Garmin GTX 33 User Manual

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Page 1

GTX 33

Transponder

Installation Manual

190-00906-00 September, 2012 Revision H

Page 2

Garmin Ltd. or its subsidiaries

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.

1200 E. 151st 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.

Liberty House, Bulls Copse Road

Hounsdown Business Park

Southampton, SO40 9RB U.K.

+44/ (0) 870.8501241

Garmin AT, Inc.

2345 Turner Rd., SE

Salem, OR 97302 USA

Telephone: 503.581.8101

RECORD OF REVISIONS

Revision Revision Date Description

A 9/22/08 Production Release

B 2/26/09 Clarified model name

C 9/3/10

D 10/27/10

E 3/21/12 Added ADS-B info

F 6/13/12 Added TNC connectors

G 09/11/12 Updated per SW v7.00

H 09/24/12 Updated per SW v7.01

Updated outline/installation drawings and interconnects, added ETSO information

Added GTX 33H, GTX 33DH, and non-extended squitter units info, simplified doc title

GTX 33 Installation Manual 190-00906-00 Page A Rev. H

Page 3

CURRENT REVISION DESCRIPTION

Revision

Page

Number(s)

1-3 1.3.1 Updated SW version

1-4 1.3.1.2 Updated SW version

1-10

Section

Number

1.9.1 Updated SW version

DOCUMENT PAGINATION

Section Page Range

Table of Contents i – x

Section 1 1-1 – 1-12 Section 2 2-1 – 2-10 Section 3 3-1 – 3-8

Section 4 4-1 – 4-10 Appendix A A-1 – A-2 Appendix B B-1 – B-18 Appendix C C-1 – C-6 Appendix D D-1 – D-7

Description of Change

190-00906-00 GTX 33 Installation Manual Rev. H Page i

Page 4

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

WARNING

NOTE

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 the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual.

DEFINITIONS OF WARNINGS, CAUTIONS, AND NOTES

WARNING

Warni n gs 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

result 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.

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 33 shall equally apply to the GTX 33, GTX 33D, GTX 33H, and GTX 33DH, with or without Extended Squitter; except where specifically noted.

GTX 33 Installation Manual 190-00906-00 Page ii Rev. H

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GTX 33 HARDWARE MOD LEVEL HISTORY

The following table identifies hardware modification (Mod) Levels for the GTX 33. 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 web site at www.garmin.com using their Garmin-provided user name and password.

GTX 33 P/N 011-00779-00, 011-00779-20 HARDWARE MOD LEVEL HISTORY

MOD

LEVEL

1 0710 05/18/07 Improve decay time of the suppression circuit

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF MODIFICATION

GTX 33 P/N 011-00779-10, 011-00779-30 HARDWARE MOD LEVEL HISTORY

MOD

LEVEL

1 0624 04/28/07 Improve rejection of high-power in-band signals

2 0710 05/18/07 Improve decay time of the suppression circuit

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF MODIFICATION

GTX 33 P/N 011-00779-01, 011-00779-21 HARDWARE MOD LEVEL HISTORY

MOD

LEVEL

1 0311 02/06/04

2 0624 04/25/07 Improve rejection of high-power in-band signals

3 0710 05/18/07 Improve decay time of the suppression circuit

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF MODIFICATION

GTX 33D Only. Switch/Diplexer Assembly reworked to prevent +200 Volt supply line from shorting to the chassis.

GTX 33 P/N 011-00779-50, 011-00779-70 HARDWARE MOD LEVEL HISTORY

MOD

LEVEL

None at

this time

190-00906-00 GTX 33 Installation Manual Rev. H Page iii

SERVICE

BULLETIN

NUMBER

SERVICE

BULLETIN

DATE

PURPOSE OF MODIFICATION

Page 6

Limited Warranty

All Garmin avionics products are warranted to be free from defects in materials or workmanship for: one years from the date of purchase for new Remote-Mount and Panel-Mount products; one year from the date of purchase for new portable products and any purchased newly-overhauled products; six months for newly-overhauled products exchanged through a Garmin Authorized Service Center; and 90 days for factory repaired or newly-overhauled products exchanged at Garmin in lieu of repair. Within the applicable 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 apply to: (i) cosmetic damage, such as scratches, nicks and dents; (ii) consumable parts, such as batteries, unless product damage has occurred due to a defect in materials or workmanship; (iii) damage caused by accident, abuse, misuse, water, flood, fire, or other acts of nature or external causes; (iv) damage caused by service performed by anyone who is not an authorized service provider of Garmin; or (v) damage to a product that has been modified or altered without the written permission of Garmin. In addition, Garmin reserves the right to refuse warranty claims against products or services that are obtained and/or used in contravention of the laws of any country.

THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES, WHETHER EXPRESS, 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 THE 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 (with a new or newly-overhauled replacement product) the product 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.

Online Auction Purchases: Products purchased through online auctions are not eligible for warranty coverage. Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an original or copy of the sales receipt from the original retailer is required. Garmin will not replace missing components from any package purchased through an online auction.

International Purchases: A separate warranty may be provided by international distributors for devices purchased outside the United States depending on the country. If applicable, this warranty is provided by the local in-country distributor and this distributor provides local service for your device. Distributor warranties are only valid in the area of intended distribution. Devices purchased in the United States or Canada must be returned to the Garmin service center in the United Kingdom, the United States, Canada, or Taiwan for service.

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 Romsey, SO40 9RB, U.K. FAX:913/397.0836 Phone:44/ (0) 870.8501241 FAX:44/ (0) 870.850125

GTX 33 Installation Manual 190-00906-00 Page iv Rev. H

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TABLE OF CONTENTS

PARAGRAPH PAGE

Section 1 GENERAL DESCRIPTION .............................................................1-1

1.1 Introduction...................................................................................................................... 1-1

1.2 Equipment Description .................................................................................................... 1-1

1.3 ADS-B Capabilities ......................................................................................................... 1-2

1.4 TIS System Capabilities................................................................................................... 1-4

1.5 Mutual Suppression Pulses .............................................................................................. 1-4

1.6 Interface Summary...........................................................................................................1-5

1.7 Technical Specifications .................................................................................................. 1-6

1.8 Operating Instructions......................................................................................................1-8

1.9 Aircraft Station Licensing Requirements ........................................................................ 1-8

1.10 Certification ................................................................................................................... 1-9

1.11 Operating Instructions.................................................................................................. 1-11

1.12 Reference Documents .................................................................................................. 1-12

Section 2 INSTALLATION OVERVIEW........................................................2-1

2.1 Introduction...................................................................................................................... 2-1

2.2 Installation Materials ....................................................................................................... 2-1

2.3 Installation Considerations .............................................................................................. 2-3

2.4 Cabling and Wiring..........................................................................................................2-5

2.5 Installation Approval Considerations for Pressurized Aircraft........................................ 2-6

2.6 Cooling Air ...................................................................................................................... 2-6

2.7 GTX 33 Mounting Requirements .................................................................................... 2-7

Section 3 INSTALLATION PROCEDURE.....................................................3-1

3.1 Unpacking Unit................................................................................................................ 3-1

3.2 Wiring Harness Installation ............................................................................................. 3-1

3.3 Backshell Assembly......................................................................................................... 3-3

3.4 Weight and Balance ......................................................................................................... 3-5

3.5 Electrical Load Analysis.................................................................................................. 3-5

3.6 Final Installation .............................................................................................................. 3-5

3.7 Post Installation Configuration and Checkout ................................................................. 3-6

3.8 Continued Airworthiness ................................................................................................. 3-8

Section 4 SYSTEM INTERCONNECTS..........................................................4-1

4.1 Pin List............................................................................................................................. 4-1

4.2 Power Functions .............................................................................................................. 4-3

4.3 Temperature Inputs ..........................................................................................................4-4

4.4 Altitude Functions............................................................................................................ 4-4

4.5 Discrete Functions ........................................................................................................... 4-6

4.6 Serial Data Electrical Characteristics .............................................................................. 4-7

190-00906-00 GTX 33 Installation Manual Rev. H Page v

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PARAGRAPH PAGE

4.7 RS-232 Input/Output, Software Update Connections...................................................... 4-9

Appendix A CONSTRUCTION AND VALIDATION OF

STRUCTURES.............................................................................A-1

A.1 Static Test Loading ........................................................................................................ A-1

A.2 Determining Static Load Capability .............................................................................. A-1

Appendix B VERSION 1 ADS-B FIELD APPROVAL COMPLIANCE

MATRIX .......................................................................................B-1

Appendix C OUTLINE AND INSTALLATION DRAWINGS.....................C-1

Appendix D INTERCONNECT DRAWINGS................................................D-1

GTX 33 Installation Manual 190-00906-00 Page vi Rev. H

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LIST OF FIGURES

FIGURE PAGE

Section 1 GENERAL DESCRIPTION .............................................................1-1

Section 2 INSTALLATION OVERVIEW........................................................2-1

Figure 2-1. Antenna Installation Considerations .................................................................. 2-4

Figure 2-2. GTX 33 Modular Rack (115-00438-00) ............................................................ 2-8

Figure 2-3. GTX 33 Stand-Alone Rack (115-00629-00)...................................................... 2-8

Figure 2-4. GTX 33H Stand-Alone Rack (011-02422-00)................................................... 2-9

Figure 2-5. GTX 33 Stand-Alone Rack, Suggested Mounting Locations .......................... 2-10

Section 3 INSTALLATION PROCEDURE.....................................................3-1

Section 4 SYSTEM INTERCONNECTS..........................................................4-1

Figure 4-1. View of J3301 connector from back of unit ...................................................... 4-1

Figure 4-2. GTX 33 Software Update Connections ............................................................. 4-9

Appendix A CONSTRUCTION AND VALIDATION OF

STRUCTURES.............................................................................A-1

Figure A-1. Upward Static Load Test.................................................................................. A-2

Figure A-2. Forward Static Load Test ................................................................................. A-2

Appendix B VERSION 1 ADS-B FIELD APPROVAL COMPLIANCE

MATRIX.......................................................................................B-1

Appendix C OUTLINE AND INSTALLATION DRAWINGS ....................C-1

Figure C-1 GTX 33 in Modular Rack, Outline Drawing......................................................C-1

Figure C-2 GTX 33 G1000 Connector/Rack Assembly Drawing ........................................C-2

Figure C-3 GTX 33 Remote Stand-Alone Rack/Connector Assembly (Sheet 1 of 2) .........C-3

Figure C-3 GTX 33 Remote Stand-Alone Rack/Connector Assembly (Sheet 2 of 2) .........C-4

Figure C-4 GTX 33H Remote Stand-Alone Rack/Connector Assembly (Sheet 1 of 2) ......C-5

Figure C-4 GTX 33H Remote Stand-Alone Rack/Connector Assembly (Sheet 2 of 2) ......C-6

Appendix D INTERCONNECT DRAWINGS ...............................................D-1

Figure D-1 GTX 33 Typical Garmin Integrated Flight Deck Interconnect Wiring

Diagram ................................................................................................................................ D-1

Figure D-2 GTX 33 to GNS 480 (CNX 80) Simplified Interconnect Wiring Diagram ...... D-2

Figure D-3 GTX 33 to MFD, Simplified Interconnect Wiring Diagram............................. D-3

Figure D-4 Dual GTX 33 to GNS 480 (CNX80) Interconnect Wiring Diagram,

Single Altitude Encoder (Sheet 1 of 2)................................................................................. D-4

190-00906-00 GTX 33 Installation Manual Rev. H Page vii

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FIGURE PAGE

Figure D-4 Dual GTX 33 to GNS 480 (CNX80) Interconnect Wiring Diagram,

Single Altitude Encoder (Sheet 2 of 2)................................................................................. D-5

Figure D-5 Dual GTX 33 to GTN 6XX/7XX Interconnect Wiring Diagram, Encoding

Altitude Connections (Sheet 1 of 2) ..................................................................................... D-6

Figure D-5 Dual GTX 33 to GTN 6XX/7XX Interconnect Wiring Diagram, Encoding

Altitude Connections (Sheet 2 of 2) ..................................................................................... D-7

GTX 33 Installation Manual 190-00906-00 Page viii Rev. H

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LIST OF TABLES

TABLE PAGE

Section 1 GENERAL DESCRIPTION .............................................................1-1

Table 1-1 ADS-B Versions................................................................................................... 1-3

Table 1-2. GTX 33 Physical Characteristics ........................................................................ 1-6

Table 1-3. GTX 33 General Specifications .......................................................................... 1-7

Table 1-4. GTX 33 Power Requirements ............................................................................. 1-7

Table 1-5 TSO/ETSO/RTCA/ICAO Compliance ................................................................ 1-9

Table 1-6 TSO/ETSO Deviations ....................................................................................... 1-11

Table 1-7. GTX 33 Reference Documents ......................................................................... 1-12

Section 2 INSTALLATION OVERVIEW........................................................2-1

Table 2-1. GTX 33 Part Numbers......................................................................................... 2-1

Table 2-2. GTX 33 Accessories............................................................................................ 2-2

Table 2-3. GTX 33 Cabling and Wiring ............................................................................... 2-5

Section 3 INSTALLATION PROCEDURE.....................................................3-1

Table 3-1 Pin Contact Part Numbers (High Density) ........................................................... 3-1

Table 3-3. Recommended Crimp Tools................................................................................ 3-2

Table 3-2 Recommended Crimp Tools (High Density)........................................................ 3-2

Table 3-4. Unit Power Loads................................................................................................ 3-5

Section 4 SYSTEM INTERCONNECTS..........................................................4-1

Table 4-1. P3301 Pin List ..................................................................................................... 4-1

Table 4-2. Aircraft Power ..................................................................................................... 4-3

Table 4-3. Temperature Inputs.............................................................................................. 4-4

Table 4-4. Altimeter Inputs................................................................................................... 4-5

Table 4-5. Discrete Outputs .................................................................................................. 4-6

Table 4-6. Discrete Inputs.....................................................................................................4-6

Table 4-7. RS-232 Input/Output ........................................................................................... 4-7

Table 4-8. ARINC 429 Channels.......................................................................................... 4-8

Table 4-9. ARINC Labels..................................................................................................... 4-8

Appendix A CONSTRUCTION AND VALIDATION OF

STRUCTURES ............................................................................A-1

Table A-1. Static Test Load............................................................................................... A-1

Appendix B VERSION 1 ADS-B FIELD APPROVAL COMPLIANCE

MATRIX ......................................................................................B-1

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix ....................................B-2

190-00906-00 GTX 33 Installation Manual Rev. H Page ix

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TABLE PAGE

Appendix C OUTLINE AND INSTALLATION DRAWINGS ....................C-1

Appendix D INTERCONNECT DRAWINGS ...............................................D-1

GTX 33 Installation Manual 190-00906-00 Page x Rev. H

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1 GENERAL DESCRIPTION

NOTE

1.1 Introduction

This manual is intended to provide mechanical and electrical information for use in the planning and design of an installation of the Garmin GTX 33 Mode S Transponder into an aircraft. These versions include all GTX 33, GTX 33D, GTX 33H, and GTX 33DH units with or without Extended Squitter Enabled; as part of a Garmin Integrated Flight Deck. This manual is not a substitute for an approved airframe-specific maintenance manual, installation design drawing, or complete installation data package. Attempting to install equipment by reference to this manual alone and without first planning or designing an installation specific to your aircraft may compromise your safety and is not recommended. The content of this manual assumes use by competent and qualified avionics engineering personnel and/or avionics installation specialists using standard aviation maintenance practices in accordance with Title 14 of the Code of Federal Regulations and other relevant accepted practices. This manual is not intended for use by individuals who do not possess the competencies and abilities set forth above.

