GTX 330/33 with ADS-B Out System Maintenance Manual

GTX 330/33 with ADS-B Out System Maintenance Manual
GTX 330/33 with ADS-B Out
System Maintenance Manual
Contains
Instructions for Continued Airworthiness for STC SA01714WI
Aircraft Make, Model, Registration Number, and Serial Number along with
applicable STC Configuration information must be completed in Appendix A and
saved as aircraft permanent records.
190-00734-11
May 2013
Rev. 1
© Copyright 2013
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,
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to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of
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Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9LR, UK
Phone: +44 (0) 23 8052 4000
Fax: +44 (0) 23 8052 4004
Garmin AT, Inc.
2345 Turner Rd., SE
Salem, OR 97302 USA
Telephone: 503.581.8101
RECORD OF REVISIONS
Revision
1
Revision Date
5/1/13
Description
Initial Release
ECO #
-----
DOCUMENT PAGINATION
190-00734-11
Rev. 1
Section
Table of Contents
Pagination
v
Section 1
1-1 to 1-4
Section 2
2-1 to 2-4
Section 3
3-1 to 3-4
Section 4
4-1 to 4-6
Section 5
5-1 to 5-8
Section 6
6-1 to 6-4
Section 7
7-1 to 7-4
Section 8
8-1 to 8-2
Section 9
9-1 to 9-2
Appendix A
A-1 to A-12
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
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.
DEFINITIONS OF WARNINGS, CAUTIONS AND NOTES
WARNING
Warnings are used to bring to the installer’s immediate attention that not only damage
to the equipment but personal injury may occur if the instruction is disregarded.
CAUTION
Cautions are used to alert the individual that damage to equipment may results if the
procedural step is not followed to the letter.
NOTE
Notes are used to expand and explain the preceding step and provide further
understanding of the reason for the particular operation.
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.
CAUTION
The GTX 330 and GTX 330D have a display that is coated with a special anti-reflective
coating and is very sensitive to waxes and abrasive cleaners. CLEANERS
CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is
very important to clean the display using a microfiber cloth or with a clean, lint-free
cloth and an eyeglass lens cleaner that is safe for anti-reflective coatings
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Table of Contents
1 1.1 1.2 1.3 1.4 1.5 1.6 2 2.1 2.2 3 3.1 3.2 4 4.1 4.2 4.3 4.4 4.5 4.6 4.7 5 5.1 5.2 5.3 6 6.1 6.2 6.3 7 7.1 7.2 7.3 8 8.1 8.2 8.3 8.4 9 9.1 INTRODUCTION ............................................................................................................................................ 1-1 CONTENT, SCOPE, PURPOSE .......................................................................................................................... 1-1 ORGANIZATION ............................................................................................................................................. 1-1 APPLICABILITY .............................................................................................................................................. 1-2 PUBLICATIONS .............................................................................................................................................. 1-2 REVISON AND DISTRIBUTION ........................................................................................................................ 1-2 REFERENCE .................................................................................................................................................... 1-2 SYSTEM DESCRIPTION................................................................................................................................ 2-1 GTX 330/330D............................................................................................................................................... 2-1 GTX 33/33D................................................................................................................................................... 2-2 GTX CONTROL & OPERATION ................................................................................................................... 3-1 GTX 330/330D ............................................................................................................................................. 3-1 GTX 33/33D ................................................................................................................................................. 3-3 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ........................................................................... 4-1 APPLICABILITY .............................................................................................................................................. 4-1 AIRWORTHINESS LIMITATIONS...................................................................................................................... 4-1 SERVICING INFORMATION ............................................................................................................................. 4-1 MAINTENANCE INTERVALS ........................................................................................................................... 4-2 VISUAL INSPECTION ...................................................................................................................................... 4-4 ELECTRICAL BONDING TEST ......................................................................................................................... 4-5 ADDITIONAL INSTRUCTIONS .......................................................................................................................... 4-6 TROUBLESHOOTING.................................................................................................................................... 5-1 GTX GENERAL TROUBLESHOOTING .............................................................................................................. 5-1 GTX FAILURE ANNUNCIATIONS .................................................................................................................... 5-2 CONNECTOR PINOUT INFORMATION .............................................................................................................. 5-3 UNIT REMOVAL AND REINSTALLATION ............................................................................................... 6-1 GTX 330/330D ............................................................................................................................................. 6-1 GTX 33/33D ................................................................................................................................................. 6-3 TRANSPONDER ANTENNA.............................................................................................................................. 6-4 SOFTWARE ..................................................................................................................................................... 7-1 SOFTWARE CHECK ........................................................................................................................................ 7-1 SOFTWARE UPDATE ...................................................................................................................................... 7-2 SOFTWARE LOADING..................................................................................................................................... 7-2 SYSTEM CONFIGURATION AND CHECKOUT......................................................................................... 8-1 OVERVIEW ................................................................................................................................................. 8-1 SYSTEM CHECKOUT ....................................................................................................................................... 8-1 CONFIGURATION ............................................................................................................................................ 8-1 GTX TEST ..................................................................................................................................................... 8-2 SYSTEM RETURN TO SERVICE PROCEDURE ......................................................................................... 9-1 MAINTENANCE RECORDS .............................................................................................................................. 9-1 APPENDIX A. INSTALLATION SPECIFIC DATA......................................................................................... A-1 TABLE OF FIGURES
FIGURE 1. GTX 330/330D TRANSPONDER ................................................................................................................. 2-1 190-00734-11
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FIGURE 2. GTX 330 OR GTX 330D INTERFACE SUMMARY ........................................................................................ 2-2 FIGURE 3. GTX 33/33D TRANSPONDER ..................................................................................................................... 2-3 FIGURE 4. GTX 33 OR GTX 33D INTERFACE SUMMARY ............................................................................................ 2-3 FIGURE 5. GTX 330/330D FRONT PANEL................................................................................................................... 3-1 FIGURE 6. GTN 7XX TRANSPONDER CONTROL ......................................................................................................... 3-4 FIGURE 7. GTN 6XX TRANSPONDER CONTROL ......................................................................................................... 3-4 FIGURE 8. BONDING CHECK ....................................................................................................................................... 4-5 FIGURE 9. REAR VIEW, CONNECTOR P3301 ............................................................................................................... 5-3 FIGURE 10. GTX 330 MOUNTING RACK/CONNECTOR ASSEMBLY ............................................................................. 6-2 FIGURE 11. GTX 33 MOUNTING RACK/CONNECTOR ASSEMBLY ............................................................................... 6-3 FIGURE 12. GTX 330 STATUS PAGE ........................................................................................................................... 7-1 FIGURE 13. GTN 6XX/7XX SYSTEM PAGE ................................................................................................................ 7-2 FIGURE 14. SOFTWARE UPDATE CONNECTION ........................................................................................................... 7-2 Table of Tables
TABLE 1. GARMIN GTX 330/33 WITH ADS-B OUT REFERENCE DOCUMENTATION ................................................... 1-2 TABLE 2. GTN 7XX SERIES TRANSPONDER CONTROL REFERENCE DOCUMENTS ...................................................... 3-3 TABLE 3. GTN 6XX SERIES TRANSPONDER CONTROL REFERENCE DOCUMENTS ...................................................... 3-3 TABLE 4. MAINTENANCE INTERVALS ......................................................................................................................... 4-2 TABLE 5. GTX ELECTRICAL LOAD ............................................................................................................................. 4-6 TABLE 6. GTX (ALL MODELS) TRANSPONDER TROUBLESHOOTING .......................................................................... 5-1 TABLE 7. GTX 330/330D TRANSPONDER FAILURE/FAULT MESSAGES ...................................................................... 5-2 TABLE 8. GTX 33/33D TRANSPONDER FAILURE/FAULT MESSAGES .......................................................................... 5-2 TABLE 9. CONNECTOR PINOUT ................................................................................................................................... 5-3 TABLE 10. LIGHTING/POWER PIN ASSIGNMENTS ....................................................................................................... 5-5 TABLE 11. TEMPERATURE PROBE PIN ASSIGNMENTS ................................................................................................. 5-6 TABLE 12. ENCODED ALTITUDE PIN ASSIGNMENTS ................................................................................................... 5-6 TABLE 13. DISCRETE OUTPUTS .................................................................................................................................. 5-6 TABLE 14. DISCRETE INPUTS ...................................................................................................................................... 5-7 TABLE 15. RS-232 CONNECTIONS .............................................................................................................................. 5-7 TABLE 16. ARINC 429 CONNECTIONS ......................................................................................................................... 5-7 TABLE 17. #1 GTX 330/33 INTERFACED EQUIPMENT ............................................................................................... A-4 TABLE 18. #2 GTX 330/33 INTERFACED EQUIPMENT ............................................................................................... A-5 GTX 330/33 with ADS-B Out
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1
1.1
INTRODUCTION
CONTENT, SCOPE, PURPOSE
This document provides Instructions for Continued Airworthiness (ICA) for the Garmin GTX 330/33
with ADS-B Out functionality installed and compliant to version 2, under AML STC SA01714WI. This
document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and
Appendix G. Information in this document is required to maintain the continued airworthiness of the
GTX 330/33.
