FCC ID: IPH-0183700 LICENSED NON-BROADCAST AERONAUTICAL TRANSMITTER

GDR 66 Transceiver Installation Manual 190-00303-24 January, 2012 Revision A DRAFT Copyright 2011 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited. Aviation Panel-Mount Technical Support Line (Toll Free) 1.888.606.5482 Garmin International, Inc. 1200 E. 151st Street Olathe, KS 66062 USA Telephone: 913.397.8200 www.garmin.com Garmin (Europe) Ltd. Liberty House, Bulls Copse Road Hounsdown Business Park Southampton, SO40 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 A 01/17/2012 Initial Release Description Page A Revision A GDR 66 Installation Manual 190-00303-24 DRAFT INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations

("EAR") issued by the United States Department of Commerce (15 CFR, Chapter VII, Subchapter C) and which may not be exported, released, or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual. WARNING This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65. CURRENT REVISION DESCRIPTION Revision Page Number(s) Section Number A All All Initial release Description of Change DOCUMENT PAGINATION Section Table of Contents Section 1 Section 2 Section 3 Section 4 Appendix A Appendix B Page Range i vi 1-1 1-8 2-1 2-4 3-1 3-4 4-1 4-10 A-1 A-3 B-1 B-3 GDR 66 Installation Manual 190-00303-24 Page i Revision A DRAFT TABLE OF CONTENTS PARAGRAPH PAGE Section 1 GENERAL DESCRIPTION............................................................. 1-1 1.1 Introduction.....................................................................................................................1-1 1.2 Equipment Description...................................................................................................1-1 1.3 Interface Summary.........................................................................................................1-1 1.4 Technical Specifications .................................................................................................1-2 1.4.1 Environmental Qualification Form..................................................................................... 1-2 1.4.2 Physical Characteristics ...................................................................................................... 1-2 1.4.3 General Specifications ........................................................................................................ 1-2 1.4.4 Power Requirements ........................................................................................................... 1-3 1.4.5 Transmitter Power Versus Aircraft Bus Voltage................................................................ 1-3 1.4.6 COM Transceiver Specifications........................................................................................ 1-4 1.4.7 Digital Transceiver Characteristics..................................................................................... 1-4 1.4.8 License Requirements......................................................................................................... 1-6 1.5 Certification.....................................................................................................................1-6 1.5.1 TSO/ETSO Compliance...................................................................................................... 1-7 1.5.2 TSO/ETSO Deviations........................................................................................................ 1-7 1.6 Reference Documents .....................................................................................................1-7 1.7 Aviation Limited Warranty.............................................................................................1-8 Section 2 INSTALLATION OVERVIEW....................................................... 2-1 2.1 Introduction.....................................................................................................................2-1 2.2 Installation Materials.......................................................................................................2-1 2.2.1 Equipment Available .......................................................................................................... 2-1 2.2.2 Additional Equipment Required ......................................................................................... 2-1 2.3 Installation Considerations..............................................................................................2-2 2.3.1 Antenna Considerations...................................................................................................... 2-2 2.3.2 Com Antenna Location....................................................................................................... 2-2 2.4 Cabling and Wiring.........................................................................................................2-3 2.5 Cooling Air......................................................................................................................2-3 2.6 Mounting Requirements..................................................................................................2-4 Section 3 INSTALLATION PROCEDURE .................................................... 3-1 3.1 Unpacking Unit ...............................................................................................................3-1 3.2 Wiring Harness Installation.............................................................................................3-1 3.3 Antenna Installation ........................................................................................................3-2 3.4 Cable Installation ............................................................................................................3-3 3.5 Backshell Assembly........................................................................................................3-4 3.6 Final Installation..............................................................................................................3-4 3.7 Post Installation Configuration & Checkout...................................................................3-4 3.8 Continued Airworthiness ................................................................................................3-4 Page ii Revision A GDR 66 Installation Manual 190-00303-24 DRAFT TABLE OF CONTENTS PARAGRAPH PAGE Section 4 SYSTEM INTERCONNECTS......................................................... 4-1 4.1 Pin Function List.............................................................................................................4-1 4.1.1 P661 (COM)........................................................................................................................ 4-1 4.1.2 P662 (Main) ........................................................................................................................ 4-2 4.2 Power Functions..............................................................................................................4-4 4.2.1 Aircraft Power..................................................................................................................... 4-4 4.2.2 Remote Power Off .............................................................................................................. 4-4 4.2.3 GDR System ID Program ................................................................................................... 4-4 4.3 Serial Data.......................................................................................................................4-5 4.3.1 RS-422 ................................................................................................................................ 4-5 4.3.2 RS-232 ................................................................................................................................ 4-5 4.3.3 ARINC 429 ......................................................................................................................... 4-6 4.4 Discrete I/O .....................................................................................................................4-7 4.4.1 Active Low Discrete Inputs ................................................................................................ 4-7 4.4.2 Key Event Out..................................................................................................................... 4-7 4.5 Audio...............................................................................................................................4-8 4.5.1 Analog Audio...................................................................................................................... 4-8 4.5.2 ACARS/SELCAL............................................................................................................... 4-9 Appendix A Outline and Installation Drawings............................................. A-1 Appendix B Interconnect Examples.................................................................B-1 GDR 66 Installation Manual 190-00303-24 Page iii Revision A DRAFT LIST OF FIGURES FIGURE PAGE Section 1 GENERAL DESCRIPTION............................................................. 1-1 Section 2 INSTALLATION OVERVIEW....................................................... 2-1 Figure 2-1: GDR 66 Standalone Rack ..................................................................................2-4 Section 3 INSTALLATION PROCEDURE .................................................... 3-1 Figure 3-1 TNC Connector Installation ................................................................................3-3 Section 4 SYSTEM INTERCONNECTS......................................................... 4-1 Figure 4-1 View of J661 connector, from back of unit.........................................................4-1 Figure 4-2 View of J662 connector, from back of unit.........................................................4-2 Appendix A Outline and Installation Drawings ............................................ A-1 Figure A-1 GDR 66 Outline Drawing.................................................................................. A-1 Figure A-2 GDR 66 Connector/Rack Assembly Drawing.................................................. A-2 Figure A-3 GDR 66 Minimum Installation/Removal Clearance ......................................... A-3 Appendix B Interconnect Examples ................................................................B-1 Figure B-1 GDR 66 Power and Antenna Interconnect Example ......................................... B-1 Figure B-2 GDR 66 VDL Mode 2 Interconnect Example ................................................... B-2 Figure B-3 GDR 66 Analog Voice Mode Interconnect Example........................................ B-3 Page iv Revision A GDR 66 Installation Manual 190-00303-24 DRAFT LIST OF TABLES TABLE PAGE Section 1 GENERAL DESCRIPTION .............................................................1-1 Table 1-1 Physical Characteristics........................................................................................ 1-2 Table 1-2 General Specifications.......................................................................................... 1-2 Table 1-3 Power Requirements............................................................................................. 1-3 Table 1-4 TX Power (into 50 load) vs Bus Voltage .......................................................... 1-3 Table 1-5 Transceiver Specifications ................................................................................... 1-4 Table 1-6 Digital Transceiver Characteristics ...................................................................... 1-4 Table 1-7 License Requirements .......................................................................................... 1-6 Table 1-8 TSO/ETSO Compliance ....................................................................................... 1-7 Table 1-9 TSO/ETSO Deviations ......................................................................................... 1-7 Table 1-10 Reference Documents......................................................................................... 1-7 Section 2 INSTALLATION OVERVIEW........................................................2-1 Table 2-1 Available Units..................................................................................................... 2-1 Table 2-2 Equipment Available............................................................................................ 2-1 Table 2-3 Additional Equipment Required........................................................................... 2-1 Section 3 INSTALLATION PROCEDURE.....................................................3-1 Table 3-1: Pin Contact Part Numbers................................................................................... 3-1 Table 3-2 Recommended Crimp Tools................................................................................. 3-2 Section 4 SYSTEM INTERCONNECTS..........................................................4-1 Table 4-1 P661 Connector .................................................................................................... 4-1 Table 4-2 P662 Connector .................................................................................................... 4-2 Table 4-3 Aircraft Power ...................................................................................................... 4-4 Table 4-4 Remote Power Off................................................................................................ 4-4 Table 4-5 System ID Program .............................................................................................. 4-4 Table 4-6 Unit Number Configuration ................................................................................. 4-5 Table 4-7 RS-422.................................................................................................................. 4-5 Table 4-8 RS-232.................................................................................................................. 4-5 Table 4-9 ARINC 429........................................................................................................... 4-6 Table 4-10 Discrete Inputs.................................................................................................... 4-7 Table 4-11 Key Event Out .................................................................................................... 4-7 Table 4-12 Com Mic Audio.................................................................................................. 4-8 Table 4-13 Com Audio Out .................................................................................................. 4-8 Table 4-14 Com Mic Key ..................................................................................................... 4-8 Table 4-15 Com Remote Transfer ........................................................................................ 4-9 Table 4-16 SELCAL Audio and ACARS Data Out ............................................................. 4-9 GDR 66 Installation Manual 190-00303-24 Page v Revision A DRAFT Page vi Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 1 GENERAL DESCRIPTION 1.1 Introduction This manual presents mechanical and electrical installation requirements for installing the GDR 66 as part of a Garmin Integrated Flight Deck. The GDR 66 can be integrated into a variety of airframes under an appropriate TC or STC. Each airframe installation may vary. Use only approved (type or supplemental type) data for specific installation instructions in a particular aircraft. 1.2 Equipment Description The GDR 66 is a remote mounted digital communications transceiver. The GDR 66 operates in the following modes in the 118.000 to 137.000 MHz VHF aviation communications band:

Analog Voice Mode (ARINC 716 Voice): Voice communications using DSB-AM modulation with 8.33 and 25 kHz channel spacing. VDL Mode 0/A (ARINC 716 Data): ACARS using DSB-AM modulation with a 2.4 kbps data rate VDL Mode 2 (ARINC 750 Data): Data link using D8PSK modulation with a 31.5 kbps data rate and 25 kHz channel spacing. and 25 kHz channel spacing. 1.3 Interface Summary The GDR 66 provides the following interfaces:

2 RS-422 inputs 2 RS-422 outputs 1 RS-232 input 1 RS-232 output 5 configurable ARINC 429 inputs 2 configurable ARINC 429 outputs 8 configurable active low discrete inputs 5 active low discrete inputs: COM MIC KEY*, COM REMOTE TRANSFER*, GDR SYSTEM ID PROGRAM* 1, GDR SYSTEM ID PROGRAM* 2, GDR SYSTEM ID PROGRAM* 3 1 active high discrete input: COM REMOTE POWER OFF 1 active low discrete outputs: KEY EVENT OUT*

1 analog microphone audio input 1 analog audio output 1 SELCAL audio/ACARS analog data output 2 aircraft power bus inputs GDR 66 Installation Manual 190-00303-24 Page 1-1 Revision A DRAFT 1.4 Technical Specifications 1.4.1 Environmental Qualification Form It is the responsibility of the installing agency to obtain the latest revision of the GDR 66 Environmental Qualification Form. This form is available directly from Garmin under the following part number:

GDR 66 Environmental Qualification Form, Garmin part number 005-00548-01 To obtain a copy of this form, see the dealer/OEM portion of the Garmin web site (www.garmin.com). 1.4.2 Physical Characteristics Table 1-1 list the physical characteristics for the GDR 66 unit, rack, and connectors. Please refer to Appendix A for additional information. Table 1-1 Physical Characteristics Characteristics Width (w/out Rack) Height (w/out Rack) Depth (w/out Rack) Width (with Rack) Height (with Rack) Depth (with Rack & Connectors) Unit Weight Rack Weight Connector Weight Specifications 2.06 inches (5.23 cm) 6.46 inches (16.4 cm) 8.78 inches (22.3 cm) 2.06 inches (5.23 cm) 6.62 inches (16.8 cm) 10.1 inches (25.8 cm) 4.2 lbs. (1.9 kg) 0.36 lbs. (0.16 kg) 0.33 lbs. (0.15 kg) 1.4.3 General Specifications For detailed specifications, see the Environmental Qualification Form. Characteristics Operating Temperature Range Humidity Altitude Range Software Compliance Environmental Conditions Table 1-2 General Specifications Specifications

-55C to +70C. For more details see Environmental Qualification Form. 95% non-condensing