Garmin recommends installation of the GTX 33 by a Garmin-authorized installer. To the extent allowable by law, Garmin will not be liable for damages resulting from improper or negligent installation of the GTX 33. For questions, please contact Garmin Aviation Product Support at 1-888-606-5482.

The GTX 33 can also be incorporated as a remote mounted unit in installations with other compatible control/display units such as the Garmin GNS 480 (CNX80), GTN 6XX/7XX, and GMX 200 (MX20) Multifunction Display (MFD).

1.2 Equipment Description

The Garmin GTX 33 rack mounted Mode S Transponder is a radio transmitter and receiver that operates on radar frequencies, receiving ground radar and TCAS interrogations at 1030 MHz and transmitting a coded response of pulses on a frequency of 1090 MHz. The GTX 33 is equipped with IDENT capability that activates the Special Position Identification (SPI) pulse for 18 seconds.

The GTX 33 replies to Mode A, Mode C and Mode S interrogation. Mode A replies consist of framing pulses and any one of 4,096 codes, which differ in the position and number of pulses transmitted. Mode C replies include framing pulses and encoded altitude.

The GTX 33 with Extended Squitter Enabled provides Automatic Dependent Surveillance-Broadcast (ADS-B) technology that 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 the transmission of interrogations for pertinent aircraft information at a slower update rate. ADS-B provides immediate surveillance of air-to-air traffic and aircraft in remote or inhospitable areas not currently covered by radar.

Ground stations can interrogate Mode S Transponders individually using a 24-bit ICAO Mode S address, which is unique to the particular aircraft. In addition, ground stations may interrogate a GTX 33 for its Transponder data capability and the aircraft's Flight ID, which is the registration number or other call sign. The GTX 33 makes the maximum airspeed capability (set during configuration setup) available to TCAS systems on-board nearby aircraft to aid in the determination of TCAS advisories.

The unit features an altitude monitor and TIS traffic advisories. A voice or tone audio output announces altitude and traffic alerts. The GDU Primary Flight Display screen displays the code, reply symbol and mode of operation, depending on equipment connections and configuration selection. The GNS 480

190-00906-00 GTX 33 Installation Manual Rev. H Page 1-1

Page 14

(CNX80), GTN 6XX/7XX, and GMX 200 (MX20) MFD provide similar information with the addition of

NOTE

pressure altitude.

The GTX 33 features multiple transmit/receive ARINC 429 and RS-232 data ports. The unit concentrates data from three ARINC 429 inputs, gray code, RS-232 input data and discrete inputs to the high-speed RS-232 data ports for display on the flight displays. Although multiple output capability is available, the unit is designed to feed all outgoing data via RS-232 data ports. Two RS-232 data ports send and receive data to/from the GIA 63(W) Integrated Avionics Units (IAU), GNS 480 (CNX80), GTN 6XX/7XX, or GMX 200 (MX20) Multifunction Display.

Provision is made for unit software upgrade by means of RS-232 data through rear connector pins. In installations where the transponder interfaces with a GNS 480 (CNX80) or GTN 6XX/7XX the installation of an optional connector is highly recommended. If the optional connector is placed in the aircraft, transponder removal and reinstallation for software upgrade is not required. The software can be changed while the unit is still mounted inside the aircraft.

The GTX 33 meets Mode S Enhanced Surveillance (EHS) requirements. Mode S Enhanced Surveillance is used predominantly in European airspace. It provides information consisting of additional aircraft parameters (see JAA NPA 20-12a) to ground radar systems. Compliance with Enhanced Surveillance may require additional interface between aircraft systems and the GTX 33.

The GTX 33 and GTX 33D differ from the GTX 33H and GTX 33DH in the qualified DO-160 vibration categories. See the GTX 33 Environmental Qualification Form (005-00131-03) for details.

1.3 ADS-B Capabilities

The Extended Squitter Enabled GTX 33 provides the capabilities of Automatic Dependent SurveillanceBroadcast (ADS-B) technology, which improves situational awareness and flight safety. With ADS-B capabilities, position, velocity, and heading information are automatically transmitted to other aircraft and ground stations. The current air traffic control system depends on a transponder request for pertinent aircraft information. ADS-B provides automatic transmission of aircraft information without a request.

RS-232 ADS-B Out from a Garmin 4XX/5XX WAAS, GTN 6XX/7XX with GPS software version 3.20 or later, or a GPS WAAS source that supports ARINC 743A output is required to support ADS-B transmissions.

GTX 33 Installation Manual 190-00906-00 Page 1-2 Rev. H

Page 15

1.3.1 ADS-B Versions

NOTE

There are three distinct ADS-B versions recognized by regulatory authorities. As show in the table below, the Garmin GTX 33 w/ES currently supports ADS-B Out 1090MHz Extended Squitter capability meeting ‘Version 1’ ADS-B or ‘Version 2' ADS-B system requirements depending on software version (see Table 1-1).

GTX 33 w/ES transponders with software version 6.20 or earlier are not compliant with ADS-B version required by the 14 CFR 91.225(a) equipage mandate.

Table 1-1 ADS-B Versions

ADS-B

Version

Version 0 No None Equipment designed to TSO-166 / RTCA DO-260

Version 1 Yes 6.00 - 6.20 Equipment designed to TSO-166a / RTCA DO-260A

Version 2* Yes

*Version required by 2020 ADS-B Out mandate defined in 14 CFR 91.225

GTX 33 w/ES

Compliant

Supported

SW Version

7.01

and later

Regulatory Standard/Minimum Performance

Specification

Equipment designed to TSO-166b / RTCA DO-260B

1.3.1.1 Installation Approval of Version 1 ADS-B Systems

GTX 33 w/ES transponders running software versions v6.00 through v6.20 support Version 1 ADS-B Out functionality. According to AIR-130 Policy Memo ‘Approval for ADS-B Out Systems’, dated August 30, 2010, the FAA has suspended field approvals of Version 2

ADS-B Out equipment. At the time of this publication, there is currently no FAA policy addressing field approvals of Version 0 or Version 1 systems. GTX 33 w/ES transponders with Version 1 ADS-B remain eligible for field approval.

There are three options for installers wanting to install GTX 33 w/ES transponders with software versions

6.00 through 6.20:

1. Installers may elect to disable the ADS-B Extended Squitter function, as described in Section

3.7.1.

2. Installers may utilize a Supplemental Type Certificate (STC) for the GTX 33 with the Version 1 ADS-B Extended Squitter activated.

3. Installers may obtain a field approval with the Version 1 ADS-B Extended Squitter activated. EASA AMC 20-24 compliance matrix provided in Appendix B may be used to assist installers in showing compliance to the AMC requirements. This data together with Form 337 may be used for approval by the appropriate FSDO inspector.

190-00906-00 GTX 33 Installation Manual Rev. H Page 1-3

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1.3.1.2 Installation Approval of Version 2 ADS-B Systems

NOTE

GTX 33 w/ES transponders running software versions v7.01 and later support Version 2 ADS-B Out functionality. According to AIR-130 Policy Memo ‘Approval for ADS-B Out Systems’, dated August 30, 2010, a Supplemental Type Certificate (STC) is required for the approval of Version 2 ADS-B Out equipment.

There are two options for installers wanting to install GTX 33 w/ES transponders running software versions v7.01 and later:

1. Installers may elect to disable the ADS-B Extended Squitter function, as described in Section

3.7.1.

2. Installers must utilize a Supplemental Type Certificate (STC) for the GTX 33 with the Version 2 ADS-B Extended Squitter activated.

It is the installer’s responsibility to ensure the ADS-B Out system is compliant with AC 20-165 and to ensure compatibility between the GTX 33 and the ADS-B Out position source equipment. See Garmin ADS-B Out Compatible Equipment (190-01533-00) for compatible equipment shown to be eligible for 14 CFR 91.227-compliant installations in accordance with AC 20-165

1.4 TIS System Capabilities

Traffic Information Service (TIS) provides a graphic display of traffic advisory information in the cockpit for non-TCAS equipped aircraft.

TIS is a ground-based service providing relative location of all transponder equipped aircraft within a specified service volume. The TIS ground sensor uses real time track reports to generate traffic notification.

Traffic display is available to aircraft equipped with a Mode S data link such as the Garmin GTX 33 transponder. Traffic can then be displayed on a Garmin GDU Primary Flight Display, GMX 200 (MX20) Multifunction Display, GNS 480 (CNX80), GTN 6XX/7XX or other compatible display unit.

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.

1.5 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 is suppressed by an external source and other equipment on board is suppressed by the GTX 33 transponder. This feature is designed to limit mutual interference.

GTX 33 Installation Manual 190-00906-00 Page 1-4 Rev. H

Page 17

1.6 Interface Summary

The GTX 33 provides the following interface connections via the rear connector. See Section 4 and

Appendix D

• 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 (14/28 Vdc)

• Remote power turn on

• Serial airdata or GPS groundspeed input

• Serial altitude input (Reduces wire count vs. parallel wire gray code altimeter interface.)

• Software update input

• Supports 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

• Diversity: GTX 33D is available with the diversity feature

• ARINC 429 input

The GTX 33 P/N 010-00267-() and GTX 33D 010-00294-() support the following list of Comm-B Definition Subfield (BDS) registers:

for connection details.

are exceeded

• 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.

• BDS (4,0) Selected Vertical Intention

• BDS (5,0) Track and Turn Report

• BDS (6,0) Heading and Speed Report

• BDS (0,6) Extended Squitter surface Position

• BDS (0,5) Extended Squitter Airborne Position

• BDS (0,8) Extended Squitter Aircraft Identification and Category

• BDS (0,9) Extended Squitter Airborne Velocity – Subtypes 1 and 3

• BDS (0,A) Extended Squitter Event Driven Data

• BDS (6,1) Emergency/Priority Status

• BDS (6,5) Aircraft operational Status

190-00906-00 GTX 33 Installation Manual Rev. H Page 1-5

Page 18

1.7 Technical Specifications

It is the responsibility of the installing agency to obtain the latest revision of the GTX 33 Environmental Qualification Form. This form is available directly from Garmin under the following part number:

GTX 330/GTX 33/GTX 328/GTX 23 Environmental Qualification Form, Garmin part number 005-00131-03

To obtain a copy of this form, see the dealer/OEM portion of the Garmin web site (www.garmin.com

1.7.1 Physical Characteristics

Table 1-2. GTX 33 Physical Characteristics

Characteristic Specification

Modular Rack Width 1.72 Inches (44 mm)

Modular Rack Height 6.30 Inches (160 mm)

Modular Rack Weight 0.4 lbs. (0.18 kg)

Stand-Alone Rack Width 1.78 Inches (45 mm)

Stand-Alone Rack Height 6.92 Inches (176 mm)

Stand-Alone Rack Weight 0.9 lbs. (0.41 kg)

Stand-Alone H Rack Width 1.77 Inches (45 mm)

Stand-Alone H Rack Height 6.98 Inches (177 mm)

Stand-Alone H Rack Weight 0.7 lbs. (0.29 kg)

Depth Including Connectors (measured from front face of unit to rear of connector backshells)

Depth Including Connectors and Shield Blocks (measured from front face of unit to rear of shield blocks)

11.05 Inches (281 mm)

(Modular and Stand-Alone)

11.44 inches (291 mm)

(Modular and Stand-Alone)

Connecter Weight (including backshell) 0.4 lbs (0.18 kg)

GTX 33 Unit Weight 3.1 lbs. (1.41 kg)

GTX 33D Unit Weight 3.4 lbs. (1.54 kg)

GTX 33H Unit Weight 3.2 lbs. (1.45 kg)

GTX 33DH Unit Weight 3.3 lbs. (1.49 kg)

GTX 33 Installation Manual 190-00906-00 Page 1-6 Rev. H

Page 19

1.7.2 General Specifications

Table 1-3. GTX 33 General Specifications

Characteristic Specification

Regulatory Compliance; GTX 33 w/ES, GTX 33D w/ES

Unit Software

Complex Electronic Hardware

FCC Authorization Emission Designator 12M0M1D

Temperature Range -45°C to +70°C (continuous operation)

Altitude 55,000 Feet

Transmitter Frequency 1090 MHz ±1 MHz

Transmitter Power 125 Watts minimum, 250 Watts nominal

Receiver Frequency 1030 MHz

Receiver Sensitivity -74 dBm nominal for 90% replies

Mode A Capability 4096 Identification Codes

Mode C Capability

RTCA DO-160D, RTCA DO-181C, RTCA DO-260B, EuroCAE ED-102A, EuroCAE ED-73A, EuroCAE ED-73B

RTCA DO-178B Level C/D (refer to Section 1.9.1 for specific applicability)

RTCA/DO-254 Level C (refer to Section 1.9.1 for specific applicability)

100 Foot Increments from -1000 to 62,700 feet.

25 Foot Increments from -1000 to 50,175 feet with suitable serial data altitude.

Mode S Capability Selective Identification Codes, Aircraft Type

External Suppression Input Low ≤ 0.5 V; High ≥ 8 V

External Suppression Output

Audio Output 4.04 Vrms to 7.85 Vrms into a 500 ohm load

Output: minimum is +18V (for 300 ohm load) and maximum of +23V (for 2000 ohm load)

1.7.3 Power Requirements

Table 1-4. GTX 33 Power Requirements

Characteristic Specification

Input Voltage

Power Input 22 Watts Typical, 45 Watts Maximum

Maximum Full TSO Reply Rate; 1200 PRF, Code 7777

Maximum Quiescent 0.85 A @ 27.5 Vdc, 1.1 A @ 13.75 Vdc

14/28 Vdc See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages.