1.2
ORGANIZATION
The following outline briefly describes the organization of this manual:
Section 2: System Overview
Provides a complete description of the type design change associated with installing a Garmin GTX
330/33 with ADS-B Out functionality. An overview of the GTX 330/33 with ADS-B Out system
interface is also provided.
Section 3: Control & Operation
Presents basic control and operation information specifically tailored to maintenance practices.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for continued airworthiness of the GTX 330/33 with ADS-B Out.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with the GTX
330/33 with ADS-B Out systems.
Section 6: Unit Installation & Removal
Gives instructions for the removal and replacement of a GTX 330/33.
Section 7: Software
Gives instructions for loading software on the Garmin GTX 330/33.
Section 8: System Configuration & Checkout
Gives instructions for configuring, and testing of the Garmin GTX 330/33.
Section 9: System Return to Service Procedure
Specifies return-to-service procedures to be performed upon completion of maintenance to the Garmin
GTX 330/33.
Appendix A: Aircraft Specific Information
Contains aircraft specific installation and configuration data for the Garmin GTX 330/33.
1.2.1
UNITS OF MEASURE
Unless otherwise stated, all units of measure are English units.
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1.3
APPLICABILITY
This document applies to all aircraft with GTX 330/33 with ADS-B Out functionality installed in
accordance with STC SA01714WI. Modification of an aircraft by this Supplemental Type Certificate
(STC) obligates the aircraft operator to include the maintenance information provided by this document in
the operator’s Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program.
1.4
PUBLICATIONS
In addition to this manual, the following documents are required to perform maintenance. It is the
responsibility of the owner / operator to ensure latest versions of these documents are used during
operation, servicing or maintenance of the airplane.
Table 1. Garmin GTX 330/33 with ADS-B Out Reference Documentation
Document
Garmin P/N
GTX 330/33 with ADS-B Out AML STC Equipment List
1.5
005-00734-05
REVISON AND DISTRIBUTION
This document is required for maintaining the continued airworthiness of the aircraft.
document is revised, every page will be revised to indicate current revision level.
When this
Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center
website.
Owner/operators may obtain the latest revision of this document from the www.flyGarmin.com/ Support
page, or by contacting a Garmin dealer, contacting Garmin Product Support at 913-397-8200, toll free
866-739-5687, or using around the world contact information on www.flyGarmin.com.
A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the
revision is determined to be significant.
1.6
REFERENCE
1.6.1
TERMINOLOGY
Except where specifically noted, references made to the ‘GTX’ or ‘GTX 330/33’ will equally apply to the
GTX 330/330D/33/33D. Additionally, ‘ADS-B’ refers to version 2 ADS-B Out only.
Throughout this document references will be made to ‘metallic’ aircraft. For the purposes of this manual,
metal aircraft will be those with an aluminum skin.
1.6.2
ACRONYMS
•
AC: Advisory Circular
•
ADC: Air Data Computer
•
ADS-B: Automatic Dependant Surveillance – Broadcast
•
ADS-B Out: The transmission of ownship position, altitude, velocity, and other information to
other aircraft and ATC ground based surveillance systems.
•
AHRS: Attitude Heading Reference System
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•
AML: Approved Model List
•
ATCRBS: Air Traffic Control Radar Beacon System
•
EGNOS: European Geostationary Navigation Overlay Service
•
ES: Extended Squitter
•
FAA: Federal Aviation Administration
•
GNS: Garmin Navigation System
•
GPS: Global Positioning System
•
GTN: Garmin Touchscreen Navigator
•
GTX: Garmin Transponder
•
HSDB: High Speed Data Bus
•
ICA: Instructions for Continued Airworthiness
•
STC: Supplemental Type Certificate
•
TAS: Traffic Advisory System
•
TCAS: Traffic Alert and Collision Avoidance System
•
TIS: Traffic Information Service
•
TSO: Technical Standard Order
•
WAAS: Wide Area Augmentation System
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SYSTEM DESCRIPTION
Automatic Dependent Surveillance-Broadcast (ADS-B) technology improves situational awareness and
flight safety. A Garmin transponder with ADS-B capabilities will automatically transmit position,
velocity, and heading information to other aircraft and ground stations. The current air traffic control
system depends on a transponder request for pertinent aircraft information, whereas ADS-B provides
automatic transmission of aircraft information without a request.
All Garmin transponders have a radio transmitter/receiver that operates on radar frequencies, receiving
ground radar or TCAS interrogations at 1030 MHz and transmitting a coded response of pulses to groundbased radar on a frequency of 1090 MHz. Each unit is equipped with IDENT capability and will reply to
ATCRBS Mode A, Mode C and Mode S All-Call interrogation.
The Garmin transponders approved by this STC are the GTX 330 and GTX 33 (Non-Diversity Mode S
Transponders) and the GTX 330D and GTX 33D (Diversity Mode S Transponders). The ES option of
any of the transponders provides ADS-B Extended Squitter functionality.
2.1
GTX 330/330D
The GTX 330/330D transponders are panel mounted and contain an integrated display to inform the crew
of the current code, reply symbol and mode of operation. The GTX 330/330D screen also 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. Additionally, the GTX 330/330D display will annunciate when the unit is actively
transmitting ADS-B information.
The GTX 330/330D feature multiple transmit/receive ARINC 429 and RS-232 data ports. The units
concentrate 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 Garmin GTX 330/330D panel mounted transponder(s) is a stand alone transponder that can operate
via the faceplate or can communicate with the on-side GTN 6XX/7XX or GNS 4XX/5XX through RS232 digital interface. This STC installation allows for installation of two GTX 330 non-diversity
transponders, two GTX 330D Diversity transponders, one of each type, or a single transponder.
