GTX 330/330D

Mode S Transponder

Pilots Guide

Copyright 2002, 2007, 2008 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited. This manual is written for software version 6.00 or later, and is not suitable for earlier software versions. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions.
Software License Agreement
BY USING THE GTX 330, YOU AGREE TO BE BOUND BY THE TERMS AND CONDITIONS OF THE FOLLOWING SOFTWARE LICENSE AGREEMENT. PLEASE READ THIS AGREEMENT CAREFULLY. Garmin grants you a limited license to use the software embedded in this device (the Software) in binary executable form in the normal operation of the product. Title, ownership rights and intellectual property rights in and to the Software remain in Garmin. You acknowledge that the Software is the property of Garmin and is protected under the United States of America copyright laws and international copyright treaties. You further acknowledge that the structure, organization and code of the Software are valuable trade secrets of Garmin and that the Software in source code form remains a valuable trade secret of Garmin. You agree not to decompile, disassemble, modify, reverse assemble, reverse engineer or reduce to human readable form the Software or any part thereof or create any derivative works based on the Software. You agree not to export or re-export the Software to any country in violation of the export control laws of the United States of America.
CAUTION: The GTX 330 should be turned off before starting or shutting down aircraft engine(s).
NOTE: Reference to the GTX 330 Transponder throughout this Pilots Guide includes operation of the GTX 330D Diversity Transponder also. NOTE: Contact a Garmin authorized dealer for software updates.
Part Number 190-00207-00 Rev. F Printed in USA

September 2008

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 you. Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY. 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. Garmin International, Inc. Garmin (Europe) Ltd. 1200 East 151st Street Liberty House, Bulls Copse Road Olathe, Kansas 66062, U.S.A. Hounsdown Business Park Phone: 913/397.8200 Southampton, SO40 9RB, U.K. FAX: 913/397.8282 Phone: 44/0870.8501241 FAX: 44/0870.8501251
NOTE: It is the responsibility of the GTX 330 owner to obtain proper licensing before using the transponder. NOTE: The coverage expected from the GTX 330 is limited to line of sight. Low altitude or aircraft antenna shielding by the aircraft itself may result in reduced range. Range can be improved by climbing to a higher altitude. It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes.

The GTX 330 transponder is powered on by pressing the STBY, ALT or ON keys, or by a remote avionics master switch (if applicable). After power on, a start-up page is displayed while the unit performs a self test.

Mode Selection Keys

OFF Powers off the GTX 330. Pressing STBY, ON, or ALT key powers on the transponder displaying the last active identification code. STBY Selects the standby mode. When in standby mode, the transponder will not reply to any interrogations. ON Selects Mode A. In this mode, the transponder replies to interrogations, as indicated by the Reply Symbol ( ). Replies do not include altitude information. ALT Selects Mode A and Mode C. In ALT mode, the transponder replies to identification and altitude interrogations as indicated by the Reply Symbol ( ). Replies to altitude interrogations include the standard pressure altitude received from an external altitude source, which is not adjusted for barometric pressure. The ALT mode may be selected in aircraft not equipped with an optional altitude encoder; however, the reply signal will not include altitude information. Any time the function ON or ALT is selected 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.

Code Selection

Code selection is done with eight keys (0 7) providing 4,096 active identification codes. Pushing one of these keys begins the code selection sequence. Digits that are not yet entered appear as dashes. The new code is activated when the fourth digit is entered. Pressing the CLR key moves the cursor back to the previous digit. Pressing the CLR key when the cursor is 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 is 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, and for adjusting contrast and display brightness.
Keys for Other GTX 330 Functions
IDENT Pressing the IDENT key activates the Special Position Identification (SPI) Pulse for 18 seconds, identifying your transponder return from others on the air traffic controllers screen. The word IDENT will appear in the upper left corner of the display during this time. VFR Sets the transponder code to the pre-programmed VFR code selected during installation configuration (this is set to 1200 at the factory). Pressing the VFR key again restores the previous identification code. If the VFR Key is pressed when disabled (dependent upon installation configuration) a VFR Key Disabled message appears to indicate that no operation took place. FUNC 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. Also displays Outside Air Temperature, Density Altitude, Contrast, Display, and ADS-B Operation (dependent upon installation configuration). START/STOP Starts and stops the Altitude Monitor, Count Up, Count Down, and Flight timers. CRSR Initiates starting time entry for the Count Down timer and cancels transponder code entry. CLR Resets the Count Up, Count Down, and Flight timers. Cancels the previous keypress during code selection and Count Down entry. Returns cursor to the fourth code digit within five seconds after entry. 8 Reduces Contrast and Display Brightness when the respective fields are displayed (dependent upon installation configuration) and enters the number eight into the Count Down timer. 9 Increases Contrast and Display Brightness when the respective fields are displayed (dependent upon installation configuration) and enters the number nine into the Count Down timer.

Function Display

NOTE: GTX 330 options are normally set at time of installation. For changes to the GTX330 parameters, contact your Garmin authorized dealer.
PRESSURE ALT: Displays the altitude data supplied to the GTX330 in feet, hundreds of feet (i.e., flight level), or meters (dependent upon installation configuration). FLIGHT TIME: Timer start is configured as either Manual or Automatic. When Manual, displays the Flight Time, controlled by the START/STOP and CLR keys. When Automatic, the timer begins when take off is sensed. ALTITUDE MONITOR: Controlled by START/STOP key. Activates a voice alarm and warning annunciator when altitude limit is exceeded. OAT/DALT: Displayed when the GTX330 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 is entered with the keys. CONTRAST: This page is only displayed if manual contrast mode is selected during installation configuration. Contrast is controlled by the 8 and 9 keys. DISPLAY: This page is only displayed if manual backlighting mode is selected during installation configuration. Backlighting is controlled by the 8 and 9 keys. ADS-B: This page is displayed if the ADS-B pilot set option is selected during installation configuration of an ES enabled GTX 330. ADS-B defaults to ON at each power cycle. ADS-B ON/OFF is controlled by the START/ STOP key. Turn ADS-B OFF only at the request of ATC.