1.6 A @ 27.5 Vdc, 3.1 A @13.75 Vdc

190-00906-00 GTX 33 Installation Manual Rev. H Page 1-7

Page 20

1.8 Aircraft Station Licensing Requirements

CAUTION

NOTE

The Telecommunications Act of 1996, effective February 8, 1996, provides the FCC discretion to eliminate radio station license requirements for aircraft and ships. The GTX 33 installation must comply with current transmitter licensing requirements. To find out the specific details on whether a particular installation is exempt from licensing, please visit the FCC web site http://wireless.fcc.gov/aviation

If an aircraft license is required, make application for a license on FCC form 404, Application for Aircraft Radio Station License. The FCC also has a fax-on-demand service to provide forms by fax. The GTX 33 owner accepts all responsibility for obtaining the proper licensing before using the GTX 33.

The UHF transmitter in this equipment is guaranteed to meet federal communications commission acceptance over the operating temperature range. Modifications not expressly approved by Garmin could invalidate the license and make it unlawful to operate the equipment.

For non-US installations consult the local spectrum management agency for requirements.

GTX 33 Installation Manual 190-00906-00 Page 1-8 Rev. H

Page 21

1.9 Certification

The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft. The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements.

1.9.1 GTX 33 TSO/ETSO/RTCA/ICAO Compliance

Table 1-5 TSO/ETSO/RTCA/ICAO Compliance

Function

Air Traffic Control Radar Beacon System/Mode Select (ATCRBS/MODE S) Airborne Equipment

Traffic Information Service (TIS)

Air Traffic Control Radar Beacon System/Mode Select (ATCRBS/MODE S) Airborne Equipment

Performance Standard

(TSO/ETSO/RTCA/

EUROCAE)

TSO-C112 Class 2A

RTCA DO-239 -

ETSO-2C112a

1.10 Operating Instructions

For operating instructions, see Section 3.7.3 of this document.

Ident Function

Selecting the Ident function sends an ID indication to ATC for 18 seconds. This ID indication distinguishes your transponder from all others on the air traffic controller’s radar screen.

For GX000 installations, refer to the applicable airframe specific pilot’s guide documentation for operating instructions (available at www.garmin.com

190-00906-00 GTX 33 Installation Manual Rev. H Page 1-11

Page 24

1.11 Reference Documents

The following publications are sources of additional information for installing the GTX 33. Before installing the unit, the technician should read all relevant referenced materials along with this manual.

Table 1-7. GTX 33 Reference Documents

Part Number Document

190-00303-00 G1000 System Installation Manual

190-00303-04 G1000 Line Maintenance and Configuration Manual

560-1025-07 MX20 MFD Installation Manual

190-00607-04 GMX 200 Installation Manual

560-0982-01 GNS 480 (CNX80) Installation Manual

190-01004-02 GTN 625/635/650 TSO Installation Manual

190-01007-02 GTN 725/750 TSO Installation Manual

GTX 33 Installation Manual 190-00906-00 Page 1-12 Rev. H

Page 25

2 INSTALLATION OVERVIEW

2.1 Introduction

This section provides hardware equipment information for installing the GTX 33 Mode S Transponder, related hardware and optional accessories. Installation of the GTX 33 should follow the data detailed in this manual. Cabling is fabricated by the installing agency to fit each particular aircraft. The guidance of FAA advisory circulars AC 43.13-1B and AC 43.13-2B, where applicable, may be found useful for making retro-fit installations that comply with FAA regulations.

Refer to the G1000 System Installation Manual, Garmin part number 190-00303-00 for further details on the mechanical aspects of the G1000 system rack. For installation in an aircraft using the remote mounted stand-alone rack refer to Appendix C

2.2 Installation Materials

The GTX 33 is available as a single unit under the following part numbers:

Item Catalog Part Number Diversity

GTX 33, Unit Only, (011-00779-00) 010-00267-00 No

GTX 33 and Install Kit, (011-00779-00) 010-00267-01 No

GTX 33D, Unit Only (011-00779-01) 010-00294-00 Yes

for rack drawings and dimensions.

Table 2-1. GTX 33 Part Numbers

GTX 33D and Install Kit (011-00779-01) 010-00294-01 Yes

GTX 33, Unit Only (011-00779-10) 010-00267-10 No

GTX 33 and Install Kit (011-00779-10) 010-00267-11 No

GTX 33 w/ ES, Unit Only, (011-00779-20) 010-00267-20 No

GTX 33 w/ ES and Install Kit, (011-00779-20) 010-00267-21 No

GTX 33D w/ ES, Unit Only, (011-00779-21) 010-00294-20 Yes

GTX 33D w/ ES and Install Kit, (011-00779-21) 010-00294-21 Yes

GTX 33 w/ ES, Unit Only, (011-00779-30) 010-00267-30 No

GTX 33 w/ ES and Install Kit, (011-00779-30) 010-00267-31 No

GTX 33DH, Unit Only, (011-00779-41) 010-00294-40 Yes

GTX 33DH and Install Kit, (011-00779-41) 010-00294-41 Yes

GTX 33H, Unit Only (011-00779-50) 010-00267-50 No

GTX 33H and Install Kit (011-00779-50) 010-00267-51 No

GTX 33DH w/ ES, Unit Only, (011-00779-61) 010-00294-60 Yes

GTX 33DH w/ ES and Install Kit, (011-00779-61) 010-00294-61 Yes

GTX 33H w/ ES, Unit Only (011-00779-70) 010-00267-70 No

GTX 33H w/ ES and Install Kit (011-00779-70) 010-00267-71 No

190-00906-00 GTX 33 Installation Manual Rev. H Page 2-1

Page 26

2.2.1 Equipment Available

Each of the following accessories is provided separately for the GTX 33 unit. Either rack and the remainder of the accessories is required for installation.

Table 2-2. GTX 33 Accessories

Item Garmin Catalog Part Number

Modular Install Rack, GTX 33/GTX 33D

G1000 Nutplate Kit

GTX 33/GTX 33D Stand-Alone Install Rack

(Alternate Configuration)

GTX 33H/GTX 33DH Stand-Alone Install Rack

Connector Kit, GTX 33 011-01012-01 (Shield Block)

Back-plate Assembly, GTX 33

Back-plate Assembly, w/TNC, GTX 33

Back-plate Assembly, GTX 33D

(For use with GTX 33 and GTX 33D)

(For use with GTX 33H and GTX 33DH)

115-00438-00

011-00915-01 (preferred)

011-01148-01

115-00629-00

011-02422-00

011-00582-00

(For use with GTX 33)

011-00582-04

(For use with GTX 33)

011-00582-01

(For use with GTX 33D)

Back-plate Assembly, w/TNC, GTX 33D

Back-plate Assembly, GTX 33H

Back-plate Assembly, GTX 33DH

Garmin Transponder Antenna kit*

(two required for diversity)

*Note: A transponder antenna approved to TSO C66( ) or C74( ) that has been installed to meet the requirements of this manual may be used with the GTX 33.

011-00582-05

(For use with GTX 33D)

011-00582-02

(For use with GTX 33H)

011-00582-03

(For use with GTX 33DH)

010-10160-00

GTX 33 Installation Manual 190-00906-00 Page 2-2 Rev. H

Page 27

2.2.2 Additional Equipment Required

The following installation accessories are required but not provided:

• Cables – The installer will supply all system cables including circuit breakers. Cable requirements and fabrication is detailed in Section 3 of this manual.

• Hardware – #6-32 x 100° Flathead SS Screw [(MS24693, AN507R or other approved fastener) (4 ea.)] for horizontal mounting of the remote stand-alone rack.

• Hardware – #8-32 Panhead Machine Screw [(MS35206, AN526 or other approved fastener) (4 ea.)] for vertical mounting of the remote stand-alone rack for GTX 33 and GTX 33D.

• Hardware – #8 x 100° Flathead Machine Screw [(see install drawing in Appendix C for more detail) (4 ea.)] for mounting of the remote stand-alone rack for GTX 33H and GTX 33DH.

• Encoding Altitude Digitizer – For GNS 480 (CNX80), GTN 6XX/7XX, and GMX 200 (MX20) installation. Use encoding altimeter manufacturer’s instructions. The Garmin GAE 43 (Garmin P/N 013-00066-00) can provide altitude data in either serial or parallel gray code format.

2.3 Installation Considerations

In a Garmin Integrated Flight Deck, the GTX 33 interfaces with both GIA units. Optional available discrete line interfaces are shown in Section 4.5

2.3.1 Preservation of Previous Systems

It is the installer’s responsibility to preserve the essential characteristic of the aircraft being modified with this equipment to be in accordance with the aircraft manufacturer’s original design. This includes the preservation of multiple power buses, which reduces the probability of interrupting power to essential instruments and avionics.

Discrete Functions.

190-00906-00 GTX 33 Installation Manual Rev. H Page 2-3

Page 28

2.3.2 Antenna Location Considerations

NOTE

Antenna mounting should utilize the aircraft manufacturer’s Type Certificated antenna location and style of antenna. If a second (diversity) antenna is installed in the aircraft, considerations for its mounting should be made as outlined in Figure 2-1 AC 43.12-2A Chapter 3. Note that penetration of the pressure vessel on the pressurized aircraft requires additional data not contained in this manual. (Section 2.5

. The antenna installation should be installed in accordance with

)

Figure 2-1. Antenna Installation Considerations

• The antenna(s) (Garmin P/N 010-010160-00) or equivalent should be mounted away from major protrusions, such as engine(s), propeller(s), and antenna masts. It should also be as far as practical from landing gear doors, access doors, or other openings that could affect the radiation pattern.

• The main antenna should be mounted vertically on the bottom of the aircraft. The optional second (diversity) antenna should be mounted vertically on top of the aircraft. Horizontal separation must be no more than 7.6 meters (25 feet).

• Avoid mounting the antenna within three feet of the ADF sense antenna or any other communication antenna and six feet from the DME antenna.

• To prevent RF interference, the antenna must be physically mounted a minimum distance of three feet from the GTX 33.

If the antenna is being installed on a composite aircraft, sufficient ground plane material must be added. Conductive wire mesh, radials, or thin aluminum sheets embedded in the composite material provide the proper ground plane allowing the antenna gain pattern to be maximized for optimum transponder performance.

GTX 33 Installation Manual 190-00906-00 Page 2-4 Rev. H

Page 29

2.4 Cabling and Wiring

Refer to the interconnect examples in Appendix D for wire gauge guidance.

For special installations that require the use of #18 or #20 AWG wire for power connections, the provided connector kit supplies extended barrel contacts for AWG #18 wire. Special thin-wall heat shrink tubing is also provided to insulate the extended barrels inside the backshell. If using #18 barrel contacts, ensure that no two contacts are mounted directly adjacent to each other. This minimizes the risk of contacts touching and shorting to adjacent pins and to ground. Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference. Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and routing near aircraft control cables.

The GTX 33 and GTX 33D back-plate assemblies utilize BNC-type (bayonet connection) coaxial connectors. The GTX 33H and GTX 33DH back-plate assemblies utilize TNC-type (threaded connection) coaxial connectors.

The following table lists examples of the recommended antenna cable vendors and the type of cable to be used for specific lengths of cable. Any cable meeting specifications is acceptable for the installation.

The maximum coaxial cable attenuation at 1090 MHz must not exceed 1.5 dB, including connectors. In the diversity installation the cable loss characteristics must be the same within ±0.1 dB (cables within 4 inches of the same length will have less than 0.1 dB difference in their loss characteristics).

The following table is for reference only, and lists some suitable cable types, along with the maximum length based on an assumed loss figure of 0.2 dB per connector. Any 50 Ω, double shielded coaxial cable assembly that meets airworthiness requirements and the 1.5 dB maximum loss figure (including connectors) may be used.