Power is provided by the aircraft’s existing Avionics Bus. Each non-diversity GTX 330 transponder
interfaces with a transponder antenna mounted to the bottom of the fuselage whereas each GTX 330D
diversity transponder interfaces to a transponder antenna mounted to the top of the fuselage as well as the
antenna mounted to the bottom.
Figure 2 provides a summary of the interfaces provided for the GTX 330 or GTX 330D.
Figure 1. GTX 330/330D Transponder
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Figure 2. GTX 330 or GTX 330D Interface Summary
2.2
GTX 33/33D
The GTX 33/33D transponders are remote mounted and require a display/control interface as provided by
the Garmin GTN 6XX/7XX Series Navigators in order to be installed in accordance with this STC. Basic
transponder functions of the GTX 33/33D are identical to that GTX 330/330D, only the GTX 33/33D are
remote mounted. As the GTX 33/33D installation requires the use of the GTN, many optional functions
are not required because control of the GTX is then handled through the GTN.
The Garmin GTX 33/33D transponder(s) communicates with the on-side GTN 6XX/7XX through RS232 digital interface. This STC installation allows for installation of two GTX 33 non-diversity
transponders, two GTX 33D Diversity transponders, or one of each type.
Power is provided by the aircraft’s existing Avionics Bus. Each non-diversity GTX 33 transponder
interfaces with a transponder antenna mounted to the bottom of the fuselage whereas each GTX 33D
diversity transponder interfaces to a transponder antenna mounted to the top of the fuselage as well as the
antenna mounted to the bottom.
Figure 4 provides a summary of the interfaces provided for the GTX 33 or GTX 33D.
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Figure 3. GTX 33/33D Transponder
Figure 4. GTX 33 or GTX 33D Interface Summary
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GTX CONTROL & OPERATION
All control and operation of GTX 330/330D transponder as normally used in flight occurs through the
front panel of the GTX. Control and operation of the remote mounted GTX 33/33D is handled through
the external interface provided via the GTN 6XX/7XX. Figure 6 and Figure 7 identify various interface
buttons for these units.
3.1
GTX 330/330D
Figure 5. GTX 330/330D Front Panel
Function Selector Switches
The function selection switches are:
OFF Powers off the GTX 330. Pressing the 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 does not reply to any
interrogations. Pressing and holding the STBY key selects ground (GND) mode if Automated
Airborne Determination is not otherwise selected from another source. When GND is
annunciated, the transponder does not respond to ATCRBS interrogations but squitters and
replies to discretely addressed Mode S interrogations.
ON 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 (“®”), but the replies do not include
altitude information.
ALT 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 (“®”). 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 does not include altitude
information.
NOTE
Any time the function switch is in the ON or ALT position the transponder becomes an
active part of the Air Traffic Control Radar Beacon System (ATCRBS). The
transponder also responds to interrogations from TCAS equipped aircraft.
IDENT Pressing the IDENT key activates the Special Position Identification (SPI) Pulse for 18
seconds, identifying the transponder return from others on an air traffic controller’s screen.
During the IDENT period the word ‘IDENT’ appears in the upper left corner of the display.
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VFR 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.
NOTE
The VFR button is on (functional) by default, but can be disabled in configuration
mode
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. In the
Configuration mode, steps through the function pages.
START Starts and stops the Altitude Monitor, Count Up, Count Down and Flight timers
STOP In Configuration mode, steps through functions in reverse.
CRSR Initiates entry of the starting time for the Count Down timer and cancels transponder code
entry. Selects changeable fields in Configuration mode.
CLR Resets the Count Up, Count Down and Flight timers. Cancels the previous key press during
code selection and Count Down entry. Used in Configuration mode.
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.
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.
Code Selection
Code selection is entered with eight keys (0 – 7) providing 4,096 active identification codes. Pushing one
of these keys begins the code selection sequence. The new code is 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 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, 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.
Important Codes
1200 ⎯ VFR 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 is subject to unlawful interference)
7600 ⎯ Loss of communications
7700 ⎯ Emergency
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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 code changes.
Function Display
PRESSURE ALT Displays the altitude data supplied to the GTX 330 in feet, hundreds of feet (i.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 Controlled by START/STOP key. Activates a voice alarm and warning annunciator
MONITOR when altitude limit is exceeded
OAT/DALT Displayed when the GTX 330 is configured with temperature input.
Outside Air Temperature and Density Altitude.
Displays
COUNT UP Controlled by START/STOP and CLR keys.
TIMER
COUNT DOWN Controlled by START/STOP, CLR, and CRSR keys. The initial Count Down time
TIMER is entered with the 0 – 9 keys.
CONTRAST This page is only displayed if manual contrast mode is selected in Configuration
mode. Contrast is controlled by the 8 and 9 keys.
DISPLAY This page is only displayed if manual backlighting mode is selected in
Configuration mode. Backlighting is controlled by the 8 and 9 keys.
ADS-B TX Controlled by START/STOP key. Starts/stops extended squitter function.
FLIGHT ID If system is configured for FLT ID PWR-UP ENTRY at installation, the FLIGHT
ID entry page will be present on power up of GTX 330. This allows the pilot/crew to
enter the specific Flight ID for transmission to ATC interrogations.
3.2
GTX 33/33D
Figure 6 shows a screenshot of the GTX control page associated with the GTN 7XX series touchscreen
navigator. Refer to the following Garmin documents for details regarding the controls and their functions.
Table 2. GTN 7XX Series Transponder Control Reference Documents
Document Title
Document Number
GTN 725/750 Cockpit Reference Guide (CRG)
190-01007-04
GTN 725/750 Pilot’s Guide
190-01007-03
Figure 7 shows a screenshot of the GTX control page associated with the GTN 6XX series touchscreen
navigator. Refer to the following Garmin documents for details regarding the controls and their functions.
Table 3. GTN 6XX Series Transponder Control Reference Documents
Document Title
Document Number
GTN 625/635/650 Cockpit Reference Guide (CRG)
190-01004-04
GTN 625/635/650 Pilot’s Guide
190-01004-03
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Figure 6. GTN 7XX Transponder Control
Figure 7. GTN 6XX Transponder Control
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•
•
•
4.4
Calibrated pitot/static ramp tester
Outdoor line-of-site to GPS satellite signals or GPS indoor repeater
Ground Power Unit (Capable of supplying aircraft power)
MAINTENANCE INTERVALS
Table 4 shows systems and items, installed by this STC, which must undergo tests or checks at specific
intervals. Those inspections that are based on calendar elapsed time shall have specific intervals stated in
Table 4.
NOTE
The maintenance intervals listed in the table below must be adhered to for each
installed GTX.
Table 4. Maintenance Intervals
Item
Description/Procedure
Equipment Removal
Removal and reinstallation of GTX LRUs
& Reinstallation
Section No.
Interval
6
On Condition
Testing
The GTX 330/33 transponders must be tested
and shown to comply with Title 14 CFR Part
91.225 and 91.227.
8.4
Replacement of GPS
Position source(s).
Cleaning
The GTX 330 display and bezel may be
cleaned periodically when required.
Cleaning can be accomplished using a soft
cotton cloth dampened with clean water.
DO NOT use any chemical cleaning agents.
Care should be taken to avoid scratching the
surface of the display.
N/A
On Condition
Testing
The GTX 330/33 transponders must be tested
and shown to comply with Title 14 CFR Part
91.411, 91.413, 91.225, 91.227 and Part 43
Appendix E and F.
