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GIA 63 Installation Manual 190-00303-05 November, 2012 Revision W DRAFT Copyright 2012 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 permis-
sion 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 www.garmin.com Aviation Dealer Technical Support Line (Toll Free): (888) 606-5482 Garmin (Europe) Ltd Liberty House Bulls Copse Road Hounsdown Business Park Southampton, SO40 9RB, UK Telephone: +44 (0) 8708501241 RECORD OF REVISIONS Description Production Release Updated pinout list, removed EQF and ETSO 2C37e deviation Added additional interconnects, TSO-C9c, and TSO-C52b Added TSO-C151b and boot block instructions Edited document to include the GIA 63W Corrected WAAS TSO Added RTCA/DO-229C deviation Added Comant antennas Added Comant antenna and revised ICAW Added the 011-01105-01 unit Changed operational limitations and added antennas Added ETSO information Added TSO-C92c and other TSO info Added Level A CLD information Added antenna note Added standalone rack info Added updated NAV/COM unit Added GIA 63H model info, changed doc title Added GIA 63W and 63H ETSOs Added TSO-C54 Added -40 GIA 63W Revision Date 11/15/04 3/16/05 6/23/05 10/26/05 6/8/06 7/21/06 9/19/06 10/18/06 4/10/07 6/6/07 8/23/07 2/29/08 5/27/09 9/09/09 12/29/09 3/23/10 7/29/10 11/24/10 12/27/11 8/23/12 11/12/12 Revision A B C D E F G H J K L M N P Q R S T U V W 190-00303-05 Rev. W GIA 63 Installation Manual Page A DRAFT CURRENT REVISION DESCRIPTION Revision Page Number(s) Section Number Description of Change W 1-3 1-6 1-9 1-10 1-11 1-12 1-34 - 1-39 1-41 - 1-43 1-46 1-47 2-1 2-2 2-3 2-3 2-6 2-9 2-13 2-14 3-6 4-1 - 4-5 4-24 4-25 - 4-27 4-28 - 4-30 1.4.2 1.4.6 1.4.10 1.4.11 1.5 1.6 1.6.8 & 1.6.9 1.6.10.2 1.6.12 1.7 2.1.1 2.1.2 2.1.3 2.1.3.2 2.2.1 2.2.3 2.7 2.8.1 3.8 4 4.6.1 4.6.2.3 - 4.6.2.5 4.7.1 - 4.7.2.7 Specified unit and connector weights Specified squelch specifications Specified power requirements Added -40 unit, edited RTCA reference, and added note Specified emission type for each unit Replaced WAAS with LNAV/VNAV, LP, and LPV and added software specific paragraph Added -40 TSOs and TSO deviations Added TSOs and edited AC references Specified regulatory specs by unit Added GDR 66 Installation Manual reference Added -40 unit Added IF Seal kit Added TSOs and specified units Clarified software version and corrected section reference Standardized antenna wording Clarified Com antenna location wording Added TSO Added Mounting Limitations section Edited RTCA reference and added -40 unit Added -40 pins Specified functions based on unit and software Clarified spec descriptions and added -40 pins Added -40 pins DOCUMENT PAGINATION Section Page Range Table of Contents Section 1 Section 2 Section 3 Section 4 Section 5 Appendix A Appendix B Appendix C i viii 1-1 1-48 2-1 2-18 3-1 3-8 4-1 4-40 5-1 5-6 A-1 A-4 B-1 B-6 C-1 C-7 190-00303-05 Rev. W GIA 63 Installation Manual Page i 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 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. GIA 63 Installation Manual Page ii 190-00303-05 Rev. W DRAFT Limited Warranty All Garmin avionics products are warranted to be free from defects in materials or workmanship for: two 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 E. 151st Street Olathe, KS 66062, U.S.A. Phone: 800/800.1020 FAX: 913/397.0836 Garmin (Europe) Ltd. Liberty House Bulls Copse Road Hounsdown Business Park Southampton, SO40 9RB, UK Telephone: 44 (0) 8708501241 190-00303-05 Rev. W GIA 63 Installation Manual Page iii DRAFT 1 GENERAL DESCRIPTION ...........................................................................1-1 1.1 Introduction ..................................................................................................................... 1-1 1.2 Equipment Description.................................................................................................... 1-1 1.3 Interface Summary .......................................................................................................... 1-2 1.4 Technical Specifications.................................................................................................. 1-3 1.5 License Requirements.................................................................................................... 1-11 1.6 Certification................................................................................................................... 1-12 1.7 Reference Documents.................................................................................................... 1-47 2 INSTALLATION OVERVIEW......................................................................2-1 2.1 Introduction ..................................................................................................................... 2-1 2.2 Installation Considerations .............................................................................................. 2-6 2.3 Rack Considerations...................................................................................................... 2-10 2.4 Cabling and Wiring ....................................................................................................... 2-11 2.5 Cooling Air.................................................................................................................... 2-11 2.6 GIA 63 Minimum Installation Requirements................................................................ 2-12 2.7 GIA 63W and GIA 63H Minimum Installation Requirements ..................................... 2-13 2.8 Mounting Requirements ................................................................................................ 2-14 3 INSTALLATION PROCEDURE...................................................................3-1 3.1 Unpacking Unit................................................................................................................ 3-1 3.2 Wiring Harness Installation ............................................................................................. 3-2 3.3 Antenna Installation......................................................................................................... 3-3 3.4 Cable Installation............................................................................................................. 3-3 3.5 Backshell Assembly ........................................................................................................ 3-4 3.6 Unit Installation ............................................................................................................... 3-4 3.7 Post Installation Configuration & Checkout ................................................................... 3-5 3.8 Continued Airworthiness................................................................................................. 3-6 4 SYSTEM INTERCONNECTS........................................................................4-1 4.1 Pin Function List ............................................................................................................. 4-1 4.2 Power and Antennas ...................................................................................................... 4-17 4.3 GIA System ID Program ............................................................................................... 4-19 4.4 Serial Data ..................................................................................................................... 4-19 4.5 Discrete I/O.................................................................................................................... 4-23 4.6 COM/VOR/ILS/Digital Audio ...................................................................................... 4-24 4.7 VOR/ILS Indicator ........................................................................................................ 4-28 4.8 RMI/OBI........................................................................................................................ 4-32 4.9 DME Tuning and ADF.................................................................................................. 4-33 4.10 Auto Pilot..................................................................................................................... 4-35 GIA 63 Installation Manual Page iv 190-00303-05 Rev. W DRAFT Appendix A GIA 63 MAIN BOOT BLOCK UPLOADING INSTRUCTIONS .....A-1 A.1 Introduction.................................................................................................................... A-1 A.2 Determining Current Boot Block................................................................................... A-1 A.3 Loading Boot Block Version 4.01................................................................................. A-2 A.4 Loading GIA Main Software (only if GIA main software was cancelled in Section A.2)A-3 Appendix B OUTLINE AND INSTALLATION DRAWINGS................................B-1 Appendix C INTERCONNECT DRAWINGS...........................................................C-1 190-00303-05 Rev. W GIA 63 Installation Manual Page v DRAFT GIA 63 HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification (Mod) Levels for the GIA 63. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice. Authorized Garmin Sales and Service Centers are encouraged to access the most up-to-date bulletin and advisory information on the Garmin Dealer Resource web site at www.garmin.com using their Garmin-provided user name and password. GIA 63 P/N 011-00781-00, 011-00781-01 HARDWARE MOD LEVEL HISTORY APPLICABLE LRU PART NUMBER MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION 1 2 3 4 1 0416 9/13/2004 0418 9/8/2004 0505 1/19/2005 N/A N/A N/A N/A This modification consists of modifying the voice alert audio output circuit, enabling it to power down when not in use. This Service Bulletin consists of visually inspecting the GIA 63 Main2 board for incorrectly installed capacitors. This modification addresses a potential GIA 63 COM transceiver interference condition. More robust capacitors installed in the power supply backup circuit. More robust capacitors installed in the power supply backup circuit. 011-00781-00 011-00781-01 GIA 63 Installation Manual Page vi 190-00303-05 Rev. W DRAFT GIA 63W/GIA 63H HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification (Mod) Levels for the GIA 63W and GIA 63H. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice. Authorized Garmin Sales and Service Centers are encouraged to access the most up-to-date bulletin and advisory information on the Garmin Dealer Resource web site at www.garmin.com using their Garmin-provided user name and password. GIA 63W/GIA 63H P/N 011-01105-XX HARDWARE MOD LEVEL HISTORY APPLICABLE LRU PART NUMBER MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION 011-01105-00 011-01105-01 011-01105-20 011-01105-30 1 N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A N/A More robust capacitors installed in the power supply backup circuit. N/A N/A N/A 190-00303-05 Rev. W GIA 63 Installation Manual Page vii DRAFT This page intentionally left blank GIA 63 Installation Manual Page viii 190-00303-05 Rev. W DRAFT 1 GENERAL DESCRIPTION 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 GIA 63(X) into an aircraft. 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. NOTE Garmin recommends installation of the GIA 63(X) 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 GIA 63(X). For questions, please contact Garmin Aviation Product Support at 1-888-606-5482. 1.2 Equipment Description The GIA 63(X) is a microprocessor-based input/output Line Replaceable Unit (LRU) used in a Garmin Integrated Flight Deck. The GIA 63(X) communicates with the GDU via Ethernet high-speed data bus
(HSDB), and with other LRUs using RS-232, RS-485/422, and ARINC 429. All configuration is done through the GDU. The GIA 63(X) contains the following sub-assemblies:
A main processor that interfaces with all LRUs in the G1000 sub-system and performs calculations for the GFC 700 autopilot (if equipped). A twelve channel parallel GPS receiver that simultaneously tracks and uses up to 12 satellites. The GIA 63W and GIA 63H include a 15 channel WAAS certified GPS receiver. A VHF COM transceiver that provides tuning from 118.00 to 136.992 MHz in 25 kHz or 8.33 kHz spacing for 760 or 2280 channel configuration respectively. A VOR/ILS localizer receiver that provides tuning from 108.00 to 117.95 MHz in 50 kHz increments. An ILS glideslope receiver that provides tuning from 328.6 to 335.4 MHz as paired with the frequency tuned on the VOR/ILS localizer receiver. CAUTION The operation of unapproved cellular telephones or other unapproved cellular devices aboard aircraft while airborne is prohibited by FCC rules. Due to the potential for interference with onboard systems, the operation of unapproved cellular communication devices while onboard an aircraft that is on the ground is subject to FAA regulations 14 CFR 91.21. FCC regulation 47 CFR 22.925 prohibits airborne operation of unapproved cellular telephones installed in or carried aboard aircraft. Unapproved cellular telephones must not be operated aboard any aircraft while the aircraft is off the ground. When any aircraft leaves the ground, all unapproved cellular telephones on board that aircraft must be turned off. Unapproved cellular telephones that are on, even in a monitoring state, can disrupt GPS performance. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-1 DRAFT 1.3 Interface Summary 1.3.1 Primary Interfaces The GIA 63(X) is designed as an open architecture system that provides the following interfaces:
1 dedicated Ethernet High-Speed Data Bus (HSDB) input/output channel 2 Controller Area Network (CAN) I/O channels 8 Main ARINC 429 inputs 3 Main ARINC 429 outputs 1 VOR/ILS ARINC 429 input 1 VOR/ILS ARINC 429 output 5 RS-485 input/output channels (any two RS-485 channels can be configured to form a single RS-422 channel) 8 RS-232 input/output channels 41 Discrete inputs 14 Discrete outputs 24 Annunciator outputs 1.3.2 Additional Interfaces The GIA 63(X) can provide interfaces for the following additional equipment:
Autopilot Altitude encoder/serializer Fuel management systems Lightning detection systems Traffic awareness systems Data link systems DME (including King Serial) ADF External annunciators GIA 63 Installation Manual Page 1-2 190-00303-05 Rev. W 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 GIA 63(X) Environmental Qualification Form. This form is available directly from Garmin under the following part number:
GIA 63 Environmental Qualification Form, Garmin part number 005-00148-02 GIA 63W Environmental Qualification Form, Garmin part number 005-00235-00 The GIA 63H and the GIA 63W are included in the 005-00235-00. 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. GIA 63(X) Physical Characteristics Characteristic Modular Rack Width Modular Rack Height Standalone Rack Width Standalone Rack Height Depth w/connectors (Modular and Standalone) Specification 3.83 inches (97.3 mm) 7.26 inches (184.4 mm) 3.88 inches (98.5 mm) 6.91 inches (175.5 mm) 10.20 inches (259.1 mm) Unit Weight Modular Rack Weight w/Back Plate Standalone Rack Weight w/Back Plate Helicopter Rack Width Helicopter Rack Height Depth w/connectors (Helicopter) Unit Weight (Helicopter) Helicopter Rack Weight w/Back Plate Connector Kit Weight*
011-00781-0X: 5.3 lbs. (2.40 kg) 011-01105-0X/-1X/-2X: 5.3 lbs. (2.40 kg) 011-01105-4X: 5.5 lbs. (2.49 kg) 1.0 lbs. (0.45 kg) 1.3 lbs. (0.59 kg) 3.76 inches (95.4 mm) 7.00 inches (177.8 mm) 10.18 inches (258.6 mm) 011-01105-3X: 5.4 lbs (2.45 kg) 1.6 lbs (0.74 kg) 011-01000-00: 1.3 lbs (0.59 kg) 011-01000-01: 1.1 lbs (0.50 kg) 011-01000-03: 1.1 lbs (0.50 kg)
* Only the GIA 63H unit (011-01105-3X) together with the Helicopter Rack (011-02425-00), Back Plate (011-00963-01), and Connector Kit
(011-01000-01) is approved for DO-160F, Category U, Curve G vibration levels. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-3 DRAFT 1.4.3 General Specifications For detailed specifications, see the Environmental Qualification Form. Table 1-2. GIA 63(X) General Specifications Characteristic Specification Operating Temperature Range Humidity Altitude Range
-40C to +65C. For more details see Environmental Qualification Form 95% non-condensing
-1,500 ft to 50,000 ft GIA 63 Installation Manual Page 1-4 190-00303-05 Rev. W DRAFT 1.4.4 GPS Specification (GIA 63 only) Table 1-3. GIA 63 GPS Specifications Characteristic Specification a) Search-the-Sky (without almanac, without initial position or time): 5 minutes b) AutoLocate (with almanac, without initial position or time): 5 minutes c) Cold Start (position known to 300 nm, time known to 10 minutes, with valid almanac): 45 seconds d) Warm Start (position known to 10 nm, time known to 10 minutes, with valid almanac and ephemeris): 15 seconds 1000 knots 6g 20 mA typical, 40 mA max at 4.6 VDC Acquisition Times Max Velocity Dynamics Antenna power supply 1.4.5 WAAS Specific GPS Specifications (GIA 63W & GIA 63H) Table 1-4. GIA 63W and GIA 63H GPS Specifications Characteristic Number of channels Frequency Sensitivity
(acquisition) Sensitivity
(drop lock) Lat/Long position accuracy Velocity TTFF (time to first fix) Reacquisition Position update interval 1 pps (pulse per second) Datum SATCOM compatibility Specification 15 (12 GPS and 3 GPS/WAAS/SBAS) 1575.42 MHz L1, C/A code
-116 dBm to -134.5 dBm GPS
-116 dBm to -134.5 dBm WAAS
-144 dBm
<1.25 meter RMS horizontal, <2 meter vertical, with WAAS 1000 knots maximum (above 60,000 ft) 1:45 min. typical with current almanac, position, and tim 10 seconds typical for signal outages of 30 seconds or less 0.2 sec (5 Hz) 275 nsec of UTC second during steady-state navigation WGS-84 Compatible on aircraft equipped with SATCOM (see Section 2.1.3.2 for SATCOM compatible antennas) Antenna power supply at GPS port 4.3 VDC to 4.8 VDC @ 60 mA 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-5 DRAFT 1.4.6 COM Transceiver Specifications Table 1-5. GIA 63(X) COM Transceiver Specifications Characteristic Audio Output Audio Response Audio Distortion AGC Characteristics Sensitivity 25 kHz Channel Squelch 8.33 kHz Channel Squelch Selectivity Spurious Response Transmitter Power Specification 100 mW minimum into a 500 load Less than 6 dB of variation between 350 and 2500 Hz The distortion in the receiver audio output shall not exceed 25% at all levels up to 100 mW The audio output shall not vary by more than 6 dB when the level of the RF input signal, modulated 30% at 1000 Hz, is varied from 5 V to 100,000 V
(hard)
(S+N)/N on all channels shall be greater than 6 dB when the RF level is 2 V
(hard) modulated 30% at 1000 Hz at rated audio 2 v (hard) 6 dB 011-00781-0X and 011-01105-0X:
3 v (hard) 6 dB 011-01105-2X/-3X/-4X:
2 v (hard) 6 dB 6 dB BW is greater than 8 kHz for 25 kHz channeling 60 dB BW is less than 25 kHz for 25 kHz channeling 6 dB BW is greater than 2.778 kHz for 8.33 kHz channeling 60 dB BW is less than 7.37 kHz for 8.33 kHz channeling Greater than 80 dB At Least 16 watts when Vin = 28 VDC At least 10 watts when Vin = 14 VDC (011-01105-2X and 011-01105-3X only) Transmitter Duty Cycle Recommended 10% maximum Modulation Capability*
Carrier Noise Level Frequency Stability Demodulated Audio Distortion Sidetone Demodulated Audio Response The modulation shall not be less than 70% and not greater than 99.9% with a standard modulator signal applied to the transmitter Shall be at least 45 dB (S+N)/N 0.0005%
Less than 10% distortion when the transmitter is modulated at least 70%
1.4 VRMS into a 500 load when the transmitter is modulated at least 70%
Shall be less than 6 dB when the audio input frequency is varied from 350 to 2500 Hz
*When utilizing the configurable microphone gain adjustments, the modulation capability specification can be met with a 70 mVrms to 3.0 Vrms analog microphone input signal applied to the transmitter. When a digital audio microphone signal is provided by a compatible Garmin audio panel, the modulation capability specification can be met with a minimum 70 mVrms microphone input signal applied to the audio panel. GIA 63 Installation Manual Page 1-6 190-00303-05 Rev. W DRAFT 1.4.7 VOR Specifications Characteristic Receiver Audio Sensitivity Course Deviation Sensitivity Flag AGC Characteristics Spurious Response VOR OBS Bearing Accuracy Audio Output Audio Response Audio Distortion Selectivity Table 1-6. GIA 63(X) VOR Specifications Specification At -103.5 dBm (S+N)/N shall not be less than 6 dB At 103.5 dBm deviation output shall not be less than 60% of standard deflection (90 mV) when a VOR deviation test signal is applied (10 degrees course difference) The VLOC Course Deviation Flag must be flagged:
a) in the absence of an RF signal b) in the absence of the 9960 Hz modulation c) in the absence of either one of the two 30 Hz modulations d) When the level of a standard VOR deviation test signal produces less than a 50% of standard deflection From -99 dBm to -13 dBm input of a Standard VOR Audio Test Signal, audio output levels shall not vary more than 3 dB Greater than 60 dB The bearing information as presented to the pilot shall not have an error in excess of 2.7 as specified by RTCA DO-196 and EuroCAE ED-22B A minimum 100 mW into a 500 load Less than 6 dB of variation between 350 and 2500 Hz. In voice mode, an ident tone of 1020 Hz shall be attenuated at least 20 dB The distortion in the receiver audio output shall not exceed 10% at all levels up to 100 mW 6 dB BW is greater than 16.5 kHz 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-7 DRAFT 1.4.8 LOC Specifications Characteristic Receiver Audio Sensitivity Course Deviation Sensitivity Flag AGC Characteristics Selectivity Standard Deflection Spurious Response Centering Accuracy Audio Output Audio Response Audio Distortion Table 1-7. GIA 63(X) LOC Specifications Specification At -103.5 dBm (S+N)/N shall not be less than 6 dB At 103.5 dBm, deviation output shall not be less than 60% of standard deflection when a LOC deviation test signal is applied The VLOC Course Deviation Flag must be flagged:
a) When the level of a standard deviation test signal produces 50% or less of standard deflection of the deviation indicator b) In the absence of 150 Hz modulation c) In the absence of 90 Hz modulation d) In the absence of both 90 Hz and 150 Hz modulation e) In the absence of RF From 99 dBm and 13 dBm input of a Standard VOR Audio Test Signal, audio output levels shall not vary more than 3 dB 6 dB BW is greater than 9 kHz 69 dB BW is less than 36 kHz a) With a standard deflection FLY LEFT condition (90 Hz dominant), the output shall be +90 mV 9 mV b) With a standard deflection FLY RIGHT condition (150 Hz dominant), the output shall be -90 mV 9 mV Greater than 60 dB Typical 0 3 mV (Max error 9.9 mV per RTCA DO-195) A minimum 100 mW into a 500 load Less than 6 dB of Variation between 350 and 2500 Hz. In voice mode, an ident tone of 1020 Hz shall be attenuated at least 20 dB The distortion in the receiver audio output shall not exceed 10% at all levels up to 100 mW GIA 63 Installation Manual Page 1-8 190-00303-05 Rev. W DRAFT 1.4.9 Glideslope Specifications Characteristic Sensitivity Centering Accuracy Selectivity Standard deflection Flag Table 1-8. GIA 63(X) Glideslope Specifications Specification At 93 dBm, deviation output shall not be less than 60% of standard deflection when glideslope deviation test signal is applied 0 .0091 ddm or 0 7.8 mV 6 dB BW is greater than 17 kHz 69 dB BW is less than 132 kHz a) With a standard deflection FLY DOWN condition (90 Hz dominant), the output shall be -78 mV 7.8 mV b) With a standard deflection FLY UP condition (150 Hz dominant), the output shall be +78 mV 7.8 mV The GS Course Deviation Flag must be flagged:
a) When the level of a standard deviation test signal produces 50% or less of standard deflection of the deviation indicator b) In the absence of 150 Hz modulation c) In the absence of 90 Hz modulation d) In the absence of both 90 Hz and 150 Hz modulation e) In the absence of RF 1.4.10 Power Requirements Table 1-9. GIA 63(X) Power Specifications Characteristic Specification Input Voltage Range Power Requirements for P601
(COM Connector) For P601:
011-00781-0X and 011-01105-0X: 28 Vdc 011-01105-2X/-3X: 14/28 Vdc 011-01105-4X: 28 Vdc For P605:
011-00781-0X and 011-01105-0X/-1X/-2X/-3X: 14/28 Vdc 011-01105-4X: 28 Vdc See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages. 011-00781-0X and 011-01105-0X/-2X/-3X:
0.3 A max @ 27.5 Vdc (not transmitting);
4.3 A max @ 27.5 Vdc (transmitting) 011-01105-4X:
0.4 A max @ 27.5 Vdc (not transmitting);
4.4 A max @ 27.5 Vdc (transmitting) 011-01105-2X/-3X only:
0.6 A max @ 13.75 Vdc (not transmitting);
6.0 A max @ 13.75 Vdc (transmitting) 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-9 DRAFT Table 1-9. GIA 63(X) Power Specifications Characteristic Specification Power depends upon loads present on Superflag output pins
(see Sections 4.7.2.1 and 4.10.7) Superflag Power Requirements for P605
(Main 2 Connector) Power Requirements for P605
(Main 2 Connector)
*Only 011-01105-20 and 011-01105-30 units support both 14 Vdc and 28 Vdc COMs. All other units only support 28 Vdc COMs. 1.0 A max @ 27.5 Vdc (Without Superflags Active) 2.0 A max @ 13.75 Vdc (Without Superflags Active) 1.4.11 Power Interrupt Table 1-10. GIA 63(X) Power Interrupt Unit Name Unit Part Number Mod Status*
Long Term Power Interrupt Category Per RTCA DO-160**
GIA 63 GIA 63W 011-00781-00 011-00781-01 011-01105-00 011-01105-01 011-01105-20 011-01105-40 011-01105-30 4 0, 1, 2, 3 1 0 1 0 0 0 0 0 A (200mS) B (50mS) A (200mS) B (50mS) A (200mS) B (50mS) A (200mS) A (200mS) A (200mS) A (200mS) GIA 63H
*Refer to Mod Status Table in front of manual for applicable mod levels.