Table 2-3. GTX 33 Cabling and Wiring

Max. Length

(feet - [m])

6’ 1.3” [1.86m] 18.0 M17/128-RG400 RG-400

7’ 7.3” [2.32m] 14.45 3C142B

9’ 2.0” [2.79m] 12.00 M17/112-RG304 RG-304

12’ 6.0” [3.81m] 8.80 311601 M17/127-RG393 RG-393

15’ 5.4” [4.71m] 7.12 311501

19’ 9.4” [6.03m] 5.56 311201

30’ 3.6” [9.24m] 3.63 310801

Supplier Information

Insertion loss

(dB/100ft)

Carlisle IT Type MIL-C-17 Type RG Type

Vendor: Carlisle Interconnect Technologies 100 Tensolite Drive St. Augustine, FL 32092 Tel: 800-458-9960 904-829-5600 Fax: 904-829-3447

www.carlisleit.com

See current issue

of Qualified

Products List

QPL-17

RG types are

obsolete and

are shown for

reference only;

replaced by

M17 type numbers.

190-00906-00 GTX 33 Installation Manual Rev. H Page 2-5

Page 30

2.4.1 Cable Routing Considerations

When routing antenna cables, observe the following precautions:

• All cable routing should be kept as short and as direct as possible

• Avoid sharp bends

• Avoid routing cables near power sources (e.g., 400 Hz generators, trim motors, etc.) or near power for fluorescent lighting

• Avoid routing antenna cables near ADF antenna cable (allow at least a 12-inch separation)

2.5 Installation Approval Considerations for Pressurized Aircraft

Antenna and cable installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such installations incorporate alteration (penetration) of the cabin pressure vessel by connector holes and/or mounting arrangements. Use of existing bulkhead connectors previously approved by other means is permissible without additional approval.

For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations, it is recommended that the installer proceed according to any of the following listed options:

1. Obtain approved antenna installation design data from the aircraft manufacturer.

2. Obtain an FAA approved Supplemental Type Certificate (STC) pertaining to and valid for the subject antenna installation.

3. Contact the FAA Aircraft Certification Office in the appropriate Region and request identification of FAA Designated Engineering Representatives (DERs) who are authorized to prepare and approve the required antenna installation engineering data.

4. Obtain FAA Advisory Circular AC-183C and select (and contact) a DER from the roster of individuals identified thereunder.

5. Contact an aviation industry organization such as the Aircraft Electronics Association and request their assistance.

2.6 Cooling Air

Refer to the G1000 System Installation manual, Garmin part number 190-00303-00, for information on cooling requirements. For remote mounted units, forced air cooling is not required. However, the application of forced air cooling is recommended to provide beneficial cooling if the unit is located in a confined space or near a source of heat.

A 5/8 inch air fitting is provided on the rear of the backplate for the purpose of admitting cooling air under such conditions. If a form of forced air cooling is installed, make certain that rainwater or condensation cannot enter and be sprayed on the equipment.

GTX 33 Installation Manual 190-00906-00 Page 2-6 Rev. H

Page 31

2.7 GTX 33 Mounting Requirements

The GTX 33 mounting surface must be capable of providing structural support and electrical bond to the aircraft to minimize radiated EMI and provide protection from High-Intensity Radiation Fields (HIRF). The GTX 33 and GTX 33D can be mounted using the G1000 main system rack, or may be mounted remotely if desired. Figure 2-2 system rack using the nutplate kit listed in Section 2.2.1 Assembly Drawing, for nutplate placement locations. The installer must provide any additional remote mounting equipment.

2.7.1 Remote Mounted Stand-Alone Rack Considerations

shows the GTX 33 G1000 unit rack. The unit rack is fastened to the main

. Refer to Figure C-2, GTX 33 Connector/Rack

Figure 2-3

racks can be installed in a variety of locations, such as the electronics bay, under a seat or on an avionics shelf behind the rear baggage area. Refer to Figure 2-5 between the GTX 33 and any obstruction. Install the rack in accordance with AC 43.13-2B Chapter 2 “Communication, Navigation, and Emergency Locator Transmitter System Installations”. The rack should be mounted to a surface known to have sufficient structural integrity to withstand additional inertia forces imposed by a 4.3-pound (1.95 kg) GTX 33 unit, rack, and connectors (see Section 1.7.1 information). If it is necessary to build a shelf or bracket to mount the GTX 33 stand-alone rack or it is not certain that the chosen location is of sufficient structural integrity, refer to Appendix A for validation of rack mounting structures and determining static load capability.

Figure C-3

vertically using four 8-32 pan head screws (MS35206, AN526 or other approved fastener). It can also be mounted horizontally using four 6-32 100° counter-sunk flathead screws (MS24693, AN507R or other approved fastener). Ensure that the GTX 33 chassis has a ground path to the airframe by having at least one mounting screw in contact with the airframe. If more water-resistance is desired, the rack should be installed in the upright vertical orientation only, otherwise, the rack may be mounted in either vertical or horizontal orientation.

Figure 2-4

the stand-alone rack dimensions for the GTX 33H and GTX 33DH. The rack can be mounted in any orientation using screws as defined in Section 2.2.2 the airframe by having at least one mounting screw in contact with the airframe. If more water-resistance is desired, the rack should be installed in the upright vertical orientation only, otherwise, the rack may be mounted in either vertical or horizontal orientation.

, Figure C-3, and Figure C-4show the GTX 33 remote mounted stand-alone racks. The remote

for suggested location. Leave sufficient clearance

for weight

gives the stand-alone rack dimensions for the GTX 33 and GTX 33D. The rack can be mounted

shows the stand-alone rack used for GTX 33H and GTX 33DH installations. Figure C-4 gives

. Ensure that the GTX 33 chassis has a ground path to

After the cable assemblies are made and wiring installed to the rack back plate, route wiring bundle as appropriate. Use cable ties to secure the cable assemblies and coax to provide strain relief for the cable assemblies.

190-00906-00 GTX 33 Installation Manual Rev. H Page 2-7

Page 32

Figure 2-2. GTX 33 Modular Rack (115-00438-00)

Figure 2-3. GTX 33 Stand-Alone Rack (115-00629-00)

GTX 33 Installation Manual 190-00906-00 Page 2-8 Rev. H

Page 33

Figure 2-4. GTX 33H Stand-Alone Rack (011-02422-00)

190-00906-00 GTX 33 Installation Manual Rev. H Page 2-9

Page 34

Figure 2-5. GTX 33 Stand-Alone Rack, Suggested Mounting Locations

GTX 33 Installation Manual 190-00906-00 Page 2-10 Rev. H

Page 35

3 INSTALLATION PROCEDURE

CAUTION

3.1 Unpacking Unit

Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment. If the unit is damaged, notify the carrier and file a claim. To justify a claim, save the original shipping container and all packing materials. Do not return the unit to Garmin until the carrier has authorized the claim.

Retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement.

3.2 Wiring Harness Installation

Allow adequate space for installation of cables and connectors. The installer shall supply and fabricate all cables. All electrical connections to the GTX 33 are made through one 62-pin D-subminiature connector. Section 4 defines the electrical characteristics of all input and output signals. Required connectors and associated hardware are supplied with the connector kit.

See Appendix D

for examples of interconnect wiring diagrams. Construct the actual harnesses in

accordance with the aircraft manufacturer authorized interconnect standards.

Check wiring connections for errors before inserting the GTX 33 into the rack. Incorrect wiring could cause internal component damage.

Table 3-1 Pin Contact Part Numbers (High Density)

Manufacturer*

18-20 AWG (Power Only) 22-28 AWG

Garmin P/N 336-00044-00 336-00021-00

Military P/N N/A M39029/58-360

*Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.

62 pin connector (P3301)

190-00906-00 GTX 33 Installation Manual Rev. H Page 3-1

Page 36

Table 3-2 Recommended Crimp Tools (High Density)

18-20 AWG 22-28 AWG

Manufacturer

(note 1)

Military P/N M22520/2-01 N/A M81969/1-04 M22520/2-09 M81969/1-04

Positronic 9507-0 9502-11 M81969/1-04 9502-4 M81969/1-04

AMP 601966-1 N/A 91067-1 601966-6 91067-1

Daniels AFM8 K774 M81969/1-04 K42 M81969/1-04

Astro 615717 N/A M81969/1-04 615725 M81969/1-04

1) Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.

2) Extracting the #18 or #20 contact requires that the expanded wire barrel be cut off from the contact. It may also be necessary to push the pin out from the face of the connector when using an extractor due to the absence of the wire. A new contact must be used when reassembling the connector.

Hand Crimp-

ing Tool

Positioner

Insertion/

Extraction Tool

(note 2)

Positioner

Insertion/

Extraction

Tool

Table 3-3. Recommended Crimp Tools

18-20 AWG 22-28 AWG

Manufacturer

(Note 1)

Military P/N M22520/2-01 N/A M81969/1-04 M22520/2-09 M81969/1-04

Positronic 9507 9502-11 M81969/1-04 9502-3 M81969/1-04

AMP 601966-1 N/A 91067-1 601966-6 91067-1

Daniels AFM8 K774 M81969/1-04 K42 M81969/1-04

Astro 615717 N/A M81969/1-04 615725 M81969/1-04

Hand

Crimping Tool

Positioner

(Note 3)

Insertion/

Extraction Tool

(Note 2)

Positioner

Insertion/

Extraction

Tool

NOTES

1. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice.

2. Extracting the 18 AWG contacts requires that the expanded wire barrel be cut off from the contact. It may also be necessary to push the pin out from the face of the connector when using an extractor due to the absence of the wire. A new contact must be used when reassembling the connector.

GTX 33 Installation Manual 190-00906-00 Page 3-2 Rev. H

Page 37

3.3 Backshell Assembly

NOTE

The GTX 33 connector kit includes one Garmin backshell assembly. Garmin’s backshells give the installer the ability to quickly and easily terminate shield grounds at the backshell housing using one of two methods available (SPIDER or Shield Block).

The SPIDER grounding method is permitted for previous installations, however Garmin recommends the use of the Shield Block grounding method for all new installations.

G1000 Installations:

To assemble the backshell and grounding system, refer to the instructions provided in the G1000 System Installation Manual (190-00303-00), as well as the SPIDER Installation Instructions (190-00313-03) and Shield Block Installation Instructions (190-00313-09).

Non-G1000 Installations:

GTX 33 installations mounted as a remote transponder system, the connector and backshell assembly is shown below. Refer to the SPIDER Installation Instructions (190-00313-02) and Shield Block Installation Instructions (190-00313-09) for grounding instructions.

1. Backshell Cast Housing. Provides a mounting point for connector accessories.

2. D-Subminiature 62 pin connector.

3. Ground System (SPIDER ground shown). Allows shield grounds to be made to the backshell housing.

4. Strain Relief Tab. Fastens wiring bundle to housing.

190-00906-00 GTX 33 Installation Manual Rev. H Page 3-3

Page 38

5. Backshell Lid. Provides access when servicing the connector.

Figure 3-1. Backshell Connector Assembly

(Top: Exploded View. Bottom: Assembled.)

GTX 33 Installation Manual 190-00906-00 Page 3-4 Rev. H

Page 39

3.4 Weight and Balance

CAUTION

Weight and balance computation is required after the installation of the GTX 33. Follow the guidelines as established in AC 43.13-1B, Chapter 10, Section 2. Make appropriate entries in the equipment list indicating items added, removed or relocated along with the date accomplished. Include your name and certificate number in the aircraft records. Section 1.7.1 and Figure C-1 in Appendix C shows the center of gravity.

identifies the weight of the new GTX 33 equipment

3.5 Electrical Load Analysis

An electrical load analysis should be completed on each aircraft prior to installation in accordance with AC43.13-1B, Chapter 11. Use the following values for computation:

Table 3-4. Unit Power Loads

GTX 33 Input

Typical Max. Typical Max.

GTX 33 Main Power 1.6 A 3.1 A 0.85 A 1.6 A

14 VDC 28 VDC

3.6 Final Installation

For final installation and assembly, refer to the outline and installation drawings shown in Appendix C of this manual.

1. Assemble the connector backshell as described in Section 3.3

2. Attach the connector to the rear plate using the screws provided in the connector kit.

3. Mount the unit rack to the main system rack or other suitable mounting location using the provided nutplates or installer supplied screws.

4. Assemble the rear plate into the GTX 33 unit rack using screws provided with the rear plate.

5. Insert the GTX 33 into the rack, noting proper orientation as shown on the installation drawing in Appendix C.

Do not use excessive force when inserting the GTX 33 into the rack. This may cause damage to occur to the connectors, unit, and/or unit rack. If heavy resistance is felt during installation, stop! Remove the GTX 33 and identify the source of resistance.

190-00906-00 GTX 33 Installation Manual Rev. H Page 3-5

6. GTX 33/33D Only: Lock the GTX 33/33D in place using the lever-locking handle. Fasten the handle to the GTX 33/33D body using the provided Phillips screw. (Note that some early GTX 33/ 33D units use a D-ring ¼-turn fastener)

Start the handle screw into the hole carefully, to avoid cross-threading. Do not apply torque in excess of 14 in-lbs to the handle screw. The application of torque exceeding 14 in-lbs to the screw will damage the LRU case and/or retaining hardware.

7. GTX 33H/33DH Only: Lock the GTX 33H/33DH in place using the install screw. Tighten the screw until the connectors are fully mated and the retaining wedge in the rack is fully mated with the wedge attached to the unit. Tighten to the torque specification shown in Appendix C

Page 40

3.7 Post Installation Configuration and Checkout

NOTE

The GTX 33 Mode S Transponder will not provide valid outputs until the aircraft post installation configuration procedures are completed.

3.7.1 Configuration

When installed as part of the Garmin Integrated Flight Deck, the GTX 33 transponder must have FAA approved configuration data. Configuration data is loaded to the GTX 33 from an aircraft-specific Software Loader Card. Transponder settings are predetermined for a specific aircraft and are typically contained within the file named ‘GTX1’. However, the aircraft registration number must be entered manually.