8.4
24 Calendar Months
Equipment Visual
Inspection
A visual inspection of the equipment installed
by this STC must be performed.
4.5
12 Calendar Months
Electrical Bonding
Test
An electrical bonding test must be performed
on equipment installed by this STC.
4.6
10 Years or 2000 hours
Antenna Visual
Inspection
Removal and replacement
4.5
On Condition
4.6
On Condition
Lightning Protection
Electrical Bonding
Test
Perform the electrical bonding resistance check
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
4-2
Item
Description/Procedure
Inspect the antenna and surrounding
installation.
Lightning Strike Actual or Suspected The GTX 330/33 transponder receiver
sensitivity must be tested and shown to comply
with Title 14 CFR Part 43 Appendix F.
190-00734-11
Rev. 1
Section No.
Interval
4.5
On Condition
8.4
On Condition
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
4-3
4.5
VISUAL INSPECTION
Perform a visual inspection in accordance with requirements in Table 4. Check for corrosion, damage, or
other defects for each of the installed items. Replace any damaged parts as required. Inspection may
require the temporary removal of a unit or units to gain access to connectors. Follow guidance in Section
6 for equipment removal and replacement. Refer to A 2 of this manual for equipment locations and refer
to the specific aircraft Maintenance Manual for instructions on removing any access panels.
GTX 330/330D Visual Inspection
During normal aircraft inspections not to exceed 12 calendar month intervals, conduct a visual inspection
of the GTX 330/330D installation in the following locations:
Instrument Panel
1) Inspect all GTX 330/330D knobs and buttons for legibility of labels and markings.
2) Inspect GTX 330/330D units for security of attachment.
3) Inspect mounting rack and hardware for integrity.
a. Verify the racks, fasteners, and support structure are in good condition and are securely fastened.
b. Inspect for signs of corrosion.
c. For composite aircraft, inspect any aluminum foil tape used to ground the GTX and verify that it
is not torn, damaged or showing signs of corrosion. If any of these occurs then the tape must be
replaced.
4) Inspect any bonding straps for corrosion, loose connections, or signs of damage.
5) Inspect the condition of the wiring harnesses and coaxial cables.
a. Inspect all instrument panel wiring and coax for chafing, damage, proper routing of wire bundles
and security of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph
11-96. Pay particular attention to possible areas of chaffing.
b. Verify that the harness shows no signs of cracking, chaffing, abrasion, melting, or any other form
of damage.
c.
Inspect the GTX 330/330D connectors for corrosion or other defects. Check the integrity of the
shield block ground attachments to the harness connector assembly as well as the integrity of the
individual shields and their attachment.
GTX 33/33D Visual Inspection
During normal aircraft inspections not to exceed 12 calendar month intervals, conduct a visual inspection
of the GTX 33/33D installation in the following locations:
Remote Mount Rack
1) Inspect GTX 33/33D units for security of attachment.
2) Inspect mounting rack and hardware for integrity.
a. Verify the racks, fasteners, and support structure are in good condition and are securely fastened.
b. Inspect for signs of corrosion.
c. For composite aircraft, inspect any aluminum foil tape used to ground the GTX and verify that it
is not torn, damaged or showing signs of corrosion. If any of these occurs then the tape must be
replaced.
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
4-4
3) Inspect any bonding straps for corrosion, loose connections, or signs of damage.
4) Inspect the condition of the wiring harnesses and coaxial cables.
a. Verify that all wiring and cables are securely fastened.
b. Verify that the harness shows no signs of cracking, chaffing, abrasion, melting, or any other form
of damage.
Antenna Visual Inspection
During normal aircraft inspections not to exceed 12 calendar month intervals, conduct a visual inspection
of the transponder antennas for the following:
1) Leading edge erosion, cracks, dents, or broken antenna. If present, antenna must be replaced.
2) If the attachment is not secure, re-work the installation and complete electrical bonding test specified
in Section 4.6.
3) Condition of base seals. In the event the antenna seal shows sign of damage or decomposition, re-seal
and complete the Electrical bonding test specified in Section 4.6.
Post Lightning Strike Inspection
A post lightning strike inspection must be done for a suspected or actual lightning strike to antennas.
Inspect antenna and surrounding installation to ensure that there is no structural damage around the areas
where lightning may have attached. If there is visible sign of damage to the antenna, then it should be
replaced.
4.6
ELECTRICAL BONDING TEST
A milliohm meter and Kelvin probes are recommended for this test. However, a standard voltmeter,
power supply with adjustable current limit and ammeter may be substituted. The following procedure is
written using the voltmeter, power supply and ammeter. All test equipment must have valid calibration
records.
Procedures
1.
Connect the positive lead of the power supply to the engine compartment grounding bracket (battery
negative connection to the airframe). Connect/touch the positive lead of the voltmeter to the same
point.
Figure 8. Bonding Check
190-00734-11
Rev. 1
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
4-5
NOTE
Ensure that the voltmeter and power supply probes do not touch, so as not to induce
contact resistance.
2.
Touch negative lead of power supply to each of the test points listed while performing Step 3. At
each point, configure the power supply to produce 1 amp before measuring voltage. (Use an
ammeter to ensure current is within 1 amp ±100 milliamp at each point).
3.
Set the voltmeter to measure millivolts and null the reading. Measure the voltage from the engine
grounding bracket (step 1) to each of the following points and record the voltage. (Perform Step 2 at
each point to ensure that 1 amp ±100 milliamp is present before measuring.)
•
Top metal case of GTX 330 #1: __________ millivolts (if installed)
•
Top metal case of GTX 330 #2: __________ millivolts (if installed)
•
GTX 33 #1 top: __________ millivolts (if installed)
•
GTX 33 #2 top: __________ millivolts (if installed)
•
Upper Transponder Antenna: __________ millivolts (if installed)
•
Lower Transponder Antenna: __________ millivolts (if installed)
Ensure that at each test point, no more than 5 millivolts (5 mΩ) are present. In this case, voltage is
equivalent to resistance (Ω), given that precisely 1 amp reference current is present.
TIP: If 1 amp reference current cannot be maintained, note the difference between the attainable current
and 1 amp reference current. Calculate the percentage difference and apply this to the voltage reading to
obtain the equivalent resistance. Example: If the measured current is 1.2 amps, (20% high from the target
1 amp current), then the allowable voltage measurement would be 20% high, 5 millivolts would now be 6
millivolts.
4.7
ADDITIONAL INSTRUCTIONS
Electrical load information for the GTX is provided below. Appendix A of this document contains details
specific to the load changes for the installation.
Table 5. GTX Electrical Load
Specification
Characteristic
14 Volt Current Draw
28 Volt Current Draw
Maximum Full TSO Reply Rate
3.1 A
1.6 A
Maximum Quiescent
1.1 A
0.85 A
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
4-6
5
5.1
TROUBLESHOOTING
GTX GENERAL TROUBLESHOOTING
This section provides information to assist troubleshooting if problems occur after completing the
maintenance. Refer to the GTX System Configuration Log retained in the aircraft permanent records for a
list of the interfaced equipment and system configuration data. When troubleshooting the GTX, refer to
the wire routing drawings and interconnect wiring diagrams that are retained in the aircraft permanent
records.
The following table describes possible symptoms associated with the Garmin transponders and provides
corresponding actions for troubleshooting:
Table 6. GTX (All Models) Transponder Troubleshooting
Symptom
Recommended Action
Ensure the XPDR circuit breaker is closed.