**Refer to Section 3.8 for Continued Airworthiness. The DO-160 revision used for qualification of each unit is specified in the applicable environmental qualification form. GIA 63 Installation Manual Page 1-10 190-00303-05 Rev. W DRAFT 1.5 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 GIA 63(X) 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. Transmitter Description:
Antenna Characteristics:
Rated Power:
Aviation-band VHF transceiver with 25 and 8.33 kHz channel spacing. Broad band, 50 ohm, vertically polarized. 16 Watts (28 VDC Operation) 10 Watts (14 VDC Operation; 011-01105-2X and -3X only) 6K00A3E (25 kHz Channel Spacing Mode) 5K6A3E (8.33 kHz Channel Spacing Mode; 011-01105-2X/-3X/-4X only) 118.000 136.992 MHz Frequency of Operation:
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 GIA 63(X) 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. Emission Type:
CAUTION 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. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-11 DRAFT 1.6 Certification The GIA 63 GPS receiver is certified for IFR enroute, terminal, and non-precision approaches. The GIA 63W and the GIA 63H GPS receivers are certified for LNAV/VNAV, LP, and LPV approaches. The GIA 63(X) has been qualified to RTCA/DO-160 Section 20 RF susceptibility and Section 22 lightning requirements. Special installation considerations are required, refer to the Environmental Qualification Form. The GIA 63(X) meets the requirements for GPS as a Primary Means of Navigation for Oceanic/Remote Operations per FAA Notice N8110.60. The GIA 63(X) is eligible for B-RNAV in accordance with AMC 20-4. Eligible for PRNAV in accordance with PRNAV requirements: JAA Administrative & Guidance Material Section One: General Part 3: Temporary Guidance Leaflets, Leaflet No 10: Airworthiness and Operational Approval for Precession RNAV Operations in Designated European Airspace 7.1 Required Functions. The GIA 63(X) with main software version 7.00 or later and GPS software version 5.0 or later have been shown to comply with AC 20-165 Appendix 2 and AC 20-138C Appendix 4 and are eligible for use as an ADS-B Out Position Source meeting the requirements of 14 CFR 91.227 when installed in accordance with Garmins installation instructions. 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. The quantitative safety objective for the VHF Comm radio in the GIA 63W and the GIA 63H is 1 X 10-4 per flight hour for Class I Part 23 Airplanes, and 1 X 10-5 per flight hour for all other Part 23 airplanes and Parts 25, 27, and 29 aircraft. GIA 63 Installation Manual Page 1-12 190-00303-05 Rev. W DRAFT 1.6.1 GIA 63 TSO/ETSO Compliance Table 1-11. GIA 63 TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Automatic Pilots TSO-C9c ETSO-C9c Glideslope Receiver TSO-C34e ETSO-2C34f Localizer Receiver TSO-C36e ETSO-2C36f Class A VHF COM Transmitter TSO-C37d ETSO-2C37e Class 3 and 5 VHF COM Receiver TSO-C38d ETSO-2C38e Class C and E VOR Receiver TSO-C40c ETSO-2C40c Flight Director Equipment TSO-C52b ETSO-C52b All 006-B0190-() except 006-B0190-00 through 006-B0190-19 All 006-B0190-() except 006-B0190-00 through 006-B0190-04 All 006-B0190-() except 006-B0190-00 through 006-B0190-04 All 006-B0190-() except 006-B0190-00 through 006-B0190-04 All 006-B0190-() except 006-B0190-00 through 006-B0190-04 All 006-B0190-() except 006-B0190-00 through 006-B0190-04 006-B0083-01 006-B0082-02 All 006-B0081-0() except 006-B0081-00 through 006-B0081-04 All 006-B0081-0() except 006-B0081-00 through 006-B0081-04 006-B0082-02 All 006-B0190-() except 006-B0190-00 through 006-B0190-19 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0053-00 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0053-00 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-13 DRAFT Table 1-11. GIA 63 TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Ground Proximity Warning Glide Slope Deviation Alerting Equipment TSO-C92c GPS TSO-C129a ETSO-C129a Class A1 TSO-C151b Class A and B TAWS ETSO-C151a Class B All 006-B0190-() except 006-B0190-00 through 006-B0190-29 All 006-B0190-() except 006-B0190-00 through 006-B0190-04 006-B0093-00 006-B0093-01 All 006-B0190-() except 006-B0190-00 through 006-B0190-29 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 006-C0046-() 006-C0044-() 006-C0047-() 006-C0046-() 006-C0044-() 006-C0047-() 006-C0039-01 GIA 63 Installation Manual Page 1-14 190-00303-05 Rev. W DRAFT 1.6.2 GIA 63 TSO/ETSO Deviations TSO/ETSO TSO-C9c ETSO-C9c TSO-C34e TSO-C36e TSO-C37d TSO-C38d TSO-C40c TSO-C52b ETSO-C52b Table 1-12. GIA 63 TSO/ETSO Deviations Deviation 1. Garmin was granted a deviation from TSO-C9c to use SAE AS 402B instead of AS-402A. 2. Garmin was granted a deviation from TSO-C9c to use DO-160D instead of specified environmental tests. 3. Garmin was granted a deviation from TSO-C9c subpart A (c), which requires marking the weight of the unit on the unit. Garmin will provide this information in the installation manual in lieu of marking on the serial tag. Garmin does not currently list the weight on other avionics units. 4. Garmin was granted a deviation from SAE AS 402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 5. Garmin was granted a deviation from SAE AS 402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 1. Garmin was granted a deviation from ETSO-C9c to use SAE AS-402B instead of AS-402A. 2. Garmin was granted a deviation from ETSO-C9c to use DO-160D instead of the specified environmental tests. 3. Garmin was granted a deviation from AS-402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 4. Garmin was granted a deviation from AS-402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 1. Garmin was granted a deviation from TSO-C34e to use DO-160D Change 3 instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from TSO-C36e to use DO-160D Change 3 instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from TSO-C37d to use DO-160D Change 3 instead of DO-160B, and DO-178B instead of DO-178A. 2. Garmin was granted a deviation from TSO-C37d paragraph (a)(1) to allow using RTCA document DO-186a Change 2 instead of RTCA document DO-186 to specify minimum performance standards. 3. Garmin was granted a deviation from TSO-C37d by allowing a 6dB reduction of transmitter power during the Normal Operating Conditions - Emergency Operation Voltage as described in RTCA document DO-186a paragraph 2.5.13.1 and RTCA document DO-160C paragraph 16.5.2.1. 4. Garmin was granted a deviation from TSO-C37d paragraph (a)(5) to allow 8.33 kHz spacing in addition to the 25 kHz spacing. 5. Garmin was granted a deviation from TSO-C37d paragraph (b)(1) to allow the marking to call out 8.33 kHz spacing in addition to the 25 kHz spacing. 1. Garmin was granted a deviation from TSO-C38d to use DO-160D Change 3 instead of DO-160B, and DO-178B instead of DO-178A. 2. Garmin was granted a deviation from TSO-C38d paragraph (a)(1) to allow using RTCA document DO-186a Change 2 instead of RTCA document DO-186 to specify minimum performance standards. 3. Garmin was granted a deviation from TSO-C38d paragraph (a)(5) to allow 8.33 kHz spacing in addition to the 25 kHz spacing. 1. Garmin was granted a deviation from TSO-C40c to use DO-160D Change 3 instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from SAE AS 8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 2. Garmin was granted a deviation from TSO-C52b to use DO-160D instead of DO-160C. 1. Garmin was granted a deviation from AS-8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-15 DRAFT TSO/ETSO TSO-C92c TSO-C129a ETSO-C129a TSO-C151b Table 1-12. GIA 63 TSO/ETSO Deviations Deviation 1. Garmin was granted a deviation from TSO-C92c to use DO-160D Change 3 instead of DO-160C. 2. Garmin was granted a deviation from TSO-C92c to not include the version and levels of software or the modification status of hardware in the appliance number. 1. Garmin was granted a deviation from TSO-C129a to use DO-160D Change 3 instead of DO-
160C. 2. Garmin was granted a deviation from TSO-C129a to eliminate the annunciation for pending CDI scale change 3.0 NM from the FAF. 3. Garmin was granted a deviation from TSO-C129a involving the use of GPS calibrated altitude in approach mode based on the enclosed TSO deviation request dated August 24, 1994 and the approval letter dated November 29, 1994. 4. Garmin was granted a deviation from TSO-C129a to extend automatic CDI sensitivity changes to non-approach mode navigation. 5. Garmin was granted a deviation from TSO-C129a to eliminate the requirement in (a)(3)(xi)1.b.ii to alert the pilot of the need to manually insert the barometric pressure. 6. Garmin was granted a deviation from TSO-C129a to eliminate the requirement in (a)(3)(xv)4.b to provide a means to manually identify a satellite that is expected to be unavailable at the destination
(for scheduled maintenance as identified in FAA Notice to Airmen) shall be provided for the RAIM prediction process. 7. Garmin was granted a deviation from TSO-C129a to change the requirement in (a)(6)(iii) from The navigation data contains all 1s or 0s to All data bits in subframe 1, 2, or 3 are 0s. 8. Garmin was granted a deviation from TSO-C129a to change the requirement in paragraph
(a)(7)(ii) to match the WAAS TSO-C145a and DO-229 requirements for Power input testing. 1. Garmin was granted a deviation from ED-72A 3.2.2.1.f (list item 3) and 3.2.2.4.j.4 to eliminate the annunciation for pending CDI scale change 3.0 nm from the FAF. 2. Garmin was granted a deviation from ED-72A 3.2.2.4.j.3 to extend automatic CDI sensitivity changes for approach mode navigation to non-approach mode navigation as well. 3. Garmin was granted a deviation from ED-72A 3.2.2.1.f (list item 4) and 3.2.2.3.e.4 and 3.2.2.4.j.2 to eliminate the requirement to alert the pilot of the need to manually insert the barometric pressure. 4. Garmin was granted a deviation from ED-72A 3.2.2.3.d.2 to eliminate the requirement to provide a means to manually identify a satellite that is expected to be unavailable at the destination (for scheduled maintenance as identified in FAA Notice to Airmen) for the RAIM prediction process. 5. Garmin was granted a deviation from ED-72A 3.1.4.1.c to change the requirement from the navigation data contains all 1s or 0s to all data bits in subframe 1,2, or 3 are 0s. 6. Garmin was granted a deviation from ED-72A 4.16.2 to eliminate the requirement for valid position within 10 seconds of power interrupt for abnormal operating conditions power input tests. For abnormal operating conditions power input tests, satellite acquisition time of 5 minutes applies. 1. Garmin was granted a deviation from TSO-C151b 4.a. to mark the unit with the serial number instead of the date of manufacture. GIA 63 Installation Manual Page 1-16 190-00303-05 Rev. W DRAFT 1.6.3 GIA 63W TSO/ETSO Compliance Table 1-13. GIA 63W TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Automatic Pilots TSO-C9c ETSO-C9c Glideslope Receiver TSO-C34e ETSO-2C34f All 006-B0544-1() through 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-B0544-1() through All 006-B0544-4() 006-B0083-0() and all except 006-B0544-B() 006-B0083-00 except through 006-B0544-BA 006-B0083-01 through 006-B0544-BB Localizer Receiver TSO-C36e ETSO-2C36f 006-B0544-1() through 006-B0544-4() and all Class A 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-B0082-0() except 006-B0082-00 through 006-B0082-02 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0053-0() except 006-C0053-00 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-17 DRAFT Table 1-13. GIA 63W TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers VOR Receiver TSO-C40c ETSO-2C40c Flight Director Equipment TSO-C52b ETSO-C52b Stall Warning Instruments TSO-C54 Type II All 006-B0544-1() through All 006-B0544-4() 006-B0082-0() and all except 006-B0544-B() 006-B0082-00 except through 006-B0544-BA 006-B0082-02 through 006-B0544-BB All 006-B0544-1() through 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0053-0() except 006-C0053-00 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() GIA 63 Installation Manual Page 1-18 190-00303-05 Rev. W DRAFT Table 1-13. GIA 63W TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Ground Proximity Warning Glide Slope Deviation Alerting Equipment Airborne Navigation Sensors Using the Global Positioning System Augmented by the Wide Area Augmentation System*
TAWS TSO-C92c ETSO-C92c TSO-C145a ETSO-C145 Class 3 TSO-C151b ETSO-C151a Class B TSO-C151b ETSO-C151b Class A and B All 006-B0544-3() through 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-B0544-1() through All 006-B0544-4() 006-B0339-0() and all except 006-B0544-B() 006-B0339-00 except through 006-B0544-BA 006-B0339-03 through 006-B0544-BB All 006-B0544-1() through 006-B0544-2() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-B0544-3() through 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BB All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-19 DRAFT Table 1-13. GIA 63W TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers VHF Radio Communications Transceiver Equipment TSO-C169 Equivalent to ETSO-2C37e
ETSO-2C38e Class 3 and 5
(transmitter) Class C and E
(receiver) All 006-B0544-1() through All 006-B0544-4() 006-B0081-0() and all except 006-B0544-B() 006-B0081-00 except through 006-B0544-BA 006-B0081-04 through 006-B0544-BB All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0039-0() except 006-C0039-00 through 006-C0039-02
*GIA63W ARINC output labels 310 and 311 are not to be used as navigation data per RTCA/DO-229c. GIA 63 Installation Manual Page 1-20 190-00303-05 Rev. W DRAFT 1.6.4 GIA 63W TSO/ETSO Deviations TSO/ETSO TSO-C9c ETSO-C9c TSO-C34e ETSO-2C34f TSO-C36e ETSO-2C36f ETSO-2C37e ETSO-2C38e TSO-C40c ETSO-2C40c TSO-C52b ETSO-C52b TSO-C54 Table 1-14. GIA 63W TSO/ETSO Deviations Deviation 1. Garmin was granted a deviation from TSO-C9c to use SAE AS 402B instead of AS-402A. 2. Garmin was granted a deviation from TSO-C9c to use DO-160E instead of specified environmental tests. 3. Garmin was granted a deviation from TSO-C9c subpart A (c), which requires marking the weight of the unit on the unit. Garmin will provide this information in the installation manual in lieu of marking on the serial tag. Garmin does not currently list the weight on other avionics units. 4. Garmin was granted a deviation from SAE AS 402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 5. Garmin was granted a deviation from SAE AS 402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 1. Garmin was granted a deviation from ETSO-C9c to use SAE AS-402B instead of AS-402A. 2. Garmin was granted a deviation from ETSO-C9c to use DO-160E instead of the specified environmental tests. 3. Garmin was granted a deviation from AS-402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 4. Garmin was granted a deviation from AS-402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 1. Garmin was granted a deviation from TSO-C34e to use DO-160E instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from ETSO-2C34f to use DO-160E instead of DO-160D. 1. Garmin was granted a deviation from TSO-C36e to use DO-160E instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from ETSO-2C36f to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-2C36f to use ED-46B amendment 2 in addition to ED 46B. 1. Garmin was granted a deviation from ETSO-2C37e to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-2C37e to use ED-23B amendment 3 in addition to ED-23B. 1. Garmin was granted a deviation from ETSO-2C38e to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-2C38e to use ED-23B amendment 3 in addition to ED-23B. 1. Garmin was granted a deviation from TSO-C40c to use DO-160E instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from ETSO-2C40c to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ED-22B paragraph 5.2.9 to have a deflection response of 0.5 to 2.7 seconds instead of 0.5 to 2 seconds. 1. Garmin was granted a deviation from SAE AS 8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 2. Garmin was granted a deviation from TSO-C52b to use DO-160E instead of DO-160C. The justification for this deviation is to use the latest accepted environmental standards. 1. Garmin was granted a deviation from ETSO-C52b to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from AS-8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 1. Garmin was granted a deviation from TSO-C54 to use RTCA DO-160E instead of SAE AS 403A. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-21 DRAFT TSO/ETSO TSO-C92c ETSO-C92c TSO-C145a ETSO-C145 TSO-C151b ETSO-C151a ETSO-C151b Table 1-14. GIA 63W TSO/ETSO Deviations Deviation 1. Garmin was granted a deviation from TSO-C92c to use DO-160E instead of DO-160C. 2. Garmin was granted a deviation from TSO-C92c to not include the version and levels of software or the modification status of hardware in the appliance number. 1. Garmin was granted a deviation from ETSO-C92c to use DO-160E instead of DO-160D. 1. Garmin was granted a deviation from TSO-C145a to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from RTCA/DO-229C paragraphs 2.1.1.10, 2.1.1.7, 2.1.1.8.1, 2.1.1.8.2, 2.1.1.9, 2.1.2.1, 2.1.3.1, 2.1.4.1.4, 2.1.4.1.5 and 2.1.5.1 in the form of an operational limitation to achieve an equivalent level of safety. This operational limitation applies to the GIA63W with GPS software version 2.40 or earlier, or GIA63W installations with certain models of GPS/WAAS antennas identified in Section 2.1.3.2. The operational limitation is based on:
1. The ability to use antennas that may not meet the minimum gain performance requirements of DO-228. 2. The ability to mitigate the effects of the different gain characteristics of those antennas by increasing the effective mask angle through operational limitations. 3. The ability to further increase the effective mask angle, through operational limitations, to a level commensurate with test conditions used in the original TSO qualification tests. 4. The ability to use -128 dBmic as the minimum GPS satellite signal-in-space for the purpose of assessing the operational limitation. 5. The ability to use -128 dBmic as the minimum SBAS satellite signal-in-space for the purpose of assessing the operational limitation. 3. Garmin was granted a deviation from RTCA/DO-229C paragraph 2.1.1.9 to use a 20 second satellite reacquisition time instead of a 10-second reacquisition time. 1. Garmin was granted a deviation from ETSO-C145 to use DO-160E instead of DO-160D 2. Garmin was granted a deviation from ETSO-C145 to use DO-229C instead of DO-229A 3. Garmin was granted a deviation from DO-229C paragraphs 2.1.1.10, 2.1.1.7, 2.1.1.8.1, 2.1.1.8.2, 2.1.1.9, 2.1.2.1, 2.1.3.1, 2.1.4.1.4, 2.1.4.1.5 and 2.1.5.1 in the form of an operational limitation to achieve an equivalent level of safety. This operational limitation applies to the GIA63W with GPS software version 2.40 or earlier, or GIA63W installations with certain models of GPS/