-1,500 ft to 55,000 ft RTCA/DO-178B Level C, EUROCAE/ED-12B Level C RTCA/DO-160E, EUROCAE/ED-14E Page 1-2 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 1.4.4 Power Requirements Characteristics Input Voltage 14V 28V Table 1-3 Power Requirements Specifications 14/28 Vdc. See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages. Receive (AM or VDL) Transmit (AM or VDL) Receive (AM or VDL) Transmit (AM or VDL) Maximum 3.0A Maximum 9.0A Maximum 1.5A Maximum 8.0A 1.4.5 Transmitter Power Versus Aircraft Bus Voltage Table 1-4 TX Power (into 50 load) vs Bus Voltage Aircraft Power Bus Voltage

(V) Tx Power AM Mode Tx Power VDL Mode V 22.0 V 22.0 > V 11.0 11.0 > V 10.25 16 W minimum 20 W Typical 8 W minimum 10 W Typical 4 W minimum 5 W Typical NOTE 15 W minimum 20 W Typical 7.5 W minimum 10 W Typical 4 W minimum 5 W Typical GDR 66 does not claim Emergency Operation as defined by RTCA DO-160E, Section 16 GDR 66 Installation Manual 190-00303-24 Page 1-3 Revision A DRAFT 1.4.6 COM Transceiver Specifications The GDR 66 Transceiver minimally meets the requirements of DO-186B and ED-23B. Refer to Table 1-5 for detailed specifications. Table 1-5 Transceiver Specifications Characteristics Specifications Audio Outputs Audio Response Audio Distortion Receiver Dynamic Range Sensitivity Squelch Spurious Response Multi-Carrier Operation Transmitter Power Transmitter Duty Cycle Modulation Capability Carrier Noise Level Frequency Stability Demodulated Audio Distortion Sidetone Transmit Modulation Fidelity Microphone Sensitivity Spurious Emissions - Global Navigation Satellite System Band Received Audio: 40 mW minimum into a 600 load SELCAL/Data: 10.4 mW minimum into a 600 load Less than 6 dB of variation between 300 and 2500 Hz Greater than 40dB rejection above 3750 Hz Not greater than 20.0% across the band from 300 Hz to 2500 Hz with a 90% modulated signal. No greater than 7.5% with a 30% modulated signal

-107 dBm to +10 dBm typical

(S+N)/N on all channels shall be greater than 6 dB when the RF level is -107dBm modulated 30% at 1000 Hz Selectable between 0 to 20 dB SNR. Squelch hysteresis is selectable up to 15 dB 74 dB minimum (-33 dBm signal produces no more output than desired signal producing 6 dB (S+N)/N) Meets multi-carrier sensitivity, distortion, and audio output level requirements of ED-23C for Class C and Class H2 reveivers. See Section 1.4.5 10% maximum, thermally limited, 30 second limit per transmission The modulation shall not be less than 70% with a standard modulator signal applied to the transmitter Shall be at least 45 dB (S+N)/N

+ / - 5ppm (-55C to +70C with a 5-minute warmup at -55C) Less than 10% distortion when the transmitter is modulated at least 70%

1.4 Vrms into a 600 load Shall be less than 6 dB when the audio input frequency is varied from 350 to 2500 Hz See Section 4.5.1.1 Harmonic Emission products in the band extending from 1559 to 1610 Mhz shall be no greater than -60dBm 1.4.7 Digital Transceiver Characteristics The GDR 66 Transceiver minimally meets the requirements of DO-281A. Refer to Table 1-6 for detailed specifications. Characteristics Table 1-6 Digital Transceiver Characteristics Specifications Dynamic Range Sensitivity Transmitter Power Transmitter Duty Cycle Modulation Capability Frequency Stability Transmit Symbol Constellation Error Spurious Emissions - Global Navigation Satellite System Band

+10dBm to -98dBm typical Uncorrected BER of no more than 0.001 at -98 dBm See Section 1.4.5 20% maximum, thermally limited D8PSK

+ / - 5ppm (-55C to +70C with a 5-minute warmup at -55C) EVM of less than 6%

Harmonic Emission products in the band extending from 1559 to 1610 Mhz shall be no greater than -60dBm Page 1-4 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 1.4.8 License Requirements The Telecommunications Act of 1996, effective February 8, 1996, provides the FCC discretion to eliminate radio station license requirements for aircraft and ships. The GDR 66 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. Characteristic Transmitter Description:

Antenna Characteristics:

Rated Power:

Emission Type (Voice):

Emission Type (Data):

Frequency of Operation:

Table 1-7 License Requirements Specification Aviation-band VHF transceiver with 25 and 8.33 kHz channel spacing. Broad band, 50 ohm, vertically polarized. 20 Watts 6K00A3E (25 kHz Channel Spacing Mode) 5K60A3E (8.33 kHz Channel Spacing Mode) 13K0A2D (VDL Mode A, ACARS) 14K0G1D (VDL Mode 2) 118.000 136.975 MHz in 25 KHz AM or VDL Mode 118.000 136.99166 MHz in 8.3 KHz AM Mode 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 GDR 66 owner accepts all responsibility for obtaining the proper licensing before using the transmitter. International transmitter license procedures vary by country. Contact the local spectrum agency for license requirements. NOTE The VHF 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. 1.5 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. At the time of publication, installations of this TSO approved article are only approved when installed in an aircraft as part of a Garmin Integrated Flight Deck under an appropriate TC or STC. The Appliance Project Identifier (API) for the GDR 66 is GMN-00832. Documents submitted to the FAA, EASA and other regulatory agencies on behalf of this project will be filed under and referred to by this number. GDR 66 Installation Manual 190-00303-24 Page 1-5 Revision A DRAFT 1.5.1 TSO/ETSO Compliance Table 1-8 TSO/ETSO Compliance Function TSO/ETSO/