The PFD serves as the graphics user interface to the installer configuring the system. For basic configuration information, refer to the G1000 Line Maintenance and Configuration Manual, Garmin part number 190-00303-04. For actual aircraft installation/checkout, use only aircraft manufacturer approved checkout procedures.

Verify proper operation of the transponder by testing in accordance with Appendix F to 14 CFR Part 43 – ATC Transponder Tests and Inspections.

For transponder installations operating with a Garmin GNS 480 (CNX80), refer to GNS 480 (CNX80) Installation Manual, 560-0982-01 for configuration procedures and operation checks.

For transponder installations operating with a Garmin GTN 6XX/7XX, refer to the GTN 625/635/650 TSO Installation Manual (190-01004-02) or the GTN 725/750 TSO Installation Manual (190-01007-02) for configuration procedures and operation checks.

3.7.2 Interference Check

Turn on and verify operation of all avionics equipment except GTX 33. Then power GTX 33 on and verify there is no interference with any other equipment in the aircraft. The operation/performance checks should be made with all other avionics turned on. Verify that there is no interference during any mode of transponder operation.

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3.7.3 Operation/Performance Checkout

CAUTION

If the unit is removed from the aircraft and operated, always connect J3302, (and J3303 for GTX 33D) to an antenna or a 50 Ω, 5-Watt load. The GTX 33 transmits Mode S acquisition squitter replies about once per second whether interrogations are received or not.

Verify proper operation of the transponder by testing as specified in Appendix F of 14 CFR, Part 43, to AC 43-6B, and/or other appropriate regulations. The test is typically done as a ramp test using a transponder ramp test set, such as the TIC TR-220, IFR ATC-601 or other suitable Mode S transponder test set.

Self Test

Verify that the unit does not display a failure indication when turned on.

Altitude Input

Verify that the displayed altitude matches pressure altitude (at 29.92).

External Inputs

If the external ident or standby inputs are connected, verify operation by:

a) Verify that the unit goes to standby when the external standby input is pulled low.

b) Verify that the ident indication turns on when the external ident button is pressed (must be in

the “ON” or “ALT” modes.

3.7.4 Performance (Ramp) Test

After installation, the transponder should be tested as specified in 14 CFR Part 43 Appendix F, AC 43-6B, and other appropriate regulations. The test is typically done as a ramp test using a transponder ramp test set, such as the IFR ATC-601A. The ramp test includes checks as follows:

Reference Part 43 Appendix F:

a) Reply Frequency

b) Suppression

c) Receiver Sensitivity

d) Reply RF Output Power

e) Mode S Diversity Channel Isolation (if applicable)

f) Mode S Address

g) Mode S Formats

h) Mode S All-Call

i) ATCRBS - Only All Call

j) Squitter

Reference AC 43-6B and 14 CFR Part 43, Appendix E (c):

Altitude Reporting

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3.8 Continued Airworthiness

Test according to Title 14 CFR §§ 91.411 and 91.413 as well as Part 43 Appendix F. Other than for regulatory checks, maintenance of the GTX 33 is ‘on condition’ only.

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4 SYSTEM INTERCONNECTS

4.1 Pin List

4.1.1 P3301 Connector

Figure 4-1. View of J3301 connector from back of unit

Table 4-1. P3301 Pin List

Pin Pin Name I/O

1 RESERVED In

2 ALTITUDE A1 In

3 ALTITUDE C2 In

4 ALTITUDE A2 In

5 ALTITUDE A4 In

6 ALTITUDE C4 In

7 ALTITUDE B1 In

8 ALTITUDE C1 In

9 ALTITUDE B2 In

10 ALTITUDE B4 In

11 ALTITUDE D4 In

12 EXTERNAL IDENT SELECT* In

13 EXTERNAL STANDBY SELECT* In

14 NOT USED In

15 AUDIO OUT HI Out

16 AUDIO OUT LO Out

17 SQUAT SWITCH IN In

18 RESERVED --

19 ALTITUDE ALERT ANNUNCIATE* Out

20 RESERVED --

21 AIRCRAFT POWER 1 In

*Indicates Active Low (Ground to activate)

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Table 4-1. P3301 Pin List

Pin Pin Name I/O

22 RS-232 IN 1 In

23 RS-232 OUT 1 Out

24 RS-232 IN 2 In

25 RS-232 OUT 2 Out

26 ARINC 429 IN 3 A In

27 POWER GROUND --

28 ARINC 429 OUT 2 B Out

29 ARINC 429 IN 3 B In

30 ARINC 429 OUT 2 A Out

31 EXTERNAL SUPPRESSION I/O I/O

32 ARINC 429 IN 1 A In

33 ARINC 429 IN 2 A In

34 ARINC 429 OUT 1 B Out

35 ARINC 429 IN 1 B In

36 ARINC 429 IN 2 B In

37 ARINC 429 OUT 1 A Out

38 RESERVED --

39 RESERVED --

40 SPARE --

41 CURRENT TEMPERATURE PROBE OUT Out

42 AIRCRAFT POWER 1 In

43 POWER GROUND --

44 CURRENT TEMPERATURE PROBE IN In

45 NOT USED In

46 TIS CONNECT SELECT* In

47 AUDIO MUTE SELECT* In

48 ARINC 429 IN 4 A In

49 ARINC 429 IN 4 B In

50 ALTITUDE COMMON (GROUND) In

51 SIGNAL GROUND --

52 RESERVED --

*Indicates Active Low (Ground to activate)

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Table 4-1. P3301 Pin List

Pin Pin Name I/O

53 RESERVED --

54 XPDR REMOTE POWER OFF In

55 NOT USED --

56 AIRCRAFT POWER 2 In

57 NOT USED --

58 SIGNAL GROUND --

59 NOT USED --

60 AIRCRAFT POWER 2 In

61 NOT USED --

62 SWITCHED POWER OUT Out

*Indicates Active Low (Ground to activate)

4.2 Power Functions

Power Input requirements are listed in the following tables. The power-input pins accept 14/28 Vdc. Switched Power Out is a power source available for devices such as a remote digital altitude encoder. Refer to Figure D-1

and Figure D-2 for power interconnections.

4.2.1 Aircraft Power

Table 4-2. Aircraft Power

Pin Name Connector Pin I/O

AIRCRAFT POWER 1 P3301 21 In

AIRCRAFT POWER 1 P3301 42 In

AIRCRAFT POWER 2 P3301 56 In

AIRCRAFT POWER 2 P3301 60 In

SWITCHED POWER OUT P3301 62 Out

XPDR REMOTE POWER OFF P3301 54 In

POWER GROUND P3301 27 --

POWER GROUND P3301 43 --

SIGNAL GROUND P3301 51 --

SIGNAL GROUND P3301 58 --

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4.3 Temperature Inputs

NOTE

Temperature function with pin assignments are shown for reference since the temperature function is available in the GTX 33. In the Garmin Integrated Flight Deck system, temperature data is received from the GIA 63 in RS-232 format.

Table 4-3. Temperature Inputs

Pin Name Connector Pin I/O

CURRENT TEMPERATURE PROBE OUT P3301 41 Out

CURRENT TEMPERATURE PROBE IN P3301 44 In

Temperature function is provided for the external display system via input to the GTX 33 transponder. The Temperature input is used for Outside Air Temperature (OAT) display and Density Altitude computations. The type of temperature probe required is a current sensor type, such as a Garmin GTP 59 or an AD590-KH or AD592 made by Analog Devices. The GTX 33 is not configurable for different types of temperature sensors. The temperature-input specification is 1 micro amp per degree Kelvin (1 uA/°K).

4.4 Altitude Functions

Altitude functions with pin assignments are shown for reference since the altitude function is available in the GTX 33. In the Garmin Integrated Flight Deck system, altitude data is received from the GIA 63 in RS-232 format.

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 11-33 Vdc.

The GTX 33 contains internal altitude code line isolation diodes to prevent the unit from pulling the encoder lines to ground when the transponder is turned off.

If two separate altitude encoders are connected to the GTX 33, one providing parallel gray code and the other, serial data, the unit selects only one for use at a time, with serial data input receiving the highest priority.

For altitude encoders that can be connected in both serial data and parallel gray code format, such as the Garmin GAE 43 (Garmin P/N 013-00066-00), select one or the other but not both wiring connections.

When connecting two GTX 33 transdponders to a Garmin GNS 480 (CNX80), the unit can only receive serial data from one transponder at a time. Use a DPDT switch to connect both serial data and External Standby Select. Refer to Figure D-4

Among the surveillance items the Mode S transponder will transmit to the ground stations and other aircraft are altitude reporting in 25-foot increments with the proper encoder. In order to report altitude in 25-foot increments the GTX 33 must receive altitude from suitable altitude reporting devices through serial input connections. Altitude input to the GTX 33 received from parallel wire gray code encoders is supplied to the unit in 100-foot increments and thus reported in 100-foot increments.

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4.4.1 Altimeter Inputs

Table 4-4. Altimeter Inputs

Pin Name Connector Pin I/O

ALTITUDE D4 P3301 11 In

ALTITUDE A1 P3301 2 In

ALTITUDE A2 P3301 4 In

ALTITUDE A4 P3301 5 In

ALTITUDE B1 P3301 7 In

ALTITUDE B2 P3301 9 In

ALTITUDE B4 P3301 10 In

ALTITUDE C1 P3301 8 In

ALTITUDE C2 P3301 3 In

ALTITUDE C4 P3301 6 In

ALTITUDE COMMON P3301 50 --

4.4.2 Altimeter Interconnect, Dual GTX 33 Installation

For complete dual installation in which digital altitude encoders are connected to the GTX 33, it is best to install two digital sources, connecting one encoder to each transponder.

4.4.3 Altimeter Selection Priority

When connecting the transponder to a GNS 480 (CNX80) or GTN 6XX/7XX the installer must be aware of the GTX 33 priority for selecting encoded altimeter interconnections. The GTX 33 searches in this sequence for altitude, and stops when it finds a valid pressure altitude input.

Altitude reporting equipment order of precedence:

1. ARINC 429 Air Data Computer (label 203, if configured W/ALT) (25’)

2. ARINC 429 EFIS (label 203, if configured W/ALT) (25’)

3. RS-232 data from GNS 480 (CNX80), GTN 6XX/7XX, or Garmin Integrated Flight Deck (25')

4. RS-232 Fuel/Air Data Computer (if configured W/ALT.) (25’)

5. Shadin Altitude Serializer/Encoder (if configured for 25’)

6. Icarus Altitude Serializer/Encoder (if configured for 25’)

7. Parallel wire Gray Code input (100’)

8. Shadin Altitude Serializer/Encoder (if configured for 100’)

9. Icarus Altitude Serializer/Encoder (if configured for 100’)

Only approved devices may provide altitude to the GTX 33 in accordance with 14 CFR 91.217. In addition, all altitude reporting devices installed in the aircraft must meet certification requirements of 14 CFR 91.413. The installer must select an altitude reporting device that is a certified altitude source for the particular aircraft.

It is the installing agency’s responsibility to determine that the installed encoder is compatible with the selected altitude reporting criteria, either 100’ or 25’. Refer to the GNS 480 (CNX80) Installation Manual or the appropriate GTN 6XX/7XX Installation Manual for the altitude data reporting configuration.

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4.5 Discrete Functions

Discrete functions with pin assignments are shown for reference since the functions are available in the GTX 33. External suppression should be connected if another transponder or DME is installed in the aircraft avionics system. Depending on system configuration, the Garmin Integrated Flight Deck may not use these inputs, as many functions are received from the GIA 63 in RS-232 format.

4.5.1 Discrete Outputs

External suppression should be connected if a DME is installed in the aircraft avionics system. The GTX 33 suppression I/O pulses may not be compatible with all models of DME. Known incompatible units include the Bendix/King KN 62, KN 64 and KNS 80. These models have an output-only suppression port and can be damaged by the GTX 33 mutual suppression output. In this case, leave the suppression pin open.

Table 4-5. Discrete Outputs

Pin Name Connector Pin I/O

ALTITUDE ALERT ANNUNCIATE* P3301 19 Out

EXTERNAL SUPPRESSION I/O (TXP/DME) P3301 31 I/O

SIGNAL GROUND P3301 51 --

SIGNAL GROUND P3301 58 --

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

4.5.2 DISCRETE INPUTS

Table 4-6. Discrete Inputs

Pin Name Connector Pin I/O

EXTERNAL IDENT SELECT* P3301 12 In

EXTERNAL STANDBY SELECT* P3301 13 In

SQUAT SWITCH IN P3301 17 In

TIS CONNECT SELECT* P3301 46 In

AUDIO MUTE SELECT* P3301 47 In

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

EXTERNAL IDENT SELECT (remote IDENT) is a momentary input. Refer to the GNS 480 (CNX80) or the appropriate GTN 6XX/7XX Installation Manual for remote ident configuration.

EXTERNAL STANDBY SELECT (remote STANDBY) is used when two GTX 33 systems are installed in an aircraft. Refer to Figure D-4, for the EXTERNAL STANDBY SELECT interconnect. When

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EXTERNAL STANDBY SELECT is grounded, ARINC 429 OUT PORT 1 remains active, while PORT 2 is inactive.

When TIS is inactive, the GTX 33 logs onto TIS service when a momentary ground is applied to P3301-46. When TIS is active, a momentary ground logs off of TIS service. Refer to the GNS 480 (CNX80) Installation Manual, MX20 Installation Manual, or appropriate GTN 6XX/7XX Installation Manual for TIS configuration.