Altitude Trend Indicator

When the PRESSURE ALT page is displayed, an arrow may be displayed to the right of the altitude, indicating that the altitude is increasing or decreasing. One of two sizes of arrows may be displayed depending on the vertical speed rate. The sensitivity of these arrows is initially set during transponder installation.
Timer Operation To operate the Flight Timer:
1) Press the FUNC key until FLIGHT TIME is displayed. 2) If the GTX330 is configured with Automated Airborne Determination, the timer begins automatically when the unit senses that the aircraft has become airborne. The timer may be reset to zero at every take off, continue accumulating time at take off, or may be controlled manually. 3) If desired, press START/STOP to pause or restart the timer. 4) Press CLR to reset the timer to zero. 5) If the timer is configured to start automatically it will stop when the Automated Airborne Determination senses that the aircraft is on the ground.

To operate the Count Up timer:
1) Press the FUNC key until COUNT UP is displayed. 2) If necessary, press CLR to reset the Count Up timer to zero. 3) Press START/STOP to begin count up. 4) Press START/STOP again to pause the timer. 5) Press CLR to reset the timer to zero.
To operate the Count Down timer:
1) Press the FUNC key until COUNT DOWN is displayed. 2) Press CRSR and use the 0 - 9 keys to set the initial time. All digits must be entered (use the 0 key to enter leading zeros). 3) Press START/STOP to begin count down. 4) Press START/STOP again to pause the timer. 5) When the Count Down timer expires, the COUNT DOWN banner is replaced with a flashing EXPIRED, the message Timer Expired is heard, and the time begins counting up. 6) Press CLR to reset the timer to the initial time value.
Automatic ALT/GND Mode Switching
If the GTX330 is configured for Automated Airborne Determination, normal operation begins when take off is sensed. When the aircraft is on the ground the screen automatically displays GND. The transponder does not respond to ATCRBS interrogations when GND is annunciated. When a delay time is set (dependent upon installation configuration), the GTX330 waits a specified length of time after landing before changing to GND mode.

Failure Annunciation

If the unit detects an internal failure, the screen displays FAIL. When FAIL is annunciated no transponder data is transmitted.

Mode S Data Transmission

In addition to 4096 code and pressure altitude, the GTX330 is capable of transmitting aircraft identification, transponder capability, and maximum speed range. Aircraft identification is commonly referred to as FLT ID (Flight Identification). The GTX330 may be configured by the installer to allow the flight crew to enter FLT ID for each flight. An example is when air-carrier service requires changing the FLT ID. The FLT ID may consist of the aircraft registration or a flight number as agreed upon with the local aviation authority. In either case, the FLT ID must be the same aircraft identification that appears in the flight plan to correlate the aircraft identification seen on ATC radar with the correct voice call sign for the aircraft. If no flight plan is filed with the aviation authority (as may be permitted by regulations), the FLT ID entered is the aircraft registration marking. When flight crew entry of the FLT ID is not required, the installer configures the system to report the aircraft identification according to local aviation requirements. In this configuration, alteration of the FLT ID by the flight crew is not possible.

Altitude Monitor Operation To operate the Altitude Monitor:
1) Climb to assigned altitude. 2) Press the FUNC key until ALT MONITOR is displayed. 3) Press START/STOP key to start monitoring altitude. 4) Press START/STOP key again to cancel Altitude Monitor.
Altitude deviation is shown in hundreds of feet ABOVE or BELOW the selected altitude. When the aircrafts altitude exceeds the deviation limit, ABOVE or BELOW flashes and an audio tone or the message Leaving Altitude is heard. ABOVE or BELOW flashes until the aircraft returns to within 100 of the selected altitude. To select a new monitored altitude, press the START/STOP key to deactivate, then press again to activate the new monitored altitude. If another function is selected for viewing, such as a Timer or Pressure Altitude, the Altitude Monitor is automatically displayed with a flashing alert when the altitude excursion exceeds the configured deviation value. The Altitude Monitor stops when the current deviation exceeds 1000 feet plus the configured deviation value. The maximum configured deviation values that can be set by a Garmin authorized service center are as follows: Flight Level or Feet Maximum Limits 300 feet BELOW, 0 feet to 1999 feet ABOVE Meters Maximum Limits 300 meters BELOW, 0 meters to 609 meters ABOVE
Entering a Flight ID Number
When configured for FLT ID PWR-UP ENTRY at installation, the flight crew must enter the Flight ID before the GTX330 will operate. After the flight crew enters the correct Flight ID, the aircraft identification that is transmitted in response to ATC radar interrogations is properly correlated with the associated call sign for voice communication with the aircraft. If the FLT ID PWR-UP ENTRY is required but does not appear at power up, contact a Garmin authorized service center for GTX330 configuration. No space is needed when entering Flight ID characters. When a Flight ID contains a space, the GTX330 automatically removes the spaces upon completion of Flight ID entry. At system power-up the FLT ID may appear with no number (as shown) or with the last FLT ID entered. The cursor covers the entire FLT ID field. If the Flight ID appearing at turn-on is correct, press the CRSR key to move the cursor to the OK? field. Press CRSR again to accept the FLT ID. The transponder then begins normal operation. When no FLT ID appears or the FLT ID must be changed, press the number keys corresponding to the alphanumeric character entry. For example, to enter the letter R press the 5 key four times. Each time an alphanumeric character is entered, press the CRSR key to move the cursor to the next blank field. Pressing the CLR key moves the cursor back to the previous character. After the complete FLT ID is entered, press the CRSR key to move the cursor to the OK? field. Press CRSR again to accept the FLT ID. When FLT ID entry is complete the transponder begins normal operation. If an error is made while entering a FLT ID, press the CLR key to back up to any point, including highlighting the OK? field. If an incorrect FLT ID is discovered after the unit begins operation, turn the GTX330 off. Then turn it back on and reenter the correct FLT ID.

GTX330 Mode S Transponder Features
GTX330D Diversity Mode S Transponder
The GTX 330D Diversity Mode S Transponder incorporates antennas mounted on the top and bottom of the aircraft for dependable operation while maneuvering. Top and bottom antennas are less prone to antenna shadowing by the aircraft structure while turning. A top mounted antenna is in a better viewing position for interrogation and reply to overhead aircraft.
Traffic Information Service
The GTX 330 Mode S transponder provides a data link for Traffic Information Service (TIS). TIS is derived through a Mode S transponder data link and viewed on a multifunction display. ATC radar sends a traffic picture within a radius of 55 miles from select sites. The TIS protected area is a cylinder of 7-mile radius, extending 3500 above and 3000 below the aircraft. Refer to the AIM Chapter 1 for more details. TIS provides a graphic display of traffic information in the cockpit for non-TCAS equipped aircraft. Transponder-equipped aircraft can be displayed within the coverage volume within range of your position on indicators such as a Garmin GNS430 or GNS530, GNS480, and GMX200. Aircraft without an operating transponder are invisible to TIS. Refer to 400/500 series, GNS480, or GMX200 pilot literature for details.

