteristics Max Length feet ECS Type MIL C 17 Type M17 128 3C142B M17 112 311601 M17 127 311501 311201 Supplier Information 310801 Vendor Electronic Cable Specialists 5300 W Franklin Drive Franklin WI 53132 Tel 800 327 9473 414 421 5300 Fax 414 4
59. ii 4 6 AT Discrete Inputs Pru ASIO nie Ds icono A E 4 6 4 5 epa Denm aaa 4 7 2 9 ARTNC 420 4 9 GTX 330 Installation Manual Page v 190 00207 02 Revision F GTX 330 HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification Mod Levels for the GTX 330 and GTX 330D Mode S Transponders Mod Levels are listed with the associated service bulletin number service bulletin date and the purpose of the modification The table is current at the time of publication of this manual see date on front cover and is subject to change without notice Authorized Garmin Sales and Service Centers are encouraged to access the most up to date bulletin and advisory information on the Garmin Dealer Resource web site at www garmin com using their Garmin provided user name and password SERVICE SERVICE PURPOSE OF MODIFICATION LEVEL BULLETIN BULLETIN NUMBER DATE GTX 330D Only Switch Diplexer Assembly reworked to prevent 200 volt supply line from shorting to the chassis Page vi GTX 330 Installation Manual Revision F 190 00207 02 1 GENERAL DESCRIPTION 1 1 Introduction This manual describes the physical mechanical and electrical characteristics and the installation requirements for the GTX 330 M
60. ii GTX 330 Installation Manual Revision F 190 00207 02 TABLE OF CONTENTS PARAGRAPH GENERAL DESCRIPTION do eoe o E uote or 1 22 Equipment Descent Ont unen ttti ttes Los TES System Capablanca 4 Mutual Suppression Pulse L gt nterface ica AA da add LO Technical A O iS Iii ua a O m E 1 8 Aircraft Station Licensing RequiremMentS ooooooononncnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnonononos 1 9 Limited W casos e OR Me 2 INSLAELAIION OVER VIBW nt Ma ve Con tend ei Zl O 2 2 Unpacking and Inspecting Equipment eese 229 Amer Instala riada 2 4 Installation Approval Considerations for Pressurized 1 2 able and E UM etae ed S D EDD DAL M COOTAD ctas ina S cle MOL cutn O 2 7 TEX 390 doce rM Obi ete ce MD Vd INSTALLATION PROCEDURE caco zE o AA A O 3 25 Electrical CONE io 3 3 Post Installation C BeeKOUt 4 SYSTEM INTERCONNECTS aci dj Inn UA CO MA 42 Power And Lighting FUNCIONA ace ai 245 Temperature ioo d HD OT D 44 ali Discreto PUN CUON
61. iled specifications see the Environmental Qualification form in Appendix A 1 6 1 Electrical Specifications Power Requirements 11 0 to 33 0 Vdc Power Input 22 watts typical 45 watts maximum Humidity 95 O 50 C for 6 hours 85 38 C for 16 hours Tested to Category A in DO 160D 74 dBm nominal for 90 replies Mode S Altitude Capability 25 Foot Increments from 1000 to 50 175 feet with suitable serial data altitude 100 Foot Increments from 1000 to 62 700 feet Mode S Capability Selective Identification Codes Aircraft Type External Suppression Input Low 0 5 V High gt 8 V Audio Output 4 04 Vrms to 7 85 Vrms into 500 load Note Refer to Paragraph 1 6 3 Configurations Available for TSO class Page 1 4 GTX 330 Installation Manual Revision F 190 00207 02 1 6 2 Physical Characteristics Depth Behind Panel with Connectors 11 25 inches 286 mm measured from face of aircraft panel to rear of connector backshells GTX 330 GTX 330D Unit Weight 3 4 lbs 1 5 kg GTX 330 GTX 330D Rack Weight 4 2 lbs 1 9 kg Installed with rack and connectors 1 6 3 Configurations Available Catalog Unit Part Diversity Front Install TSO Class Part Number Kit Docs Number GTX 330 010 00230 00 011 00455 00 2 1 121 010 330 010 00230 01 011 00455 00 2 1 121 010 330 010 00230 20 011 00455 20 2 1 121 010 Note Documentation includes pilot s guide and warranty registratio
62. ircraft information Ground stations can interrogate Mode S Transponders individually using a 24 bit ICAO Mode 5 address which is unique to the particular aircraft In addition ground stations may interrogate a GTX 330 for its Transponder data capability and the aircraft s Flight ID which may be the registration number or other call sign The GTX 330 makes the maximum airspeed capability set via configuration pages see Section 5 available to TCAS systems on board nearby aircraft to aid in the determination of TCAS advisories In addition to displaying the code reply symbol and mode of operation the GTX 330 screen displays pressure altitude density altitude temperature