Transponder will not turn on.
Ensure connectors are seated on transponder and transponder is
seated properly in mounting rack.
Check and verify integrity of the antenna installation, ground planes,
and coaxial cables.
Poor transponder performance.
Weak or intermittent radar
contact reported by ATC.
Check for proper electrical bonding / grounding of the antenna
installation.
Test coaxial cables for insertion loss and VSWR (Voltage Standing
Wave Ratio). VSWR should be checked with an in-line type
VSWR/wattmeter inserted in the coaxial transmission line between
the transponder and the antenna. Ideally, the VSWR should be 1.5:1
at 1090 MHz or less. Insertion loss should be less than 1.5 dB at
1090 MHz.
Loss of, or incorrect altitude
reporting by the transponder.
Check and verify the integrity of the transponder-altitude encoder
interface, including wiring and altitude encoder operation.
Transponder audio too quiet /
loud
Verify that the volume setting is at or above the minimum required
setting.
Incorrect Mode S Aircraft
Data Transmitted
Check the configuration mode settings and reset if necessary.
Transponder will not come out
of standby.
Check the transponder select switch for proper output.
190-00734-11
Rev. 1
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
5-1
5.2
GTX FAILURE ANNUNCIATIONS
Table 7. GTX 330/330D Transponder Failure/Fault Messages
Failure Message
Cause
Solution
Transponder FAIL message
The internal transmit or
squitter monitors have
detected a failure.
Return the unit to Garmin.
Fatal Error Page Displayed
The GTX330/330D has failed
the internal power-up integrity
check.
Return the unit to Garmin.
Ensure the aircraft has a clear view
of the sky.
The transponder has
insufficient data to support
ADS-B Out transmission.
NO ADSB
Ensure position source (GPS) is
powered and receiving valid GPS
position data.
Ensure ADS-B TX is selected to
ON.(This option only available is
ADS-B TX is configured for
PILOT SET)
Table 8. GTX 33/33D Transponder Failure/Fault Messages
Failure Message
Cause
Solution
Ensure the aircraft has a clear view
of the sky.
TRANSPONDER 1 – ADSB
is not transmitting position.
The transponder has
insufficient data to support
ADS-B Out transmission.
Ensure GTN 6XX/7XX is powered
and receiving valid GPS position
data.
Ensure ADS-B TX is selected to
ON.
TRANSPONDER 2 – ADSB
is not transmitting position.
TRANSPONDER 1 –
Transponder 1 needs service.
The transponder is reporting a
system failure.
Return the unit to Garmin.
TRANSPONDER 2 –
Transponder 2 needs service.
The transponder is reporting a
system failure.
Return the unit to Garmin.
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
5-2
Failure Message
Cause
Solution
TRANSPONDER 1 –
Transponder 1 is inoperative
or connection to GTN is lost.
TRANSPONDER 2 –
Transponder 2 is inoperative
or connection to GTN is lost.
TRANSPONDER –
Transponder 1 and 2 Mode S
addresses do not match.
5.3
If two transponders are installed,
ensure both GTNs are powered on.
The GTN cannot communicate
with the transponder or the
transponder is reporting a
system failure.
Check for proper configuration.
Check for correct wiring.
The transponders are
configured for different Mode
S addresses.
Verify the Mode S address for each
transponder and verify that they
match.
CONNECTOR PINOUT INFORMATION
Figure 9. Rear View, Connector P3301
Table 9. Connector Pinout
GTX 33/33D
Pin Name
Pin
GTX 330/330D
Pin Name
I/O
1
RESERVED
AVIONICS MASTER ON SELECT
In
2
ALTITUDE A1
ALTITUDE A1
In
3
ALTITUDE C2
ALTITUDE C2
In
4
ALTITUDE A2
ALTITUDE A2
In
5
ALTITUDE A4
ALTITUDE A4
In
6
ALTITUDE C4
ALTITUDE C4
In
7
ALTITUDE B1
ALTITUDE B1
In
8
ALTITUDE C1
ALTITUDE C1
In
9
ALTITUDE B2
ALTITUDE B2
In
10
ALTITUDE B4
ALTITUDE B4
In
11
ALTITUDE D4
ALTITUDE D4
In
12
EXTERNAL IDENT SELECT*
EXTERNAL IDENT SELECT*
In
13
EXTERNAL STANDBY SELECT*
EXTERNAL STANDBY SELECT*
In
190-00734-11
Rev. 1
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
5-3
GTX 33/33D
Pin Name
Pin
GTX 330/330D
Pin Name
I/O
14
NOT USED
28 V LIGHTING BUS HI
15
AUDIO OUT HI
AUDIO OUT HI
Out
16
AUDIO OUT LO
AUDIO OUT LO
Out
17
SQUAT SWITCH IN
SQUAT SWITCH IN
In
18
RESERVED
RESERVED
--
19
ALTITUDE ALERT
ANNUNCIATE*
ALTITUDE ALERT
ANNUNCIATE*
20
RESERVED
RESERVED
--
21
AIRCRAFT POWER 1
AIRCRAFT POWER 1
In
22
RS-232 IN 1
RS-232 IN 1
In
23
RS-232 OUT 1
RS-232 OUT 1
24
RS-232 IN 2
RS-232 IN 2
25
RS-232 OUT 2
RS-232 OUT 2
26
ARINC 429 IN 3 A
ARINC 429 IN 3 A
In
27
POWER GROUND
POWER GROUND
--
28
ARINC 429 OUT 2 B
ARINC 429 OUT 2 B
29
ARINC 429 IN 3 B
ARINC 429 IN 3 B
30
ARINC 429 OUT 2 A
ARINC 429 OUT 2 A
Out
31
EXTERNAL SUPPRESSION I/O
EXTERNAL SUPPRESSION I/O
I/O
32
ARINC 429 IN 1 A
ARINC 429 IN 1 A
In
33
ARINC 429 IN 2 A
ARINC 429 IN 2 A
In
34
ARINC 429 OUT 1 B
ARINC 429 OUT 1 B
35
ARINC 429 IN 1 B
ARINC 429 IN 1 B
In
36
ARINC 429 IN 2 B
ARINC 429 IN 2 B
In
37
ARINC 429 OUT 1 A
ARINC 429 OUT 1 A
38
RESERVED
RESERVED
--
39
RESERVED
RESERVED
--
40
SPARE
SPARE
--
41
CURRENT TEMPERATURE
PROBE OUT
CURRENT TEMPERATURE
PROBE OUT
42
AIRCRAFT POWER 1
AIRCRAFT POWER 1
In
43
POWER GROUND
POWER GROUND
--
44
CURRENT TEMPERATURE
PROBE IN
CURRENT TEMPERATURE
PROBE IN
In
45
NOT USED
14 V/5 V LIGHTING BUS HI
In
46
TIS CONNECT SELECT*
TIS CONNECT SELECT*
In
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
In
Out
Out
In
Out
Out
In
Out
Out
Out
190-00734-11
Rev. 1
5-4
Pin
GTX 33/33D
Pin Name
GTX 330/330D
Pin Name
47
AUDIO MUTE SELECT*
AUDIO MUTE SELECT*
In
48
ARINC 429 IN 4 A
ARINC 429 IN 4 A
In
49
ARINC 429 IN 4 B
ARINC 429 IN 4 B
In
50
ALTITUDE COMMON (GROUND)
ALTITUDE COMMON (GROUND)
In
51
SIGNAL GROUND
SIGNAL GROUND
--
52
RESERVED
RESERVED
--
53
RESERVED
RESERVED
--
54
XPDR REMOTE POWER OFF
RESERVED
In
55
NOT USED
SPARE
--
56
AIRCRAFT POWER 2
AIRCRAFT POWER 2
In
57
NOT USED
SPARE
--
58
SIGNAL GROUND
RESERVED
--
59
NOT USED
SPARE
--
60
AIRCRAFT POWER 2
AIRCRAFT POWER 2
In
61
NOT USED
SPARE
--
62
SWITCHED POWER OUT
SWITCHED POWER OUT
I/O
Out
* Denotes Active Low (Ground to activate).