An AUDIO MUTE SELECT mute switch may be used to control TIS audio alerts. TIS (Traffic) Mute must be clearly marked with MUTE ON/MUTE OFF or TIS Audio ON/Audio OFF labels. The muting feature may be enabled through a Multi-Function display. In order to prevent inadvertent muting, the status of muting must default to "Mute off" upon each power cycle. Refer to the GNS 480 (CNX80) Installation Manual or appropriate GTN 6XX/7XX Installation Manual for AUDIO configuration.

4.6 Serial Data Electrical Characteristics

The GTX 33 manages support for several equipment interfaces. The GTX 33 can be configured to include GPS, Airdata, AHRS, EFIS/Airdata, and ADLP 429 inputs, functioning as an ARINC 429 data concentrator.

The GTX 33 has four ARINC 429 input ports, making it capable of taking altitude, air data, heading, EFIS selected course and possible future features, and then concentrating it on the ARINC 429 OUT 2 ports for possible data link applications.

The GTX 33 is designed to feed all outgoing data to the external display via RS-232 data ports.

4.6.1 RS-232 Input/Output

Table 4-7. RS-232 Input/Output

Pin Name Connector Pin I/O

RS-232 OUT 1 P3301 23 Out

RS-232 IN 1 P3301 22 In

RS-232 OUT 2 P3301 25 Out

RS-232 IN 2 P3301 24 In

SIGNAL GROUND P3301 51 --

SIGNAL GROUND P3301 58 --

The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ±5 V when driving a standard RS-232 load. Refer to figures in Appendix D

for the RS-232 serial data

interconnect.

When connecting two GTX 33 transponders to a GPS, the unit can only receive RS-232 serial data from one unit at a time. Use a DPDT switch for connecting both serial data and External Standby Select. Refer to Figure D-4

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4.6.2 ARINC 429 Input/Output

Table 4-8. ARINC 429 Channels

Pin Name Connector Pin I/O

ARINC 429 OUT 1A P3301 37 Out

ARINC 429 OUT 1B P3301 34 Out

ARINC 429 IN 1A P3301 32 In

ARINC 429 IN 1B P3301 35 In

ARINC 429 IN 2A P3301 33 In

ARINC 429 IN 2B P3301 36 In

ARINC 429 OUT 2A P3301 30 Out

ARINC 429 OUT 2B P3301 28 Out

ARINC 429 IN 3A P3301 26 In

ARINC 429 IN 3B P3301 29 In

ARINC 429 IN 4A P3301 48 In

ARINC 429 IN 4B P3301 49 In

SIGNAL GROUND P3301 51 --

SIGNAL GROUND P3301 58 --

The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to five standard ARINC 429 receivers.

The following data is sent out at specified intervals using high speed ARINC 429 (100 kHz). The transmit data labels and their rates are as follows:

Table 4-9. ARINC Labels

Label Data Rate

100 Selected Course (degrees) 200 ms

203 Pressure Altitude [in feet set to 29.92” Hg (1013.25 mb)] 100 ms

204 Barometric Corrected Altitude (feet) 100 ms

206 Indicated Air Speed (knots) 100 ms

210 True Air Speed (knots) 100 ms

211 Total Air Temperature (degrees) 100 ms

213 Static Air Temperature (degrees) 100 ms

306 Joystick Lat 500 ms

307 Joystick Lon 500 ms

314 True Heading 100 ms

320 Magnetic Heading (Degrees) 100 ms

371 GA Equipment Identifier 500 ms

377 Equipment Identifier 500 ms

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4.7 RS-232 Input/Output, Software Update Connections

NOTE

CAUTION

When the GTX 33 is installed in a system other than a Garmin Integrated Flight Deck an optional RS-232 serial data connector should be installed in the aircraft for future software upgrades, negating the need to remove the transponder from the aircraft. The connector can be mounted anywhere convenient for access, such as under the instrument panel, on a remote avionics shelf next to the unit or in the instrument panel itself. Be sure to label the connector for Software Update. Do not include the Test Mode Select switch in the aircraft. See Figure 4-2

If the GTX 33 installation interfaces with a GNS 480 (CNX80) in the aircraft, the GNS 480 (CNX80) must be turned off during GTX 33 software upload, due to loading of RS-232 port 1.

The installation of an optional software upgrade connector is highly recommended. If the connector is wired in the aircraft, transponder removal and reinstallation for software upgrade is not required.

for software update connections.

Beginning with software version 3.06, the GTX 33 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.

Figure 4-2. GTX 33 Software Update Connections

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APPENDIX A CONSTRUCTION AND VALIDATION OF STRUCTURES

A.1 Static Test Loading

This appendix includes information necessary for testing load-carrying capabilities of equipment mounting structures, such as shelves, mounting plates and mounting brackets, used to mount the GTX 33 remote mounting tray.

Baggage compartments and cabins or cockpit floors are good mounting platforms providing the floor attachments meet the strength requirements. If support racks, brackets or shelves need to be fabricated, they should be fabricated and attached to the aircraft structure in accordance with the methods outlined in AC 43.13-2B Chapter 2. After the structure is installed, it should be tested as outlined in AC 43.13-2B Chapter 1 to verify that it is capable of supporting the required loads.

The GTX 33 installation must be capable of withstanding the Ultimate Load Factors listed in Table A-1 for at least 3 seconds in each direction specified without damage or permanent deformation. Note that these required loads differ somewhat from those normally required for equipment installations.

Since the combined weight of the GTX 33 and its equipment mounting rack and connector is 4.3 lbs, the static loads which must be applied (Load Factor x 4.3 lbs.) will be as follows:

Table A-1. Static Test Load

Direction of Force Load Factor

DOWNWARD 6.6 G (6.6 x 4.3) = 28.4 lbs

UPWARD 6.0 G (6.0 x 4.3) = 25.8 lbs

SIDEWAYS 4.5 G (4.5 x 4.3) = 19.4 lbs

FORWARD 18.0 G (18.0 x 4.3) = 77.4 lbs

(Load Factor x GTX 33 weight)

Static Test Load

A.2 Determining Static Load Capability

A recommended method of determining the static load capability is as follows:

1. Mark and drill the holes where the GTX 33 equipment rack will be mounted.

2. Install four 8-32 machine screws (MS35206, AN526 or other approved fastener) in the four holes which will be used to mount the GTX 33 equipment rack using washers, nuts and nutplates to mount the equipment rack to the mounting surface. Note that some means of locking fastener must be used, e.g. either lock nuts or steel nuts with lock washers.

3. For testing downward loading, place shot bags or other suitable weights totaling 28.4 pounds within the footprint outlined by the four screw holes (assuming the mounting surface is horizontal) or use a calibrated force gauge at the location of the center of gravity when the unit is mounted.

4. Verify there is no damage or permanent deformation of the structure after 3 seconds.

5. Fasten a 36 inch loop of suitable material such as fishing line, braided wire, or other similar material having a breaking strength of at least 100 lbs., diagonally between two of the screws. Then fasten another loop diagonally between the other two screws, adjusting the length of the loop so it exactly matches the first.

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6. Hook a calibrated force gauge through both loops and apply a sustained pull for at least 3 seconds in each of the other three directions (upward, sideward and forward) at the above calculated forces (i.e. 25.8 lb. upward, 19.4 lb. sideward and 77.4 lb. forward).

7. Examine the support structure carefully. If there has been damage or permanent deformation, the structure is not suitable and must be replaced with one that is strong enough to withstand the test loads. Examine all aircraft stringers, bulkheads and skin surfaces, which may have direct or indirect contact with the fabricated shelf. If it is determined that no damage or permanent deformation has occurred, the structure is of sufficient strength and the GTX 33 equipment rack may be permanently mounted on it.

Figure A-1. Upward Static Load Test

Figure A-2. Forward Static Load Test

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APPENDIX B VERSION 1 ADS-B FIELD APPROVAL COMPLIANCE

MATRIX

This section provides a compliance matrix template which installers may use to obtain field approvals for the activation of the GTX 33 ADS-B Extended Squitter function, as described in Section 1.3 provides a break-down of EASA AMC 20-24 requirements and corresponding compliance statements.

For installations that utilize a Garmin GNS 480 or GTN 6XX/7XX device (collectively referred to as ‘Garmin GNS/GTN equipment’), no additional data is required for the compliance matrix. Compliance statements are pre-populated for all aspects involving GNSS position source requirements.

If a non-Garmin GPS position source is used, the installer must:

1. Determine the GPS position source is compliant with the ARINC 743A standard

2. Obtain and input the appropriate data into the compliance matrix:

a) Item 14, Horizontal Position and Horizontal Position Quality Indicator(s)

b) Item 17, Horizontal Position Source Accuracy

c) Item 18, Horizontal Position Source Integrity

d) Item 19, Horizontal Position Source Integrity - Source Failure Probability

. The table

e) Item 20, Horizontal Position Source Integrity - Alert Failure Probability

f) Item 21, Horizontal Position Source Integrity - Time to Alert

g) Item 26, GPS Engine and GPS processing design assurance levels

h) Item 28, Horizontal position data latency requirements

i) Item 53, Position source minimum requirements

j) Item 55, Alternative means of establishing integrity containment radius (if not provided by

the horizontal position data source)

k) Item 58, GNSS position source TSO compliance

l) Item 59, Identify whether the system incorporates Fault Detection and Exclusion capability

as defined in AC 20-138A

m) Item 60, Identify use of Alternative Compliant Position Data Sources, if equipped

n) Item 61, Identify use of Temporary Back-up Position Data Sources, if equipped

o) Item 75, Ground Velocity

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Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

1. 7.0 Functional Criteria

2. 7.1

3. 7.1

4. 7.1

AMC

Section #

In line with ED-126 (section 4), the ADS-B System needs to meet the following surveillance data transmission requirements, as a minimum;

A unique ICAO 24 bit aircraft address (contained within each ADS-B message transmission);

Horizontal Position (latitude and longitude);

AMC Item Compliance Summary

[Section heading, no

compliance statement req’d]

[Section heading, no

compliance statement req’d]

Supported in all Mode S

transmissions from the

GTX 33. Aircraft address data

is sourced from transponder

internal configuration settings.

Supported in BDS (0,5) Airborne Position.

Supported in BDS (0,5) Surface

Position.

Horizontal Position Quality Indicator(s) (position integrity for both ED-102/DO-260 and

5. 7.1

6. 7.1 Barometric Altitude;

DO-260A based ADS-B transmit

systems, as well as accuracy for DO260A based ADS-B transmit systems);

The GPS source sends this data to the transponder when it has a position solution.

Supported in BDS (0,5) Airborne Position.

Supported in BDS (0,5) Surface

Position.

Supported in BDS (6,5) Aircraft

Operational Status.

The GPS source sends this data to the transponder when it has a position solution.

Supported in BDS (0,5) Airborne Position.

An encoding altimeter or other

altitude source provides this

data to the transponder.

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Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

7. 7.1 Aircraft Identification;

8. 7.1 Special Position Identification (SPI);

9. 7.1

AMC

Section #

AMC Item Compliance Summary

Emergency Status and Emergency Indicator;

Supported in BDS (0,8) Aircraft

Identification and Category.

Aircraft data is sourced from

transponder internal

configuration settings.

Supported in BDS (6,5) Aircraft

Operational Status.

SPI data is sourced from

transponder internal IDENT

status. The IDENT function is

controlled via GTX 33 control and display device.

Supported in BDS (6,1)

Emergency/Priority Status.

Data is sourced from current

Mode A code status. The Mode

A code is entered via GTX 33 control and display device.

Version Number (in aircraft

10. 7.1

11. 7.2

12. 8 Airworthiness Considerations

operational status message, if avionics are DO-260A

compliant).

In line with ED-126 (section 4), it is

recommended that the ADS-B System meets the following optional surveillance

data transmission requirement: Ground Velocity

Supported in BDS (6,5) Aircraft

Operational Status.

Supported in BDS (0,5) Airborne Velocity.

The GPS source sends this data to the transponders when it has a position solution.

[Section heading, no

compliance statement req’d]

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Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

Section #

13. 8.1

14. 8.1

AMC

AMC Item Compliance Summary

Airworthiness Certification Objectives

For the purposes of the ADS-B-NRA application, the ADS-B System installed in

the aircraft needs to be designed to deliver data that satisfy the airborne domain requirements in line with ED126 Section 3.4, (Appendix 3 provides a summary for information purposes).

Horizontal Position and Horizontal Position Quality Indicator(s)

Requirement: 10

-5

/fh

(Appendix 3, Table 1)

See items below compiled from

AMC 20-24 Appendix 3 Tables:

Garmin GNS/GTN Equipment:

GPS/SBAS engine meets the

-5

per hour requirement.

Other:

15. 8.1

16. 8.1

17. 8.1

ADS-B System Continuity

-4

Requirement: 2*10

/fh

(Appendix 3, Table 1)

Horizontal Position Latency

Requirement: 1.5 sec/95% (Appendix 3,Table 1)

Horizontal Position Source Accuracy (95%) (Appendix 3,Table 2)

5 NM Sep: 926 m

The GTX 33 meets the

continuity requirement of

-4

/fh.

2*10

See Item 28 Response.

Garmin GNS/GTN Equipment: The GPS/SBAS engine meets the ≤926m accuracy requirement under conditions of sufficient GPS satellite coverage.

Other:

GTX 33 Installation Manual 190-00906-00 Page B-4 Rev. H

Page 59

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

Section #

18. 8.1

19. 8.1

AMC

AMC Item Compliance Summary

Horizontal Position Source Integrity -

Containment Radius (Rc) (Appendix 3,Table 2)

Requirement: 5 NM Sep: Rc=2 NM

Horizontal Position Source Integrity - Source Failure Probability (Appendix 3, Table 2)

Requirement: 10

-4

Garmin GNS/GTN Equipment: The GPS/SBAS engine meets the ≤2NM containment radius

requirement under conditions of

sufficient GPS satellite

coverage.