and timer functions depending on equipment connections and configuration selection The unit also features an altitude monitor TIS traffic advisories and flight timers A voice or tone audio output announces altitude deviation TIS traffic advisory and count down timer expiration The GTX 330 features multiple transmit receive ARINC 429 and RS 232 data ports The unit concentrates data from three ARINC 429 inputs gray code RS 232 input data and discrete inputs to the high speed ARINC 429 output bus used by display systems such as the Garmin 400 Series 500 Series units The GTX 330 15 configured with all key controls The layout of the front panel keys and displays segregates the transponder s primary functions from the secondary functions The unit can be configured so the
63. ke it unlawful to operate the equipment GTX 330 Installation Manual Page 1 7 190 00207 02 Revision F 1 9 Limited Warranty This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase Within this 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 cover failures due to abuse misuse accident or unauthorized alteration or repairs THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR 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 THIS 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 Garmin retains the exclusive right to repair replace the unit or software or offer full refund of the purchase price at its sole discretion S
64. lay 72 GTX 330 Installation Manual Page 5 5 190 00207 02 Revision F CONFIGURATION MENU CONFIGURATION MENU Page The JUMP TO menu page provides the capability to select a configuration mode starting page without having to step through all of the pages Press the CRSR key and sequence through to the desired section with the 8 and 9 keys Jump to the selection by pressing the CRSR key again with the desired selection highlighted The FUNC key steps to the next configuration page after which the START STOP key reverses until stopping at the JUMP TO menu page SELECTION DESCRIPTION DIAGNOSTICS Jumps to Gray Code Input page DISPLAY AUDIO Jumps to Audio Volume page I O CONFIG Jumps to ARINC 429 INPUT 1 page ACFT CONFIG Jumps to Operation Configuration Z1 page Page 5 6 GTX 330 Installation Manual Revision F 190 00207 02 VOICE and VOLUME AUDIO MODE First Page Select desired VOICE The choice of OFF 15 not available for traffic TIS audio Make sure the volume level is sufficient for AUDIO MODE Second Page the aircraft environment involved MESSAGE Message 15 used as a test function only Message 0 15 a continuous tone Message 1 15 a short tone and 2 through 5 are voice messages Choose each selection to listen to the message SELECTION DESCRIPTION VOICE MALE FEMALE Sets the voice to male or female Default is male voice VOLUME Volume 15 adjusted from 0 default to maximum with the 8 or 9 key
65. ms 100 m i00 ms 100 m 100 m 100 ms 100 ms 500 ms 500 ms 100 ms 100 m 500 ms Eguipment Identifier 500 ms 100 203 204 206 210 211 213 306 307 314 320 371 377 5 12 GTX 330 Installation Manual Revision F 190 00207 02 5 2 9 RS 232 Input and Output Page LT RS 232 INPUT Altitude Source GPS Data RS 232 INPUT OUTPUT Page This 1s the electrical source for the GTX 330 altitude and GPS data input Refer to Section 4 4 4 for altimeter data selection priority SELECTION DESCRIPTION F DEFAULT The altitude code input is not from an RS 232 source PS RS 232 ground speed from a GPS device ICARUS ALT RS 232 serial altitude from an Icarus Instruments 3000 or Garmin GAE 43 ICRS ALT 25ft Reports Icarus Instruments or Garmin GAE 43 altitude in 25 foot increments ADC NO ALT RS 232 serial air data information from Shadin ADC 200 200 2000 ADC W ALT RS 232 serial air data information from Shadin ADC 200 200 2000 plus altitude data SHADIN ALT RS 232 serial altitude from Shadin 8800T 9000T 9200T SHDN ALT 256 Reports Shadin altitude in 25 foot increments FADC NO ALT RS 232 serial air data from Shadin 9628XX X family of Air Data Computers and Fuel Air Data Computers FADC W ALT RS 232 serial air data from Shadin 9628XX X family of Air Data Computers and Fuel Air Data Computers plus altitude data REMOTE RS 232 serial input remote data Reserved for future use