5.3.1
POWER AND LIGHTING FUNCTION
Table 10. Lighting/Power Pin Assignments
Pin Number
I/O
Unit
(33/330)
AIRCRAFT POWER 1
21
In
Both
AIRCRAFT POWER 1
42
In
Both
AIRCRAFT POWER 2
56
In
Both
AIRCRAFT POWER 2
60
In
Both
SWITCHED POWER OUT
62
Out
Both
POWER GROUND
27
--
Both
POWER GROUND
43
--
Both
14 V/5 V LIGHTING BUS HI
45
In
330 Only
28 V LIGHTING BUS HI
14
In
330 Only
SIGNAL GROUND
51
--
33 Only
SIGNAL GROUND
58
--
33 Only
XPDR REMOTE POWER OFF
54
In
33 Only
Pin Name
190-00734-11
Rev. 1
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
5-5
5.3.2
TEMPERATURE INPUTS
Table 11. Temperature Probe Pin Assignments
Pin Number
I/O
Unit
(33/330)
CURRENT TEMPERATURE PROBE OUT
41
Out
Both
CURRENT TEMPERATURE PROBE IN
44
In
Both
Pin Name
5.3.3
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 < 375 Ω. These inputs are considered inactive if the voltage to ground is 1133 VDC.
Table 12. Encoded Altitude Pin Assignments
Pin Number
I/O
Unit
(33/330)
ALTITUDE D4
11
In
Both
ALTITUDE A1
2
In
Both
ALTITUDE A2
4
In
Both
ALTITUDE A4
5
In
Both
ALTITUDE B1
7
In
Both
ALTITUDE B2
9
In
Both
ALTITUDE B4
10
In
Both
ALTITUDE C1
8
In
Both
ALTITUDE C2
3
In
Both
ALTITUDE C4
6
In
Both
ALTITUDE COMMON
50
--
Both
Pin Number
I/O
Unit
(33/330)
ALTITUDE ALERT ANNUNCIATE*
19
Out
Both
EXTERNAL SUPPRESSION I/O
31
In/Out
Both
Pin Name
5.3.4
DISCRETE FUNCTIONS
Discrete Outputs
Table 13. Discrete Outputs
Pin Name
* INACTIVE: 10
Vin
33VDC or Rin 100kΩ
ACTIVE: Vin 1.9VDC with
75 uA sink current, or Rin 375Ω
Sink current is internally limited to 200 uA max for a grounded input
Discrete Inputs
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
5-6
Table 14. Discrete Inputs
Pin Number
I/O
Unit
(33/330)
AVIONICS MASTER ON SELECT
1
In
330 Only
EXTERNAL IDENT SELECT*
12
In
Both
EXTERNAL STANDBY SELECT*
13
In
Both
SQUAT SWITCH IN
17
In
Both
TIS CONNECT SELECT*
46
In
Both
AUDIO MUTE SELECT*
47
In
Both
Pin Name
* This output is considered active if either the voltage to ground is < 1.9 VDC or the resistance to
ground is < 375 Ω. This output is considered inactive if the voltage to ground is 11-33 VDC.
5.3.5
RS-232 INPUT/OUTPUT
Table 15. RS-232 Connections
Pin Number
I/O
Unit
(33/330)
RS-232 OUT 1
23
Out
Both
RS-232 IN 1
22
In
Both
RS-232 OUT 2
25
Out
Both
RS-232 IN 2
24
In
Both
Pin Number
I/O
Unit
(33/330)
ARINC 429 OUT 1A
37
Out
Both
ARINC 429 OUT 1B
34
Out
Both
ARINC 429 IN 1A
32
In
Both
ARINC 429 IN 1B
35
In
Both
ARINC 429 IN 2A
33
In
Both
ARINC 429 IN 2B
36
In
Both
ARINC 429 OUT 2A
30
Out
Both
ARINC 429 OUT 2B
28
Out
Both
ARINC 429 IN 3A
26
In
Both
ARINC 429 IN 3B
29
In
Both
ARINC 429 IN 4A
48
In
Both
ARINC 429 IN 4B
49
In
Both
Pin Name
5.3.6
ARINC 429 INPUT/OUTPUT
Table 16. Arinc 429 Connections
Pin Name
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GTX 330/33 with ADS-B Out
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Maintenance Manual with ICA
190-00734-11
Rev. 1
5-8
6
6.1
UNIT REMOVAL AND REINSTALLATION
GTX 330/330D
Removal:
1. Insert the hex drive tool into the access hole on the unit face and rotate counterclockwise until the unit
is forced out about 3/8 inch.
2. Pull the unit straight out of the rack.
Reinstallation:
NOTE
It may be necessary to insert the hex drive tool into the access hole and rotate the cam
mechanism 90° counterclockwise to insure correct position prior to placing the unit in
the rack.
1. Slide the GTX 330/330D in the rack straight in until it stops, about 1 inch short of the final position.
2. A 3/32-inch hex drive tool is then inserted into the access hole at the bottom of the unit face.
3. Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly seated
in the rack.
4. Count the number of complete revolutions the Allen screw can be turned until it cannot turn any
more. Take care not to over-tighten. Three (3) turns is the minimum for proper installation. If fewer
than three (3) turns are possible, ensure there are no obstructions to the unit fully seating in the rack.
Also, the mounting rack may need to be moved aft (toward the pilot) such that the aircraft panel does
not obstruct the unit from properly engaging in the rack.
CAUTION
Be sure not to over-tighten the unit into the rack. The application of hex drive tool
torque exceeding 15 in-lbs can damage the locking mechanism.
190-00734-11
Rev. 1
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
6-1
Figure 10. GTX 330 Mounting Rack/Connector Assembly
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
6-2
6.2
GTX 33/33D
Removal:
1. Gain access to the transponder.
2. Unlock the GTX 33/33D handle by loosening the Phillips screw on the handle.
3. Pull the handle upward to unlock the GTX 33/33D. Gently remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage.
2. Gently insert the GTX 33/33D into its rack. The handle should engage the dogleg track.
3. Press down on the GTX 33/33D handle to lock the unit into the rack.
4. Lock the handle to the GTX 33/33D body using the Philips head screw.
Figure 11. GTX 33 Mounting Rack/Connector Assembly
190-00734-11
Rev. 1
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
6-3
6.3
TRANSPONDER ANTENNA
Removal:
1. Gain access to the antenna coaxial cable connector and mounting hardware. Refer to A 2 for
antenna location.