GTX 330 ES Options

Automatic Dependent Surveillance-Broadcast (ADS-B) technology improves situational awareness and flight safety. With ADS-B capabilities, position, velocity, and heading information are automatically transmitted to other aircraft and ground stations. The current air traffic control system depends on a transponder request for pertinent aircraft information and does not include 3D position. ADS-B provides automatic transmission of aircraft information without a request.

Audio Alerts

(Setting options; male/female voice or tone, and volume level.) Leaving Altitude - Altitude Monitor deviation is exceeded. Traffic - TIS traffic alert is received. Traffic Not Available - TIS service is not available or out of range. Timer Expired - Count down time has expired.
2002, 2007, 2008 Garmin Ltd. or its subsidiaries Garmin International, Inc. 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Garmin (Europe) Ltd. Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K. Garmin Corporation No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan www.garmin.com Part Number 190-00207-00 Rev. F

GTX 330, GTX 330D TRANSPONDER MAINTENANCE MANUAL
Garmin International, Inc. 1200 E. 151st Street Olathe, KS 66062 USA
190-00207-05 Revision B September 2003
Copyright 2003 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.
Garmin International, Inc. st 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, SO51 9DL, U.K. Telephone: 44/1794.519944

RECORD OF REVISIONS

Revision A B Revision Date 6/13/03 09/09/03 Description Initial Release Added text to reflect new service parts ECO # ---22374

LIST OF EFFECTIVE PAGES

Page Rev. A.. B i.. B ii. B iii.. B iv.. B v. B vi.. B 1-1. B 1-2. B Page Rev. 1-3.B 1-4.B 1-5.B 1-6.B 1-7.B 1-8.B 1-9.B 1-10.B 1-11.B Page Rev. 1-12.B 1-13.B 1-14.B 1-15.B 1-16.B 1-17.B 1-18.B 2-1.B 2-2.B Page Rev. 2-3.B 2-4.B 3-1.B 3-2.B 4-1.B 4-2.B 4-3.B 4-4.B 5-1.B Page Rev. 5-2.B 5-3.B 5-4.B 5-5.B 5-6.B 5-7.B 5-8.B 6-1.B 6-2.B Page Rev. 6-3.B 6-4.B 6-5.B 6-6.B 7-1.B 7-2.B 7-3.B 7-4.B 7-5.B Page Rev. Page Rev. 7-6. B 7-15. B 7-7. B 7-16. B 7-8. B 7-9. B 7-10. B 7-11. B 7-12. B 7-13. B 7-14. B

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GTX 330 Maintenance Manual 190-00207-05
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.

WARNING

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.
Throughout this document references made to GTX 330 shall equally apply to the GTX 330D except where specifically noted.
Repair centers operated by Garmin Ltd. or its subsidiaries are authorized to perform component-level repairs to Garmin products. Repair centers operated by Garmin Ltd. or its subsidiaries are authorized to use Garmin proprietary documentation as references during any component-level repairs performed.

Page i Rev B

TABLE OF CONTENTS
PARAGRAPH 1. 1.1 1.2 1.3 1.4 PAGE
DESCRIPTION AND OPERATION... 1-1 INTRODUCTION..... 1-1 EQUIPMENT DESCRIPTION.... 1-1 INTERFACE SUMMARY.... 1-2 TRANSPONDER OPERATION.... 1-3 1.4.1 ATCRBS System Operation... 1-4 1.4.2 Interrogator.... 1-5 1.4.3 Transponder Mode A and Mode C Operation... 1-5 1.4.4 ATCRBS Transmission Overview.... 1-6 1.4.5 ATCRBS Signals.... 1-8 1.5 MODE S OVERVIEW..... 1-9 1.5.1 Transponder Mode S Operation... 1-10 1.5.2 DPSK Pulse Characteristics.... 1-10 1.5.3 PAM Characteristics... 1-11 1.5.4 All Calls.... 1-12 1.5.5 Radar Screen, TCAS Display.... 1-12 1.6 TIS SYSTEM CAPABILITIES.... 1-13 1.7 MUTUAL SUPPRESSION PULSES... 1-13 1.8 TECHNICAL SPECIFICATIONS.... 1-14 1.9 SCOPE OF MAINTENANCE.... 1-14 1.10 EQUIPMENT DESCRIPTION... 1-14 1.10.1 Main Board Assembly.... 1-16 1.10.2 Front Panel..... 1-16 1.10.3 Transmitter..... 1-16 1.10.4 Receiver.... 1-16 1.10.5 Antenna Switch Board (GTX 330D ONLY)... 1-17 1.10.6 Flex Circuit Cables.... 1-17
2. SPECIAL TEST EQUIPMENT.... 2-1 2.1 INTRODUCTION..... 2-1 2.2 SPECIAL TOOLS AND TEST EQUIPMENT... 2-1 2.2.1 Antenna Test Cable Connector.... 2-1 2.2.2 Transponder Bench Test.... 2-2 2.2.3 Test Harness..... 2-2 2.2.4 J3301 and Pin Assignment List.... 2-3

LIST OF TABLES

TABLE 1-1 1-2 1-3 2-1 3-1 5-1 5-2 6-1 6-2 6-3 6-4 6-5 6-6 6-7 6-8 PAGE ATCRBS Pulse Position.... 1-9 PAM Pulse Shape.... 1-12 PAM Pulse Patterns.... 1-12 P3301 Pin Assignments.... 2-3 Testing Failures.... 3-1 Test Equipment.... 5-2 Audio Voltage/Frequency Test.... 5-7 Sub-Assy., GTX 330 Black (Dwg. No. 015-00455-xx)... 6-1 Sub-Assy., GTX 330 Gray (Dwg. No. 015-00455-xx)... 6-2 Sub-Assy., GTX 330D Black (Dwg. No. 015-00455-xx)... 6-3 Sub-Assy., GTX 330D Gray (Dwg. No. 015-00455-xx)... 6-4 Sub-Assy., Front Panel Black (Dwg. No. 015-00456-xx)... 6-5 Sub-Assy., Front Panel Gray (Dwg. No. 015-00456-xx)... 6-6 Sub-Assy., Display Module (Dwg. No. 015-00492-00)... 6-6 Sub-Assy., Bottom Cover (Dwg. No. 115-00293-00)... 6-6

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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.