RTCA/EUROCAE Category Applicable LRU SW Part Numbers VHF COM Transceiver from 117.975 137.000 MHz VDL Mode 2 Communications Equipment Equipment that prevents blocked channels due to unintentional transmissions TSO-C169a ETSO-2C37e ETSO-2C38e RTCA/DO-186B EUROCAE/ED-23B TSO-C160 RTCA/DO-281A EUROCAE/ED-92A TSO-C128A ETSO-2C128 RTCA/DO-207 EUROCAE/ED-67 TX 3,4,5,6 RX C,E 006-B1055-(_) 006-B1056-(_) TX 7,8 RX F Architecture Y N/A 006-B1055-(_) 006-B1056-(_) 006-B1055-(_) 006-B1056-(_) 1.5.2 TSO/ETSO Deviations Table 1-9 TSO/ETSO Deviations TSO/ETSO TSO-C169a ETSO-2C37e ETSO-2C38e ETSO-2C128 Deviation 1. Garmin was granted a deviation from TSO-C169a paragraph 4.a.2 to allow the unit to be perma-

nently and legibly marked with a serial number and not the date of manufacture. The justification for this deviation is per FAA Memorandum FAA Order 8150.1B, Technical Standard Order Pro-

gram, Policy Clarification which states that the date of manufacture must be used in lieu of the optional serial number when that information is critical for maintenance and/or inspections. An equivalent level of safety is provided since the date of manufacture is not critical for maintenance and/or inspections of this appliance. The appliance will be marked with a serial number. 1. Garmin was granted a deviation from ETSO-2C37e to use DO-160E instead of DO-160D. Equivalent Level of Safety (ELOS) is provided by use of a later revision requirement document. 2. Garmin was granted a deviation from ETSO-2C37e to use ED-23B amendment 3 in addition to ED-23B. ELOS is provided by use of a later revision requirement document. 1. Garmin was granted a deviation from ETSO-2C38e to use DO-160E instead of DO-160D. ELOS is provided by use of a later revision requirement document. 2. Garmin was granted a deviation from ETSO-2C38e to use ED-23B amendment 3 in addition to ED23B. ELOS is provided by use of a later revision requirement document. 1. Garmin was granted a deviation from ETSO-2C128 to use DO-160E instead of DO-160D. ELOS is provided by use of a later revision requirement document. 1.6 Reference Documents The following publications are sources of additional information for installing the GDR 66. Before installing the GDR 66, the technician should read all referenced materials along with this manual. Part Number 190-00303-00 190-00303-04 190-00313-11 190-00313-50 190-00313-51 Table 1-10 Reference Documents Document G1000 System Installation Manual G1000 Line Maintenance and Configuration Manual Jackscrew Backshell Installation Instructions Garmin Integrated Avionics System Thermal Management Plan Garmin Integrated Avionics System Thermal Validation Procedure Page 1-6 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 1.7 Aviation 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. 1200 East 151st Street Olathe, Kansas 66062, U.S.A. Phone:913/397.8200 FAX:913/397.0836 Garmin (Europe) Ltd. Liberty House, Bulls Copse Road Hounsdown Business Park Romsey, SO40 9RB, U.K. Phone:44/ (0) 870.8501241 FAX:44/ (0) 870.850125 GDR 66 Installation Manual 190-00303-24 Page 1-7 Revision A DRAFT This page intentionally left blank Page 1-8 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 2 INSTALLATION OVERVIEW 2.1 Introduction This section provides hardware equipment information for installing the GDR 66, related hardware, and antennas. Installation of the GDR 66 must follow the aircraft TC or STC requirements. 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 Appendix A for rack drawings and dimensions. 2.2 Installation Materials The GDR 66 is only available as a single unit under the following part number:

Table 2-1 Available Units Item GDR 66 Unit Only, (011-02303-00) Garmin P/N 010-00832-00 2.2.1 Equipment Available Each of the following accessories are provided separately from the GDR 66 and are required for installation. Table 2-2 Equipment Available Item GDR 66 Standalone Install Rack GDR 66 Connector Kit Garmin P/N 011-02477-00 011-02304-00 2.2.2 Additional Equipment Required The following installation accessories are required but not provided:

Table 2-3 Additional Equipment Required Specification Shall meet TSO-C37(), C38(), and C-169(). Broad band, 50 , vertically polarized with coaxial cable 500 nominal impedance Low impedance, carbon or dynamic, with transistorized pre-amp

#10 pan head or hex head fastener (qty 4) Characteristic COM Antenna Headphones*

Microphone*

Hardware**

* Only required for voice mode

** Used for mounting unit rack to airframe GDR 66 Installation Manual 190-00303-24 Page 2-1 Revision A DRAFT 2.3 Installation Considerations Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GDR 66. 2.3.1 Antenna Considerations Antenna installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such antenna installations incorporate alteration (penetration) of the cabin pressure vessel by connector holes and/or mounting arrangements. For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations, it is recommended that the installer proceed according to any of the following listed alternatives:

1. Obtain approved antenna installation design data from the aircraft manufacturer. 2. Obtain an FAA approved STC, pertaining to, and valid for the 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 5. Contact an aviation industry organization such as the Aircraft Electronics Association for individuals listed in it. assistance. 2.3.2 Com Antenna Location The GDR 66 COM antenna should be well removed from all projections, engines and propellers. The ground plane surface directly below the antenna should be a flat plane over as large an area as possible (18 inches square, minimum). The antenna should be mounted a minimum of three feet from any DME antennas, three feet from any GPS antennas, and as far as practical from the ELT antenna. Some ELTs have exhibited re-radiation problems generating harmonics which may interfere with other signals. In addition, the COM antenna must have at least 16 dB of isolation from other COM antennas to prevent damage to the GDR 66 COM receiver. For COM antennas mounted on the same side of the fuselage, 16 dB of isolation can be achieved by a physical separation of approximately 3 feet (0.9 meters). If simultaneous use of two or more COM transceivers is desired the COM antennas must be spaced for maximum isolation. For a two COM installation, one COM antenna should be mounted on the top of the fuselage and the other antenna should be mounted on the bottom of the fuselage. For installations with three COMs, one COM antenna should be mounted on the top of the fuselage and the other two antennas should be mounted on the bottom of the fuselage and physically separated from each other as much as possible. The recommended minimum isolation between COM antennas for simultaneous use of two or more COMs is 40 dB. Separating the COM antennas between the top and bottom of the fuselage typically provides 35 45 dB of isolation for metal skin aircraft. For COM antennas mounted on the same side of the fuselage, 40 dB of isolation can be achieved by a physical separation of approximately 60 feet (18.3 meters). Receiver sensitivity could be significantly reduced during the transmission of a co-located COM for installations with less than 40 dB of isolation between the COM antennas. For installations with less than 23 dB of isolation between COM antennas, cross modulation (bleed-through) could also be experienced during the transmission of a co-located COM. For COM antennas mounted on the same side of the fuselage, 23 dB of isolation can be achieved by a physical separation of approximately 9 feet (2.7 meters). Simultaneous COM performance varies significantly across installations and is affected by both the isolation between the COM antennas and the separation of the tuned frequencies. Each installation should be individually examined to determine the expected performance of simultaneous COM. Page 2-2 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 2.4 Cabling and Wiring Refer to the interconnect examples in Appendix B for wire gauge guidance. The power connection can be run with three AWG #18 wires back to the breaker or can be spliced near the unit to one AWG #16 or larger wire. Special thin-wall heat shrink tubing is also provided to insulate the extended barrels inside the backshell. If using AWG #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. Coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation. NOTE RTCA DO-224A assumes 3dB of cable loss in its VDL Typical Uplink Power Budget. Losses greater than 3dB can reduce transceiver range. Cabling for the GDR 66 should not be routed near components or cabling which are sources of electrical noise. Route the GPS, VOR/LOC, and Glideslope antenna cables as far as possible away from all COM transceivers and antenna cables. 2.5 Cooling Air Dedicated cooling is not required for the GDR 66 to meet indicated EQF categories. Thermal analysis must be performed to verify that high temperature limits implied by the indicated EQF categories for the GDR 66 are not exceeded during normal operation of the aircraft. Guidance can be found in the Garmin Integrated Avionics System Thermal Management Plan document (GPN 190-00313-50) and the Garmin Integrated Avionics System Thermal Validation Procedure (GPN 190-00313-51). Contact Garmin for additional cooling guidance. GDR 66 Installation Manual 190-00303-24 Page 2-3 Revision A DRAFT 2.6 Mounting Requirements The GDR 66 mounting surface should be capable of providing a sufficient electrical bond to the aircraft to minimize radiated EMI and provide protection from High-Intensity Radiation Fields (HIRF). Bonding resistance measured between the GDR 66 standalone install rack and the airframe should be less than 2.5 mlliOhms. The GDR 66 must be mounted in the vertical position using the GDR 66 standalone rack. Approximately one inch of clearance should be provided on the left side of the GDR 66 to allow for cooling of the heat sink. Refer to Appendix A for outline and installation drawings. Figure 2-1: GDR 66 Standalone Rack Page 2-4 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 3 INSTALLATION PROCEDURE 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 of the cables. All electrical connections are made through 44 and 62-pin D-subminiature connectors. 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 B for examples of interconnect wiring diagrams. Construct the actual harnesses in accordance with aircraft manufacturer authorized interconnect standards. Contacts for the 62 and 44 pin connectors must be crimped onto the individual wires of the aircraft wiring harness. Tables 3-1 and 3-2 list contact part numbers (for reference) and recommended crimp tools. Manufacturer 62 pin connector (P662), 44 pin connector (P661) Table 3-1: Pin Contact Part Numbers Garmin P/N Military P/N AMP Positronic ITT Cannon 18-20 AWG

(Power Only) 336-00044-00 N/A N/A N/A N/A 22-28 AWG 336-00021-00 M39029/58-360 204370-2 MC8522D 030-2042-000 GDR 66 Installation Manual 190-00303-24 Page 3-1 Revision A DRAFT Manufacturer Hand Crimping Tool Table 3-2 Recommended Crimp Tools 18-20 AWG 22-28 AWG Positioner Insertion/

Extraction Tool

(note 2) Positioner Military P/N Positronic ITT Cannon AMP Daniels Astro M22520/2-01 9507 995-0001-584 601966-1 AFM8 615717 N/A 9502-11 N/A N/A K774 N/A M81969/1-04 M81969/1-04 N/A 91067-1 M81969/1-04 M81969/1-04 M22520/2-09 9502-4 M22520/2-09 601966-6 K42 615725 Insertion/

Extraction Tool M81969/1-04 M81969/1-04 274-7048-000 91067-1 M81969/1-04 M81969/1-04 NOTE 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. 3.3 Antenna Installation Follow the manufacturers instructions for installation of the COM antenna. CAUTION Do not use construction grade RTV sealant or sealants containing acetic acid. These sealants may damage the electrical connections to the antenna. Use of these type sealants may void the antenna warranty. Page 3-2 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 3.4 Cable Installation 1. Route the coaxial cable to the rack location keeping in mind the recommendations of Section 2. Secure the cable in accordance with good aviation practice. 2. Trim the coaxial cable to the desired length and install the TNC connector per the cabling instructions on Figure 3-1. If the connector is provided by the installer, follow the connector manufacturers instructions for cable preparation. Figure 3-1 TNC Connector Installation GDR 66 Installation Manual 190-00303-24 Page 3-3 Revision A DRAFT 3.5 Backshell Assembly The GDR 66 connector kit includes two Garmin backshell assemblies. Garmins backshell gives the installer the ability to easily terminate shield grounds at the backshell housing. Refer to the Jackscrew Backshell Installation Instructions (Garmin part number 190-00313-11) for backshell assembly instructions. 3.6 Final Installation For final installation and assembly, refer to the outline and installation drawings shown in Appendix A of this manual. 3.7 Post Installation Configuration & Checkout The GDR 66 must be installed as part of a Garmin Integrated Flight Deck and have FAA approved configuration data. Configuration data is loaded to the GDR 66 from an aircraft-specific Garmin SW Loader Card. GDR 66 settings are predetermined for a specific aircraft. For aircraft installation/checkout, use only aircraft manufacturer approved checkout procedures. 3.8 Continued Airworthiness Maintenance of the GDR 66 is on condition only. For regulatory periodic functional checks, refer to approved aircraft maintenance manuals or manual supplements for actual aircraft maintenance requirements. Page 3-4 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 4 SYSTEM INTERCONNECTS 4.1 Pin Function List 4.1.1 P661 (COM) 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 44 43 42 41 40 39 38 37 36 35 34 33 32 31 Figure 4-1 View of J661 connector, from back of unit Table 4-1 P661 Connector Pin Name SPARE SPARE SPARE COM MIC KEY*

SPARE SPARE COM MIC AUDIO IN HI COM MIC AUDIO IN LO (GROUND) COM 600 OHM AUDIO OUT HI COM 600 OHM AUDIO OUT LO RESERVED COM REMOTE TRANSFER*

RESERVED RESERVED SIGNAL GROUND COM REMOTE POWER OFF SPARE RESERVED SPARE GDR SYSTEM ID PROGRAM* 1 SPARE GDR SYSTEM ID PROGRAM* 2 SPARE GDR SYSTEM ID PROGRAM* 3 SPARE SIGNAL GROUND SPARE RESERVED SIGNAL GROUND SIGNAL GROUND SIGNAL GROUND RS-232 OUT 1 RS-232 IN 1 RESERVED KEY EVENT OUT*

Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35

*Denotes Active Low (Ground to activate). I/O

In

In

Out Out

In

In

In

In

In

Out In

Out GDR 66 Installation Manual 190-00303-24 Page 4-1 Revision A DRAFT Table 4-1 P661 Connector, continued 36 37 38 39 40 41 42 43 44 RESERVED SPARE SPARE RESERVED RESERVED SELCAL AUDIO AND DATA OUT HI SELCAL AUDIO AND DATA OUT LO SIGNAL GROUND SIGNAL GROUND

*Denotes Active Low (Ground to activate). 4.1.2 P662 (Main) 21 20 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 44 Figure 4-2 View of J662 connector, from back of unit Table 4-2 P662 Connector Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 Pin Name POWER GROUND RS-422 IN 1 B RS-422 IN 1 A RS-422 OUT 1 B RS-422 OUT 1 A RS-422 IN 2 B RS-422 IN 2 A RS-422 OUT 2 B RS-422 OUT 2 A DISCRETE IN* 1 DISCRETE IN* 2 DISCRETE IN* 3 DISCRETE IN* 4 DISCRETE IN* 5 DISCRETE IN* 6 DISCRETE IN* 7 DISCRETE IN* 8 ARINC 429 OUT 1 A ARINC 429 OUT 1 B ARINC 429 OUT 2 A ARINC 429 OUT 2 B SPARE

Out Out

I/O

In In Out Out In In Out Out In In In In In In In In Out Out Out Out

*Denotes Active Low (Ground to activate). Page 4-2 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT Table 4-2 P662 Connector, continued 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 SPARE POWER GROUND SPARE POWER GROUND SPARE AIRCRAFT POWER 1 SPARE AIRCRAFT POWER 1 SPARE AIRCRAFT POWER 1 SPARE AIRCRAFT POWER 2 SPARE AIRCRAFT POWER 2 SPARE AIRCRAFT POWER 2 SPARE POWER GROUND SPARE POWER GROUND POWER GROUND SPARE SIGNAL GROUND SPARE SIGNAL GROUND SPARE ARINC 429 IN 1 A ARINC 429 IN 1 B ARINC 429 IN 2 A ARINC 429 IN 2 B ARINC 429 IN 3 A ARINC 429 IN 3 B ARINC 429 IN 4 A ARINC 429 IN 4 B ARINC 429 IN 5 A ARINC 429 IN 5 B SPARE SIGNAL GROUND SIGNAL GROUND RESERVED

In

In

In

In

In

In

In In In In In In In In In In

GDR 66 Installation Manual 190-00303-24 Page 4-3 Revision A DRAFT 4.2 Power Functions 4.2.1 Aircraft Power The GDR 66 provides two aircraft power bus inputs. Pins 28, 30, and 32 of P662 are internally connected to form AIRCRAFT POWER 1. Pins 34, 36, and 38 of P662 are internally connected to form AIRCRAFT POWER 2. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are diode ORed to provide power redundancy. Use of three AIRCRAFT POWER pins (either AIRCRAFT POWER 1 or AIRCRAFT POWER 2) and three POWER GROUND pins is recommended for all installations. Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 AIRCRAFT POWER 2 POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND Table 4-3 Aircraft Power Connector P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 Pin 28 30 32 34 36 38 1 24 26 40 42 43 I/O In In In In In In

4.2.2 Remote Power Off The GDR 66 powers down when the COM REMOTE POWER OFF input is active. COM REMOTE POWER OFF is a non-configurable discrete input conforming to:

Low: 0 VDC < Vin < 3.5 VDC, OR Rin > 100k ohms (inactive) High: 8 VDC < Vin < 36 VDC (active) Table 4-4 Remote Power Off Pin Name COM REMOTE POWER OFF Connector P661 Pin 16 I/O In 4.2.3 GDR System ID Program The GDR 66 determines its unit number based on the status of three GDR SYSTEM ID PROGRAM*

non-configurable discrete inputs conforming to:

Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active) High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive) Table 4-5 System ID Program Pin Name GDR SYSTEM ID PROGRAM* 1 GDR SYSTEM ID PROGRAM* 2 GDR SYSTEM ID PROGRAM* 3 Connector P661 P661 P661 Pin 20 22 24 I/O In In In Page 4-4 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT The unit number is determined by the table below:

GDR SYSTEM ID PROGRAM* 1 Open Ground Open Ground Open Ground Open Ground Table 4-6 Unit Number Configuration GDR SYSTEM ID GDR SYSTEM ID PROGRAM* 2 PROGRAM* 3 Open Open Ground Ground Open Open Ground Ground Open Open Open Open Ground Ground Ground Ground UNIT NUMBER

#1

#2

#3

#4

#5

#6

#7 INVALID, DO NOT USE 4.3 Serial Data 4.3.1 RS-422 The GDR 66 provides two RS-422 inputs and two RS-422 outputs conforming to TIA/EIA/ANSI-422-B. RS-422 is the only interface between the GDR 66 and the rest of the Garmin system. Pin Name RS-422 IN 1 B RS-422 IN 1 A RS-422 OUT 1 B RS-422 OUT 1 A RS-422 IN 2 B RS-422 IN 2 A RS-422 OUT 2 B RS-422 OUT 2 A Table 4-7 RS-422 Connector P662 P662 P662 P662 P662 P662 P662 P662 Pin 2 3 4 5 6 7 8 9 I/O In In Out Out In In Out Out 4.3.2 RS-232 The GDR 66 provides one RS-232 input and one RS-232 output. The RS-232 output conforms to EIA Standard RS-232C with an output voltage swing of at least 5V when driving a standard RS-232 load. The RS-232 port is used for testing and as a back up tuning port. Table 4-8 RS-232 Pin Name RS-232 OUT 1 RS-232 IN 1 Connector P661 P661 Pin 32 33 I/O Out In GDR 66 Installation Manual 190-00303-24 Page 4-5 Revision A DRAFT 4.3.3 ARINC 429 The GDR 66 provides five configurable ARINC 429 inputs and two configurable ARINC 429 outputs conforming to ARINC Specifications 429P1-17, 429P2-16 and 429P3-18. The ARINC 429 outputs conform to ARINC 429 specifications when loaded with up to five standard ARINC 429 receivers. The speed of the ARINC 429 outputs can be configured for low speed (14.29 kHz) or high speed (100 kHz). Pin Name ARINC 429 IN 1 A ARINC 429 IN 1 B ARINC 429 IN 2 A ARINC 429 IN 2 B ARINC 429 IN 3 A ARINC 429 IN 3 B ARINC 429 IN 4 A ARINC 429 IN 4 B ARINC 429 IN 5 A ARINC 429 IN 5 B ARINC 429 OUT 1 A ARINC 429 OUT 1 B ARINC 429 OUT 2 A ARINC 429 OUT 2 B Table 4-9 ARINC 429 Connector P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 P662 Pin 49 50 51 52 53 54 55 56 57 58 18 19 20 21 I/O In In In In In In In In In In Out Out Out Out Page 4-6 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 4.4 Discrete I/O 4.4.1 Active Low Discrete Inputs The GDR 66 provides 8 configurable discrete inputs conforming to:

Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active) High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive) Table 4-10 Discrete Inputs Pin Name DISCRETE IN* 1 DISCRETE IN* 2 DISCRETE IN* 3 DISCRETE IN* 4 DISCRETE IN* 5 DISCRETE IN* 6 DISCRETE IN* 7 DISCRETE IN* 8 Connector P662 P662 P662 P662 P662 P662 P662 P662 Pin 10 11 12 13 14 15 16 17 I/O In In In In In In In In 4.4.2 Key Event Out The GDR 66 provides one output to signal when the GDR 66 is transmitting, regardless of what mode the radio is in. KEY EVENT OUT* can be used as needed to decrease the sensitivity of other COM receivers on the aircraft when the GDR 66 is transmitting. KEY EVENT OUT* is a non-configurable discrete output conforming to:

Active: 0 VDC < Vout < 1.0 VDC with < 20 mA sink current; sink current must be externally limited to 20 mA max. Inactive: Open circuit, can be pulled up to an externally sourced Vout in the range 3.3 VDC < Vout

< 36 VDC; leakage current is typically <10 uA to ground. Table 4-11 Key Event Out Pin Name KEY EVENT OUT*

Connector P661 Pin 35 I/O Out GDR 66 Installation Manual 190-00303-24 Page 4-7 Revision A DRAFT 4.5 Audio When the GDR 66 is in analog voice mode (ARINC 716 Voice), audio from the microphone and audio to the headset can be transferred to/from the GDR 66 as analog audio or digital audio. If analog audio is used, the COM MIC KEY* discrete input must be used. If digital audio is used all of this information is transferred in the digital audio stream. 4.5.1 Analog Audio 4.5.1.1 Com Mic Audio The GDR 66 provides one microphone audio input. COM MIC AUDIO has a 150 ohm AC input impedance and supplies the microphone with a 12 V bias through 400 +/ 20%. COM MIC AUDIO is set in the factory for 250 mVrms to modulate the transmitter at 90% nominally. The microphone gain is adjustable during installation to increase the sensitivity to 20 mVrms or decrease the sensitivity to 2.5 Vrms. Table 4-12 Com Mic Audio Pin Name COM MIC AUDIO IN HI COM MIC AUDIO IN LO (GROUND) Connector P661 P661 Pin 7 8 I/O In

4.5.1.2 Com Audio Out The GDR 66 provides one audio output that is intended to drive a headset or an audio panel. The rated output is 4.90 Vrms into a 600 ohm load (40 mWavg). A volume control is available during flight to reduce the output by at least 40 dB to 49 mVrms. COM 600 OHM AUDIO OUT is the summation of the COM receiver audio and COM sidetone audio. Table 4-13 Com Audio Out Pin Name COM 600 OHM AUDIO OUT HI COM 600 OHM AUDIO OUT LO Connector P661 P661 Pin 9 10 I/O Out Out 4.5.1.3 Com Mic Key The GDR 66 transmits the audio from the microphone (COM MIC AUDIO IN) when the COM MIC KEY* input is active. The COM MIC KEY* should be connected to the microphones PTT output. COM MIC KEY* is a non-configurable discrete input conforming to:

Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active) High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive) Table 4-14 Com Mic Key Pin Name COM MIC KEY*

Connector P661 Pin 4 I/O In Page 4-8 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT 4.5.1.4 Com Remote Transfer The GDR 66 provides one COM REMOTE TRANSFER* input which allows the COM Emergency State to be entered or exited. When the GDR 66 enters Emergency State, it automatically switches to AM COM mode and tunes to the emergency channel, 121.500 MHz. When in Emergency State, the GDR 66 ignores inputs from the front panel controls for COM selections and cannot be used for digital data link. The COM REMOTE TRANSFER* input controls Emergency State via one of two modes: Hold-to-

Acitvate mode and On/Off mode. A GDR 66 aircraft configuration parameter selects the mode as well as the activation time for Hold-to-Acitvate mode. In Hold-to-Acivate mode, the Emergency State is entered when the COM REMOTE TRANSFER* input is held active for the configured time, and is exited immediately when the COM REMOTE TRANSFER* input becomes active after having been inactive. In On/Off mode, COM REMOTE TRANSFER* acts as an on/off switch for Emergency State, which is entered immediately when COM REMOTE TRANSFER* becomes active, and is exited immediately when COM REMOTE TRANSFER* becomes inactive. Low: 0 VDC < Vin < 3.5 VDC, OR Rin < 375 ohms (active) High: 8 VDC < Vin < 36 VDC, OR Rin > 100k ohm (inactive) Table 4-15 Com Remote Transfer Pin Name COM REMOTE TRANSFER*

4.5.2 ACARS/SELCAL Connector P661 Pin 12 I/O In 4.5.2.1 SELCAL Audio and ACARS Data Out The GDR 66 provides one SELCAL audio/ACARS data output that can either be used for SELCAL or VDL Mode 0 (ARINC 716 Data). The rated output is 2.45 Vrms into a 600 ohm load (10 mWavg). The gain is adjustable during installation to decrease the output by at least 40 dB to 24.5 mVrms. A gain setting of -7.0 dB (1.2 Vrms minimum) is recommended. Refer to EQF for certification considerations for this output. Table 4-16 SELCAL Audio and ACARS Data Out Connector Pin Name SELCAL AUDIO AND DATA OUT HI SELCAL AUDIO AND DATA OUT LO P661 P661 Pin 41 42 I/O Out Out GDR 66 Installation Manual 190-00303-24 Page 4-9 Revision A DRAFT This page intentionally left blank Page 4-10 Revision A GDR 66 Installation Manual 190-00303-24 DRAFT APPENDIX A Outline and Installation Drawings 6.62 168.1 3.2 81 CG P661 COM