WAAS antennas identified in Section 2.1.3.2. The operational limitation is based on:
1. The ability to use antennas that may not meet the minimum gain performance requirements of DO-228. 2. The ability to mitigate the effects of the different gain characteristics of those antennas by increasing the effective mask angle through operational limitations. 3. The ability to further increase the effective mask angle, through operational limitations, to a level commensurate with test conditions used in the original TSO qualification tests. 4. The ability to use -128 dBmic as the minimum GPS satellite signal-in-space for the purpose of assessing the operational limitation. 5. The ability to use -128 dBmic as the minimum SBAS satellite signal-in-space for the purpose of assessing the operational limitation. 4. Garmin was granted a deviation from RTCA/DO-229C paragraph 2.1.1.9 to use a 20 second satellite reacquisition time instead of a 10-second reacquisition time. 1. Garmin was granted a deviation from TSO-C151b to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from TSO-C151b 4.a. to mark the unit with the serial number instead of the date of manufacture. 1. Garmin was granted a deviation from ETSO-C151a to use DO-160E instead of DO-160D. 1. Garmin was granted a deviation from ETSO-C151b to use DO-160E instead of DO-160D. GIA 63 Installation Manual Page 1-22 190-00303-05 Rev. W DRAFT TSO/ETSO TSO-C169 Table 1-14. GIA 63W TSO/ETSO Deviations Deviation 1. Garmin was granted a deviation from TSO-C169 to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation to TSO-C169, paragraph 4.d requirement to mark the installation procedures drawing number on the equipment. Garmin will mark as follows, which Garmin believes meets the intent of the requirement. The Install Manual is part of the furnished data package. TSO-C145a See Install Manual for additional appliance approvals 3. Garmin was granted a deviation to TSO-C169, paragraph 4.e requirement to mark (DEV) after the TSO number on the equipment. Garmin will mark as follows, as TSOC169 is not the primary TSO and the Install Manual contains all of the TSO-C169 information including deviations. TSO-C145a See Install Manual for additional appliance approvals 4. Garmin was granted to deviate from TSO-C169 by allowing a 6dB reduction of transmitter power during the Normal Operating Conditions Emergency Operation Voltage as described in RTCA document DO-186a paragraph 2.5.13.1 and RTCA document DO-160E paragraph 16.6.1.1. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-23 DRAFT 1.6.5 GIA 63W Updated NAV/COM TSO/ETSO Compliance Table 1-15. GIA 63W Updated NAV/COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Automatic Pilots TSO-C9c ETSO-C9c Glideslope Receiver TSO-C34e ETSO-2C34f Localizer Receiver TSO-C36e ETSO-2C36f Class A All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0082-1() except 006-B0082-10 All 006-B0082-1() except 006-B0082-10 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-C0124-0() GIA 63 Installation Manual Page 1-24 190-00303-05 Rev. W DRAFT Table 1-15. GIA 63W Updated NAV/COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers VOR Receiver TSO-C40c ETSO-2C40c Flight Director Equipment TSO-C52b ETSO-C52b Stall Warning Instruments TSO-C54 Type II All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0082-1() except 006-B0082-10 All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-C0124-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-25 DRAFT Table 1-15. GIA 63W Updated NAV/COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Ground Proximity Warning Glide Slope Deviation Alerting Equipment TSO-C92c ETSO-C92c All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD GIA 63 Installation Manual Page 1-26 190-00303-05 Rev. W DRAFT Table 1-15. GIA 63W Updated NAV/COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Airborne Navigation Sensors Using the Global Positioning System Augmented by the Wide Area Augmentation System*
TSO-C145a ETSO-C145 Class 3 TAWS TSO-C151b ETSO-C151b Class A and B All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all All 006-B0339-0() except 006-B0339-00 through 006-B0544-B() 006-B0339-03 except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD VHF Radio Communications Transceiver Equipment TSO-C169a Equivalent to ETSO-2C37e
ETSO-2C38e All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-34 and all Class 3, 4, 5, and 6
(transmitter) Class C and E
(receiver) 006-B0544-B() except 006-B0544-BA through 006-B0544-BD 006-B0081-1()
*GIA 63W ARINC output labels 310 and 311 are not to be used as navigation data per RTCA/DO-229c. All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-27 DRAFT 1.6.6 GIA 63H TSO/ETSO Compliance Table 1-16. GIA 63H TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Automatic Pilots TSO-C9c ETSO-C9c Glideslope Receiver TSO-C34e ETSO-2C34f Localizer Receiver TSO-C36e ETSO-2C36f Class A All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0082-1() except 006-B0082-10 All 006-B0082-1() except 006-B0082-10 All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-C0124-0() GIA 63 Installation Manual Page 1-28 190-00303-05 Rev. W DRAFT Table 1-16. GIA 63H TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers VOR Receiver TSO-C40c ETSO-2C40c Flight Director Equipment TSO-C52b ETSO-C52b Stall Warning Instruments TSO-C54 Type II All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0082-1() except 006-B0082-10 All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-C0124-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-29 DRAFT Table 1-16. GIA 63H TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Ground Proximity Warning Glide Slope Deviation Alerting Equipment TSO-C92c ETSO-C92c Airborne Navigation Sensors Using the Global Positioning System Augmented by the Wide Area Augmentation System*
TSO-C145a ETSO-C145 Class 3 TAWS TSO-C151b ETSO-C151b Class A and B All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all All 006-B0339-0() except 006-B0339-00 through 006-B0544-B() 006-B0339-03 except 006-B0544-BA through 006-B0544-BD All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() GIA 63 Installation Manual Page 1-30 190-00303-05 Rev. W DRAFT Table 1-16. GIA 63H TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers VHF Radio Communications Transceiver Equipment TSO-C169a Equivalent to ETSO-2C37e
ETSO-2C38e All 006-B0544-3() through 006-B0544-4() except 006-B0544-30 through 006-B0544-35 and all Class 3, 4, 5, and 6
(transmitter) Class C and E
(receiver) 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-B0081-1()
*GIA 63H ARINC output labels 310 and 311 are not to be used as navigation data per RTCA/DO-229c. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-31 DRAFT 1.6.7 GIA 63W Updated NAV/COM and GIA 63H TSO/ETSO Deviations Table 1-17. GIA 63W Updated NAV/COM and GIA 63H TSO/ETSO Deviations TSO/ETSO TSO-C9c ETSO-C9c TSO-C34e ETSO-2C34f TSO-C36e ETSO-2C36f ETSO-2C37e ETSO-2C38e TSO-C40c ETSO-2C40c TSO-C52b ETSO-C52b TSO-C54 Deviation 1. Garmin was granted a deviation from TSO-C9c to use SAE AS 402B instead of AS-402A. 2. Garmin was granted a deviation from TSO-C9c to use DO-160E instead of specified environmental tests. 3. Garmin was granted a deviation from TSO-C9c subpart A (c), which requires marking the weight of the unit on the unit. Garmin will provide this information in the installation manual in lieu of marking on the serial tag. Garmin does not currently list the weight on other avionics units. 4. Garmin was granted a deviation from SAE AS 402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 5. Garmin was granted a deviation from SAE AS 402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 1. Garmin was granted a deviation from ETSO-C9c to use SAE AS-402B instead of AS-402A. 2. Garmin was granted a deviation from ETSO-C9c to use DO-160E instead of the specified environmental tests. 3. Garmin was granted a deviation from AS-402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 4. Garmin was granted a deviation from AS-402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 1. Garmin was granted a deviation from TSO-C34e to use DO-160E instead of DO-160B, and DO-178B instead of DO-178A 1. Garmin was granted a deviation from ETSO-2C34f to use DO-160E instead of DO-160D. 1. Garmin was granted a deviation from TSO-C36e to use DO-160E instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from ETSO-2C36f to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-2C36f to use ED-46B amendment 2 in addition to ED 46B. 1. Garmin was granted a deviation from ETSO-2C37e to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-2C37e to use ED-23B amendment 3 in addition to ED-23B. 1. Garmin was granted a deviation from ETSO-2C38e to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-2C38e to use ED-23B amendment 3 in addition to ED-23B. 1. Garmin was granted a deviation from TSO-C40c to use DO-160E instead of DO-160B, and DO-178B instead of DO-178A. 1. Garmin was granted a deviation from ETSO-2C40c to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ED-22B paragraph 5.2.9 to have a deflection response of 0.5 to 2.7 seconds instead of 0.5 to 2 seconds. 1. Garmin was granted a deviation from SAE AS 8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 2. Garmin was granted a deviation from TSO-C52b to use DO-160E instead of DO-160C. The justification for this deviation is to use the latest accepted environmental standards. 1. Garmin was granted a deviation from ETSO-C52b to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from AS-8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 1. Garmin was granted a deviation from TSO-C54 to use RTCA DO-160E instead of SAE AS 403A. GIA 63 Installation Manual Page 1-32 190-00303-05 Rev. W DRAFT Table 1-17. GIA 63W Updated NAV/COM and GIA 63H TSO/ETSO Deviations TSO/ETSO TSO-C92c ETSO-C92c TSO-C145a ETSO-C145 TSO-C151b ETSO-C151b TSO-C169a Deviation 1. Garmin was granted a deviation from TSO-C92c to use DO-160E instead of DO-160C. 2. Garmin was granted a deviation from TSO-C92c to not include the version and levels of software or the modification status of hardware in the appliance number. 1. Garmin was granted a deviation from ETSO-C92c to use DO-160E instead of DO-160D. 1. Garmin was granted a deviation from TSO-C145a to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from RTCA/DO-229C paragraphs 2.1.1.10, 2.1.1.7, 2.1.1.8.1, 2.1.1.8.2, 2.1.1.9, 2.1.2.1, 2.1.3.1, 2.1.4.1.4, 2.1.4.1.5 and 2.1.5.1 in the form of an operational limitation to achieve an equivalent level of safety. This operational limitation applies to the GIA63W or GIA 63H with GPS software version 2.40 or earlier, or GIA63W or GIA 63H installations with certain models of GPS/WAAS antennas identified in Section 2.1.3.2. The operational limitation is based on:
1. The ability to use antennas that may not meet the minimum gain performance requirements of DO-228. 2. The ability to mitigate the effects of the different gain characteristics of those antennas by increasing the effective mask angle through operational limitations. 3. The ability to further increase the effective mask angle, through operational limitations, to a level commensurate with test conditions used in the original TSO qualification tests. 4. The ability to use -128 dBmic as the minimum GPS satellite signal-in-space for the purpose of assessing the operational limitation. 5. The ability to use -128 dBmic as the minimum SBAS satellite signal-in-space for the purpose of assessing the operational limitation. 3. Garmin was granted a deviation from RTCA/DO-229C paragraph 2.1.1.9 to use a 20 second satellite reacquisition time instead of a 10-second reacquisition time. 1. Garmin was granted a deviation from ETSO-C145 to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from ETSO-C145 to use DO-229C instead of DO-229A. 3. Garmin was granted a deviation from DO-229C paragraph 2.1.1.9 to use a 20 second satellite reacquisition time instead of a 10 second reacquisition time. 1. Garmin was granted a deviation from TSO-C151b to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from TSO-C151b 4.a. to mark the unit with the serial number instead of the date of manufacture. 1. Garmin was granted a deviation from ETSO-C151b to use DO-160E instead of DO-160D. 1. Garmin was granted a deviation from TSO-C169a paragraph 4.a.2 to allow the unit to be permanently and legibly marked with a serial number and not the date of manufacture. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-33 DRAFT 1.6.8 GIA 63W with Enhanced COM TSO/ETSO Compliance Table 1-18. GIA 63W with Enhanced COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Automatic Pilots TSO-C9c Glideslope Receiver TSO-C34e Localizer Receiver TSO-C36e Class A VOR Receiver TSO-C40c Flight Director Equipment TSO-C52b All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0082-1() except 006-B0082-10 All 006-B0082-1() except 006-B0082-10 All 006-B0082-1() except 006-B0082-10 All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-C0124-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 006-C0124-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() GIA 63 Installation Manual Page 1-34 190-00303-05 Rev. W DRAFT Table 1-18. GIA 63W with Enhanced COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Stall Warning Instruments TSO-C54 Type II Ground Proximity Warning Glide Slope Deviation Alerting Equipment TSO-C92c All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-35 DRAFT Table 1-18. GIA 63W with Enhanced COM TSO/ETSO Compliance Function TSO/ETSO Category Applicable LRU SW Part Numbers Applicable CLD Part Numbers Airborne Navigation Sensors Using the Global Positioning System Augmented by the Wide Area Augmentation System*
TSO-C145c Class 3 All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD 006-B0339-2() TAWS TSO-C151b Class A and B VDL Mode 2 Communications Equipment TSO-C160 Architecture Class Z All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD VHF Radio Communications Transceiver Equipment TSO-C169a Class 3, 4, 5, and 6
(transmitter) Class C and E
(receiver) All 006-B0544-4() and all 006-B0544-B() except 006-B0544-BA through 006-B0544-BD 006-B0081-1() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0() All 006-C0084-0() except 006-C0084-00 006-C0072-0() 006-C0085-0()
*GIA 63W with Enhanced COM ARINC output labels 310 and 311 are not to be used as navigation data per RTCA/DO-229D GIA 63 Installation Manual Page 1-36 190-00303-05 Rev. W DRAFT 1.6.9 GIA 63W with Enhanced COM TSO/ETSO Deviations Table 1-19. GIA 63W with Enhanced COM TSO/ETSO Deviations TSO/ETSO TSO-C9c TSO-C34e TSO-C36e TSO-C40c TSO-C52b TSO-C54 TSO-C92c TSO-C145c TSO-C151b Deviation 1. Garmin was granted a deviation from TSO-C9c to use SAE AS 402B instead of AS-402A. 2. Garmin was granted a deviation from TSO-C9c to use DO-160E instead of specified environmen-
tal tests 3. Garmin was granted a deviation from TSO-C9c subpart A (c), which requires marking the weight of the unit on the unit. Garmin will provide this information in the installation manual in lieu of marking on the serial tag. Garmin does not currently list the weight on other avionics units. 4. Garmin was granted a deviation from SAE AS 402B paragraph 4.4.1 to limit autopilot engagement to attitudes considered safe for the certified aircraft. 5. Garmin was granted a deviation from SAE AS 402B paragraph 4.3.2 to not provide servo effort indications when the automatic pilot is not engaged. 1. Garmin was granted a deviation from TSO-C34e to use DO-160E instead of DO-160B, and DO-
178B instead of DO-178A. 1. Garmin was granted a deviation from TSO-C36e to use DO-160E instead of DO-160B, and DO-
178B instead of DO-178A. 1. Garmin was granted a deviation from TSO-C40c to use DO-160E instead of DO-160B, and DO-
178B instead of DO-178A. 1. Garmin was granted a deviation from SAE AS 8008 paragraph 3.6 to limit flight director operation to attitudes considered safe for the certified aircraft. 2. Garmin was granted a deviation from TSO-C52b to use DO-160E instead of DO-160C. 1. Garmin was granted a deviation from TSO-C54 to use RTCA DO-160E instead of SAE AS 403A. 1. Garmin was granted a deviation from TSO-C92c to use DO-160E instead of DO-160C. 2. Garmin was granted a deviation from TSO-C92c paragraph b.(2) to not include the version and levels of software or the modification status of hardware in the appliance part number. 1. Garmin was granted a deviation from RTCA/DO-229D paragraph 2.1.1.10 to use GPS antennas that meet Garmin minimum performance specifications (Doc No. 004-00287-00) instead of DO-301 qualified antennas. 1. Garmin was granted a deviation from TSO-C151b to use DO-160E instead of DO-160D. 2. Garmin was granted a deviation from TSO-C151b 4.a. to mark the unit with the serial number instead of the date of manufacture. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-37 DRAFT Table 1-19. GIA 63W with Enhanced COM TSO/ETSO Deviations TSO/ETSO TSO-C160 Deviation 1. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.2.5.4.7 to meet Attachment 2, Table 2-1-3, Item HO-argi of ARINC 631-5, which states that neither the VDL ground station or air-
craft will support aircraft requested ground initiated handoffs. 2. Garmin was granted a deviation from RTCA/DO-224B table 3-7 to allow the lower bound of the aircraft T4 parameter to be 1 minute as defined in Attachment 2, Table 2-3-2, Item aT4.min of ARINC 631-5, which will supercede the value of 10 minutes defined by the aircraft T4 parameter in RTCA/
DO-224B table 3-7. 3. Garmin was granted a deviation from RTCA/DO-224B table 3-18 to allow bit 7 to be set as defined in paragraph 7.9 of ARINC 631-5 so that the air/ground bit can be utilized for the purpose of inform-
ing the avionics whether the ground or air Frequency Support List should be used. 4. Garmin was granted a deviation from RTCA/DO-224B table 3-17 to allow the value of the AVLC Options parameter ID to be set as 0x04 as defined in table 5-15, ICAO 9776 1st edition, which is ref-
erenced by ARINC 631-5, paragraph 7, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 5. Garmin was granted a deviation from RTCA/DO-224B table 3-18 to allow bit 1 to be set as defined in table 5-16, ICAO 9776 1st edition, which is referenced by ARINC 631-5, paragraph 7, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 6. Garmin was granted a deviation from RTCA/DO-224B table 3-39 to allow the value of the Fre-
quency Support List parameter ID to be set as 0xC0 as defined in table 5-37, ICAO 9776 1st edition, which is referenced by ARINC 631-5, paragraph 7, in order to correct a discrepancy between RTCA/