Other:

This requirement is met by the

GPS/SBAS system and is not

applicable to the GPS position

equipment itself.

20. 8.1

Horizontal Position Source Integrity - Alert Failure Probability (Appendix 3, Table 2)

Requirement: 10

-3

(per position

source failure event)

Garmin GNS/GTN Equipment: The GPS/SBAS missed alert

probability is 10

-3

/hr in all

modes.

Other:

190-00906-00 GTX 33 Installation Manual Rev. H Page B-5

Page 60

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

21. 8.1

22. 8.1

23. 8.1

Section #

AMC

AMC Item Compliance Summary

Horizontal Position Source Integrity - Time to Alert (Appendix 3, Table 2)

Requirement: 5 NM Sep: 10 sec

Barometric Altitude Accuracy (Appendix 3, Table 3)

Requirement: as per the installed sensors

(refer to section 8.5.2)

Barometric Altitude maximum latency

(Appendix 3, Table 3)

Requirement: 1 sec (as for SSR)

Garmin GNS/GTN Equipment: The GPS/SBAS engine meets the 10 second time to alert requirement in all modes.

Other:

See response to Item 64.

The ADS-B transmit and

transponder functions utilize the same source of barometric

altitude. The latency

requirement is met when the

latency requirement for SSR is

met.

This data is sourced within the

Aircraft Identification, SPI,

24. 8.1

25. 8.2 ADS-B System

Emergency Status (Appendix 3, Table

Requirement: As for SSR [AMC20-13]

GTX 33 unit, based on internal

configuration settings, IDENT

status and Mode A code. Data

integrity is consistent with Level

C design assurance.

[Section heading, no

compliance statement req’d]

GTX 33 Installation Manual 190-00906-00 Page B-6 Rev. H

Page 61

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

AMC

Section #

26. 8.2.1

27. 8.2.2

AMC Item Compliance Summary

The (overall) ADS-B System integrity level with respect to the processing of horizontal

position data and horizontal position quality indicators, covering the processing (and

data exchange) chain from horizontal position data source(s) to ADS-B transmit data string encoding)

needs to be 10

-5

/fh

(refer also to Table 1 in Appendix 3).

The (overall) ADS-B System continuity level needs to be

-4

2*10

/fh (refer also to

Table 1 in Appendix 3).

GTX 33 design assurance is

Level C which satisfies the

-5

/flight hour requirement.

Garmin GNS/GTN Equipment

: The

GPS/SBAS engine design

assurance levels are qualified to Level B.

Other:

The GTX 33 meets the

continuity requirement of

-4

2*10

/fh.

190-00906-00 GTX 33 Installation Manual Rev. H Page B-7

Page 62

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

28. 8.2.3

AMC

Section #

AMC Item Compliance Summary

The latency of the horizontal position data, including any uncompensated latency,

introduced by the (overall) ADS-B System does not exceed 1.5 second in 95% and 3 seconds in 99.9% of all ADS-B message

transmission cases (refer also to Table 1 in Appendix 3).

Garmin GNS/GTN Equipment: Total position data latency is ≤ 1

second:

GPS antenna signal to Time of Applicability: ≤500 ms

Position solution relayed to the transponder ≤200 ms

Potential position solution update delay until the next solution overwrite is relayed to the transponder ≤300 ms (given a 200 ms update rate)

Other:

29. 8.3 ADS-B Transmit System

Compliance with the air-ground

interoperability requirements, as

30. 8.3.1

31. 8.3.1 Aircraft identification

32. 8.3.1 SPI

33. 8.3.1 Emergency indicator

34. 8.3.1 Barometric altitude

35. 8.3.1 Quality indicator (NUC/NIC)

specified in ED-126 and presented in Section 7.1

and Appendix 4, needs to be

demonstrated.

[Section heading, no

compliance statement req’d]

See items below:

Supported in BDS (0,8) Aircraft

Identification and Category.

Supported in BDS (6,5) Aircraft

Operational Status.

Supported in BDS (6,1)

Emergency/Priority Status.

Supported in BDS (0,5) Airborne Position.

GTX 33 Installation Manual 190-00906-00 Page B-8 Rev. H

Page 63

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

36. 8.3.1 Airborne Position Latitude

37. 8.3.1 Airborne Position Longitude

38. 8.3.1 Emergency status

39. 8.3.1 Quality indicator (NACp)

40. 8.3.1 Quality indicator (SIL)

41. 8.3.1 Version Indicator

42. 8.3.1 Airborne Ground Velocity

43. 8.3.2

44. 8.3.3

AMC

Section #

AMC Item Compliance Summary

For 1090 MHz Extended Squitter ADS-B transmit systems, this should be demonstrated by the relevant tests documented in:

• ED-73B/ETSO-2C112b (or DO181C);

• ED-102, as a minimum, or an equivalent standard which is acceptable to the Agency (e.g. DO-260 or DO260A).

ADS-B transmit systems need to transmit horizontal position quality indicators consistent with the associated position information at the time of transmission.

Supported in BDS (0,5) Airborne Position.

Supported in BDS (6,1)

Emergency/Priority Status.

Supported in BDS (6,5) Aircraft

Operational Status.

Supported in BDS (6,5) Aircraft

Operational Status.

Supported in BDS (6,5) Aircraft

Operational Status.

Supported in BDS (0,9) Airborne Velocity.

The GTX 33 is compliant with:

• ETSO – 2C112b (DO-181C).

• ETSO – C166a (DO-260A).

Garmin GNS/GTN Equipment: GPS quality metrics are applicable at the same Time of Applicability as the position and velocity

Other:

190-00906-00 GTX 33 Installation Manual Rev. H Page B-9

Page 64

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

45. 8.3.4

46. 8.3.5

47. 8.3.6

AMC

Section #

AMC Item Compliance Summary

The value of the horizontal position quality indicators need to be based on the integrity

information for the encoding of the ED-102/DO-260 related NUC and the DO-260A related NIC quality indicator, as related to the horizontal position sources.

In addition, the encoding of the DO260A NAC quality indicator needs to be based on

the accuracy information of the horizontal position sources.

In case of ED-102/DO-260 based ADS-B transmit systems, the NUC Quality Indicator value need to be encoded based on the integrity containment radius only.

If the ADS-B transmit system does not have a means to determine an appropriate integrity containment radius and a valid position is reported, then the Quality

Indicator (i.e. NUC or NIC) need to be encoded to indicate that the integrity containment radius is unknown (i.e. NUC/NIC should be set to ‘zero’).

GTX 33 calculates DO-260A

NIC using Horizontal Protection

Limit (HPL) provided by the

GPS position source per DO-

260A.

GTX 33 calculates DO-260A

NAC using Horizontal Figure of

Merit (HFOM) provided by the

GPS position source per DO-

260A.

Not Applicable – GTX 33 is

compliant to DO-260A not

DO-260.

Per DO-260A, GTX 33

encodes Type Codes

corresponding to 'unknown' (e.g. 'zero') when valid HPL data is not available.

Transmitter antenna installation needs to comply with guidance for

48. 8.3.7

49. 8.3.8

50. 8.4 Horizontal Position Data Sources

installation of ATC transponders to ensure satisfactory functioning. (Also refer to ED-73B)

If more than one ADS-B transmit system is installed, simultaneous operation of both transmit systems needs to be prevented.

Transponder antenna is

compliant to TSO-C74c.

When two GTX 33

transponders are installed IAW

requirements, simultaneous

operation of both transponders

is not possible. Selection of the

active transponder is

accomplished by a dedicated

transponder 1 / 2 discrete switch located in the cockpit.

[Section heading, no

compliance statement req’d]

GTX 33 Installation Manual 190-00906-00 Page B-10 Rev. H

Page 65

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

AMC

Section #

51. 8.4.1

52. 8.4.2

53. 8.4.3

AMC Item Compliance Summary

The requirements on horizontal position data sources are based on the ED-126 safety and performance assessments.

Components of horizontal position data sources external to the aircraft ADS-B system (such as the GNSS space segment) fall outside these airworthiness

considerations. Such external components are assumed to operate in accordance with

their specified nominal performance.

Nevertheless, failures of the external data source components are required to be detected through onboard monitoring (as

expressed in section 8.4.3).

Any eligible horizontal position data source needs to meet the following minimum requirements (refer also to Table 2 in Appendix 3):

• Correct encoding of quality indicator information in line with the actual performance of the selected horizontal position data source(s), i.e. in relation to position integrity containment bound (ED-102/DO-260 and DO-260A ADS-B transmit systems) and position accuracy (DO-260A ADS-B transmit systems);

• Position source failure probability:

-4

per hour;

• Position integrity alert failure probability, commensurate with the performance characteristics of GNSS integrity

monitoring: 10

-3

(per position source

failure event);

• Position integrity time to alert: 10 seconds.

[General information, no

compliance statement req’d]

[General information, no

compliance statement req’d]

• “Correct encoding” -The GTX 33 encoding is compliant with DO260A.

Garmin GNS/GTN Equipment:

• "Position source failure

probability" - This requirement is met by the GPS/SBAS system and is not applicable to the GPS position equipment itself.

• “Position integrity alert failure

probability” - missed alert

probability is 10

-3

/hr in all modes.

• “Position integrity time-to-alert” –

the 10 second position integrity time to alert is met in all modes.

Other:

190-00906-00 GTX 33 Installation Manual Rev. H Page B-11

Page 66

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

54. 8.4.4

55. 8.4.5

56. 8.4.6

57. 8.4.6.1

58. 8.4.6.2

AMC

Section #

AMC Item Compliance Summary

If available and valid, integrity containment radius information should be provided to the ADS-B transmit system from the position data source, or equivalent, on the same interface as and together with each positional data.

If the integrity containment radius is not provided by the horizontal position data source, the ADS-B transmit system may use other means to establish an appropriate integrity containment radius,

provided a requirements compliant integrity alert mechanism is available.

Use of GNSS Systems as Primary Position Data Source

GNSS is considered as primary horizontal position data source for the provision of an acceptable accuracy and integrity performance in support of the ATC separation services contained within the ADS-B-NRA application. The ED-126 safety and performance assessments are based on the specified performance and characteristics of GNSS systems, including receiver autonomous integrity monitoring. Therefore, for GNSS systems as specified in section 8.4.6.2, a safety and performance demonstration is not required.

If GNSS is used as a positional source, the GNSS system should be either compatible with:

• ETSO C-129A, TSO C-129 or TSO C-129A; or

• ETSO C-145/C-146 or TSO C145A/C-146A,

capable of delivering position data with a periodic interval of at least 1.2 s

The transponder only receives position related parameters from a Garmin GNS/GTN Equipment position source or other compliant position source.

Garmin GNS/GTN Equipment: Not applicable.

Other:

[Section heading, no compliance statement req’d]

[General information, no compliance statement req’d]

Garmin GNS/GTN Equipment: Compliant with TSO-C146a/c and ETSO-C146, Class 3.

Other:

GTX 33 Installation Manual 190-00906-00 Page B-12 Rev. H

Page 67

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

59. 8.4.6.3

60. 8.4.7

AMC

Section #

AMC Item Compliance Summary

For GNSS systems compatible with (E)TSO C-129 (any revision), it is highly desired that the system incorporates Fault Detection and Exclusion capability as defined in AC 20-138A, Appendix 1, “GPS

as a Primary Means of Navigation for Oceanic/Remote Operations”.

Use of Alternative Compliant Position Data Sources

As the ED-126 safety and performance assessments are based on the performance and characteristics of GNSS systems, for alternative position sources a

dedicated safety and performance

assessment is required to demonstrate compliance with the ED126 requirements.

Garmin GNS/GTN Equipment: Meets the requirements for GPS as a Primary Means of Navigation for Oceanic/Remote Operations per FAA Advisory Circular 20-138A, Appendix 1.

Other:

Garmin GNS/GTN Equipment: Not applicable.

Other:

Use of Temporary Back-up Position Data Sources

Back-up position data sources not

complying with the requirements referred to in section 8.4.3 may prove very useful in enhancing the continuity of ADS-B surveillance provision during temporary

61. 8.4.8

62. 8.5 Barometric Altitude Data Sources

outages of the primary (or equivalent alternative) position data sources.

Any such back-up position data source needs to report its accuracy and integrity

performance to the ADS-B transmit system, in a format compliant with ED-102/DO-260

or DO-260A, as appropriate.

Garmin GNS/GTN Equipment: Not applicable.

Other:

[Section heading, no compliance statement req’d]

190-00906-00 GTX 33 Installation Manual Rev. H Page B-13

Page 68

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

63. 8.5.1

64. 8.5.2

AMC

Section #

AMC Item Compliance Summary

Pressure altitude provided to the ADS-B transmit system needs to be in accordance with existing requirements for ATC

transponders.

The digitizer code selected needs to correspond to within plus or minus

38.1 m (125 ft), on a 95% probability basis, with the pressure-altitude information

(referenced to the standard pressure setting of 1013.25 hectopascals), used on board the aircraft to adhere to the assigned flight profile. (ICAO Annex 10, Vol IV,

3.1.1.7.12.2.4. See also EUROCAE ED-26).

The performance of the encoders and of the sensors needs to be independent from the pressure setting selected.

An encoding altimeter or other

altitude source provides

pressure altitude to the

transponder.

The Mode C altitude data

reported by the GTX

transponder is the same as the

altitude used by the flight crew

to adhere to the assigned flight

profile.

Per the requirements of 14 CFR

91.411(a) and Part 43 Appendix

E sub-paragraph (c), installers

are required to verify

transponder altitude reporting

correspondence, both at initial

installation, as well as

subsequently every 24 calendar months.

Therefore, an installation that

meets the requirements for ATC

transponders also meets this

requirement.