2. Disconnect the antenna coaxial cable.
3. Remove the hardware securing the antenna.
4. Remove antenna.
Reinstallation:
1. Install antenna using retained hardware.
2. Connect the antenna coaxial cable.
3. Test the GTX according to Section 8.4.
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
6-4
7
7.1
SOFTWARE
SOFTWARE CHECK
Anytime software loading procedures are accomplished during maintenance, conduct a final software
review of the system.
NOTE
Screenshots in this section are provided for reference only. For actual GTX software
versions, refer to the GTX 330/33 with ADS-B Out AML STC Equipment List, 00500734-05.
CAUTION
It is essential that the software version be correct. Earlier GTX software versions will
be non-compliant with ADS-B Out Version 2 requirements.
If the software version and/or part number does not match those specified, or if the
software is not successfully loaded, DO NOT continue. Troubleshoot and resolve the
issue before continuing.
GTX 330/330D Software Version Check
1. Start the GTX 330/330D in normal mode.
2. Observe the start up screen (as shown below) and verify the Software Version number matches the
approved version listed in the AML Equipment List Doc. 005-00734-05.
Figure 12. GTX 330 Status Page
GTX 33/33D Software Version Check
NOTE
The following procedures provide an overview to verify the software version of the
GTX 33/33D as interfaced with the GTN 6XX/7XX Series Navigators. For additional
details refer to the GTN 6XX/7XX Series Pilot Guides.
1. On the GTN 6XX/7XX System Page, press the External LRUs button
190-00734-11
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.
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
7-1
2. Observe the reported GTX software version number (as shown below) and verify the Version: number
matches the approved version listed in the AML Equipment List Doc. 005-00734-05.
Figure 13. GTN 6XX/7XX System Page
7.2
SOFTWARE UPDATE
The GTX 330/33 comes pre-loaded from the factory with software. However, the Software Version
number must match the approved version listed in the AML Equipment List Doc. 005-00734-05. If a unit
is replaced and does not have the approved version of software installed, software can be downloaded
from the Dealer Resource Center at www.flyGarmin.com. For dual GTX installations the software
loading procedures below must be carried out on each GTX.
The GTX 330 software can be updated in the Configuration mode as well as in Test mode. Updating
software in Configuration mode does not require the TEST MODE SELECT switch. However, for the
GTX 33 series, the TEST MODE SELECT switch is required. See Figure 14 for software update
connections.
Figure 14. Software Update Connection
7.3
SOFTWARE LOADING
NOTE
Screenshots in this section are provided for reference only. For actual GTX software
versions, refer to the GTX 330/33 with ADS-B Out AML STC Equipment List, 00500734-05.
GTX 330/33 with ADS-B Out
Maintenance Manual with ICA
190-00734-11
Rev. 1
7-2
7.3.1
DOWNLOAD PROCEDURES
1. Access the Dealer Resource Center on (www.flyGarmin.com).
2. Obtain the transponder software as specified in the AML Equipment List Doc. 005-00734-05.
3. Click on the hyperlink for the software download and download to a laptop computer.
4. Access the target directory for the software on the laptop computer.
5. Extract the files by double clicking on the downloaded ‘.exe’ file.
7.3.2
GTX SOFTWARE LOADING
CAUTION
If the unit is removed from the aircraft and operated, always connect J3302 (GTX
33/330/33D/330D) and J3303 (GTX 330D/33D) to a 50 Ω 5 watt load. The GTX
transmits Mode S acquisition squitter replies once per second whether interrogations
are received or not. Failure to connect a dummy load or antenna during this procedure
will cause the transponder to fail.
1.
Remove power from the GTX.
2.
Connect the test harness to the GTX and laptop as shown in Figure 14.
3.
Enable the TEST MODE switch on the test harness.
4.
Power on the GTX.
5.
Double click on the file ‘UPLOADXX.BAT’ (‘XX’ is an incremental number assigned to a specific
software version). The program will begin communicating with the GTX.
6.
The upload process could take up to 6 (six) minutes to complete.
NOTE
GTX 330 transponders will show a dynamic display test screen.
7.
Once the upload is completed, the unit will reset itself, and turn on.
8.
Remove power from the GTX.
9.
Remove the test harness between the laptop and the GTX.
10. Install GTX into aircraft and power up system.
11. Verify the software version is correctly displayed.
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8
8.1
SYSTEM CONFIGURATION AND CHECKOUT
OVERVIEW
This section contains instructions for configuring the GTX as well as checks to ensure the system is
properly installed and functioning correctly. The steps that are not applicable to a particular installation
may be skipped.
8.2
SYSTEM CHECKOUT
Original GTX 330/33 is Reinstalled
No software or configuration loading is required if the removed GTX is re-installed. This does not
include units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Continue to GTX Test (Section 8.4).
New, Repaired or Exchange GTX 330/33 is Installed
If a new, repaired or exchange GTX is installed, the correct software and configuration files must be
loaded to the unit per Sections 7.3 & 8.3.
8.3
CONFIGURATION
Retrieve the Post Installation Checkout Log from the aircraft permanent records. For those maintenance
activities that repaired or replaced the previous GTX 330/33, configure the GTX 330/33 as defined by the
data contained in the Post Installation Checkout Log.
NOTE
Ensure the Post Installation Checkout Log remains with the aircraft permanent records
upon completion of any maintenance activities.
8.3.1
GTX 330/330D CONFIGURATION
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 is highlighted, the 0 – 9 keys enter numeric data and the 8 or 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.
8.3.2
GTX 33/33D CONFIGURATION (GTN 6XX/7XX)
For those installations that utilize the GTX 33/33D, the configuration of the transponder is conducted
through the Garmin GTN 6XX/7XX series navigator. Access the Interfaced Equipment page by touching
the ‘Interface Equipment’ key on the GTN Setup page. Next, go to the External Systems page and touch
the corresponding key for the transponder to be configured, XPDR1 or XPDR2 (if present). This key
displays a page which allows the remote transponder to be configured.
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8.4
GTX TEST
Operation of the GTX 330/330D/33 or 33D Mode-S transponder is accomplished using either the
faceplate of the unit (on the GTX 330 series See Section 3.1) or a GTN 6XX/7XX unit (on the GTX 33
series). Refer to the operational documents listed in Table 2 and Table 3 for basic GTX 33 series
operation.
The integrated transponder/altitude reporting system must be verified in accordance with Title 14 of the
Code of Federal Regulations (14 CFR) §§ 91.411 and 91.413, every 24 calendar months, or any time the
transponder is removed/replaced/modified.
Additionally, the ADS-B Out parameters must be verified in accordance with Title 14 of the Code of
Federal Regulations (14 CFR) § 91.227 any time the position source (GPS) is replaced/modified.
The test is typically done as a ramp test using a transponder ramp test set, such as the IFR ATC-601A or
TIC TR-220 (S/W v5.30 or later). Specific instructions for operating the ramp tester are contained in the
applicable operator's manual.
Reference Part 43 Appendix F for testing criteria. The ramp test includes checks as follows:
1. Reply Frequency
2. Suppression
3. Receiver Sensitivity
4. Reply RF Output Power
5. Mode S Diversity Channel Isolation (if applicable)
6. Mode S Address
7. Mode S Formats
8. Mode S All-Call
9. ATCRBS –Only All Call
10. Squitter
Reference AC 43-6B and 14 CFR Part 43, Appendix E (c) for testing criteria. The ramp test includes
checks as follows:
1. Altitude Reporting
Reference Advisory Circular 20-165A and 14 CFR Part 91.227 for the following ADS-B Out parameters:
1. NACP ≥ 8
2. NIC ≥ 7
3. NACv ≥ 1
4. SIL ≥ 3
5. SDA ≥ 2
6. Ensure all 14 CFR 91.227(d) parameters are populated and transmitted.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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SYSTEM RETURN TO SERVICE PROCEDURE
9.1
MAINTENANCE RECORDS
After conducting required return-to-service procedures in accordance with this document, the aircraft may
be returned to service.