(TNC CONNECTOR) P662 4.6 117 CG 8.17 207.5 10.14 257.6

.8 20 CG 2X

.40 10.2 4X 2.06 52.3 2X 1.26

.010 32.00.25

.210

.005 5.33 SEE NOTE 3 0.13 NOTES:

1. 2. 3. DIMENSIONS: INCHES[mm]

DIMENSIONS ARE SHOWN FOR REFERENCE ONLY MOUNTING HOLES FOR #10 PAN HEAD OR HEX HEAD FASTENERS (4 PLACES) 2X 7.00

.010 177.8 0.25 2X .85 21.6 GDR 66 Installation Manual 190-00303-24 Figure A-1 GDR 66 Outline Drawing Page A-1 Revision A DRAFT APPENDIX A Outline and Installation Drawings CONNECTOR KIT 011-02304-00 NOTE 1 330-00776-44 330-00776-62 011-01855-02 011-01855-03 NOTE 2 GDR 66 UNIT 011-02303-00 GDR66 RACK 011-02477-00 NOTES:

1. 2. GASKETS ARE PART OF 330-00776-44 AND 330-00776-62. INSTALL GASKETS OVER PINS. REFER TO 190-00313-11 FOR ADDITIONAL PARTS LISTS. GDR 66 Installation Manual 190-00303-24 Figure A-2 GDR 66 Connector/Rack Assembly Drawing Page A-2 Revision A DRAFT APPENDIX A Outline and Installation Drawings MINIMUM RECOMMENDED INSTALLATION AND REMOVAL CLEARANCE WITH LOCKDOWN OVERHANGING MOUNTING SHELF

.30 7.6 MINIMUM RECOMMENDED INSTALLATION AND REMOVAL CLEARANCE WITH LOCKDOWN NOT OVERHANGING MOUNTING SHELF MOUNTING SHELF 1.00 25.4 MOUNTING SHELF GDR 66 Installation Manual 190-00303-24 Figure A-3 GDR 66 Minimum Installation/Removal Clearance Page A-3 Revision A DRAFT GDR 66 10A TO 14/28 VDC AIRCRAFT POWER SEE NOTE 7 16 AWG GDR 66 10A TO 14/28 VDC AIRCRAFT POWER APPENDIX B Interconnect Examples GDR 66 DIGITAL RADIO AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 1 POWER GROUND POWER GROUND POWER GROUND GDR SYSTEM ID PROGRAM* 1 GDR SYSTEM ID PROGRAM* 2 GDR SYSTEM ID PROGRAM* 3 P662 28 30 32 1 24 26 P661 20 22 24 COM ANTENNA J1 GDR 66 DIGITAL RADIO AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 1 POWER GROUND POWER GROUND POWER GROUND GDR SYSTEM ID PROGRAM* 1 GDR SYSTEM ID PROGRAM* 2 GDR SYSTEM ID PROGRAM* 3 P662 28 30 32 1 24 26 P661 20 22 24 18 AWG 18 AWG 18 AWG 18 AWG 18 AWG 18 AWG N/C N/C N/C 16 AWG COM ANTENNA J1 GDR 66 Installation Manual 190-00303-24 TO MINIMIZE VHF DIGITAL TRANSMISSION INTERFERENCE (ACARS/CPDLC) WITH RECEPTION OF VHF VOICE COMMUNICATION, IT IS RECOMMEDED THAT GIA 63W -40 UNITS SHOULD BE USED IN ALL INSTALLATIONS USING A GDR 66. 7. GIA 63W -00 AND -01 UNITS CANNOT BE USED WITH THE GDR 66. Figure B-1 GDR 66 Power and Antenna Interconnect Example Page B-1 Revision A DRAFT APPENDIX B Interconnect Examples GDR 66 DIGITAL RADIO P662 RS 422 OUT 1A RS 422 OUT 1B RS 422 IN 1A RS 422 IN 1B RS 422 OUT 2A RS 422 OUT 2B RS 422 IN 2A RS 422 IN 2B 5 4 3 2 9 8 7 6 KEY EVENT OUT*

P661 35 1P412 No. 1 GSD 41 DATA CONCENTRATOR 25 26 27 28 MAIN2 RS-485/RS-422 13A MAIN2 RS-485/RS-422 13B MAIN2 RS-485/RS-422 14A MAIN2 RS-485/RS-422 14B 2P412 No. 2 GSD 41 DATA CONCENTRATOR 5 6 7 8 MAIN2 RS-485/RS-422 3A MAIN2 RS-485/RS-422 3B MAIN2 RS-485/RS-422 4A MAIN2 RS-485/RS-422 4B 1P601 No. 1 GIA 63W 11 TRANSMIT INTERLOCK*

2P601 No. 2 GIA 63W 11 TRANSMIT INTERLOCK*

GDR 66 Installation Manual 190-00303-24 SEE NOTE 6 Figure B-2 GDR 66 VDL Mode 2 Interconnect Example Page B-2 Revision A DRAFT APPENDIX B Interconnect Examples GDR 66 DIGITAL RADIO P661 COM MIC KEY*

COM MIC AUDIO IN HI COM MIC AUDIO IN LO COM 600 OHM AUDIO OUT HI COM 600 OHM AUDIO OUT LO SELCAL AUDIO AND DATA OUT HI SELCAL AUDIO AND DATA OUT LO 4 7 8 9 10 41 42 KEY EVENT OUT*

35 1P3471 No. 1 GMA 36 AUDIO PROCESSOR 33 32 13 12 31 52 TRANSCEIVER 2 MIC KEY* OUT TRANSCEIVER 2 MIC AUDIO OUT HI TRANSCEIVER 2 AUDIO LO TRANSCEIVER 2 AUDIO IN HI RECEIVER 4 AUDIO IN HI RECEIVER 4 AUDIO IN LO SEE NOTE 6 No. 1 GIA 63W 1P601 11 TRANSMIT INTERLOCK*

2P601 No. 2 GIA 63W 11 TRANSMIT INTERLOCK*

GDR 66 Installation Manual 190-00303-24 Figure B-3 GDR 66 Analog Voice Mode Interconnect Example Page B-3 Revision A DRAFT