DO-224B and ARINC 631-5. 7. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.4.1 to define the VDL Mobile SNDCF (Sub-Network Dependent Convergence Function) with ICAO 9705 subvolume 5, 2nd edi-
tion, as modified by the PDRs (Proposed Defect Reports) defined in RTCA/DO-280B volume 2 and the PDRs defined in EUROCONTROL-SPEC-0116, in order to reflect guidance provided by AC 20-
140A. 8. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.2.4.2.3.1 to interpret that an air-ground bit set to 0 indicates that the transmitting station is airborne. This deviation is required to match the interpretation of the air-ground bit described in paragraph 5.3.3.3.1 of ICAO 9776 1st edi-
tion, which is referenced by ARINC 631-5, paragraph 7, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 9. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.2.4.3.1 to allow the value of u (the channel utilization parameter) to range between 0 and 0.99 to match the definition of u in ARINC 631-5 paragraph 7.6.1, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 10. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.2.4.3.3 to allow the calcula-
tion of T3 values by using a similar algorithm as that used to calculate T1 values (with appropriate substitutions for T3min, T3max, T3mult, and T3exp), to match the method for calculating T3 defined in ARINC 631-5 paragraph 7.6.2, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 11. Garmin was granted a deviation from RTCA/DO-224B table 3-18 to allow bit 6 to be set as defined in table 5-16, ICAO 9776 1st edition, which is referenced by ARINC 631-5, paragraph 7.9, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 12. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.2.5.2.7.1 to allow handling of the operating parameters of a ground station advertised in the FSL as defined in ARINC 631-5 paragraph 9.8.2, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. 13. Garmin was granted a deviation from RTCA/DO-224B paragraph 3.2.2.5.4.9.3 to allow handling of the scenario in which the aircraft LME cannot initiate the handoff and the autotune parameter is not included or cannot be performed to match that described in ARINC 631-5 paragraph 4.3.1.4, in order to correct a discrepancy between RTCA/DO-224B and ARINC 631-5. GIA 63 Installation Manual Page 1-38 190-00303-05 Rev. W DRAFT Table 1-19. GIA 63W with Enhanced COM TSO/ETSO Deviations TSO/ETSO TSO-C169a 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. 2. Garmin was granted a deviation from RTCA/DO-186B sections 2.4.8 and 2.5.8 to interpret Fluids Susceptibility (RTCA/DO-160E, Section 11.0) testing as "When Required in order to resolve a dis-
crepancy between guidance provided in RTCA/DO-186B, RTCA/DO-160E, EUROCAE ED-23B, and EUROCAE ED-23C. A limitation must be provided in the installation manual stating that the appli-
ance must not be installed in areas where fluid contamination could be commonly encountered if this category is not claimed in the unit environmental qualification form. 3. Garmin was granted a deviation from RTCA/DO-186B sections 2.4.7 to interpret Waterproofness
(RTCA/DO-160E, Section 10.0) testing as "When Required in order to resolve a discrepancy between guidance provided in RTCA/DO-186B, RTCA/DO-160E, EUROCAE ED-23B, and EURO-
CAE ED-23C. A limitation must be provided in the installation manual stating that the appliance must not be installed in areas where water could be commonly encountered if this category is not claimed in the unit environmental qualification form. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-39 DRAFT 1.6.10 AFM/RFM/AFMS/RFMS/POH Considerations Per TSO-C9c/ETSO-C9c deviation, the applicable AFM/RFM/AFMS/RFMS/POH shall list autopilot engagement envelope for the certified aircraft. Per TSO-C52b/ETSO-C52b deviation, the applicable AFM/RFM/AFMS/RFMS/POH shall state that the system is not designed to perform unusual attitude recoveries from attitudes outside this range (as defined in the TSO-C52b/ETSO-C52b deviation above). Ensure pilot operating guidance also states the FD operating envelope. 1.6.10.1 GIA 63W and GIA 63H GPS Software Versions 2.40 or Earlier Due to the equipments TSO qualified performance in tracking low-elevation-angle satellites, the following limitations must be included in the Aircraft Flight Manual or Aircraft Flight Manual Supplement for GIA63W or GIA 63H installations with GPS software version 2.40 or earlier, or in GIA 63W or GIA 63H installations with antennas that require operational limitations (identified in Section 2.1.3.2):
This equipment does not comply with US 14 CFR Part 91, SFAR 97 requirements for TSO-C145a/TSO-146a equipment when installed with certain models of GPS/WAAS antennas identified in Section 2.1.3.2. Until complete compliance is demonstrated and approved by the FAA, authorization to conduct any GPS or WAAS operation under Instrument Flight Rules (IFR) requires that:
1. Aircraft using the GPS or WAAS capability of the GIA 63W or GIA 63H navigation equipment under IFR must be equipped with an approved and operational alternate means of navigation appropriate to the flight with the exception of oceanic and remote operations. 2. For flight planning purposes, if an alternate airport is required, it must have an approved instrument approach procedure other than GPS or RNAV that is anticipated to be operational and available at the estimated time of arrival. All equipment required for this procedure must be installed and operational. 3. For flight planning purposes, Garmin Prediction Program 006-A0154-01 with the <insert installed antenna part number> antenna selection should be used to confirm the availability of RAIM for the intended flight in accordance with the local aviation authority guidelines for TSO-C129a equipment. WAAS NOTAMs (or their absence) and generic prediction tools do not provide an acceptable indication of the availability for the GIA 63W or GIA 63H equipment. 4. When flight planning an LNAV/VNAV or LPV approach, operators should use the Garmin Prediction Program 006-A0154-01 with the <insert installed antenna part number> antenna selection in addition to any NOTAMs issued for the approach. The applicable AFM/RFM/AFMS/RFMS/POH shall also state the following instructions regarding the use of the G1000 WFDE prediction program, which is required to be used for flight planning purposes for Oceanic/Remote operations and when operating under the operational limitations listed above:
The G1000 WFDE prediction program works in combination with the Route Planning Software
(version 1.2 or later approved version). The route planning and WFDE prediction programs can be downloaded from www.garmin.com. For information on using the WFDE prediction program, refer to the WFDE Prediction Program Instructions Garmin part number 190-00643-01. GIA 63 Installation Manual Page 1-40 190-00303-05 Rev. W DRAFT 1.6.10.2 GIA 63W and GIA 63H GPS Software Versions 3.2 or Later The following information may be used as guidance in developing an approved AFM, RFM, AFMS, RFMS, and/or POH provided the system is installed in accordance with [AC 20-138C] and is comprised of
[two or more] [TSO-C145a Class 3 or TSO-C145c Class 3] approved Garmin GIA 63Ws or GIA 63Hs,
[two or more] [TSO-C146a Class 3 or TSO-C146c Class 3] approved Garmin GDU 1XXX Display Units, Garmin-approved GPS/SBAS antennas (refer to Section 2.1.3.2), and GPS software version [3.2 or later approved version]:
NOTE Text contained in brackets [ ] is meant to serve as an example and will need to be modified in order to reflect the actual installation. GARMIN GNSS (GPS/SBAS) NAVIGATION SYSTEM EQUIPMENT APPROVALS The Garmin GNSS navigation system is a GPS system with a Satellite Based Augmentation System
(SBAS) comprised of [two or more] [TSO-C145a Class 3 or TSO-C145c Class 3] approved Garmin GIA 63Ws or GIA 63Hs, [two or more] [TSO-C146a Class 3 or TSO-C146c Class 3] approved Garmin GDU 1XXX Display Units, Garmin-approved GPS/SBAS antennas (refer to Section 2.1.3.2), and GPS software version [3.2 or later approved version]. The Garmin GNSS navigation system in this aircraft is installed in accordance with [AC 20-138C]. The Garmin GNSS navigation system as installed in this aircraft complies with the requirements of
[AC 20-138C] and has airworthiness approval for navigation using GPS and SBAS (within the coverage of a Satellite Based Augmentation System complying with ICAO Annex 10) for IFR en route, terminal area, and non-precision approach operations (including those approaches titled GPS, or GPS, and RNAV
(GPS) approaches). The Garmin GNSS navigation system is approved for approach procedures with vertical guidance including LPV and LNAV/VNAV, within the U.S. National Airspace System. The Garmin GNSS navigation system complies with the equipment requirements of AC 90-105 and meets the equipment performance and functional requirements to conduct RNP terminal departure and arrival procedures and RNP approach procedures without RF (radius to fix) legs. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval from the FAA. The Garmin GNSS navigation system complies with the equipment requirements of AC 90-100A for RNAV 2 and RNAV 1 operations. In accordance with AC 90-100A, Part 91 operators (except subpart K) following the aircraft and training guidance in AC 90-100A are authorized to fly RNAV 2 and RNAV 1 procedures. Part 91 subpart K, 121, 125, 129, and 135 operators require operational approval from the FAA. The Garmin GNSS navigation system has been found to comply with the requirements for GPS Class II oceanic and remote navigation (RNP-10) without time limitations in accordance with [AC 20-138C] and FAA Order [8400.12C]. The Garmin GNSS navigation system can be used without reliance on other long-
range navigation systems. This does not constitute an operational approval. The Garmin GNSS navigation system has been found to comply with the navigation requirements for GPS Class II oceanic and remote navigation (RNP-4) in accordance with [AC 20-138C] and FAA Order 8400.33. The Garmin GNSS navigation system can be used without reliance on other long-range navigation systems. Additional equipment may be required to obtain operational approval to utilize RNP-4 performance. This does not constitute an operational approval. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-41 DRAFT The Garmin GNSS navigation system complies with the accuracy, integrity, and continuity of function, and contains the minimum system functions required for P-RNAV operations in accordance with JAA Administrative & Guidance Material Section One: General Part 3: Temporary Guidance Leaflets, Leaflet No 10 (JAA TGL-10 Rev 1). The GNSS navigation system has [two or more] [ETSO-C145 Class 3 or ETSO-C145c Class 3 / TSO-C145a Class 3 or TSO-C145c Class 3] approved Garmin GIA 63Ws or GIA 63Hs, and [two or more] [ETSO-146 Class 3 or ETSO-C146c Class 3 / TSO-C146a Class 3 or TSO-C146c Class 3] approved Garmin GDU 1XXX Display Units. The Garmin GNSS navigation system complies with the equipment requirements for P-RNAV and B-RNAV/RNAV 5 operations in accordance with AC 90-96A CHG 1 and JAA TGL-10 Rev 1. This does not constitute an operational approval. Garmin International holds an FAA Type 2 Letter of Acceptance (LOA) in accordance with [AC 20-153A]
for database integrity, quality, and database management practices for the Navigation database. Flight crews and operators can view the LOA status at FlyGarmin.com then select Type 2 LOA Status. Navigation information is referenced to WGS-84 reference system. GIA 63 Installation Manual Page 1-42 190-00303-05 Rev. W DRAFT GARMIN GNSS (GPS/SBAS) NAVIGATION SYSTEM LIMITATIONS The flight crew must confirm at system initialization that the Navigation database is current. Navigation database is expected to be current for the duration of the flight. If the AIRAC cycle will change during flight, the flight crew must ensure the accuracy of navigation data, including suitability of navigation facilities used to define the routes and procedures for flight. If an amended chart affecting navigation data is published for the procedure, the database must not be used to conduct the procedure. GPS/SBAS based IFR en route, oceanic, and terminal navigation is prohibited unless the flight crew verifies and uses a valid, compatible, and current Navigation database or verifies each waypoint for accuracy by reference to current approved data. Discrepancies that invalidate a procedure must be reported to Garmin International. The affected procedure is prohibited from being flown using data from the Navigation database until a new Navigation database is installed in the aircraft and verified that the discrepancy has been corrected. Navigation database discrepancies can be reported at FlyGarmin.com then select Aviation Data Error Report. Flight crew and operators can view Navigation data base alerts at FlyGarmin.com then select NavData Alerts. For flight planning purposes, in areas where SBAS coverage is not available, the flight crew must check RAIM availability. Within the United States, RAIM availability can be determined using the Garmin WFDE Prediction program, [part number 006-A0154-01 (included in G1000 trainer software) version 3.00 or later approved version with GARMIN GA36 and GA37 antennas selected], or the FAAs en route and terminal RAIM prediction website: www.raimprediction.net, or by contacting a Flight Service Station. Within Europe, RAIM availability can be determined using the Garmin WFDE Prediction program or Europes AUGER GPS RAIM Prediction Tool at http://augur.ecacnav.com/augur/app/home. For other areas, use the Garmin WFDE Prediction program. This requirement is not necessary if SBAS coverage is confirmed to be available along the entire route of flight. The route planning and WFDE prediction program may be downloaded from the Garmin website on the internet. For information on using the WFDE Prediction Program, refer to Garmin WAAS FDE Prediction Program, part number 190-00643-01, WFDE Prediction Program Instructions. For flight planning purposes, operations within the U.S. National Airspace System on RNP and RNAV procedures when SBAS signals are not available, the availability of GPS RAIM shall be confirmed for the intended route of flight. In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended route of flight, the flight should be delayed, canceled, or re-routed on a track where RAIM requirements can be met. For flight planning purposes for operations within European B-RNAV/RNAV-5 and P-RNAV airspace, if more than one satellite is scheduled to be out of service, then the availability of GPS RAIM shall be confirmed for the intended flight (route and time). In the event of a predicted continuous loss of RAIM of more than five minutes for any part of the intended flight, the flight should be delayed, canceled, or rerouted on a track where RAIM requirements can be met. For flight planning purposes, operations where the route requires Class II navigation the aircrafts operator or flight crew must use the Garmin WFDE Prediction program to demonstrate that there are no outages on the specified route that would prevent the Garmin GNSS navigation system from providing GPS Class II navigation in oceanic and remote areas of operation that requires (RNP-10 or RNP-4) capability. If the Garmin WFDE Prediction program indicates fault exclusion (FDE) is unavailable for more than 34 minutes in accordance with FAA Order 8400.12C for RNP-10 requirements, or 25 minutes in accordance with FAA Order 8400.33 for RNP-4 requirements, then the operation must be rescheduled when FDE is available. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-43 DRAFT Both Garmin GPS navigation receivers must be operating and providing GPS navigation guidance to their respective PFD for operations requiring RNP-4 performance. North Atlantic (NAT) Minimum Navigational Performance Specifications (MNPS) Airspace operations per AC 91-49 and AC 120-33 require both GPS/SBAS receivers to be operating and receiving usable signals except for routes requiring only one Long Range Navigation sensor. Each display computes an independent navigation solution based on the on-side GPS sensor. However, either display will automatically revert to the cross-side sensor if the on-side sensor fails or if the cross-side sensor is determined to be more accurate. [On G1000 installations a BOTH ON GPS1 or BOTH ON GPS2 message does not necessarily mean that one GPS has failed. Refer to the MFD AUX-GPS STATUS page to determine the state of the unused GPS]. Whenever possible, RNP and RNAV routes including Standard Instrument Departures (SIDs) and Obstacle Departure Procedures (ODPs), Standard Terminal Arrival (STAR), and en route RNAV Q and RNAV T routes should be loaded into the flight plan from the database in their entirety, rather than loading route waypoints from the database into the flight plan individually. Selecting and inserting individual named fixes from the database is permitted, provided all fixes along the published route to be flown are inserted. Manual entry of waypoints using latitude/longitude or place/bearing is prohibited. GPS, or GPS, and RNAV (GPS) instrument approaches using the Garmin navigation systems are prohibited unless the flight crew verifies and uses the current Navigation database. GPS based instrument approaches must be flown in accordance with an approved instrument approach procedure that is loaded from the Navigation database. Not all published Instrument Approach Procedures (IAP) are in the Navigation database. Flight crew planning on flying an RNAV instrument approach must ensure that the Navigation database contains the planned RNAV Instrument Approach Procedure and that approach procedure must be loaded from the Navigation database into the FMS flight plan by its name. IFR non-precision approach approval using the GPS/SBAS sensor is limited to published approaches within the U.S. National Airspace System. Approaches to airports in other airspace are not approved unless authorized by the appropriate governing authority. The navigation equipment required to join and fly an instrument approach procedure is indicated by the title of the procedure and notes on the IAP chart. Use of the Garmin GPS/SBAS receivers to provide navigation guidance during the final approach segment of an ILS, LOC, LOC-BC, LDA, SDF, MLS or any other type of approach not approved for or GPS navigation is prohibited. When using the Garmin VOR/