Record the following information in appropriate aircraft maintenance logs:
•
Part number and version number of any software updates performed during maintenance.
•
Record part and serial numbers of any LRU which was replaced.
•
Any other applicable information related to the maintenance work performed on the aircraft.
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APPENDIX A. INSTALLATION SPECIFIC DATA
A 1.
GENERAL INFORMATION
Date: ____ /____ /____
By: ______________________________________
Make:
Model:
Serial #:
Reg. #:
Unit Model:
Unit P/N:
Mod Level:
Serial #:
Unit Model:
Unit P/N:
Mod Level:
Serial #:
AIRCRAFT:
GTX #1:
GTX #2:
[N/A]
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A 2.
EQUIPMENT DETAILS
The table below describes the location of the GTX 330/33, antennas, and interfaced equipment.
Document all interfaced equipment (model/part number) and installed locations in the following table.
Also sketch equipment locations and wire routing on the diagrams in A 5 or A 6 as appropriate.
LRU
Installed Location
Description of Location
(F.S.)
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A 3.
ELECTRICAL LOAD CALCULATION
Items removed from aircraft:
Electrical Load (A) [1]
Comment
Electrical Load (A) [1]
Comment
Subtotal:
Items added to aircraft:
Subtotal:
Net Change in Bus Load:
[1] Use typical current draw when performing this calculation
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A 4.
EQUIPMENT INTERFACED TO THE GTX
The purpose of Table 17 and Table 18 is to document the equipment that is interfaced to the GTX
330/33(s). Use the following guidance when filling out this table:
•
Model(s): Write in the model number or numbers of the equipment that is interfaced to the GTX
330/33.
•
GTX Port Numbers: When applicable, write in the GTX 330/33 port number or numbers used
for the interface. This column is generally applicable only to serial ports such as RS-232 and
ARINC 429.
Table 17. #1 GTX 330/33 Interfaced Equipment
#1 GTX 330/33
Equipment Type
Model
GTX 330/33 Port
Number
Audio Panel
Display
Encoding Altitude
GPS #1
GPS #2
Heading
Air Data
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Table 18. #2 GTX 330/33 Interfaced Equipment
#2 GTX 330/33
Equipment Type
Model
GTX 330/33 Port
Number
Audio Panel
Display
Encoding Altitude
GPS #1
GPS #2
Heading
Air Data
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A 5.
GTX 330/33 INSTALLATION – SINGLE ENGINE
The following diagram depicts approximate location of all LRUs along with the wire routing for the GTX
330/33 throughout the aircraft structure for a single-engine aircraft.
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A 6.
GTX 330/33 INSTALLATION – TWIN ENGINE
The following diagram depicts approximate location of all LRUs along with the wire routing for the GTX
330/33 throughout the aircraft structure for a twin-engine aircraft:
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A 7.
POST INSTALLATION CONFIGURATION LOG
GTX 330 Post-Installation Configuration Log
Date:
Aircraft Model:
Aircraft
Registration:
By:
Aircraft Serial #:
HEX Address:
#1 Unit P/N:
#1 Unit Serial #:
Aircraft Make:
#2 Unit P/N:
#2 Unit Serial #:
CONFIGURATION ITEMS
Installation Settings (All settings in this section must be the same for each installed transponder)
Field
Setting
Field
Setting
Voice Setting
Volume
Message
Altitude Monitor
Count Down Timer
Page Change
Traffic Messages
Display Mode / Level
BKLT
KEY
RSP Time
RSP Time
If MAN selected as BKLT source above, the additional
fields below must be configured
/
If MAN Selected as KEY source above, the additional fields
below must be configured
Level
Level
Min
Min
BKLT Source
KEY Source
Slope
Slope
Offset
Offset
Contrast Mode
VFR Key Configuration
Arinc 429 Configuration
Transponder #1
Input
Speed
Output
Speed
Port 1
Port 2
Port 3
N/A
Port 4
N/A
Transponder #2
Input
Speed
Output
Speed
Port 1
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GTX 330 Post-Installation Configuration Log
Port 2
Port 3
N/A
Port 4
N/A
RS-232 Configuration (Input/Output)
Either Port 1 or Port 2 must contain the following configuration:
Input – Remote
Output – Remote
Transponder #1
Input
Output
Port 1
Port 2
Transponder #2
Input
Output
Port 1
Port 2
Field
Setting
Field
Setting
VS Rate
Format
VFR ID
Altitude Alert Deviation
Squat Switch
Temperature Sensor Installed
/ Units
Sense
US Tail
Delay Time
2
Hex Address
Auto Flight Timer
Mode S Flight ID
GPS X Ofst
GPS Y Ofst
GPS Integrity
/
1E-7
Aircraft Type
Max A/S
AC Length Type
AC Width Type
ADS-B TX
1090 IN
UAT IN
EHS
Gray Code
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GTX 33 Post-Installation Configuration Log
Date:
Aircraft Model:
Aircraft
Registration:
By:
Aircraft Serial #:
HEX Address:
#1 Unit P/N:
#1 Unit Serial #:
Aircraft Make:
#2 Unit P/N:
#2 Unit Serial #:
CONFIGURATION ITEMS
INPUTS/OUTPUTS
RS-232 Configuration (Input/Output)
Either Port 1 or Port 2 must contain the following configuration:
Input – GTX Mode S + #1 (or #2 for XPDR 2 if installed)
Output – GTX Mode S + #1 (or #2 for XPDR 2 if installed)
Transponder #1
Input
Output
Baud
Parity
Port 1
9600
No Parity
Port 2
9600
No Parity
Baud
Parity
Port 1
9600
No Parity
Port 2
9600
No Parity
Transponder #2
Input
Output
Arinc 429 Configuration
Transponder #1
Input
Speed
Output
Speed
Output
Speed
Port 1
Port 2
Port 3
Port 4
Transponder #2
Input
Speed
Port 1
Port 2
Port 3
Port 4
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GTX 33 Post-Installation Configuration Log
Installation Settings (All settings in this section will be the same for each installed transponder)
Field
Setting
Field
VFR Button Code
Flight ID
Aircraft Weight
Aircraft Length
Auto Standby Delay
2
Setting
Aircraft Width
Altitude Climb Rate for
Airborne Transition
Enhanced Surveillance
Air/Ground Logic
Surveillance Integrity Level
Squat Switch Sense
Temperature Switch
Installed
Max Airspeed
1090 Input
Address Type
UAT Input
Address
GPS Antenna Longitudinal
Offset
Flight ID Type
GPS Antenna Lateral Offset
1E-7
Audio Configuration (All settings in this section will be the same for each installed transponder)
Field
Setting
Field
Altitude Monitor
N/A – Has no effect
Voice Setting
Count Down Timer
N/A – Has no effect
Volume
Setting
TIS Alert
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A 8.
AIRCRAFT WIRING DIAGRAMS
Attach the aircraft wiring diagrams showing the equipment installed by this STC or a markup of the
interconnect diagrams from the STC installation manual detailing which equipment was installed and how
it was connected.
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