66. n card GTX 330 Installation Manual Page 1 5 190 00207 02 Revision F 1 6 4 Equipment Available GarminP N Sub Assy Connector Kit GTX 330 011 00583 00 SMP Install Rack GTX 330 115 00294 00 Sub Assy Backplate GTX 330 011 00582 00 For use with GTX 330 For use with GTX 330D two required for diversity Note A transponder antenna approved to TSO C66 or C74 that has been installed to meet the requirements of this manual may be approved for use with the GTX 330 1 6 5 Additional Equipment Required e Antenna Sealant Use antenna manufacturer s instructions install according to FAA AC 43 13 1B and AC 43 13 2A Cables The installer will supply all system cables including circuit breakers Cable requirements and fabrication 15 detailed in Section 2 of this manual e Hardware 6 32 x 100 Flat Head Screw 6 ea and 6 32 Self Locking Nut 6 ea Hardware required to mount the installation rack 1s not provided Encoding Altitude Digitizer Use encoding altimeter manufacturer s instructions install according to FAA AC 43 13 1B and AC 43 13 2A The Garmin GAE 43 Garmin P N 013 00066 00 can provide altitude data in either serial or parallel gray code format 1 7 Installation Approval The conditions and tests required for TSO 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 o
67. njy BuurM 12euuooJe u XLD ein lg 9 2 8 6 2 3384 4 5 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 ALTITUDE DATA MAY BE SUPPLIED BY PARALLEL OR SERIAL SOURCE SOURCE USED IS SELECTED VIA A CONFIGURATION PAGE ALTITUDE DATA SUPPLIED TO THE GTX 330 CAN ALSO BE OUTPUT TO ANOTHER UNIT RS 232 5 THE GAE 45 CAN ALSO PROVIDE ALTITUDE DATA IN THE FORM OF PARALLEL GRAY CODE 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY 5 IF ARINC 429 15 CONECTED THE GTX 330 WILL IGNORE RS 232 INPUT FROM THE GPS RECEIVER AND RS 232 ALTITUDE INPUT APPENDIX C INTERCONNECT DRAWINGS GARMIN GIX 550 P3301 SQUAT SWITCH IN 17 m SEE NOTE 2 EXTERNAL SUPPRESSION 1 0 31 gt SEE NOTE 3 EXTERNAL STANDBY SELECT 13 m SEE NOTE 4 EXTERNAL IDENT SELECT 12 m SEE NOTE 5 SEE NOTE 6 GARMIN 400 500 Series P4001 Uni P5001 TIS CONNECT SELECT 46 lt ALTITUDE ALERT ANNUNCIATOR SONALERT ALTITUDE ALERT ANNUNCIATE 19 gt AUDIO MUTE SELECT 47 AUDIO OUT HI 15 m FROM TAWS OR WIND SHEAR RADAR SYSTEM SEE NOTE 7 ANNUNCIATE E E GARMIN GMA 3540 Audio Panel SEE NOTE 8 tg 31 ALT WRN IN V y AUDIO OUT LO 16 GTX 330 Installation Manu
68. o the local FSDO with a copy of the revised FAA Form 337 and revised ICA The FAA inspector accepts the change by signing Block 3 and including the following statement The attached revised new Instructions for Continued Airworthiness date for the above aircraft or component major alteration have been accepted by the FAA superseding the Instructions for Continued Airworthiness date Page A 4 GTX 330 Installation Manual Revision F 190 00207 02 17 Assistance Flight Standards Inspectors have the resources to respond to questions regarding the ICA 18 Implementation and Record Keeping For major alterations performed in accordance with FAA field approval policy the owner operator operating under Part 91 15 responsible for ensuring that the ICA 15 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 Block 8 of FAA Form 337 dated along with a statement that the ICA is now part of the aircraft s inspection maintenance requirements A 3 Environmental Qualification Forms GTX 330 Mode S Transponder The following pages are copies of the Environmental Qualification Forms for the Garmin GTX 330 Transponder 005 00131 03 provided for reference only GTX 330 Airborne ATCRBS Mode S Transponder
69. ode S Transponder and GTX 330D Diversity Mode S Transponder Throughout this manual the term GTX 330 applies to both transponders unless otherwise stated After installation of the GTX 330 FAA Form 337 must be completed by an appropriately certificated agency to return the aircraft to service 1 2 Equipment Description The Garmin GTX 330 1s a panel mounted Non Diversity Mode S Transponder while the GTX 330D is a Diversity Mode S Transponder The GTX 330D employs two antennas one intended to be mounted on the top and the other on the bottom of the aircraft The design meets RTCA DO 181C and EUROCAE ED 73A specifications The GTX 330 transponder is a radio transmitter and receiver that operates on radar frequencies receiving ground radar or TCAS interrogations at 1030 MHz and transmitting a coded response of pulses to ground based radar on a frequency of 1090 MHz The GTX 330 is equipped with IDENT capability that activates the Special Position Identification SPI pulse for 18 seconds The GTX 330 replies to ATCRBS Mode A Mode C and Mode All Call interrogation Mode A replies consist of any one of 4 096 codes which differ in the position and number of pulses transmitted Mode C replies include framing pulses and encoded altitude Mode S interrogations are selective The Mode 5 transponders can respond to a single directed interrogation from the ground station or another aircraft The GTX 330 15 a Level 2 transponder providing downlink of a