MOD LEVEL

SERVICE BULLETIN NUMBER

SERVICE BULLETIN DATE

PURPOSE OF MODIFICATION
At the time of this revision, the current software version for the GTX 330 is 3.03. The software version and information in this document are subject to change without notice. Visit the Garmin web site (www.garmin.com) for current manual updates and supplemental information concerning the operation of this and other Garmin products.

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SECTION 1 DESCRIPTION AND OPERATION

1.1 INTRODUCTION

This manual provides functional testing and assembly level maintenance information for the panel-mounted GTX 330 Mode S Transponder and the GTX 330D Diversity Mode S Transponder. Throughout this manual, the term GTX 330 applies to both transponders unless otherwise stated. Information pertaining to the installation and operating instructions can be found in the GTX 330 Installation Manual, 190-00207-02. This manual is designed to aid the bench technician in isolating failures to the assembly level only. If necessary, the GTX 330 can be returned to Garmin for all service work, including maintenance and repair. Contact Garmin at the following address or telephone numbers for more details: Garmin International, Inc. 1200 E. 151st Street Olathe, KS 66062 USA Telephone: 913-397-8200 Aviation Panel-Mount Technical Support Line (Toll Free): 1-888-606-5482

INTERFACE SUMMARY

The GTX 330 provides the following interface connections via the rear connector: Ten (10) encoding altimeter inputs. External IDENT input. External STBY input (useful for dual transponder installations). External suppression pulse input. Switched power output of up to 1.5 amps (for digital altitude encoder power). Aircraft power input (11 to 33 volts). Aircraft dimming bus input voltage. Aircraft master switch turn-on option. Serial altitude or GPS groundspeed input. Serial altitude input. (Reduces wire count vs. parallel wire gray code altimeter interface.) Mode S. P/N 010-00230-( ) and 010-00293-( ) support Comm-A and Comm-B protocol. Temperature, Altitude Hold and Density Altitude. Digitally recorded voice and discrete warning annunciator activated by Altitude Hold when limits are exceeded. Diversity: GTX 330 is available with or without the diversity feature.

1-2 Rev B

The GTX 330 P/N 010-00230-( ) and 010-00293-( ) support the following list of Binary Data Selector (BDS) registers: BDS (0,0) Air Initiated Comm-B (AICB) BDS (1,0) Data Link Capability Report BDS (1,7) Common Usage Ground Initiated Comm-B (GICB) Capability Report BDS (1,8) Mode S Specific Services GICB Capability Report BDS (1,9) Mode S Specific Services GICB Capability Report BDS (1,D) Mode S Specific Services Protocols (MSP) Capability Report BDS (2,0) Aircraft Identification
Note that BDS (3,0) is only required for transponders compatible with ACAS/TCAS II. The GTX 330 does not support BDS (3,0).

TRANSPONDER OPERATION

The Garmin GTX 330 Transponder System provides an air to ground link in the Air Traffic Control Radar Beacon System (ATCRBS) to report in-flight aircraft identification. It also provides air to air link participation in the airborne Traffic Alert and Collision Avoidance System (TCAS) for aircraft equipped with traffic avoidance equipment. A pulsed interrogation from the ground-based secondary radar or airborne TCAS generates a pulsed reply from the GTX 330. These pulses are processed and displayed on an ATC radar screen on the ground or traffic display in other aircraft. Normal radar returns from the primary radar system vary in intensity depending on aircraft size, distance away and perhaps other factors. The transponder system equalizes returns by providing similar digital data for all aircraft. Selected codes enable the transponder to reply with identification information useful to ATC. Special codes may be selected to indicate conditions such as emergency, VFR traffic or selected operations. In addition to Mode A operation for identification, Mode C is employed for altitude information when an altitude encoder is connected to the transponder and altitude replies are selected.

Figure 1-3. ATCRBS Interrogation without Side Lobe Suppression (SLS)

1-6 Rev B

To correct this phenomenon, a non-directional pulse, P2, is transmitted immediately following the leading pulse. When the aircraft is in the main beam, the amplitude of the second pulse is much less than that of the first pulse, thus the transponder replies. When the aircraft detects a side lobe interrogation, the second pulse is equal to or greater than the first pulse, therefore the transponder does not reply. The Side Lobe Suppression period is a 35 s (microsecond) timeout to which the transponder does not accept any ATCRBS interrogation. Figure 1-4, ATCRBS Interrogation with Side Lobe Suppression illustrates the relative amplitudes of the transmitted main lobe P1, P2 and side lobe signals. Aircraft 1 replies because it is in the main beam. With the extra Side Lobe Suppression pulse P2, Aircraft 2 and 3 would not reply because they are in the side lobes.
Figure 1-4. ATCRBS Interrogation with Side Lobe Suppression

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1.4.5 ATCRBS Signals
The 1030 MHz ATCRBS interrogations transmitted from the ground have Mode A interrogation modulated with two 0.8 s pulses separated by 8 s. The Mode C interrogation is modulated with two 0.8 s pulses separated by 21 s as shown in Figure 1-5. ATCRBS modulation is known as Pulse Amplitude Modulation (PAM). Side Lobe Suppression (SLS) is the combination of the normal ATCRBS Interrogation and the nondirectional pulse, P2. P2 is transmitted 2 s after P1. Therefore when the aircraft is in the main beam, the amplitude of P2 is less than P1. When the aircraft receives a side lobe, P2 is equal to or greater than P1. The transponder does not transmit when P2 is greater than P1.
Figure 1-5. ATCRBS Interrogation Pulses

1-8 Rev B

Each ATCRBS reply, transmitted from the transponder at 1090 MHz, uses two framing pulses, F1 and F2, nominally spaced 20.3 0.1 s apart. See Figure 1-6 ATCRBS Reply Pulses. The Special Position Identification (SPI) Pulse is placed at a spacing 4.35 s following the last framing pulse (F2) of Mode A replies only.
Figure 1-6. ATCRBS Reply Pulses
The designators of the information pulses and their positions from the first framing pulse (F1) are listed in Table 1-1, ATCRBS Pulse Position. Table 1-1. ATCRBS Pulse Position PULSE
C1 A1 C2 A2 C4 A4 X (Not Used) B1 D1 B2 D2 B4 D4

POSITION

F1+1.45 s F1+2.90 s F1+4.35 s F1+5.80 s F1+7.25 s F1+8.70 s F1+10.15 s F1+11.60 s F1+13.05 s F1+14.50 s F1+15.95 s F1+17.40 s F1 + 18.85 s

MODE S OVERVIEW

The ATCRBS system has certain limitations. The more airplanes there are in the sky, the more replies the ground station receives, causing a cluster of replies to overlap. The overlapping signals interfere with each other, thus the reception can be garbled and unusable. Mode S was developed to selectively address each transponder so that only one transponder replies at a time. Mode S operates on the same frequencies as the ATCRBS transponder, therefore the Mode S system must operate without affecting the current ACTRBS transponders. In addition the Mode S transponders must operate in the ATCRBS system. Two new interrogation types were created: Differential Phase Shift Keying (DPSK) and Pulse Amplitude Modulation (PAM) with P4 pulses.