LOC/GS receivers to fly the final approach segment, VOR/LOC/GS navigation data must be selected and presented on the CDI of the pilot flying. Navigation information is referenced to WGS-84 reference system, and should only be used where the Aeronautical Information Publication (including electronic data and aeronautical charts) conform to WGS-84 or equivalent. GIA 63 Installation Manual Page 1-44 190-00303-05 Rev. W DRAFT 1.6.11 Other Regulatory Criteria (GIA 63) RTCA/DO-178B Level B, C, D EUROCAE ED 12B RTCA/DO-160D EUROCAE ED 14D RTCA/DO-161A RTCA/DO-208 Class A1 RTCA/DO-186a Class 3 and 5 RTCA/DO-186a Class C and E RTCA/DO-196 RTCA/DO-195 Class A RTCA/DO-192 ICAO Annex 10 Volume III, EUROCAE ED-23B ICAO Annex 10 Volume I, EUROCAE ED-22B ICAO Annex 10 Volume I, EUROCAE ED-46B EUROCAE ED-47B EUROCAE ED-72A SAE AS 402B SAE AS 8008
(Software)
(Software)
(Environmental Conditions)
(Environmental Conditions)
(Airborne Ground Proximity Warning Equipment)
(GPS)
(VHF Com Transmitter)
(VHF Com Receiver)
(VOR Receiver)
(Localizer Receiver)
(Glideslope Receiver)
(VHF Com Transceiver)
(VOR Receiver)
(Localizer Receiver)
(Glideslope Receiver)
(GPS)
(Automatic Pilots)
(Flight Director Equipment) 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-45 DRAFT 1.6.12 Other Regulatory Criteria (GIA 63W and GIA 63H) All 011-01105-XX part numbers:
RTCA/DO-178B Level A*, B, C, D EUROCAE ED 12B RTCA/DO-160E EUROCAE ED 14E RTCA/DO-161A RTCA/DO-196 RTCA/DO-195 Class A RTCA/DO-192 ICAO Annex 10 Volume I, EUROCAE ED-22B ICAO Annex 10 Volume I, EUROCAE ED-46B EUROCAE ED-47B SAE AS 402B SAE AS 8008
(Software)
(Software)
(Environmental Conditions)
(Environmental Conditions)
(Airborne Ground Proximity Warning Equipment)
(VOR Receiver)
(Localizer Receiver)
(Glideslope Receiver)
(VOR Receiver)
(Localizer Receiver)
(Glideslope Receiver)
(Automatic Pilots)
(Flight Director Equipment)
*RTCA/DO-178B Level A is only supported through use of GIA software part numbers 006-B0544-3( ) and later. All other GIA software part numbers support RTCA/
DO-178B Levels B, C and D only. 011-01105-0X only:
RTCA/DO-254 Level A and C RTCA/DO-229c Class Beta 3 RTCA/DO-186a Class 3 and 5 RTCA/DO-186a Class C and E ICAO Annex 10 Volume III, EUROCAE ED-23B 011-01105-2X and 011-01105-3X only:
RTCA/DO-254 Level A RTCA/DO-229c Class Beta 3 RTCA/DO-186b Class 3 and 5 (Vin @ 28VDC) Class 4 and 6(Vin @ 14VDC) RTCA/DO-186b Class C and E ICAO Annex 10 Volume III, EUROCAE ED-23B 011-01105-4X only:
RTCA/DO-254 Level A RTCA/DO-229d Class Beta 3 RTCA/DO-186b Class 3 and 5 RTCA/DO-186b Class C and E ICAO Annex 10 Volume III, EUROCAE ED-23C RTCA/DO-281a RTCA/DO-224b
(CLD devices)
(GPS/WAAS)
(VHF Com Transmitter)
(VHF Com Receiver)
(VHF Com Transceiver)
(CLD devices)
(GPS/WAAS)
(VHF Com Transmitter)
(VHF Com Transmitter)
(VHF Com Receiver)
(VHF Com Transceiver)
(CLD devices)
(GPS/WAAS)
(VHF Com Transmitter)
(VHF Com Receiver)
(VHF Com Transceiver)
(VDL Mode 2)
(VHF Digital Data) GIA 63 Installation Manual Page 1-46 190-00303-05 Rev. W DRAFT 1.7 Reference Documents The following publications are sources of additional information for installing the GIA 63(X). Before installing the GIA 63(X), the technician should read all relevant referenced materials along with this manual. Table 1-20. GIA 63(X) Reference Documents Part Number 190-00303-00 190-00303-04 560-5047-00 II A258002 II A258005 II A42803 II A42809 II A272803 II A272806 190-00848-00 190-00355-02*
190-00522-01 190-00483-01 004-00287-00 190-00303-24 Document G1000 System Installation Manual G1000 Line Maintenance and Configuration Manual Apollo A-34 GPS Antenna Installation Manual Comant CI 2580-410 Installation Instructions Comant CI 2580-200 Installation Instructions Comant CI 428-410 Installation Instructions Comant CI 428-200 Installation Instructions Comant CI 2728-410 Installation Instructions Comant CI 2728-200 Installation Instructions GA 35, GA 36, and GA 37 Antenna Installation Instructions GDL 69/69A Installation Manual GA 55A, GA 56A, GA 57 Installation Instructions GA 56W Antenna Installation Instructions Antenna Minimum Performance Specification for Garmins GPS/WAAS Receiver System GDR 66 Installation Manual
*GA 55 technical specifications and antenna performance is contained in the GDL 69/69A Installation Manual. 190-00303-05 Rev. W GIA 63 Installation Manual Page 1-47 DRAFT This page intentionally left blank GIA 63 Installation Manual Page 1-48 190-00303-05 Rev. W DRAFT 2 INSTALLATION OVERVIEW 2.1 Introduction This section provides hardware equipment information for installing the GIA 63(X), related hardware, and antennas. Installation of the GIA 63(X) should 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 the G1000 System Installation Manual, Garmin part number 190-00303-00 for further details on the mechanical aspects. For installation in an aircraft using the remote mounted standalone rack, refer to Appendix B for rack drawings and dimensions. 2.1.1 Unit Configurations The GIA 63(X) is only available as a single unit under the following part numbers. Table 2-1. GIA 63(X) Part Numbers Item GIA 63 Unit Only, (011-00781-00) GIA 63 ETSO Unit Only, (011-00781-01) GIA 63W Unit Only, (011-01105-00) GIA 63W A2/B2 Audio Lightning Unit Only (011-01105-01) GIA 63W Updated NAV/COM (011-01105-20) GIA 63H (011-01105-30)*
GIA 63W with Enhanced COM (011-01105-40)
*Only the 010-00386-30 GIA 63H unit together with the 011-02425-00 Rack & 011-00963-01 Back Plate is approved for DO-160F, Category U, Curve G vibration levels. Garmin P/N 010-00335-00 010-00335-10 010-00386-00 010-00386-10 010-00386-20 010-00386-30 010-00386-40 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-1 DRAFT 2.1.2 Required Accessories Each of the following accessories is provided separately from the GIA 63(X). Either rack (modular, standalone, or helicopter) and reminder of the accessories are required for installation. Table 2-2. Required Accessories Item GIA 63(W) Modular Install Rack or GIA 63(W) Standalone Install Rack or GIA 63H Helicopter Install Rack*
G1000 Rack Nutplate Kit (Modular Rack Only) Garmin P/N 115-00426-00 115-01239-00 011-02425-00 011-00915-01 (preferred) or GIA 63(W) Back Plate (Modular and Standalone) GIA 63H Back Plate (Helicopter)*
GIA 63(X) Connector Kit w/ Spider GIA 63(X) Connector Kit w/ Shield Block*
GIA 63(X) Connector Kit, IF Seal
*Only the 010-00386-30 GIA 63H unit together with the 011-02425-00 Rack , 011-00963-01 Back Plate, and 011-01000-01 Con-
nector Kit is approved for DO-160F, Category U, Curve G vibration levels. 011-01148-01 011-00963-00 011-00963-01 011-01000-00 011-01000-01 011-01000-03 GIA 63 Installation Manual Page 2-2 190-00303-05 Rev. V DRAFT 2.1.3 Additional Equipment Required The following installation accessories are required but not provided:
COM Antenna:
specified by TSO-C145c. Refer to Section 2.1.3.2 for approved antennas VOR/LOC Antenna:
Glideslope Antenna:
Shall meet TSO-C169()*, or shall meet both TSO-C37() and C38(), Broad band, 50 , vertically polarized with coaxial cable GIA 63 (011-00781-0X) shall meet TSO-C129a. TSO-C144 antennas can also meet TSO-C129a requirements for the GIA 63 (Refer to Section 2.1.3.1). GIA 63H and GIA 63W (011-01105-0X/-2X/-3X) shall meet TSO-C144 and additional system requirements specified by TSO-C145a. Refer to Section 2.1.3.2 for approved antennas GIA 63W (011-01105-4X) shall meet TSO-C144 and additional system requirements Shall meet TSO-C40() and C36(). Broad band, 50 , horizontally polarized with coaxial cable Shall meet TSO-C34(). Broad band, 50 , horizontally polarized with coaxial cable or low-loss splitter used with the VOR/LOC antenna 500 nominal impedance Microphone: Low impedance, carbon or dynamic, with transistorized pre-amp
#6-32 x 100Flathead SS Screw [(MS24693, AN507R or other approved fastener) (4 ea.)] for horizontal mounting of the standalone rack.
#8-32 Panhead Machine Screw [(MS35206, AN526 or other approved fastener) (4 ea.)] for vertical mounting of the standalone rack.
#10-32 x 100Flathead Screw [(MS24694S51 or screw of same or greater strength)(4 ea.)] for mounting of the helicopter rack. GPS Antenna:
Headphones:
Hardware:
Hardware:
Hardware:
*GIA 63W and GIA 63H only 2.1.3.1 Required Antenna for the GIA 63 Antennas used with the GIA 63 (non-WAAS) must meet the antenna specifications shown in Section 2.6. In addition, TSO-C144 antennas can also meet TSO-C129a requirements for the GIA 63 (non-WAAS) if their additional gain (which is about 16dB at 1.5 GHz for antennas produced by Garmin) is offset by added attenuation in-line with the GIA 63 (non-WAAS). If an in-line attenuator is used, it must pass DC current
(40 mA max at 4.6 VDC) which is provided from the GPS receiver to the antenna pre-amplifier. 2.1.3.2 Required WAAS Antennas for the GIA 63W and GIA 63H The following is a list of TSO-C144 antennas that allow the GIA 63W and GIA 63H with GPS software version 3.2 or later to meet TSO-C145a requirements without requiring the operational limitations specified in Section 1.6.10.2 of this manual:
190-00303-05 Rev. W GIA 63 Installation Manual Page 2-3 DRAFT Table 2-3. TSO-C145a WAAS Antennas for the GIA 63W and GIA 63H Model Mount Style Conn Type SATCOM Compatible
[3]
Mfr Antenna Part Number Garmin Order Number Additional Requirements Screw Mount, Teardrop Footprint [2]
Screw Mount, ARINC 743 Footprint Screw Mount, ARINC 743 Footprint TNC Yes TNC Yes TNC Yes Aero Antenna AT575-
93GWTNCF-
000-
RG-27-NM Garmin 013-00235-00 Aero Antenna Garmin Aero Antenna Garmin AT575-
326GW-TNCF-
000-RG-27-NM 013-00244-00 AT2300-
126GW-TNCF-
000-RG-27-NM 013-00245-00 CI 2580-200 013-00235-00 013-00244-00 013-00245-00 Screw Mount, Teardrop Footprint [2]
BNC TNC
[5]
Yes Comant N/A CI 2580-410 None TNC Yes Comant N/A CI 428-200 Screw Mount, ARINC 743 Footprint CI 428-410 CI 2728-200 Screw Mount, Teardrop Footprint [7]
BNC TNC
[5]
Yes Comant N/A CI 2728-410 GA 35 GPS WAAS Antenna [6]
GA 36 GPS WAAS Antenna [6]
GA 37 FIS/WAAS Antenna [6]
Comant 2580-200 WAAS and COM Antenna
[6] [8]
Comant 2580-410 FIS/WAAS
/COM Antenna[6]
[8]
Comant 428-200 WAAS Antenna
[6] [8]
Comant 428-410 FIS/WAAS Antenna[6][8]
Comant 2728-200 WAAS and COM Antenna
[6][8]
Comant 2728-410 FIS/WAAS
/COM Antenna[6][8]
GIA 63 Installation Manual Page 2-4 190-00303-05 Rev. V DRAFT The following is a list of known TSO-C144 antennas that allow the GIA 63W and GIA 63H with any version of GPS software version to meet TSO-C145a requirements with the operational limitations specified in Section 1.6.4 and 1.6.7 of this manual:
Table 2-4. TSO-C144 WAAS Antennas for the GIA 63W and GIA 63H Model Mount Style Conn Type SATCOM Compatible
[3]
Mfr Antenna Part Number Garmin Order Number Additional Requirements A-34 GPS WAAS Antenna GA56A GPS WAAS Antenna GA56W GPS WAAS Antenna GA57 GPS WAAS and FIS Antenna Screw Mount, Teardrop Footprint [2]
Screw Mount, ARINC 743 Footprint Stud Mount, Teardrop Footprint [1]
Screw Mount, ARINC 743 Footprint TNC Yes Aero Antenna Garmin AT AT575-
93WTNCF-
000-05-
26-NM 590-1112 013-00113-00 BNC No Garmin 011-01154-00 010-10599-00 BNC No Garmin 011-01111-00 010-10561-01 BNC TNC
[4]
No Garmin 011-01032-00 010-10604-00 The operational limitation described in Section 1.6.4 and 1.6.7 requires use of 006-A0154-01 as the Predic-
tion Program in conjunction with these antennas.
[1] Same footprint and mounting hole pattern as GA 56.
[2] Same mounting hole pattern as the GA 56, but has a physically larger footprint.
[3] SATCOM compatibility requirements are as specified by RTCA/DO-229C Section 2.5.6.1, Section 2.5.8.2, Appendix C.2.1, and Appendix C.2.2.
[4] The WAAS GPS antenna connector is a BNC type. The XM antenna connector is a TNC type.
[5] The WAAS GPS antenna connector (and XM antenna connector where applicable) is TNC type. The VHF COM antenna connector is BNC type.
[6] Not approved for use with the GIA 63 (non-WAAS) since max DC current specification exceeds 40 mA.
[7] Larger footprint and mounting hole pattern than GA 56, GA 35 or CI 2580.
[8] It is the installers responsibility to ensure the antenna complies with Antenna Minimum Performance Specification for Garmins GPS/WAAS Receiver System Antenna
(004-00287-00) by communicating the requirement to the supplier and obtaining a certificate of compliance to 004-00287-00 from the supplier. An antenna that complies only with TSO-C144 requirements is not adequate for this installation. Other TSO-C144 antennas may meet the installation requirements of the GIA 63W and GIA 63H. Contact Garmin to ensure compatibility and applicable operation limitations before beginning the installation. 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-5 DRAFT 2.2 Installation Considerations The GIA 63(X) interfaces with the G1000 system and with various avionics equipment. Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GIA 63(X). 2.2.1 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. Locate an appropriate consultant FAA DER by reviewing the FAA Consultant DER Directory, which can be found at the FAA Designee and Delegation web page. 5. Contact an aviation industry organization such as the Aircraft Electronics Association for assistance. 2.2.2 GPS Antenna Location The GPS antenna is a key element in the overall system performance and integrity for a GPS/WAAS navigation system. The mounting location, geometry, and surroundings of the antenna can affect the system performance and/or availability. The following guidance provides information to aid the installer in ensuring that the most optimum location is selected for the installation of the GPS antenna. The installation guidelines presented here meet the intent of AC 20-138A section 16. The greater the variance from these guidelines, the greater the chance of decreased availability. Approach procedures with vertical guidance are the most sensitive to these effects. LNAV only approaches, terminal operations, and enroute operations may also be affected. Because meeting all of these installations guidelines may not be possible on all aircraft, these guidelines are listed in order of importance to achieve optimum performance. Items 4 below are of equal importance and their significance may depend on the aircraft installation. The installer should use their best judgment to balance the installation guidelines. GIA 63 Installation Manual Page 2-6 190-00303-05 Rev. V DRAFT For rotorcraft, locate the GPS antenna as far as possible from the main rotor hub. This reduces the percentage of time the blade blocks the antenna. Also mount it as far below the blade surface as possible if installing the antenna under the blade. This reduces signal distortion caused by the blades. 1. Mount the antenna as close to level as possible with respect to the normal cruise flight attitude of the aircraft. If the normal flight attitude is not known, substitute the waterline, which is typically referenced as level while performing a weight and balance check. 2. The GPS antenna should be mounted in a location to minimize the effects of airframe shadowing during typical maneuvers. Typically mounting farther away from the tail section reduces signal blockage seen by the GPS antenna. 3. The GPS antenna should ideally be located at the opposite end of the aircraft from the COM unit in order to make the GPS less vulnerable to harmonics radiated from the COM itself. 4. The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally three feet from any VHF COM antenna or any other antenna which may emit harmonic (or other) interfer-
ence at the L1 frequency of 1575.42 MHz. An aircraft EMC check (reference VHF COM interfer-
ence check in Post Installation Checkout procedures) can verify the degradation of GPS in the presence of interference signals. If an EMC check reveals unacceptable interference, insert a GPS notch filter in line with the offending VHF COM or the (re-radiating) ELT transmitter. NOTE The separation requirement does not apply to GPS and COM combination antennas, provided the antenna model is TSO authorized and has been tested to meet Garmins minimum performance standards. The separating requirement includes the combination with an XM antenna element as well. The GPS antenna should be mounted no closer than two feet (edge to edge) and ideally three feet from any antennas emitting more than 25 watts of power. An aircraft EMC check can verify the degradation of GPS in the presence of interference signals. To minimize the effects of shadowing at 5 elevation angles, the GPS antenna should be mounted no closer than 6 inches (edge to edge) from other antennas, including passive antennas such as another GPS antenna or XM antenna. 5. To maintain a constant gain pattern and limit degradation by the windscreen, avoid mounting the antenna closer than 3 inches from the windscreen. 6. For multiple GPS installations, the antennas should not be mounted in a straight line from the front to the rear of the fuselage. Also varying the mounting location will help minimize any aircraft shading by the wings or tail section (in a particular azimuth, when one antenna is blocked the other antenna may have a clear view). 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-7 DRAFT Figure 2-1 shows the recommended placement of antennas. Figure 2-1. GPS Antenna Considerations GIA 63 Installation Manual Page 2-8 190-00303-05 Rev. V DRAFT 2.2.3 Com Antenna Location The GIA 63(X) 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 six feet from any DME or other COM antennas, four feet from any ADF sense antennas, three feet from the GIA 63(X) and its GPS antenna, and as far as practical from any ELT antennas. 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. 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. 2.2.4 VOR/LOC Antenna Location The GIA 63(X) VOR/LOC antenna should be well removed from all projections, engines and propellers. It should have a clear line of sight if possible. The antenna must be mounted along the centerline of the aircraft, minimizing the lateral offset. 2.2.5 Glideslope Antenna Location The GIA 63(X) Glideslope antenna should be well removed from all projections, engines and propellers. It should have a clear line of sight if possible. 2.2.6 Electrical Bonding No special precautions need to be taken to provide a bonding path between the GPS antenna and the aircraft structure. Follow the manufacturers instructions for the COM, VOR/LOC and Glideslope antennas. 2.2.7 VHF COM/GPS Interference On some installation VHF COM transceivers, Emergency Locator Transmitter (ELT) antennas, and Direction Finder (DF) receiver antennas can re-radiate through the GPS antenna. The GIA 63(X) COM does not interfere with its own GPS section. However, placement of the GA 56 GPS antenna (or other comparable antenna) relative to a COM transceiver and COM antenna (including the GIA 63(X) COM antenna), ELT antenna, and DF receiver antenna is critical. Use the following guidelines, in addition to others in this document, when locating the GIA 63(X) and its antennas. GPS AntennaLocate as far as possible from all COM antennas and all COM transceivers