70. ontal separation must be no more than 7 6 meters 25 feet C Avoid mounting the antenna within three feet of the ADF sense antenna or any other communication antenna and six feet from the DME antenna D To prevent RF interference the antenna must be physically mounted a minimum distance of three feet from the GTX 330 NOTE If the antenna 15 being installed on a composite aircraft ground planes must be considered 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 1B and AC 43 13 2A 2 4 Installation Approval Considerations for Pressurized Aircraft Antenna and cable installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such installations incorporate alteration penetration of the cabin pressure vessel by connector holes and or mounting arrangements For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations it is recommended that the installer proceed according to any of the following listed alternatives 1 Obtain approved antenna installation design data from the aircraft manufacturer 2 Obtain an FAA approved Supplem
71. ord FAIL appears on the screen after 30 seconds SQUAT This field displays the state of the SQUAT SWITCH input The box 15 filled when the SQUAT SWITCH input is active the aircraft 15 on the ground as configured on the SETUP 2 page 5 2 16 Analog Input Page The Analog to Digital Converter counts are shown on the display providing troubleshooting data ANALOG INPUT Page 14 5 LTG This field displays the input level of the 14 5 V lighting bus PHOTO This field displays the input level of the photocell LCD TEMP This field displays the input level of the LCD temperature sensor 28V LTG This field displays the input level of the 28 V lighting bus GTX 330 Installation Manual Page 5 17 190 00207 02 Revision F This field displays the input level from the outside air temperature sensor UNIT TEMP This field displays the input level from the unit temperature sensor RS 232 INPUT Page Depending on the selected inputs on Channel 1 and Channel 2 from the RS 232 Input page ref para 5 2 9 this page displays the information received on the channel If GPS 15 selected as an input ground speed can be viewed GSPD latitude LAT longitude LON and track TRK If ICARUS or SHADIN ALT is selected as an input pressure altitude PALT can be viewed If FADC or ADC is selected as an input true or static air temperature SAT outside or total air temperature TAT indicated air speed IAS true air speed TAS
72. ost Installation Checkout After the installation is complete refer to Section 5 for system configuration Verify proper operation of the transponder by testing in accordance with Appendix F to 14 CFR Part 43 ATC Transponder Tests and Inspections Page 3 2 GTX 330 Installation Manual Revision F 190 00207 02 4 SYSTEM INTERCONNECTS 4 1 Pin Function List 4 1 1 J3301 21 20 19 18 17 16 15 14 13 12 11 40 9 8 7 6 5 4 3 2 1 42 41 e 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 45 44 43 Figure 4 1 Rear Connector J3301 Table 4 1 P3301 Pin Assignments 6 PALTITUDEC4 1 8 PALTITUDEC i 9 ALTITUDEB2 y n 18 RESERVED _ 20 RESERVED 0o 27 POWER GROUND 14 Denotes Active Low Ground to activate GTX 330 Installation Manual Page 4 1 190 00207 02 Revision F Table 4 1 P3301 Pin Assignments Cont d __ PinName vo 38 RESERVED 39 RESERVED _ 40 SPARE 43 POWER GROUND ____ 47 AUDIO MUTE SELECT 48 ARINC42209INJA n ALTITUDE COMMON GROUND 51 RESERVED 52 RESERVED 54 55 SPARE pa 57 SPARE a 58 RESERVED 59 SPARE a 60 AIRCRAFTPOWER2 o n 61 SPARE pa Denotes Active Low Ground to activate Page 4 2 GTX 330 Installation Man