The first phase reversal within P6 is the sync phase reversal. The midpoint of each following data phase reversal occurs only at a time 0.25 times (N + 1) 0.02 s after the sync phase reversal, where N is a positive integer greater than one (>1) and represents the bit number in the message for each bit that is equal to one.

1.5.2.4

Pulse Interval
P1 - P2 2.00 0.05 s P2 to sync phase reversal of P6 2.75 0.05 s P6 to sync phase reversal of P6 1.25 0.05 s P5 to sync phase reversal of P6 0.4 0.05 s P5 may be overlaid on P6 by the interrogator as a Side Lobe Suppression (SLS) signal in any Mode S interrogation. It is overlaid on all Mode S-Only All-Call interrogations.

1.5.2.5

Information Content
DPSK signals contain information in data chips within P6. The chips are located after the possible data phase reversals assigned as indicated in Figure 1-7. P6 pulses contain 56 chips (short) or 112 chips (long). A phase reversal preceding a chip characterizes that data bit as a binary ONE. No preceding phase reversal characterizes that data bit as a binary ZERO. The last 24 bits of P6 are overlaid with parity. The last 24 bits are also the address for each aircraft, except the Uplink Format 11 (UF11), which is an All-Call.

1.5.2.6

MODE S SUPPRESSION
The transponder enters suppression if the P1 and P2 preamble pulses of a Mode S interrogation are detected, but a sync phase reversal is not recognized. This requirement prevents the transponder from generating unwanted Mode A and/or Mode C replies to Mode S interrogations that are side lobe suppressed. Side Lobe Suppression for Mode S formats is characterized by the reception of P5, overlaying the location of the sync reversal of P6.
1.5.3 PAM Characteristics
Figure 1-8 shows the PAM with P4 pulse structure. Tables 1-3 and 1-4 summarize the PAM characteristics for ATCRBS and Mode S. The pulse shape for PAM interrogations are summarized in Table 1-3. The pulse patterns of the PAM interrogations are defined in Table 1-4. The Relative Pulse Amplitudes are as follows: P3 amplitude is PdB. P4 amplitude is PdB.

Page 1-11 Rev B

Figure 1-8. PAM with P4
Table 1-2. PAM Pulse Shape Pulse Designator
P1,P2,P3,P5 P4 (short) P4 (long)

Pulse Duration

0.8 s 0.8 s 1.6 s

Duration Tolerance

Figure 1-9. Typical Garmin 500 Series Display Showing TIS Traffic
Surveillance 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.
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 is a synchronous pulse that is 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 is designed to limit mutual interference.

Page 1-13 Rev B

TECHNICAL SPECIFICATIONS
Refer to the GTX 330 Installation Manual, 190-00207-02, for a complete list of specifications and Configurations Available.

SPECIFICATION

TSO, JTSO; GTX 330 TSO, JTSO; GTX 330D TSO ENV CAT Temperature Range Power Requirements Transmitter Frequency Transmitter Power Receiver Frequency Receiver Sensitivity Mode A Capability Mode C Altitude Capability Mode S Altitude Capability

CHARACTERISTIC

TSO-C112, Class 2A010, JTSO-2C112a. TSO-C112, Class 2A011, JTSO-2C112a. Refer to GTX 330 Installation and Operation Manual, 190-00207-02, Appendix A -45C to +70C (continuous operation) 11.0 to 33.0 Vdc; Power Input: 22 watts typical, 45 watts maximum 1090 MHz 125 watts minimum, 250 watts nominal. 1030 MHz -74 dBm nominal for 90% replies 4096 Identification Codes 100 Foot Increments from -1000 to 62,700 feet. 25 Foot Increments from -1000 to 50,175 feet with suitable serial data altitude. 100 Foot Increments from 1000 to 62,700 feet. Selective Identification Codes, Aircraft Type, Aircraft ID, Comm-A, Comm-B Low 0.5 V; High 8 V 4.04 Vrms to 7.85 Vrms into a 500 load
Mode S Capability External Suppression Input Audio Output

SCOPE OF MAINTENANCE

Garmin recommends limiting field maintenance to the following: Functional inspection to meet current FAR requirements Limited replacement of major subassemblies Replacement of Flexible Circuit Cables

EQUIPMENT DESCRIPTION

1.10.6

Flexible Circuit Cables
The major subassemblies are interconnected by ZIF (Zero Insertion Force) cables and ribbon cables. These cables are readily available from Garmin for replacement in case of damage.

Page 1-17 Rev B

This page intentionally left blank.

1-18 Rev B

SECTION 2 SPECIAL TEST EQUIPMENT

2.1 INTRODUCTION

This section identifies the special test equipment essential to maintain the GTX 330. Standard equipment is not listed. For any questions regarding warranty repair of the unit contact the Garmin Customer Service Department at the address or phone number listed in Section 1.
SPECIAL TOOLS AND TEST EQUIPMENT
Transponder Test Set or equivalent (See Section 5.5) Power Supply Oscilloscope Digital Voltmeter 50 Antenna Test Cable ConnectorLocally Fabricated Test HarnessLocally Fabricated (See Figures 7-6 and 7-7) Coaxial Adapter: Female BNC to male type N
2.2.1 Antenna Test Cable Connector
The antenna test cable requires a BNC connector at the test fixture antenna and a male BNC Blindmate connector (Garmin P/N 330-00198-00) or RF Adapter (P/N 330-00326-00) at the GTX 330 Transponder. Instructions for installing the Blindmate BNC are shown in steps 1 through 7 and illustrated in Figure 2-1. Follow BNC connector manufacturer instructions for assembly of the BNC connector. The RF attenuation of the cable at 1090 MHz must not exceed 1.50 dB.
Figure 2-1. Blindmate Antenna Connector

Page 2-1 Rev B

1. Trim coax outer insulation back 0.50. 2. Trim braid (not center conductor or insulation) back 0.25. 3. Strip Insulation back 0.12.
Place the ferrule over the coax braid, flush against the coax outer insulation before performing the next step if the outside diameter of the coax braid is smaller than the inside diameter of the center connector sidewall opening. 4. Insert cable (center conductor, dielectric and shield braid) through the sidewall of the connector and solder the center conductor to the center pin of the connector.
When using low loss cable it may be necessary to flatten the solid wire center conductor slightly so it can fit the slot on the RF connector center pin. When soldering, avoid applying excess heat to the connector body, and center conductor insulator. 5. Heat the outside of the connector sleeve and at the same time apply solder between the braid and the sleeve. Continue to apply heat until the solder flows evenly. 6. Install 50 Matching Bushing.