(including the GIA 63(X) COM), ELT antennas, and DF antennas. The GPS antenna is less susceptible to harmonic interference if a 1.57542 GHz notch filter is installed on the COM trans-
ceiver antenna output. Locate the GIA 63(X) as far as possible from all COM antennas. 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-9 DRAFT If a COM antenna is found to be the problem, a 1.57542 GHz notch filter (Garmin P/N 330-00067-00) may be installed in the VHF COM coax, as close to the COM as possible. This filter is not required for the GIA 63(X) transmitter. If a COM is found to be radiating, the following can be done:
1. Replace or clean the VHF COM rack connector to ensure good coax ground. 2. Place grounding straps between the GIA 63(X) unit, VHF COM and a good ground. 3. Shield the VHF COM wiring harness. 2.3 Rack Considerations A location away from heating vents or other sources of heat generation is optimal. The GIA 63(W) can be mounted using the G1000 system rack. The unit may be mounted remotely if desired. The GIA 63H must be mounted in the Helicopter Rack. GIA 63 Installation Manual Page 2-10 190-00303-05 Rev. V DRAFT 2.4 Cabling and Wiring Refer to the interconnect examples in Appendix C for wire gauge guidance. In some cases, a larger gauge wire such as AWG #16, #18, or #20 may be needed for power connections. Special thin-wall heat shrink tubing is also provided to insulate the extended barrels inside the backshell. If using AWG #16 or #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. A typical maximum cable length for the GPS antenna is 40 feet. The installer shall insure that the attenuation does not exceed 10 dB at 1.5 GHz for the GIA 63, and falls between 3 dB and 7 dB inclusive at 1.5 GHz for the GIA 63W or GIA 63H. Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling, particularly the COM antenna cable, and routing near aircraft control cables. Cabling for the GIA 63(X) should not be routed near components or cabling which are sources of electrical noise. Do not route the COM antenna coax near any ADF antenna cables. 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 The GIA 63(X) meets all TSO requirements without external cooling. However, as with all electronic equipment, lower operating temperatures extend equipment life. On the average, reducing the operating temperature by 15-20 C (25 to 35 F) doubles the mean time between failure (MTBF). Recommended airflow rating is 1 CFM (cubic foot per minute) at a pressure equivalent to 0.1 inches of water. Potential damage to your GIA 63(X) may occur by using outside forced air to cool the equipment. Therefore, it is recommended that an electric forced air fan be installed, of the indicated rating, to cool this equipment. Units tightly packed in the avionics stack heat each other through radiation, convection, and sometimes by direct conduction. Even a single unit operates at a much higher temperature in still air than in moving air. Fans or some other means of moving the air around electronic equipment are usually a worthwhile investment. A 5/8 diameter air fitting is provided on the rear of the mounting rack for the purpose of admitting cooling air under such conditions. If a form of forced air cooling is installed, make certain that rainwater cannot enter and be sprayed on the equipment. Refer to the G1000 System Installation manual, Garmin part number 190-00303-00, for information on cooling requirements. 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-11 DRAFT 2.6 GIA 63 Minimum Installation Requirements Below is a list of required devices for TSO-C129a category A1 certification. Pressure Altitude Device This device delivers pressure altitude data to the GIA 63. This data comes from the Garmin GDC 74A Air Data Computer. Manual Course Device This device delivers the manual course select to the GIA 63, which is required for the VOR receiver, and optional for the GPS receiver. Course information can come from an analog resolver, or from the GDU PFD/MFD via Ethernet HSDB. HSI/CDI Indicator or GDU This device displays Nav Flag, Left/Right, To/From, Glideslope Flag, and Up/Down. Qualified GPS Antenna This antenna must meet the following requirements:
1. DO-160C Environmental Conditions The antenna shall meet the environmental conditions listed below and shall conform to the test requirements of RTCA DO-160C. Environmental Condition Category Description Temperature Altitude Temperature Variation Humidity Vibration Waterproofness Fluids Lightning Icing
(operating)
(ground survival) F2 F2 F2 A C CLMY S F 2A C
-55 to +70C
-55 to +85C 55,000 feet 10oC per minute 95% at +55C Turbo/
Reciprocating/
Helicopter Continuous Stream Deicing Fluid Direct Effects 0.15 thick GIA 63 Installation Manual Page 2-12 190-00303-05 Rev. V DRAFT 2. Electrical Characteristics LNA Supply voltage LNA Supply Current LNA Operating Frequency LNA Gain LNA Noise Figure LNA Output VSWR (50 ) LNA Input power at -1 dB Gain Compression LNA Bandwidth
(-3 dB)
(-20 dB)
(-40 dB) 3. Radiation Characteristics Polarization Operating Frequency Gain
(on axis)
(at 160 beam width) Cross Pole Gain (LHCP)
(on axis)
(at 160 beam width) 4. Mounting Requirements 4.5 0.5 VDC 20 mA Maximum 1575.42 2.00 MHz 20 dB Maximum, 12dB Minimum 3.0 dB Maximum 2:1 Maximum
-6 dB Minimum 40 MHz Maximum 100 MHz Maximum 250 MHz Maximum RHCP 1575.42 2.00 MHz 2.0 dBic Minimum
-6.0 dBic Minimum
-8 dBic Maximum
-9 dBic Maximum BNC Female Four 8-32 UNC-2A studs 0.50 long Cable connection Mounting studs 2.7 GIA 63W and GIA 63H Minimum Installation Requirements Below is a list of required devices for TSO-C145a Class 3 or TSO-C145c Class 3 certification. Manual Course Device This device delivers the manual course select to the GIA 63W or GIA 63H, which is required for the VOR receiver, and optional for the GPS receiver. Course information can come from an analog resolver, or from the GDU PFD/MFD via Ethernet HSDB. GDU PFD/MFD This device displays Nav Flag, Left/Right, To/From, Glideslope Flag, and Up/Down as well as integrity messages. In addition it provides manual course selection to the GIA, which is required for the VOR receiver and optional for the GPS receiver. Qualified GPS Antenna Refer to Section 2.1.3.2 for a list of approved antennas. 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-13 DRAFT 2.8 Mounting Requirements The GIA 63(X) 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 GIA 63(W) can be mounted using the G1000 modular system rack, or may be mounted remotely using the Standalone rack. The GIA 63H must be mounted in the Helicopter Rack. Refer to drawings in Appendix B. 2.8.1 Mounting Limitations The GIA 63(X) shall not be mounted in a location where either fluid contamination or water is commonly encountered unless the applicable unit EQF indicates that the unit has claimed the appropriate RTCA DO-
160 categories for these environments. 2.8.2 Modular Rack Considerations Figure 2-2 and Figure B-2 show the GIA 63(W) G1000 modular rack. The modular rack is fastened to the main system rack using the nutplate kit listed in Section 2.1.2. Refer to Figure B-2 for nutplate placement locations. Figure B-1 gives the GIA 63(W) modular rack dimensions. The unit may also be mounted outside of the G1000 system rack. The number and positions of screws noted in Figure B-2 are to be used when mounting the GIA 63(W) modular rack outside of the G1000 system rack. Aircraft manufacturer must fabricate any additional mounting equipment needed, use outline and installation drawings in Appendix B for reference. Figure 2-2. GIA 63(W) Modular Rack GIA 63 Installation Manual Page 2-14 190-00303-05 Rev. V DRAFT 2.8.3 Remote Mounted Stand-Alone Rack Considerations Figure 2-3 and Figure B-4 show the GIA 63(W) remote mounted stand-alone rack. The remote rack 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 for suggested mounting locations. Leave sufficient clearance between the GIA 63(W) and any obstruction. The rack should be mounted to a surface known to have sufficient structural integrity to withstand additional inertia forces imposed by a 7.5-pound (3.4 kg) unit. Figure B-3 gives the GIA 63(W) stand-alone rack dimensions. The rack can be mounted 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 GIA 63(W) chassis has a ground path to the airframe by having at least one mounting screw in contact with the airframe. Figure 2-4 and Figure B-6 show the stand-alone rack used for the GIA 63H installation. Figure B-5 gives the stand-alone rack dimensions for the GIA 63H. The rack can be mounted in any orientation using screws as defined in Section 2.1.3. Ensure that the GIA 63H chassis has a ground path to the airframe by having at least one mounting screw in contact with the airframe. 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. Figure 2-3. GIA 63(W) Standalone Rack 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-15 DRAFT Figure 2-4. GIA 63H Standalone Rack GIA 63 Installation Manual Page 2-16 190-00303-05 Rev. V DRAFT Figure 2-5. GIA 63(W) Standalone Rack, Suggested Mounting Locations 190-00303-05 Rev. W GIA 63 Installation Manual Page 2-17 DRAFT This page intentionally left blank GIA 63 Installation Manual Page 2-18 190-00303-05 Rev. V 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. 190-00303-05 Rev. V GIA 63 Installation Manual Page 3-1 DRAFT 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, 62, and 78-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 C for examples of interconnect wiring diagrams. Construct the actual harnesses in accordance with aircraft manufacturer authorized interconnect standards. Table 3-1. Pin Contact Part Numbers 78 pin connectors (P603, 605, 606), 62 pin connectors (P602), 44 pin connectors (P604 and P601) 16 AWG
(Power Only) 336-00044-01 18-20 AWG
(Power Only) 336-00044-00 N/A N/A N/A N/A N/A N/A 22-28 AWG 336-00021-00 M39029/58-360 204370-02 MC8522D Manufacturer Garmin P/N Military P/N AMP Positronic Table 3-2. Recommended Crimp Tools 18-20 AWG 22-28 AWG Manufacturer Hand Crimping Tool Positioner Military P/N Positronic AMP Daniels Astro M22520/2-01 9507 601966-1 AFM8 615717 N/A 9502-11 N/A K774 N/A Insertion/
Extraction Tool
(Note 2) M81969/1-04 M81969/1-04 91067-1 M81969/1-04 M81969/1-04 Positioner M22520/2-09 9502-3 601966-6 K42 615725 Insertion/
Extraction Tool M81969/1-04 M81969/1-04 91067-1 M81969/1-04 M81969/1-04 NOTES 1. Non-Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice. 2. Extraction of 16 and 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. 3. For applications using 16 AWG wire, contact Garmin for information regarding connector crimp positioner tooling. GIA 63 Installation Manual Page 3-2 190-00303-05 Rev. V DRAFT 3.3 Antenna Installation For the COM, VOR/LOC, and Glideslope antenna, follow the manufacturers instructions. Avoid running other wires and coaxial cables near the VOR/LOC antenna cable. 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. 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 BNC connector (330-00087-00) 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. Coaxial Cable Installation 3. Contacts for the 78, 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. 190-00303-05 Rev. V GIA 63 Installation Manual Page 3-3 DRAFT 3.5 Backshell Assembly The GIA 63(X) connector kit includes six Garmin backshell connectors. The backshell assemblies house the configuration module/temperature sensor, if applicable. Garmins backshell also gives the installer the ability to easily terminate shield grounds at the backshell housing using one of two methods available
(SPIDER or Shield Block). To assemble the backshell and configuration module refer to 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). NOTE Information about the SPIDER grounding system is provided in support of existing installations. All new installations shall use the SHIELD BLOCK grounding system. 3.6 Unit Installation Installation instructions for the GIA 63(W) For installation and assembly, refer to the outline and installation drawings shown in Appendix B of this manual. 1. Assemble the backshell connectors, refer to Section 3.5. 2. Connect backshell connectors to the rear plate using the provided screws. 3. Mount the unit rack to the main system rack or other suitable mounting location, using the nutplates provided for the modular rack or appropriate hardware from Section 2.1.3 for the standalone rack. 4. Assemble the NAV and Main rear plates into the GIA 63(W) unit rack. 5. Carefully slide the GIA 63(W) into the rack. Ensure that the orientation of the unit allows for the engagement of the locking stud in the channel on the rack. The unit can only be installed in one direction. 6. Push the GIA 63(W) lever down towards the bottom of the unit. This engages the locking stud with the dogleg slot and locks unit into the rack. If there is excessive resistance, do not force the unit. 7. Lock the handle into the GIA 63(W) body and tighten the Phillips screw (or push in the D-Ring and twist clockwise 90, for units with a D-Ring). CAUTION Do not use excessive force when inserting the GIA 63(W) into the rack. This may cause damage to the connectors, unit and/or unit rack. If excessive resistance is felt during installation, stop! Remove the GIA 63(W) and identify the source of resistance. The rear plates are designed to float in the unit rack. Check to ensure the rear plates are not bound by the connectors or spring clip. GIA 63 Installation Manual Page 3-4 190-00303-05 Rev. V DRAFT Installation instructions for the GIA 63(H) For installation and assembly, refer to the outline and installation drawings shown in Appendix B of this manual. 1. Assemble the backshell connectors, refer to Section 3.5. 2. Connect backshell connectors to the rear plate using the provided screws. 3. Mount the unit rack to a suitable mounting location, using appropriate hardware from Section 2.1.3 for the helicopter rack. 4. Assemble the NAV and Main rear plates into the GIA 63H unit rack. 5. Carefully place the GIA 63H onto the rack, making sure that the mounting hardware on the bottom of the unit closest to the connectors clears the first set of spring pins on the rack. Once the unit is placed on the rack, slide the unit into the rack until the install screw makes contact. The unit can only be installed in one direction. 6. Using a Hex Driver, tighten the unit into the rack via the install screw. Tighten the screw to the torque specified in Appendix B. CAUTION Do not use excessive force when inserting the GIA 63H into the rack. This may cause damage to the connectors, unit and/or unit rack. If excessive resistance is felt during installation, stop! Remove the GIA 63H and identify the source of resistance. The rear plates are designed to float in the unit rack. Check to ensure the rear plates are not bound by the connectors or spring clip. NOTE The install screw is designed with a ratcheting socket that resists turning counterclockwise, unless pushed in. This ensures that the engagement screw cannot loosen under vibration. 3.7 Post Installation Configuration & Checkout All configuration and checkout procedures take place upon completion of the installation of the Garmin Integrated Flight Deck. The GDU serves as the graphics user interface to the installer configuring the system. For sample configuration and checkout procedures, refer to the G1000 Line Maintenance and Configuration Manual, Garmin part number 190-00303-04. Always use aircraft manufacturer approved checkout documents when performing actual checkout. 190-00303-05 Rev. V GIA 63 Installation Manual Page 3-5 DRAFT 3.8 Continued Airworthiness Maintenance of the GIA 63(X) is on condition for all units installed in airframes that require power interrupt Category B (50mS). For airframes that require the GIA 63(X) to comply with RTCA/DO-160D or RTCA/DO-160E (as specified in applicable Environmental Qualification Form) power interrupt Category A (200mS), one of the following two actions must be taken to ensure backup time is adequate:
Comply with the applicable GIA 63(X) Mod Status (refer to Table 3-3). Table 3-3. Long Term Power Interrupt Category A (200 mS) Mod Status Unit Unit Part Number GIA 63 GIA 63 GIA 63W GIA 63W GIA 63W GIA 63W GIA 63H 011-00781-00 011-00781-01 011-01105-00 011-01105-01 011-01105-20 011-01105-40 011-01105-30 Long Term Power Interrupt Category A (200 mS) Mod Status 4 1 1 0 0 0 0 Or Perform the power interrupt annual inspection as described in Section 3.8.1. GIA 63 Installation Manual Page 3-6 190-00303-05 Rev. V DRAFT 3.8.1 Category A Long Term Power Interrupt Annual Inspection NOTE In order to comply with this procedure GIA 63 main software version must be 5.30 or later, GIA 63W main software version must be 5.21 or later, and GDU main software version must be 7.10 or later. 1. Verify the air temperature around both GIAs is at least 70 Fahrenheit. 2. Apply power to both GIAs. 3. Leave both GIAs on for 10 minutes. 4. Remove power from both GIAs. 5. Wait 30 seconds. 6. Apply power to both GIAs. 7. Place the G1000 in Configuration mode by holding the ENT key on the GDUs while applying power. 8. Using the FMS knob go to the GIA STATUS page (Figure 3-2) on the PFD. 9. Verify the GIA #1 BKUP CAPS light is green. If the BKUP CAPS light is red, replace GIA #1 with a unit of mod status indicated in Table 3-3. 10. Using the FMS knob select GIA2 in the SELECT GIA UNIT field. 11. Verify the GIA #2 BKUP CAPS light is green. If the BKUP CAPS light is red, replace GIA #2, with a unit of mod status indicated in Table 3-3. Figure 3-2. GIA STATUS Page 190-00303-05 Rev. V GIA 63 Installation Manual Page 3-7 DRAFT This page intentionally left blank GIA 63 Installation Manual Page 3-8 190-00303-05 Rev. V DRAFT 4 SYSTEM INTERCONNECTS 4.1 Pin Function List 4.1.1 P601 (COM) Figure 4-1. View of J601 connector from back of unit Table 4-1. P601 (COM) Pin List Pin Name RESERVED (UNSQUELCHED AUDIO TEST) COM UNSQUELCHED AUDIO OUTPUT (011-01105-4X ONLY) RESERVED RESERVED COM MIC KEY*
RESERVED RESERVED COM MIC AUDIO IN HI COM MIC AUDIO IN LO (GROUND) COM 500 AUDIO OUT HI COM 500 AUDIO OUT LO TRANSMIT INTERLOCK*
COM REMOTE TRANSFER*
COM DIGITAL AUDIO OUT ON-SIDE COM MIC DIGITAL AUDIO IN SIGNAL GROUND COM REMOTE POWER OFF AIRCRAFT POWER 1 SPARE CROSS-SIDE COM MIC DIGITAL AUDIO IN (011-01105-2X/-3X/-4X ONLY) AIRCRAFT POWER 1 SPARE AIRCRAFT POWER 1 Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 I/O
Out
In
In
Out Out In In Out In
In In
In In
In 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-1 DRAFT Table 4-1. P601 (COM) Pin List Pin Name SPARE AIRCRAFT POWER 2 SPARE AIRCRAFT POWER 2 SPARE AIRCRAFT POWER 2 RESERVED RESERVED POWER GROUND POWER GROUND RESERVED RESERVED COM SECONDARY TX INTERLOCK* (011-01105-4X ONLY) RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED RESERVED POWER GROUND POWER GROUND Pin 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44