73. s match those of other equipment in the aircraft panel under night lighting conditions KEY SRCE Key Lighting Source Auto Only SELECTION DESCRIPTION PHOTO Photocell DEFAULT Key lighting 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 SLOPE Auto Only Sets the sensitivity of the key lighting brightness to changes in the input level The higher the number the brighter the key lighting for a given increase in the input level This field has a range of 0 zero to 99 and 15 set to 50 at the factory OFFSET Auto Only Adjusts the key lighting level up or down for any given input level This field has a range of 0 zero to 99 and 15 set to 50 at the factory This may also be used to match lighting curves with other equipment in the panel Page 5 10 GTX 330 Installation Manual Revision F 190 00207 02 5 2 7 Contrast Configuration CONTRAST MODE CONTRAST CONFIGURATION Page SELECTION DESCRIPTION AUTO Automatic DEFAULT Display contrast is automatically compensated for LCD temperature and other factors An offset can be entered in the contrast level adjustment described below MAN Manual Display contrast is manually adjusted either here or by the pilot using the GTX 330 CONTRAST
74. splay always has black characters on a light background regardless of ambient lighting LEVEL Sets the ambient light level for AUTO mode to change between negative and positive display The higher the number the brighter the ambient light level to change over This field has a range of 0 zero to 99 with the default set to 75 5 2 5 Display Backlight Page DISPLAY BACKLIGHT Page BKLT Backlight SELECTION DESCRIPTION AUTO Automatic DEFAULT Display backlighting 15 automatically controlled based on the parameters entered on this configuration page When AUTO 15 selected the DISPLAY page does not appear to the pilot MAN Manual Display backlighting is controlled manually by the pilot on the GTX 330 DISPLAY page No backlight parameters can be entered when the manual mode is selected LVL Level Shows the current level of display backlighting based on the lighting input source lighting bus voltage or the ambient light if the source is PHOTO and the settings on this configuration page This field has a range of 0 zero to 999 The level 15 set by pressing the 8 and 9 keys when MAN mode is selected When in AUTO mode the field 1s for display only RSP TIME Response Time Sets the speed with which the brightness responds to ambient light changes only for AUTO backlight mode The higher the number the slower the display responds This field has a range of 0 to 7 with the default set to 4 Page 5 8 GTX
75. ta ADLP Airborne Data Link Processor ADLP is available only on channel 4 GTX 330 Installation Manual Page 5 11 190 00207 02 Revision F ARINC 429 OUTPUT The GTX 330 can be configured to include GPS Airdata AHRS EFIS Airdata and ADLP ARINC 429 inputs ARINC 429 OUTPUT Page functioning as an ARINC 429 data concentrator Refer to Section 4 6 SERIAL DATA ELECTRICAL CHARACTERISTICS for details The ARINC 429 OUTPUT Pages configure the ARINC 429 output ports Each port can be configured independently for the desired function s Both ARINC 429 outputs send high speed ARINC 429 data SELECTION DESCRIPTION CHANNEL 1 DATA DATA SOURCE OFF ADLP GARMIN or GARMIN W TIS DEFAULTS to OFF ARINC 429 input channel 4 sets the ARINC 429 output channel 1 to the same selection CHANNEL 2 DATA DATA SOURCE OFF GARMIN or GARMIN W TIS DEFAULTS to GARMIN W TIS See Figure C 5 Note 2 for description of Garmin format Do not select GARMIN W TIS if the aircraft contains another traffic detection system In aircraft having multiple traffic systems and multiple 400 500 Series units configure ARINC 429 output CHANNEL 1 for GARMIN W TIS and ARINC 429 output CHANNEL 2 for GARMIN TIS is then enabled over CHANNEL 1 The Garmin format is a data concentration function The following data is sent out at specified intervals using high speed ARINC 429 100 kHz The transmit data labels and their rates are as follows LABEL 200
76. the GTX 330 must receive altitude from suitable altitude reporting devices through serial input connections Altitude input to the GTX 330 received from parallel wire gray code encoders is supplied to the unit in 100 foot increments and thus reported in 100 foot increments 4 4 1 Altimeter Inputs Table 4 5 Encoded Altitude Pin Assignments PinName PinNumber VO ATmTUDED4 1 ALTITUDEA 2 hmn _ ATTUEA2 4 n ALTITUDEA4 5 hmh _ ATTUDEBI _ 7 ATTUDEBA 9 h ALTITUDECI 8 h ALTITUDECA 6 h __ ALTITUDE COMMON 50 RS 232 IN 2 4 4 2 Altimeter Calibration and Checkout Refer to Section 5 2 14 for the gray code altitude checkout Page 4 4 GTX 330 Installation Manual Revision F 190 00207 02 4 4 3 Altimeter Interconnect Dual GTX 330 Installation Refer to Figure C 2 for dual GTX 330 gray code altimeter interconnections A dual GTX 330 installation can accept either parallel wire gray code altimeter input or RS 232 serial data input as shown in Figure 4 2 If transponder number 2 15 a Garmin GTX 327 connect the RS 232 output from the altitude encoder to 73271 pin 19 refer to GTX 327 Transponder Installation Manual P N 190 00187 02 RS 232 IN 2 24 GARMIN We 45 C3 1 RS 232 OUT HI pe Lt 5 RS 232 OUT LO GARMIN GTX 330 RS 232 IN 2 24 Figure 4 2 Dual GTX 330 Single