REASSEMBLY

4.4.1 Display Assembly (Figure 7-3)
1. Secure the two screws (4) securing the display module (3) to the front panel assembly (1).
4.4.2 Front Panel Assembly (Figure 7-1)
1. Carefully place the front panel assembly (2) on the unit. Attach to the unit using four black screws (22) in the top holes in the bezel. 2. Install the flexible circuit cable (19) as described in paragraph 4.4.3.

Page 4-3 Rev. B

4.4.3 Flexible Circuit Cables (Figure 7-1)
1. With the retaining lip of the ZIF connectors lifted, carefully insert the flexible circuit cable (19) into the main board (4) and front panel ZIF connectors. 2. While gently holding the flexible circuit cable in the connector, press down on the connector lip to secure the cables in place. 3. Apply RTV (291-00039-00) (See Page 7-3 Note 8) to both ends of the ZIF connector to prevent cable disengagement. 4. When installing the ribbon cables (20) carefully insert the connectors observing key orientation.

4-4 Rev B

SECTION 5 TESTING

5.1 INTRODUCTION

The test procedure in this section is provided to aid the technician in locating a faulty unit. The test procedure can be used to test a unit after it has been removed from an aircraft. All tests can be performed without accessing the inside of the unit.
The GTX 330 Transponder contains static sensitive components. proper anti-static procedures when testing the unit.

Observe

Hazardous voltages exist on the Main Board and Transmitter Board. Under normal operating conditions the voltages range up to 200 Vdc. Exercise extreme caution during unit testing. Death or serious injury could result from electrical shock.

GENERAL

This section includes testing procedures for units removed from an aircraft or from storage before use in an aircraft. Perform these tests with the dust covers on. After failure of a specific test the unit may be returned to the factory for repair. After completing all necessary maintenance or service, perform the tests in this section, Section 5, TESTING.
ADJUSTMENT/MEASUREMENT ACCURACY
Before making any adjustments to the unit, ensure that all test equipment is in calibration and traceable to NIST (National Institute of Standards and Technology). Some output parameters are factory adjusted to specific levels. Test levels may not be accurate if the unit has been readjusted in the field.

Page 5-1 Rev B

TEST EQUIPMENT PRECAUTION

Except for the DVM with standard lead length, the case of each instrument should be connected to ground. The bench power supply ground must be connected to earth ground and serve as a single point ground for the entire test setup.
Test harness misconnection could cause damage to the GTX 330 unit.

REQUIRED TEST EQUIPMENT

The following test equipment (or suitable substitute) listed in Table 5-1 is required for testing the GTX 330:
Table 5-1. Test Equipment
Test Equipment Description
Transponder Test Set, Mode S Test Set

Representative Type

Transponder field-test generator capable of performing Title 14 CFR Chapter 1, Part 43, Appendix F tests. Such as the TIC (Tel Instrument Electronics Corp) T-49CA for the GTX 330D or the TIC TR-220 for the GTX 330. Topward 2000 (+11 Vdc to +33 Vdc @ up to 3 amps if testing Switched Power Output) Fluke Model 79 Tek TDS-3034 or suitable equivalent Connector kit for SW Upgrade 9-Pin Connector to attach to computer port for SW Upgrade Fabricated Locally (See Section 2) Fabricated Locally (See Section 2)
Power Supply Digital Multimeter Oscilloscope: 100 MHz Bandwidth Minimum Garmin P/N 011-00583-00 9-Pin D-Sub Connector, Female Test Harness Coax Cable Assembly

5.5.1 Test Harness

Figures 7-6 and 7-7 provide a schematic diagram for fabricating a suggested test harness. Instructions are also given in Figure 2-1 for assembling the blindmate connector on the Coax Cable Assembly. The Coax Cable Assembly is included as part of the test harness shown in Figure 7-6.
SOFTWARE UPGRADE PROCEDURE
Software Version 3.03 is for the GTX 330 TSO C112 Class 2A units, P/Ns 011-00455-00, 011-00455-20, and GTX 330D P/Ns 011-00455-10, 011-00455-30. Refer to the latest Software Service Bulletin (SSB) for instructions on changing unit software. The unit's current software version is displayed at power up. 5-2 Rev B GTX 330 Maintenance Manual 190-00207-05

BENCH TESTING

Unless otherwise specified, this test is performed manually with covers in place. Attach a coax cable calibrated for 1.5 dB maximum attenuation at 1090 MHz with appropriate RF connectors.

STANDARD TEST SIGNALS

5.8.1 Input Voltages
Unless otherwise specified, all tests will be performed with power input voltages and RF signal as follows: GTX 330 DC power input voltage per aircraft system of either +13.75 Vdc or +27.5 Vdc. Note that the GTX 330 will operate on any DC voltage between +11 and +33 Vdc. GTX 330 Panel Lighting input per aircraft voltage with unit configured accordingly.

5.11.2

Configuration Pages
Holding down the FUNC key and pressing the ON key provides access to the configuration pages. The FUNC key will sequence through the configuration pages. The CRSR key will highlight selectable fields on each page. When a field is highlighted, numeric data entry will be performed with the 0-9 keys, and list selections will be performed with the 8 or 9 keys. Press the CRSR key to accept changes. Pressing the FUNC key moves on 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 and then on again (without holding the FUNC key). Check each configuration page for proper data entry and display. Refer to the GTX 330 Installation Manual, 190-00207-02 for each configuration page detail.

5.12 TIMER FUNCTION TEST

Press the FUNC key and verify proper operation of the count up and count down timers.