*Indicates Active Low (Ground to activate) Pin not currently supported I/O
In
In
In
In
GIA 63 Installation Manual Page 4-2 190-00303-05 Rev. V DRAFT 4.1.2 P602 (VOR/ILS) Figure 4-2. View of J602 connector from back of unit Table 4-2. P602 (VOR/ILS) Pin List Pin Name VOR/LOC +TO VOR/LOC +FROM (VOR/LOC COMMON) VOR/LOC +FROM (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) VOR/LOC +FLAG VOR/LOC -FLAG (VOR/LOC COMMON) VOR/LOC -FLAG (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) VOR/LOC +LEFT VOR/LOC +RIGHT (VOR/LOC COMMON) VOR/LOC +RIGHT (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) RESERVED VOR/LOC COMPOSITE OUT VOR OBS ROTOR C VOR OBS ROTOR H (GROUND) VOR OBS STATOR E (VOR/LOC COMMON) VOR OBS STATOR E (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) VOR OBS STATOR F VOR OBS STATOR D VOR OBS STATOR G (VOR/LOC COMMON) VOR OBS STATOR G (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) VOR/LOC SUPERFLAG VOR/LOC 500 AUDIO OUT HI VOR/LOC 500 AUDIO OUT LO KING SERIAL DME CLOCK (011-00781-0X AND 011-01105-0X ONLY) KING SERIAL DME DATA (011-00781-0X AND 011-01105-0X ON LY) KING SERIAL RNAV REQUEST (011-00781-0X AND 011-01105-0X ONLY) KING SERIAL RNAV* MODE (011-00781-0X AND 011-01105-0X ONLY) Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 I/O Out Out Out Out Out Out Out Out Out
Out Out
Out Out In In Out Out Out Out Out Out Out In In 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-3 DRAFT Table 4-2. P602 (VOR/ILS) Pin List Pin 22 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 Pin Name SIGNAL GROUND VOR/ILS ARINC 429 OUT B VOR/ILS ARINC 429 OUT A VOR OBI CLOCK VOR OBI SYNC VOR OBI DATA VOR/ILS REMOTE TRANSFER*
ILS ENERGIZE*
RESERVED RESERVED GLIDESLOPE +FLAG PARALLEL DME 1 MHZ-D GLIDESLOPE +UP VOR/ILS ARINC 429 IN B VOR/ILS ARINC 429 IN A PARALLEL DME 100 KHZ-A GLIDESLOPE SUPERFLAG PARALLEL DME 100 KHZ-B PARALLEL DME 100 KHZ-C DME COMMON PARALLEL DME 100 KHZ-D PARALLEL DME 50 KHZ RESERVED PARALLEL DME 1 MHZ-A PARALLEL DME 1 MHZ-B PARALLEL DME 1 MHZ-C RESERVED SIGNAL GROUND RESERVED SPARE SPARE I/O
Out Out Out Out Out In Out
Out Out Out In In Out Out Out Out In Out Out
Out Out Out
GIA 63 Installation Manual Page 4-4 190-00303-05 Rev. V DRAFT Table 4-2. P602 (VOR/ILS) Pin List Pin Name GLIDESLOPE FLAG (GLIDESLOPE COMMON) GLIDESLOPE FLAG (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) PARALLEL DME 100KHZ-E GLIDESLOPE +DOWN (GLIDESLOPE COMMON) GLIDESLOPE +DOWN (NAV COMMON) (011-01105-2X/-3X/-4X ONLY) PARALLEL DME 1MHZ-E RESERVED SPARE GLIDESLOPE COMPOSITE OUT (011-01105-2X/-3X/-4X ONLY) VOR/LOC DIGITAL AUDIO OUT SIGNAL GROUND POWER GROUND POWER GROUND Pin 53 54 55 56 57 58 59 60 61 62 I/O Out Out Out Out Out Out
Out Out
*Indicates Active Low (Ground to activate) Pin not currently supported 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-5 DRAFT 4.1.3 P603 (Main Serial) Figure 4-3. View of J603 connector from back of unit Table 4-3. P603 Main Serial 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 Pin Name RESERVED ETHERNET OUT A ETHERNET OUT B RS-485 4 A RS-485 4 A RS-485 4 B RS-485 4 B MAIN ARINC 429 IN 3 A MAIN ARINC 429 IN 3 B MAIN ARINC 429 IN 4 A MAIN ARINC 429 IN 4 B MAIN ARINC 429 IN 5 A MAIN ARINC 429 IN 5 B MAIN ARINC 429 IN 6 A MAIN ARINC 429 IN 6 B MAIN ARINC 429 IN 7 A MAIN ARINC 429 IN 7 B MAIN ARINC 429 IN 8 A MAIN ARINC 429 IN 8 B CAN BUS 1 HI RESERVED CAN BUS 1 LO RS-485 1 A RS-485 1 B RS-485 2 A I/O
Out Out I/O I/O I/O I/O In In In In In In In In In In In In I/O
I/O I/O I/O I/O GIA 63 Installation Manual Page 4-6 190-00303-05 Rev. V DRAFT Table 4-3. P603 Main Serial Pin 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 Pin Name RS-485 2 B RS-485 3 A/RS-422 IN A RS-485 3 B/RS-422 IN B MAIN ARINC 429 IN 1 A CAN BUS 2 LO MAIN ARINC 429 IN 1 B CAN BUS 2 H MAIN ARINC 429 IN 2 A CAN BUS 1 TERMINATION MAIN ARINC 429 IN 2 B RS-485 5 A/RS-422 OUT A RS-485 5 B/RS-422 OUT B RESERVED CAN BUS 2 TERMINATION RESERVED MAIN RS-232 IN 1 SIGNAL GROUND MAIN RS-232 OUT 1 MAIN RS-232 IN 2 SIGNAL GROUND MAIN RS-232 OUT 2 MAIN RS-232 IN 3 SIGNAL GROUND MAIN RS-232 OUT 3 MAIN RS-232 IN 4 SIGNAL GROUND MAIN RS-232 OUT 4 MAIN RS-232 IN 5 SIGNAL GROUND MAIN RS-232 OUT 5 MAIN RS-232 IN 6 SIGNAL GROUND I/O I/O I/O I/O In I/O In I/O In
In I/O I/O
In
Out In
Out In
Out In
Out In
Out In
190-00303-05 Rev. V GIA 63 Installation Manual Page 4-7 DRAFT Table 4-3. P603 Main Serial Pin 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 Pin Name MAIN RS-232 OUT 6 MAIN RS-232 IN 7 RESERVED SIGNAL GROUND MAIN RS-232 OUT 7 MAIN RS-232 IN 8 SIGNAL GROUND MAIN RS-232 OUT 8 RESERVED GPS PPS OUT RESERVED VOICE ALERT DIGITAL AUDIO OUT MAIN ARINC 429 OUT 1 B MAIN ARINC 429 OUT 1 A MAIN ARINC 429 OUT 2 B MAIN ARINC 429 OUT 2 A MAIN ARINC 429 OUT 3 B MAIN ARINC 429 OUT 3 A ETHERNET IN A ETHERNET IN B RESERVED
*Indicates Active Low (Ground to activate) Pin not currently supported I/O Out In
Out In
Out
Out
Out Out Out Out Out Out Out In In
GIA 63 Installation Manual Page 4-8 190-00303-05 Rev. V DRAFT 4.1.4 P604 (Main Discrete) Figure 4-4. View of J604 connector from back of unit Table 4-4. P604 (Main Discrete) Pin List 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 Pin Name ANNUNCIATE* 22 VOICE ALERT 500 AUDIO OUT HI VOICE ALERT 500 AUDIO OUT LO DISCRETE IN 13 DISCRETE IN 14 ANNUNCIATE* 1 DISCRETE IN* 1 DISCRETE IN* 2 DISCRETE IN* 3 DISCRETE IN 15 AUTOPILOT DISCONNECT IN DISCRETE IN* 4 DISCRETE IN* 5 DISCRETE IN* 6 DISCRETE IN 16 DISCRETE IN 17 DISCRETE IN* 7 DISCRETE IN* 8 DISCRETE IN* 9 DISCRETE IN* 10 DISCRETE IN* 11 GIA SYSTEM ID PROGRAM* 1 GIA SYSTEM ID PROGRAM* 2 DISCRETE IN* 12 ANNUNCIATE* 2 I/O Out Out Out In In Out In In In In In In In In In In In In In In In In In In Out 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-9 DRAFT Table 4-4. P604 (Main Discrete) Pin List Pin 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 Pin Name ANNUNCIATE* 3 ANNUNCIATE* 4 ANNUNCIATE* 5 ANNUNCIATE* 6 ANNUNCIATE* 7 ANNUNCIATE* 8 ANNUNCIATE* 9 ANNUNCIATE* 10 ANNUNCIATE* 11 ANNUNCIATE* 12 ANNUNCIATE* 13 ANNUNCIATE* 14 ANNUNCIATE* 15 ANNUNCIATE* 16 ANNUNCIATE* 17 ANNUNCIATE* 18 ANNUNCIATE* 19 ANNUNCIATE* 20 ANNUNCIATE* 21
*Indicates Active Low (Ground to activate) Pin not currently supported I/O Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out Out GIA 63 Installation Manual Page 4-10 190-00303-05 Rev. V DRAFT 4.1.5 P605 (I/O 1) Figure 4-5. View of J605 connector from back of unit Table 4-5. P605 (I/O 1) Pin List Pin Name RADAR ALTIMETER DC HI RADAR ALTIMETER DC LO DISCRETE IN 18A SPARE SPARE SPARE SPARE FLIGHT DIRECTOR PITCH +UP FLIGHT DIRECTOR PITCH +DOWN FLIGHT DIRECTOR ROLL +RIGHT FLIGHT DIRECTOR ROLL +LEFT DISCRETE IN 19A POTENTIOMETER SIGNAL IN POTENTIOMETER REF IN HI POTENTIOMETER REF IN LO DISCRETE IN 20A MAIN LATERAL DEVIATION +LEFT MAIN LATERAL DEVIATION +RIGHT (MAIN COMMON) MAIN LATERAL +FLAG MAIN LATERAL FLAG (MAIN COMMON) SPARE SPARE MAIN VERTICAL DEVIATION +UP MAIN VERTICAL DEVIATION +DOWN (MAIN COMMON) MAIN VERTICAL +FLAG 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 I/O In In In
In In In In In In In In In Out Out Out Out
Out Out Out 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-11 DRAFT Table 4-5. P605 (I/O 1) Pin List Pin 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 Pin Name MAIN VERTICAL FLAG (MAIN COMMON) SPARE SPARE AIRCRAFT POWER 1 POTENTIOMETER SIGNAL OUT AIRCRAFT POWER 1 POTENTIOMETER REF OUT HI AIRCRAFT POWER 2 POTENTIOMETER REF OUT LO (GROUND) AIRCRAFT POWER 2 GIA REMOTE POWER OFF DISCRETE IN* 1A DISCRETE IN* 2A DISCRETE IN* 3A DISCRETE IN* 4A DISCRETE IN* 5A DISCRETE IN* 6A DISCRETE IN* 7A DISCRETE IN* 8A DISCRETE IN* 9A DISCRETE IN* 10A DISCRETE OUT* 1A SIGNAL GROUND DISCRETE IN* 11A DISCRETE IN 21A DISCRETE IN 22A DISCRETE IN* 12A DISCRETE IN* 13A DISCRETE IN* 14A DISCRETE IN* 15A OUTER MARKER LAMP IN MIDDLE MARKER LAMP IN I/O Out
In Out In Out In Out In In In In In In In In In In In In Out
In In In In In In In In In GIA 63 Installation Manual Page 4-12 190-00303-05 Rev. V DRAFT Table 4-5. P605 (I/O 1) Pin List Pin 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 Pin Name AIRWAY/INNER MARKER LAMP IN DISCRETE IN* 16A DISCRETE IN 23A SIGNAL GROUND MAIN LATERAL SUPERFLAG MAIN VERTICAL SUPERFLAG SUPERFLAG 4A SPARE SPARE SUPERFLAG 1A DISCRETE OUT* 2A DISCRETE OUT* 3A DISCRETE OUT* 4A ANNUNCIATE* 1A ANNUNCIATE* 2A DISCRETE IN* 17A DISCRETE IN 24A SUPERFLAG 2A POWER GROUND SUPERFLAG 3A POWER GROUND
*Indicates Active Low (Ground to activate) Pin not currently supported I/O In In In
Out Out Out
Out Out Out Out Out Out In In Out
Out
190-00303-05 Rev. V GIA 63 Installation Manual Page 4-13 DRAFT 4.1.6 P606 (I/O 2) Figure 4-6. View of J606 connector from back of unit Table 4-6. P606 (I/O 2) Pin List 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 Pin Name 26 VAC VERTICAL GYRO REF HI 26 VAC VERTICAL GYRO REF LO 26 VAC ADF REF HI 26 VAC ADF REF LO 26 VAC AFCS REF HI 26 VAC AFCS REF LO DIRECTIONAL GYRO MOTOR A DIRECTIONAL GYRO MOTOR B SIGNAL GROUND ADF X/COS ADF Y/SIN ADF Z (GROUND) SIGNAL GROUND HEADING X HEADING Y HEADING Z (GROUND) SIGNAL GROUND PITCH ATTITUDE X PITCH ATTITUDE Y PITCH ATTITUDE Z (GROUND) ROLL ATTITUDE X ROLL ATTITUDE Y ROLL ATTITUDE Z (GROUND) SIGNAL GROUND SPARE I/O In In In In In In In In
In In In
In In In
In In In In In In
GIA 63 Installation Manual Page 4-14 190-00303-05 Rev. V DRAFT Table 4-6. P606 (I/O 2) Pin List Pin 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 Pin Name SPARE SPARE SPARE RESERVED SIGNAL GROUND RESERVED ADF DC REF IN RESERVED ANALOG ROLL STEERING H RESERVED ANALOG ROLL STEERING LO (GROUND) HEADING BOOTSTRAP OUT X HEADING BOOTSTRAP OUT Y HEADING BOOTSTRAP OUT Z (GROUND) AC ROLL ATTITUDE OUT HI AC ROLL ATTITUDE OUT LO (GROUND) AC PITCH ATTITUDE OUT HI AC PITCH ATTITUDE OUT LO (GROUND) YAW RATE +RIGHT YAW RATE +LEFT (GROUND) HEADING DATUM HI HEADING DATUM LO (GROUND) COURSE DATUM HI COURSE DATUM LO (GROUND) SIGNAL GROUND 26 VAC DIRECTIONAL GYRO REF HI 26 VAC DIRECTIONAL GYRO REF LO REMOTE ANNUNCIATE CLOCK REMOTE ANNUNCIATE DATA REMOTE ANNUNCIATE SYNC MAIN OBI CLOCK MAIN OBI DATA I/O
In
Out
Out Out Out Out Out Out Out Out Out Out Out Out Out Out
In In In In In Out Out 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-15 DRAFT Table 4-6. P606 (I/O 2) Pin List Pin 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 Pin Name MAIN OBI SYNC MAIN KING SERIAL DME DATA MAIN KING SERIAL DME CLOCK MAIN KING SERIAL DME HOLD* OUT MAIN KING SERIAL DME REQUEST MAIN KING SERIAL DME ON* OUT MAIN KING SERIAL RNAV REQUEST RESERVED RESERVED DISCRETE OUT* 1B DISCRETE OUT* 2B DISCRETE OUT* 3B DISCRETE OUT* 4B DISCRETE OUT* 5B DISCRETE OUT* 6B DISCRETE OUT* 7B DISCRETE OUT* 8B DISCRETE OUT* 9B RESERVED DISCRETE OUT* 10B RESERVED
*Indicates Active Low (Ground to activate) Pin not currently supported I/O Out I/O I/O Out Out Out In
Out Out Out Out Out Out Out Out Out
Out
GIA 63 Installation Manual Page 4-16 190-00303-05 Rev. V DRAFT 4.2 Power and Antennas 4.2.1 Power Functions This section covers the power input requirements. 4.2.1.1 Aircraft Power Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 AIRCRAFT POWER 2 AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFT POWER 2 POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND POWER GROUND Table 4-7. Aircraft Power Connector Pin I/O P601 P601 P601 P601 P601 P601 P605 P605 P605 P605 P601 P601 P601 P601 P602 P602 P605 P605 17 19 21 23 25 27 29 31 33 35 30 31 43 44 61 62 76 78 In In In In In In In In In In
Pins 17, 19, and 21 of P601 are internally connected to form AIRCRAFT POWER 1. Pins 23, 25, and 27 of P601 are internally connected to form AIRCRAFT POWER 2. AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are diode ORed to provide power redundancy. The same applies to pins 29/31 and pins 33/35 of P605. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-17 DRAFT 4.2.1.2 Remote On/Off Pin Name GIA REMOTE POWER OFF COM REMOTE POWER OFF Table 4-8. Remote On/Off Connector P605 P601 Pin 36 16 INACTIVE: Vin 3.5VDC ACTIVE: 10 Vin 33VDC with 75 uA source current Source current is internally limited to 1.5 mA max for a 10-33VDC input 4.2.1.3 Antennas Table 4-9. Antennas Pin Name GPS ANTENNA COM ANTENNA VOR/LOC ANTENNA GLIDESLOPE ANTENNA Connector P611 P612 P613 P614 I/O In In I/O In In In In GIA 63 Installation Manual Page 4-18 190-00303-05 Rev. V DRAFT 4.3 GIA System ID Program The GIA 63(X) utilizes a hard strapping method to assign a unit ID to a unit. Unit IDs identify a unit as a
#1, #2, #3, or #4 GIA. Table 4-10. GIA System ID Program GIA SYSTEM ID PROGRAM*
GIA SYSTEM ID PROGRAM*
1 (P604, Pin 22) 2 (P604, Pin 23) UNIT NUMBER OPEN GROUND OPEN GROUND OPEN OPEN GROUND GROUND 4.4 Serial Data 4.4.1 Serial Data Electrical Characteristics 4.4.1.1 RS-232 Pin Name MAIN RS-232 IN 1 MAIN RS-232 OUT 1 MAIN RS-232 IN 2 MAIN RS-232 OUT 2 MAIN RS-232 IN 3 MAIN RS-232 OUT 3 MAIN RS-232 IN 4 MAIN RS-232 OUT 4 MAIN RS-232 IN 5 MAIN RS-232 OUT 5 MAIN RS-232 IN 6 MAIN RS-232 OUT 6 MAIN RS-232 IN 7 MAIN RS-232 OUT 7 MAIN RS-232 IN 8 MAIN RS-232 OUT 8 Table 4-11. RS-232 Connector P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603
#1
#2
#3
#4 Pin 41 43 44 46 47 49 50 52 53 55 56 58 59 62 63 65 I/O In Out In Out In Out In Out In Out In Out In Out In Out The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least 5V when driving a standard RS-232 load. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-19 DRAFT 4.4.1.2 RS-485/422 Pin Name RS-485 3 A/RS-422 IN A RS-485 3 B/RS-422 IN B RS-485 5 A/RS-422 OUT A RS-485 5 B/RS-422 OUT B RS-485 1 A RS-485 1 B RS-485 2 A RS-485 2 B RS-485 4 A RS-485 4 A RS-485 4 B RS-485 4 B Table 4-12. RS-485/422 Connector Pin P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 27 28 36 37 23 24 25 26 4 5 6 7 I/O I/O I/O I/O I/O I/O I/O I/O I/O I/O I/O I/O I/O The GIA 63(X) contains a total of 5 channels of RS-485 serial data communications. Any two of these channels can also be configured as one RS-422 channel to allow for system flexibility. These data busses conform to EIA standard RS-485, or RS-422, depending on which mode they are currently operating in. GIA 63 Installation Manual Page 4-20 190-00303-05 Rev. V DRAFT 4.4.1.3 ARINC 429 Pin Name MAIN ARINC 429 IN 1 A MAIN ARINC 429 IN 1 B MAIN ARINC 429 IN 2 A MAIN ARINC 429 IN 2 B MAIN ARINC 429 IN 3 A MAIN ARINC 429 IN 3 B MAIN ARINC 429 IN 4 A MAIN ARINC 429 IN 4 B MAIN ARINC 429 IN 5 A MAIN ARINC 429 IN 5 B MAIN ARINC 429 IN 6 A MAIN ARINC 429 IN 6 B MAIN ARINC 429 IN 7 A MAIN ARINC 429 IN 7 B MAIN ARINC 429 IN 8 A MAIN ARINC 429 IN 8 B MAIN ARINC 429 OUT 1 B MAIN ARINC 429 OUT 1 A MAIN ARINC 429 OUT 2 B MAIN ARINC 429 OUT 2 A MAIN ARINC 429 OUT 3 B MAIN ARINC 429 OUT 3 A VOR/ILS ARINC 429 OUT B VOR/ILS ARINC 429 OUT A VOR/ILS ARINC 429 IN B VOR/ILS ARINC 429 IN A Table 4-13. ARINC 429 Connector Pin P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P603 P602 P602 P602 P602 29 31 33 35 8 9 10 11 12 13 14 15 16 17 18 19 70 71 72 73 74 75 23 24 35 36 I/O In In In In In In In In In In In In In In In In Out Out Out Out Out Out Out Out In In The MAIN and VOR/ILS ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-21 DRAFT 4.4.1.4 Can Bus Pin Name CAN BUS 1 HI CAN BUS 1 LO CAN BUS 1 TERMINATION CAN BUS 2 HI CAN BUS 2 LO CAN BUS 2 TERMINATION Table 4-14. Can Bus Connector Pin P603 P603 P603 P603 P603 P603 20 22 34 32 30 39 I/O I/O I/O
I/O I/O
This data bus conforms to the BOSCH standard for Controller Area Network 2.0-B. This bus complies with ISO 11898. CAN BUS TERMINATION should be connected to CAN BUS LO if GIA is located at the end of the bus. 4.4.1.5 Ethernet HSDB Table 4-15. Ethernet HSDB Pin Name ETHERNET OUT A ETHERNET OUT B ETHERNET IN A ETHERNET IN B Connector P603 P603 P603 P603 Pin 2 3 76 77 I/O Out Out In In This Ethernet based high speed data bus (HSDB) provides communications capability with the GDU. HSDB meets the hardware aspects of IEEE standard 802.3 for 10 base T Ethernet communications. GIA 63 Installation Manual Page 4-22 190-00303-05 Rev. V DRAFT 4.5 Discrete I/O Pin Name DISCRETE IN DISCRETE IN*
DISCRETE OUT*
ANNUNCIATE*
ANNUNCIATE*
Table 4-16. Discrete I/O Connector Pin P064 P605 P064 P605 P605 P606 P605 P604 4, 5, 10, 15, 16 3, 12, 16, 50-51, 60, 74 7-9, 12-14, 17-21, 24 37-46, 49, 52-55, 59, 73 47, 68-70 67-75, 77 71, 72 1, 6, 25-44 I/O In In In In Out Out Out Out DISCRETE IN* pins:
INACTIVE: 10 Vin 33VDC or Rin 100k ACTIVE: Vin 1.9VDC with 75 uA sink current, or Rin 375 Sink current is internally limited to 200 uA max for a grounded input DISCRETE IN pins:
INACTIVE: Vin 3.5VDC or open ACTIVE: 6.5 Vin 33VDC with 75 uA source current Source current is internally limited to 1.5 mA max for a 10-33VDC input DISCRETE OUT* pins:
INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33VDC) Leakage current in the INACTIVE state is typically 10 uA to ground ACTIVE: Vout 0.5VDC with 20 mA sink current Sink current must be externally limited to 20 mA max ANNUNCIATE* pins:
INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33VDC) Leakage current in the INACTIVE state is typically 250 uA to ground ACTIVE: Vout 0.5VDC with 500 mA sink current Sink current must be externally limited to 500 mA max 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-23 DRAFT 4.6 COM/VOR/ILS/Digital Audio 4.6.1 COM/VOR/ILS/Digital Audio Function and Emergency Mode Activation of COM MIC KEY* enables COM MIC AUDIO and causes the transceiver to transmit. 500 COM AUDIO and 500 VOR/ILS AUDIO are 100 mW audio outputs that are intended to drive a headset or an audio panel. Digital audio outputs from compatible Garmin GMA series audio panels are 3.87 Vrms into 150 ohms. For COM SW versions previous to 11.00:
Momentarily depressing the COM REMOTE TRANSFER* button toggles the active and standby COM frequencies. The COM REMOTE TRANSFER* input may also be used for EMERGENCY operation of the COM transmitter. If the remote transfer switch is depressed for two seconds, the active COM frequency changes to 121.50 MHz. Once the emergency frequency is activated through COM REMOTE TRANSFER*, the GIA 63(X) ignores inputs from the front panel controls for COM selections only. The pilot may exit this independent moderestoring COM selection control to the front panel knobs and buttonsby momentarily depressing the COM REMOTE TRANSFER* switch. For COM SW Versions 11.00 and later:
The behavior of the COM REMOTE TRANSFER key is configurable in the system configuration. It may be configured to either toggle the active and standby COM frequencies (in which case it operates in the same manner as described above for SW versions previous to 11.00), or enter emergency mode immediately (i.e., tune the COM emergency frequency of 121.500 MHz). It can further be configured to be either a momentary or latched switch. Momentarily depressing the VOR/ILS REMOTE TRANSFER* button toggles the active and standby VLOC frequencies.