The transponder should indicate correctly the altitude resolution (quantisation) used, i.e. 25ft (from an appropriate source, default resolution) or 100ft (Gillham’s coded source, permissible alternative resolution).

65. 8.5.3 The conversion of Gillham’s coded

data to another format before inputting to the transponder is not permitted unless failure detection can be provided and the resolution (quantisation) is set in the

transmitted data to indicate 100ft.

Per Section 4.4 of this manual,

GTX 33 reports altitude in 25-

foot increments when altitude is

provided serially, and 100-foot

increments when altitude is

provided from parallel wire gray

code inputs. Altitude resolution

is Supported in BDS (6,5)

Aircraft Operational Status.

Conversion of Gillham (gray)

coded altitude data to serial

data is not authorized.

GTX 33 Installation Manual 190-00906-00 Page B-14 Rev. H

Page 69

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

66. 8.5.4

67. 8.6 Aircraft Identification

68. 8.6.1

AMC

Section #

AMC Item Compliance Summary

In case more stringent barometric altimetry requirements are applicable in line with

airspace requirements (e.g. RVSM) or other function requirements (e.g. ACAS II),

then these requirements and their related regulation take precedence.

Identification needs to be provided to the ADS-B transmit system so that the information is identical to the filed ICAO flight plan. This information may be provided from:

A flight management system; or

A pilot control panel; or

For aircraft, which always operate with the same flight identification (e.g. using registration as the flight identification) it may be programmed into equipment at installation.

[General information, no

compliance statement req’d]

[General information, no

compliance statement req’d]

Flight ID is programmed as part

of the transponder configuration, and may also be manually configured by the pilot.

Flight ID is programmed as part

of the transponder configuration.

The IDENT key is available to

the pilot on the GTX 33 control and display device, or a

remote mounted IDENT button

may also be installed.

[Section heading, no

compliance statement req’d]

69. 8.6.2

70. 8.7

71. 8.8

In case no ICAO flight plan is filed, the Aircraft Registration needs to be provided to the ADS-B transmit system.

Special Position Identification (SPI)

For ATC transponder-based ADS-B transmit systems, the SPI capability needs to be provided. The SPI capability should

be integrated into the transponder

functionality and should be controlled from the transponder control panel.

Emergency Status/Emergency Indicator

190-00906-00 GTX 33 Installation Manual Rev. H Page B-15

Page 70

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

72. 8.8.1

73. 8.8.2

74. 8.9

75. 8.9.1

AMC

Section #

AMC Item Compliance Summary

When an emergency status (i.e. discrete emergency code) has been selected by the flight crew, the emergency indicator needs

to be set by the ADS-B transmit system.

For ATC transponder-based ADS-B transmit systems, the discrete emergency code declaration capability should be

integrated into the transponder functionality and should be controlled from the

transponder control panel.

Airworthiness Considerations regarding Optional Provisions

Ground Velocity (OPTIONAL)

Ground velocity, e.g. from an approved GNSS receiver, in the form of East/West and North/South Velocity (including a

velocity quality indicator) is recommended to be provided.

The Mode A code is monitored

for correspondence to an

emergency code.

The GTX 33 facilitates the

transponder code entry function.

[Section heading, no

compliance statement req’d]

Garmin GNS/GTN Equipment: The GPS/SBAS source sends this data to the transponders when it has a position solution.

Other:

Special Position Identification (SPI) (OPTIONAL)

76. 8.9.2

For non-ATC transponder-based ADS-B transmit systems (i.e. installations based on

dedicated ADS-B transmitters), a discrete input or a control panel should be provided to trigger the SPI indication.

Not applicable – GTX 33 uses ATC transponder-based system.

GTX 33 Installation Manual 190-00906-00 Page B-16 Rev. H

Page 71

Table B-1. Version 1 ADS-B Field Approval Compliance Matrix

Item #

77. 8.9.3

78. 8.9.4

79. 8.9.4.1

AMC

Section #

AMC Item Compliance Summary

Emergency Status/Emergency Indicator

(OPTIONAL)

For non-ATC transponder-based ADS-B transmit systems (i.e. installations based on

dedicated ADS-B transmitters), a discrete input or a control panel should be provided to indicate the emergency status (discrete

emergency code).

Flight Deck Control Capabilities

(OPTIONAL)

Means should be provided to the flight crew to modify the Aircraft Identification information when airborne.

Not applicable – GTX 33 uses

ATC transponder-based system.

[Section heading, no

compliance statement req’d]

Flight ID may be manually set

by the pilot, depending on

internal configuration settings

established at installation.

80. 8.9.4.2

Means should be provided to the flight crew to disable the ADS-B function on instruction from ATC without disabling the operation of

the ATC transponder function.

The GTX 33 control and display device provides a means for the pilot to disable ADS-B function without disabling the ATC transponder function, if configured for this function.

190-00906-00 GTX 33 Installation Manual Rev. H Page B-17

Page 72

This page intentionally left blank

GTX 33 Installation Manual 190-00906-00 Page B-18 Rev. H

Page 73

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

9.64

244.8

10.77

273.6

6.30

160.0

7.26

184.4

11.37

288.8

4.9

CENTER OF GRAVITY

124

3.2

CENTER OF

GRAVITY

6X NOTE 3 (BOTH SIDES)

.377

±.010

9.58

±0.25

3.350

±.010

85.09

±0.25

.480

±.010

TYP.

12.19

±0.25

.390

±.010

9.91

±0.25

1.72

43.6

NOTES:

DIMENSIONS: INCHES [mm]

1. DIMENSIONS SHOWN ARE FOR REFERENCE ONLY.

2. MOUNTING HOLES FOR #6 FLAT HEAD 100° CSK SCREW (18 PLACS).

190-00906-00 GTX 33 Installation Manual Revision H Page C-1

Figure C-1 GTX 33 in Modular Rack, Outline Drawing

Page 74

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

115-00438-00

011-00950-03 NOTE 3

211-60234-08 (2 PLACES)

211-63234-11 (2 PLACES)

330-00053-01 (BNC) OR 330-00053-02 (TNC) (1 OR 2 PLACES)

212-00022-00 (1 OR 2 PLACES)

NUT SUPPLIED WITH 330-00053-XX

NOTES:

IF REMOVED, APPLY 291-00023-02 THREAD LOCKING COMPOUND TO ALL THREADED FASTENERS

1. BEFORE REINSTALLATION.

RF ADAPTORS (330-00053-XX) MUST FLOAT IN CAVITY FOLLOWING ASSEMBLY OF NUT AND WASHER.

2. REFER TO 190-00313-09 FOR ADDITIONAL PARTS LISTS.

RACK NUTPLATE KIT 011-00915-01

NOTE: MINIMIUM OF FOUR SCREWS REQUIRED PER NUTPLATE (TWO PER POSITION)

125-00002-00

BACKPLATE ASSEMBLY

011-00582-XX

211-63207-10 (12 PLACES)

115-00657-01 (2 PLACES)

330-00185-62

CONNECTOR KIT

011-01012-01

011-01169-01 NOTE 3

190-00906-00 GTX 33 Installation Manual Revision H Page C-2

Figure C-2 GTX 33 G1000 Connector/Rack Assembly Drawing

Page 75

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

164.9

175.7

6.92

6.49

3.6

CENTER OF

GRAVITY

CENTER OF

GRAVITY

45.3

1.78

29.0

1.14

48.7

1.92

135

5.3

CENTER OF GRAVITY

246.0

9.69

158.8

6.25

274.8

10.82

290.0

11.42

4.8 .19

8.2 .32

Figure C-3 GTX 33 Remote Stand-Alone Rack/Connector Assembly (Sheet 1 of 2)

190-00906-00 GTX 33 Installation Manual Revision H Page C-3

Page 76

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

115-00629-00

125-00002-00

011-00950-03 NOTE 3

211-63234-11 (2 PLACES)

211-60234-08 (2 PLACES)

330-00053-01 (BNC) OR 330-00053-02 (TNC) (1 OR 2 PLACES)

212-00022-00 (1 OR 2 PLACES)

NUT SUPPLIED WITH 330-00053-XX

NOTES:

IF REMOVED, APPLY 291-00023-02 THREAD LOCKING COMPOUND TO ALL THREADED FASTENERS

1. BEFORE REINSTALLATION.

RF ADAPTORS (330-00053-XX) MUST FLOAT IN CAVITY FOLLOWING ASSEMBLY OF NUT AND WASHER.

2. REFER TO 190-00313-09 FOR ADDITIONAL PARTS LISTS.

BACKPLATE ASSEMBLY

011-00582-XX

330-00185-62

011-01169-01 NOTE 3

CONNECTOR KIT

011-01012-01

190-00906-00 GTX 33 Installation Manual Revision H Page C-4

Figure C-3 GTX 33 Remote Stand-Alone Rack/Connector Assembly (Sheet 2 of 2)

Page 77

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

3.3 84

5.4 137

2.5 62

.9 22

SEE NOTE 3

177.80

2x 7.00015.88

.625

1.770 44.96

2x 1.313 33.35

CENTERED

P330-1

TOP ANTENNA

BOTTOM ANTENNA

1.8 46

5.8 148

ABOVE THIS LOCATION FOR INSTALLATION OF CONNECTOR PLATE

.100 [2.54] CLEARANCE REQUIRED

250.479.861

290.6811.444

.870 22.11

1.143

29.02

1.57.062

9.98 MOUNTING SCREW DEPTH IN RACK

.393

6.983 177.37

NOTES: 1, DIMENSIONS IN INCHES [mm].

2. DIMENSIONS ARE SHOWN FOR REFERENCE ONLY.

3. MOUNTING HOLES FOR #8 FLATHEAD 100° CSK SCREW (4 PLACES) USE MS24694S7 OR SCREW OF SAME OR GREATER STRENGTH

1/8" HEX

UNIT INSTALL SCREW

.493

12.52

5.94.234

6.624 168.25

REMOVEABLE UNIT

1.515 38.48 REMOVEABLE UNIT

190-00906-00 GTX 33 Installation Manual Revision H Page C-5

Figure C-4 GTX 33H Remote Stand-Alone Rack/Connector Assembly (Sheet 1 of 2)

Page 78

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

CONNECTOR KIT 011-01012-( )

BACK PLATE ASSEMBLY

011-00582-( )

GTX 33H OR GTX 33DH

011-00779-( )

STAND-ALONE RACK 011-02422-00

MUST LIFT UNIT UP 0.34" TO CLEAR RACK WHEN REMOVING OR INSTALLING

BACKPLATE-RETAINING SPRING CLIP

TIGHTEN INSTALL SCREW TO 15

2 IN-LBS

330-00053-02 TNC CONNECTION 2 PLACES (D UNITS) 1 PLACE (NON-D UNITS)

212-00022-10 BEVELED EDGE FACES AWAY FROM NUT 2 PLACES (D UNITS) 1 PLACE (NON-D UNITS)

NUT SUPPLIED WITH 330-00053-02 2 PLACES (D UNITS) 1 PLACE (NON-D UNITS)

125-00002-01

211-63234-11

Figure C-4 GTX 33H Remote Stand-Alone Rack/Connector Assembly (Sheet 2 of 2)

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-1 GTX 33 Typical Garmin Integrated Flight Deck Interconnect Wiring Diagram

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-2 GTX 33 to GNS 480 (CNX 80) Simplified Interconnect Wiring Diagram

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-3 GTX 33 to MFD, Simplified Interconnect Wiring Diagram

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-4 Dual GTX 33 to GNS 480 (CNX80) Interconnect Wiring Diagram, Single Altitude Encoder (Sheet 1 of 2)

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-4 Dual GTX 33 to GNS 480 (CNX80) Interconnect Wiring Diagram, Single Altitude Encoder (Sheet 2 of 2)

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-5 Dual GTX 33 to GTN 6XX/7XX Interconnect Wiring Diagram, Encoding Altitude Connections (Sheet 1 of 2)

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APPENDIX D INTERCONNECT DRAWINGS

Figure D-5 Dual GTX 33 to GTN 6XX/7XX Interconnect Wiring Diagram, Encoding Altitude Connections (Sheet 2 of 2)

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Garmin GTX 33 User Manual

Specifications and Main Features

Frequently Asked Questions

User Manual

1 GENERAL DESCRIPTION

1.1 Introduction

1.2 Equipment Description

1.3 ADS-B Capabilities

1.4 TIS System Capabilities

1.5 Mutual Suppression Pulses

1.6 Interface Summary

1.7 Technical Specifications

1.8 Aircraft Station Licensing Requirements

1.9 Certification

1.10 Operating Instructions

1.11 Reference Documents

2 INSTALLATION OVERVIEW

2.1 Introduction

2.2 Installation Materials

2.3 Installation Considerations

2.4 Cabling and Wiring

2.5 Installation Approval Considerations for Pressurized Aircraft

2.6 Cooling Air

2.7 GTX 33 Mounting Requirements

3 INSTALLATION PROCEDURE

3.1 Unpacking Unit

3.2 Wiring Harness Installation

3.3 Backshell Assembly

3.4 Weight and Balance

3.5 Electrical Load Analysis

3.6 Final Installation

3.7 Post Installation Configuration and Checkout

3.8 Continued Airworthiness

4 SYSTEM INTERCONNECTS

4.1 Pin List

4.2 Power Functions

4.3 Temperature Inputs

4.4 Altitude Functions

4.5 Discrete Functions

4.6 Serial Data Electrical Characteristics

4.7 RS-232 Input/Output, Software Update Connections

APPENDIX A CONSTRUCTION AND VALIDATION OF STRUCTURES

A.1 Static Test Loading

A.2 Determining Static Load Capability

APPENDIX C OUTLINE AND INSTALLATION DRAWINGS

APPENDIX D INTERCONNECT DRAWINGS