5-6 Rev B

5.13 AUDIO TEST
AUDIO MODE (First) Page The audio test is performed by measuring voltage and audio frequency across a 500 , 1/2 watt resistor connected between the audio high and low outputs, pins 15 and 16.
Cycle through the configuration pages with the FUNC key, accessing the Audio Mode (first) page. Select Message 0 for a continuous tone. Using the 9-key, adjust audio to full volume. Measure the voltage across the resistor using the information given in Table 5-2.
Table 5-2. Audio Voltage/Frequency Test AUDIO VOLTAGE AND FREQUENCY RANGE SERIAL NUMBER RANGE 4.04 to 7.85 VRMS 490 Hz 5 Hz 84100288 and below 84200114 and below 84300109 and below 84400119 and below 6.70 to 7.85 VRMS, 490 Hz 5 Hz 84100289 and above 84200115 and above 84300110 and above 84400120 and above
EXTERNAL SWITCH STATE TEST
When EXTERNAL IDENT, EXTERNAL STANDBY and SQUAT SWITCH discrete inputs are grounded the corresponding box field is filled on the display.

EXTERNAL SWITCH Page

The EXTERNAL SWITCH STATE page is seen in both the configuration mode and test mode. Using the FUNC key, sequence through the configuration pages or test pages until the EXTERNAL SWITCH STATE page is in view.

Page 6-1 Rev B

250-00073-00 Thermal Pad,GTX330,Main 334-00039-03 Header,Bd to Bd,2x5 310-00019-09 Ca,Flat Flex,.5mm,96mm,30 cond 325-00063-03 Ribbon Ca Stp,2mm Ctrs,2x5 311-00007-06 Wire,Bus Bar,Tin/Lead 24 Awg 211-60334-06 Screw,4-40x.187,PHP-STD,SS/BO, 211-60234-08 Screw,4-40x.250,PHP,SS/P,w/NYL 211-63234-10 Scr,4-40x.375,FLHP100,SS/P,Nyl 214-00023-03 Stdoff,M/F,Hex,4-40,.27"w/Nyl 115-00394-00 SMP,Cover,PLL,RX,GTX330 115-00398-00 SMP,Cover,IF/VID Bot,RX,GTX330 334-00061-00 Pin,.040 Dia,Swage Mt 610-00027-00 Xstr,RF Pwr,Pulsed,75W,TAN75A 610-00028-00 Xstr,RF Pwr,Pulse,250W,TAN250A
Table 6-2. Sub-Assy., GTX 330 Gray (Dwg. No. 015-00455-xx, Figure 7-1 and 7-2) Reference Designator Part Number Item Description Quantity
145-00480-04 161-00422-00 291-00005-00 291-00039-10 Page 6-2 Rev B 330-00070-03 231-00020-01 125-00028-00 011-00456-01 115-00292-00 115-00293-00 115-00384-00 012-00464-00 012-00465-00 012-00466-01 012-00570-00 161-00412-01
PMP,Bezel Cover,GTX327 Lbl,Prot Bezel Cover Warning Sealant,Silicone,Gen Purpose RTV,Non-Flow,Non-Corrosive Conn,Coax,Blind Thd w/Groove Plug,BNC Hole,w/Nyl Lkg Patch DCP,Chassis,GTX 330 Sub-Assy,GTX330 Gray,Front Pnl SMP,Top Cover,GTX330 SMP,Bottom Cover Assy,GTX330 SMP,Shield,TX Pocket,GTX330 PCB Assy,GTX330 TX PCB Assy,GTX330 RX PCB Assy,GTX330 2A w/Xfrmr Mn PCB Assy,GTX330 Diplexer Bd Tag,S/N,GTX330 Gray w/JTSO
250-00067-00 250-00072-00 250-00073-00 334-00039-03 310-00019-09 325-00063-03 311-00007-06 211-60334-06 211-60234-08 211-63234-10 214-00023-03 115-00394-00 115-00398-00 334-00061-00 610-00027-00 610-00028-00
Thermal Pad,TX Bd,GTX327 Thermal Pad,Square,GTX330 Thermal Pad,GTX330,Main Header,Bd to Bd,2x5 Ca,Flat Flex,.5mm,96mm,30 cond Ribbon Ca Stp,2mm Ctrs,2x5 Wire,Bus Bar,Tin/Lead 24 Awg Screw,4-40x.187,PHP-STD,SS/BO, Screw,4-40x.250,PHP,SS/P,w/NYL Scr,4-40x.375,FLHP100,SS/P,Nyl Stdoff,M/F,Hex,4-40,.27"w/Nyl SMP,Cover,PLL,RX,GTX330 SMP,Cover,IF/VID Bot,RX,GTX330 Pin,.040 Dia,Swage Mt Xstr,RF Pwr,Pulsed,75W,TAN75A Xstr,RF Pwr,Pulse,250W,TAN250A
Table 6-3. Sub-Assy., GTX 330D Black (Dwg. No. 015-00455-xx, Figure 7-1 and 7-2) Reference Designator Part Number Item Description Quantity

PCB Assy,GTX330 TX PCB Assy,GTX330D RX PCB Assy,GTX330D 2A w/Xfrmr Mn PCB,GTX330 Ant Sw Bd Tag,S/N,GTX330D Gray w/JTSO Thermal Pad,TX Bd,GTX327 Thermal Pad,Square,GTX330 Thermal Pad,GTX330,Main Header,Bd to Bd,2x5 Ca,Flat Flex,.5mm,96mm,30 cond Ribbon Ca Stp,2mm Ctrs,2x5 Wire,Bus Bar,Tin/Lead 24 Awg Screw,4-40x.187,PHP-STD,SS/BO, Screw,4-40x.250,PHP,SS/P,w/NYL Scr,4-40x.375,FLHP100,SS/P,Nyl Stdoff,M/F,Hex,4-40,.27"w/Nyl SMP,Cover,PLL,RX,GTX330 SMP,Cover,IF/VID Top,RX,GTX330 SMP,Cover,IF/VID Bot,RX,GTX330 Pin,.040 Dia,Swage Mt Xstr,RF Pwr,Pulsed,75W,TAN75A Xstr,RF Pwr,Pulse,250W,TAN250A
Table 6-5. Sub-Assy., Front Panel Black (Dwg. No. 015-00456-xx, Figure 7-3) Reference Designator Part Number Item Description Quantity
145-00345-01 414-00066-00 340-00039-00 012-00356-00 125-00048-03 470-00034-00 011-00492-00 211-60232-08
PMP,Inlay,GTX330,Blk Keypad,Silicone,GTX330 Snapdome Array,GTX327 PCB Assy,GTX327 Keyboard DCP,Bezel,Painted,Blk,GTX327 Lens,GTX327 Sub-Assy,GTX327,Display Module Screw,2-56x.250,PHP,SS/P,w/NYL