77. ual Revision F 190 00207 02 4 2 Power and Lighting Function Power Input requirements and Lighting Bus input are listed the following tables The power input pins accept 11 33 Vdc AIRCRAFT POWER 2 15 for connecting to an alternate power source such as on aircraft with two electrical buses Switched Power Out is a power source available for devices such as a remote digital altitude encoder Refer to Figure C 1 for power and lighting interconnections 4 2 1 Aircraft Power Table 4 2 Aircraft Power Pin Assignments PinName PinNumber 10 AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 _ ARCRFTPOWER2 In POWERGROUND 70 J gt POWERGROUND 12 4 4 2 2 Lighting Bus The GTX 330 unit can be configured to track a 28 Vdc 14 Vdc 5 Vdc or 5 Vac lighting bus using these inputs The GTX 330 can also automatically adjust for ambient lighting conditions based on the photocell Refer to Sections 5 2 5 and 5 2 6 for lighting configuration Table 4 3 Aircraft Lighting Pin Assignments PinName Pin Number _ 14 V 5 V LIGHTING BUS HI 28 V LIGHTING BUS HI 4 3 Temperature Inputs Table 4 4 Temperature Probe Pin Assignments _________ PinNumber VO CURRENT TEMPERATURE PROBE OUT CURRENT TEMPERATURE PROBE IN Temperature input is used for Outside Air Temperature OAT display and Density Altitude computations The type of temperature probe required is a current sensor type suc
78. viding 4 096 active identification codes Pushing one of these keys begins the code selection sequence The new code 15 not activated until the fourth digit is entered Pressing the CLR key moves the cursor back to the previous digit Pressing the CLR key when the cursor 15 on the first digit of the code or pressing the CRSR key during code entry removes the cursor and cancels data entry restoring the previous code You may press the CLR key up to five seconds after code entry 1s complete to return the cursor to the fourth digit The numbers 8 and 9 are not used for code entry only for entering a Count Down time contrast and display brightness and data selection in the Configuration Mode NOTE The selected identification code should be entered carefully either one assigned by air traffic control for IFR flight or an applicable VFR transponder code e Important Codes 1200 VER code for any altitude in the US Refer to ICAO standards elsewhere 2000 VFR code commonly used in Europe Refer to ICAO standards 7000 VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft 15 subject to unlawful interference 7600 Loss of communications 7700 Emergency Avoid selecting code 7500 and all codes in the 7600 7777 range These codes trigger special indicators in automated facilities An aircraft s transponder code is used for ATC tracking purposes therefore exercise care when making routine co
79. witches are e OFF SIBY e ON e ALT Powers off the GTX 330 Pressing the STBY ON or ALT key powers on the transponder displaying the last active identification code Selects the standby mode When in standby mode the transponder does not reply to any interrogations selects Mode A and Mode S In this mode the transponder replies to Mode A Mode C and Mode S interrogations as indicated by the Reply Symbol amp but the replies do not include altitude information selects Mode A Mode C and Mode S In ALT mode the transponder replies to identification altitude and Mode S interrogations as indicated by the Reply Symbol By Replies to altitude interrogations include the standard pressure altitude received from an external altitude source which 15 not adjusted for barometric pressure The ALT mode may be selected in aircraft not equipped with an optional altitude encoder however the reply signal does not include altitude information Any time the function switch 15 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 VER FUNC for 18 seconds identifying the transponder return from others on an air traffic controller s screen During the IDENT period

GTXTM 330, GTXTM 330D TRANSPONDER INSTALLATION MANUAL

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