Page 6-5 Rev B

Table 6-6. Sub-Assy., Front Panel Gray (Dwg. No. 015-00456-xx, Figure 7-3) Reference Designator Part Number Item Description Quantity
145-00345-03 414-00066-00 340-00039-00 012-00356-00 125-00048-04 470-00034-00 011-00492-00 211-60232-08
PMP,Inlay,GTX330,Gray Keypad,Silicone,GTX330 Snapdome Array,GTX327 PCB Assy,GTX327 Keyboard DCP,Bezel,Painted,Gray,GTX327 Lens,GTX327 Sub-Assy,GTX327,Display Module Screw,2-56x.250,PHP,SS/P,w/NYL
Table 6-7. Sub-Assy., Display Module (Dwg. No. 015-00492-00, Figure 7-4) Reference Designator Part Number Item Description Quantity
252-00060-00 115-00304-00 440-00028-01 470-00036-00 470-00037-00 475-00004-00 012-00357-00 249-00003-00
Spacer,Sponge,GTX327 SMP,Display Frame,GTX327 LCD,200x33,.375 Pitch,DSTN,COF Film,Bright Enhancing,GTX327 Film,Diffuser,GTX327 Backlight,LED,COB,GTX327 PCB Assy,GTX327 Dspl Bd Tape,Double Sided,GPS40
Table 6-8. Sub-Assy., Bottom Cover (Dwg. No. 115-00293-00, Figure 7-5) Reference Designator 3 Part Number Item Description Quantity
115-00293-01 011-00610-00 211-63234-08
SMP,Bottom Cover,GTX330 Sub-Assy,Lock Pawl,GNC500 Screw,4-40x.250,FLHP 100,SS/P

Page 6-6 Rev B

SECTION 7 ASSEMBLY DRAWINGS

7.1 INTRODUCTION

The following assembly drawings are provided for part identification and to aid in assembly/disassembly of the GTX 330 Transponder. Figure 7-1 Assembly Drawing GTX 330 (Dwg. No. 015-00455-XX Rev. E) (Sheet 1 of 2) Figure 7-2 Assembly Drawing GTX 330 (Dwg. No. 015-00455-XX Rev. E) (Sheet 2 of 2) Figure 7-3 Sub-Assembly Front Panel (Dwg. No. 015-00456-XX Rev. A) Figure 7-4 Sub-Assembly Display Module (Dwg. No. 015-00492-XX Rev. A) Figure 7-5 Sub-Assembly Bottom Cover (Dwg. No. 115-00293-00 Rev. A) Figure 7-6 GTX 330 Test Setup/Test Harness (Sheet 1 of 2) Figure 7-7 GTX 330 Test Setup/Test Harness (Sheet 2 of 2)

Page 7-1 Rev. B

7-2 Rev B
APPLY 291-00039-00 (RTV) HERE. SEE NOTE 8

DETAIL A SCALE 4 : 1

NOTES: 1. SOME PARTS NOT USED ON SOME ASSEMBLIES. SEE BOM 011-00455-XX FOR CONTROLLING PARTS LIST. 2. REMOVE LINERS (BOTH SIDES) FROM ITEMS 11, 12, AND 13. 3. ITEM 21 TO BE SOLDERED TO ITEMS 7 AND 9 ON EACH END IN LOCATION SHOWN. ITEM 21 LENGTH TO BE APPROXIMATELY 0.5 cm IN TWO PLACES. 4. ITEM 29 TO BE SOLDERED TO ITEM 7 AND ITEM 9 IN LOCATION SHOWN. 5. ITEM 14 AND ITEM 15 TO BE SOLDERED TO ITEM 9 WHEN ITEMS 14 AND/OR 15 ARE PRESENT IN ASSEMBLY. 6. ITEM 30 AND ITEM 31 TO BE SOLDERED TO ITEM 6 AT EACH FLANGE (2 PLACES PER PART). 7. NOTE REMOVED. 8. AFTER ENGAGING CABLE WITH CONNECTOR, APPLY RTV (291-00039-00) TO BOTH ENDS OF ZIF CONNECTOR OVER SLIDING MECHANISM AS TO PREVENT SLIDER DISENGAGEMENT. CURE TIME IS 2 HOURS MINIMUM.
GTX 330 MAINTENANCE MANUAL P/N 190-00207-05

TO ITEM 19 SEE NOTE 8

DETAIL A

30 SEE NOTE 23 18

31 SEE NOTE 6
Figure 7-1. Assembly Drawing GTX 330 (Dwg. No. 015-00455-XX Rev. E) (Sheet 1 of 2) Page 7-3 (Page 7-4 blank) Rev. B
Figure 7-2. Assembly Drawing GTX 330 (Dwg. No. 015-00455-XX Rev. E) (Sheet 2 of 2)

SEE NOTE 4

21 SEE NOTE 3 ITEMS 7 AND 9 SHOULD SLIDE TOGETHER AS MUCH AS POSSIBLE AT EDGES SHOWN

SUPPLIED WITH ITEM 15

SEE NOTE 5

14 SEE NOTE 5

SUPPLIED WITH ITEM 14
Page 7-5 (Page 7-6 blank) Rev. B
Figure 7-3. Sub-Assembly Front Panel (Dwg. No. 015-00456-XX Rev. A) Page 7-7 (Page 7-8 blank) Rev. B
1 NOTES: 1. REMOVE FRONT LINER AND REAR ALIGNMENT FIX (2 PLACES, REF. BLACK PLASTIC) FROM ITEM 2. REMOVE FRONT LINER FROM ITEM 5. 3. REMOVE FRONT AND REAR LINERS FROM ITEM 4. 4. REMOVE FRONT AND REAR LINERS FROM ITEM 3. 5. REMOVE REAR LINER FROM ITEM 1.
Figure 7-4. Sub-Assembly Display Module (Dwg. No. 015-00492-XX Rev. A) Page 7-9 (Page 7-10 blank) Rev. B
Figure 7-5. Sub-Assembly Bottom Cover (Dwg. No. 115-00293-00 Rev. A) Page 7-11 (Page 7-12 blank) Rev. B
Figure 7-6. GTX 330 Test Setup/Test Harness (Sheet 1 of 2) Page 7-13 (Page 7-14 blank) Rev B
Figure 7-7. GTX 330 Test Setup/Test Harness (Sheet 2 of 2) Page 7-15 (Page 7-16 blank) Rev B