(011-00781-0X and 011-01105-0X/-2X/-3X):
When TRANSMIT INTERLOCK* is active, the GIA 63(X) COM receiver sensitivity is decreased. This input is intended to reduce interference from other transmitters in the aircraft. The TRANSMIT INTERLOCK* input should be connected to the PTT input of other transmitters in the aircraft. If connected to multiple PTT inputs, these connections must include diode isolation or multiple radios transmit simultaneously.
(011-01105-4X only):
The COM SECONDARY TX INTERLOCK* input provides a wired-OR connection with TRANSMIT INTERLOCK* to eliminate the need for diode isolation if three COM transceivers are used. If more than three COM transceivers are present, diode isolation must be included externally. For digital audio installations, all of this information is transferred in the digital audio data stream. GIA 63 Installation Manual Page 4-24 190-00303-05 Rev. V DRAFT 4.6.2 Com/VOR/ILS/DIGITAL Audio Electrical Characteristics 4.6.2.1 Com Mic Key Table 4-17. Com Mic Key Pin Name COM MIC KEY*
Connector P601 Pin 4 I/O In INACTIVE: 10 Vin 33VDC or Rin 100k ACTIVE: Vin 1.9VDC with 75 uA sink current, or Rin 375 Sink current is internally limited to 200 uA max for a grounded input 4.6.2.2 Com Mic Audio Table 4-18. Com Mic Audio Connector Pin Name COM MIC AUDIO IN HI In COM MIC AUDIO IN LO (GROUND)
COM MIC AUDIO has a 520 Ohm AC input impedance and supplies the microphone with a 9V bias through 620 Ohms. COM MIC AUDIO is set in the factory for 275 mVRMS to modulate the transmitter at 80% nominally. The microphone gain adjustment is accessible through the GDU PFD/MFD. 4.6.2.3 Com/VOR/ILS Audio P601 P601 Pin I/O 7 8 Table 4-19. Com/VOR/ILS Audio Pin Name COM UNSQUELCHED AUDIO OUT (011-01105-4X ONLY) COM 500 AUDIO OUT HI COM 500 AUDIO OUT LO VOR/LOC 500 AUDIO OUT HI VOR/LOC 500 AUDIO OUT LO VOICE ALERT 500 AUDIO OUT HI VOICE ALERT 500 AUDIO OUT LO Connector P601 P601 P601 P602 P602 P604 P604 Pin 1 9 10 16 17 2 3 I/O Out Out Out Out Out Out Out COM UNSQUELCHED AUDIO OUT supplies at least 280 mVrms across a 500 load. This output is referenced to ground. 500 COM AUDIO and 500 VOR/ILS AUDIO each supply 100 mW into a 500 load. 500 VOICE ALERT AUDIO supplies 50 mW into a 500 load. These are balanced outputs and the LO output must be connected. 500 COM AUDIO is the summation of the COM receiver audio and COM sidetone audio. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-25 DRAFT 4.6.2.4 Digital Audio Table 4-20. Digital Audio Pin Name COM DIGITAL AUDIO OUT ON-SIDE COM MIC DIGITAL AUDIO IN VOICE ALERT DIGITAL AUDIO OUT VOR/LOC DIGITAL AUDIO OUT CROSS-SIDE COM MIC DIGITAL AUDIO IN
(011-01105-2X/-3X/-4X ONLY) Connector Pin P601 P601 P603 P602 P601 13 14 69 59 18 I/O Out In Out Out In When interfaced to a compatible Garmin GMA series audio panel, these can be used in place of analog audio lines. In dual GMA installations the CROSS-SIDE COM MIC DIGITAL AUDIO IN allows a working GMA to access digital audio from both GIAs in the case of a single GMA failure. GIA 63 Installation Manual Page 4-26 190-00303-05 Rev. V DRAFT 4.6.2.5 Discrete Inputs Table 4-21. Discrete Inputs Pin Name TRANSMIT INTERLOCK*
COMM REMOTE TRANSFER*
VOR/ILS REMOTE TRANSFER*
COM SECONDARY TX INTERLOCK*
(011-01105-4X ONLY) Connector P601 P601 P602 P601 Pin 11 12 28 34 I/O In In In In INACTIVE: 10 Vin 33VDC or Rin 100k ACTIVE: Vin 1.9VDC with 75 uA sink current, or Rin 375 Sink current is internally limited to 200 uA max for a grounded input The COM REMOTE TRANSFER* input behavior is dependent on the COM software version and system configurations (refer to Section 4.6.1). VOR/ILS REMOTE TRANSFER* is a momentary input. 4.6.2.6 Marker Beacon Table 4-22. Marker Beacon Pin Name OUTER MARKER LAMP IN MIDDLE MARKER LAMP IN AIRWAY/INNER MARKER LAMP IN Connector P605 P605 P605 Pin 56 57 58 I/O In In In Active high inputs used for outer/middle/inner marker lamp inputs. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-27 DRAFT 4.7 VOR/ILS Indicator 4.7.1 VOR/ILS Indicator Function The VOR/ILS indicator displays both lateral and vertical, To/From indications, lateral flags, vertical flags, and superflags. VOR/LOC COMPOSITE OUT is a standard VOR/localizer composite signal which may be used to drive the Left/Right, TO/FROM, and Flag indications of certain navigational indicators that contain an internal converter. GLIDESLOPE COMPOSITE OUT (011-01105-2X/-3X/-4X ONLY) is a standard glideslope composite signal which may be used to drive UP/DOWN and Flag indications of certain navigational indicators that contain an internal converter. The ILS ENERGIZE* output goes low when the VLOC frequency is channeled to a localizer channel. 4.7.2 VOR/ILS Indicator Electrical Characteristics 4.7.2.1 Superflags Table 4-23. Superflags Pin Name VOR/LOC SUPERFLAG GLIDESLOPE SUPERFLAG Connector P602 P602 Pin 15 38 I/O Out Out The output supplies not less than 500 mA on a 28 volt system with the output voltage not less than
(AIRCRAFT POWER 1.5 VDC) when the flag is to be OUT OF VIEW. The output voltage with respect to ground is less than 0.25 VDC when the flag is to be IN VIEW. 4.7.2.2 Deviation Table 4-24. Deviation Pin Name VOR/LOC +LEFT VOR/LOC +RIGHT (VOR/LOC COMMON) VOR/LOC +RIGHT (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) GLIDESLOPE +UP GLIDESLOPE +DOWN (GLIDESLOPE COMMON) GLIDESLOPE +DOWN (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) Connector Pin P602 P602 P602 P602 5 6 34 55 I/O Out Out Out Out The deviation outputs are each capable of driving up to three 1000 meter loads with 150 mVDC 10%
with respect to 2.5V Common for full-scale deflection. The drive circuit provides for more than full-scale deflection with a maximum course deviation output voltage of 300 mVDC 10%. GIA 63 Installation Manual Page 4-28 190-00303-05 Rev. V DRAFT 4.7.2.3 To/From Table 4-25. To/From Pin Name VOR/LOC +TO VOR/LOC +FROM (VOR/LOC COMMON) VOR/LOC +FROM (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) Connector Pin P602 P602 1 2 I/O Out Out The output is capable of driving up to three 200 meter loads. When indicating TO, the output is
+225 75 mVDC. When indicating FROM, output is -225 75 mVDC. When invalid information is present (Flag IN VIEW) the TO/FROM output is 0 10 mVDC. 4.7.2.4 Flag Table 4-26. Flag Pin Name VOR/LOC +FLAG VOR/LOC -FLAG (VOR/LOC COMMON) VOR/LOC -FLAG (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) GLIDESLOPE +FLAG GLIDESLOPE -FLAG (GLIDESLOPE COMMON) GLIDESLOPE FLAG (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) Connector Pin P602 P602 P602 P602 3 4 32 53 I/O Out Out Out Out The Flag output is capable of driving up to three 1000 meter loads. When valid information is present
(Flag OUT OF VIEW) the Flag output is 375 80 mVDC. When invalid information is present (Flag IN VIEW) the Flag output is 0 25 mVDC. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-29 DRAFT 4.7.2.5 OBS Table 4-27. OBS Pin Name VOR OBS ROTOR C VOR OBS ROTOR H (GROUND) VOR OBS STATOR E (VOR/LOC COMMON) VOR OBS STATOR E (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) VOR OBS STATOR F VOR OBS STATOR D VOR OBS STATOR G (VOR/LOC COMMON) VOR OBS STATOR G (NAV COMMON)
(011-01105-2X/-3X/-4X ONLY) Connector P602 P602 P602 P602 P602 P602 Pin 9 10 11 12 13 14 I/O Out
Out In In Out VOR OBS ROTOR C and H are a buffered 500 Hz output that is intended to drive the OBS rotors. VOR OBS STATOR D and VOR OBS STATOR F are each phase and amplitude shifted version of the VOR ROTOR C output. Each pair is intended to read one of the two windings of the indicators OBS stator. 4.7.2.6 VOR/LOC Composite Table 4-28. VOR/LOC Composite Pin Name VOR/LOC COMPOSITE OUT Connector P602 Pin 8 I/O Out With a Standard VOR Test Signal applied, VOR/LOC COMPOSITE OUT is 0.5 0.1 VRMS into a 10 k load. With a standard localizer centering test signal applied, VOR/LOC COMPOSITE OUT is 0.350 0.05 VRMS into a 10 k load. 4.7.2.7 Glideslope Composite Table 4-29. Glideslope Composite Pin Name GLIDESLOPE COMPOSITE OUT
(011-01105-2X/-3X/-4X ONLY) Connector P602 Pin 58 I/O Out With a standard glideslope centering test signal applied, GLIDESLOPE COMPOSITE OUT is 0.35 +/- 0.05 Vrms into a 10k load. GIA 63 Installation Manual Page 4-30 190-00303-05 Rev. V DRAFT 4.7.2.8 ILS Energize Pin Name ILS ENERGIZE*
Table 4-30. ILS Energize Connector P602 Pin 29 I/O Out INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33VDC) Leakage current in the INACTIVE state is typically 10 uA to ground ACTIVE: Vout 0.5VDC with 20 mA sink current Sink current must be externally limited to 20 mA max 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-31 DRAFT 4.8 RMI/OBI 4.8.1 RMI/OBI Function The VOR OBI output provides bearing information from the active waypoint based upon the VOR receiver. When a localizer channel is tuned on the VLOC window, there is a bit in the data stream set to indicate that a localizer frequency is tuned which stows the needle or drives it to the 3 oclock position. 4.8.2 RMI/OBI Electrical Characteristics Table 4-31. RMI/OBI Pin Name VOR OBI CLOCK VOR OBI SYNC VOR OBI DATA Connector P602 P602 P602 Pin 25 26 27 I/O Out Out Out INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33VDC) Leakage current in the INACTIVE state is typically 10 uA to ground ACTIVE: Vout 0.5VDC with ?20 mA sink current Sink current must be externally limited to 20 mA max GIA 63 Installation Manual Page 4-32 190-00303-05 Rev. V DRAFT 4.9 DME Tuning and ADF 4.9.1 DME Tuning Function The GIA 63(X) can channel a DME based on the tuned VLOC frequency. The GIA 63(X) outputs 2 of 5, BCD or Slip parallel DME and King Serial DME channeling format. When DME COMMON is held low, the GIA 63(X) actively tunes the DME. 4.9.2 DME Interface and ADF Electrical Characteristics 4.9.2.1 Parallel DME Tuning Pin Name PARALLEL DME 1 MHZ-D PARALLEL DME 100 KHZ-A PARALLEL DME 100 KHZ-B PARALLEL DME 100 KHZ-C PARALLEL DME 100 KHZ-D PARALLEL DME 50 KHZ PARALLEL DME 1 MHZ-A PARALLEL DME 1 MHZ-B PARALLEL DME 1 MHZ-C PARALLEL DME 100KHZ-E PARALLEL DME 1MHZ-E NAV DME COMMON Table 4-32. Parallel DME Tuning Connector P602 P602 P602 P602 P602 P602 P602 P602 P602 P602 P602 P602 Pin 33 37 39 40 42 43 45 46 47 54 56 41 I/O Out Out Out Out Out Out Out Out Out Out Out In For each of the parallel DME tuning discrete outputs:
INACTIVE: Floating (can be pulled up to externally sourced Vout in the range 0 Vout 33VDC) Leakage current in the INACTIVE state is typically 10 uA to ground ACTIVE: Vout 0.5VDC with 20 mA sink current Sink current must be externally limited to 20 mA max NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling the DME. INACTIVE: 10 Vin 33VDC or Rin 100k ACTIVE: Vin 1.9VDC with 75 uA sink current, or Rin 375 Sink current is internally limited to 200 uA max for a grounded input 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-33 DRAFT 4.9.2.2 King Serial DME Interface Table 4-33. King Serial DME Interface Connector Pin Pin Name KING SERIAL DME CLOCK
(011-00781-0X AND 011-01105-0X ONLY) KING SERIAL DME DATA
(011-00781-0X AND 011-01105-0X ONLY) KING SERIAL RNAV REQUEST
(011-00781-0X AND 011-01105-0X ONLY) KING SERIAL RNAV* MODE
(011-00781-0X AND 011-01105-0X ONLY) MAIN KING SERIAL DME DATA MAIN KING SERIAL DME CLOCK MAIN KING SERIAL DME REQUEST These pins are used when the GIA 63(X) is configured for King Serial DME tuning. Input logic levels are:
High 6.5 Vdc or greater Low 3.5 Vdc or less 4.9.2.3 Automatic Direction Finder Inputs Table 4-34. Automatic Direction Finder Inputs Connector P606 P606 P606 P606 Pin Name ADF X/COS ADF Y/SIN ADF Z (GROUND) ADF DC REF IN Amplitude:
Input Impedance:
Range:
Resolution:
Accuracy:
DC Reference Input:
DC
-8 Vdc to +8 Vdc
> 80 k 0 to 360 degrees 0.1 degree or better 3.0 degrees 0 to 5 Vdc maximum (>40 k) P602 P602 P602 P602 P606 P606 P606 I/O Out Out In In I/O I/O Out I/O In In
In 18 19 20 21 56 60 62 Pin 10 11 12 32 GIA 63 Installation Manual Page 4-34 190-00303-05 Rev. V DRAFT 4.10 Auto Pilot 4.10.1 Flight Instruments Table 4-35. Flight Instruments Pin Name FLIGHT DIRECTOR PITCH +UP FLIGHT DIRECTOR PITCH +DOWN FLIGHT DIRECTOR ROLL +RIGHT FLIGHT DIRECTOR ROLL +LEFT Connector P605 P605 P605 P605 Pin 8 9 10 11 I/O In In In In Inputs from AFCS that direct the pilot through the PFD. Amplitude Input Impedance Range Limit Resolution Accuracy Flight Director Pitch +UP/+DOWN
-1.0 Vdc to +1.25 Vdc 19 kOhm differential 26 kOhm to ground 10 degrees down and 15 degrees up 0.7mV
+/-13mV with an input voltage of 0V
+/-63mV with an input voltage of +/-1.25V Flight Director Roll +RIGHT/+LEFT
-1.0 Vdc to +1.0 Vdc 19 kOhm differential 26 kOhm to ground
+/- 20 degrees 0.7mV
+/-17mV with an input voltage of 0V
+/-83mV with an input voltage of +/-1.25V The input voltage is positive if FLIGHT DIRECTOR PITCH +UP is greater than FLIGHT DIRECTOR PITCH +DOWN. Otherwise the input voltage is negative. The input voltage is positive if FLIGHT DIRECTOR ROLL +RIGHT is greater than FLIGHT DIRECTOR ROLL +LEFT. Otherwise the input voltage is negative. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-35 DRAFT 4.10.2 Automatic Flight Control System Outputs Table 4-36. Analog Roll Steering Pin Name ANALOG ROLL STEERING HI ANALOG ROLL STEERING LO (GROUND) Connector P606 P606 Pin 34 36 I/O Out
Variable-amplitude output, which is proportional to the aircraft roll command from the GPS navigation system. Amplitude:
Load Impedance:
Scaling:
Range:
Resolution:
Accuracy:
DC
-15 to +15 Vdc
> 5 k 2.0 Vdc per degree of roll command 0 7.5 degrees of roll 0.05 or better 0.3 Table 4-37. Heading Datum Pin Name HEADING DATUM HI HEADING DATUM LO (GROUND) Connector P606 P606 Pin 46 47 I/O Out
Outputs heading datum information to AFCS. Amplitude:
Load Impedance:
Scaling:
Range:
Resolution:
Accuracy:
DC
-15 to +15 Vdc
> 5 k 0.55 Vdc per degree of heading error 0 27 degrees 0.15 or better 1 GIA 63 Installation Manual Page 4-36 190-00303-05 Rev. V DRAFT Table 4-38. Course Datum Pin Name COURSE DATUM HI COURSE DATUM LO (GROUND) Connector P606 P606 Pin 48 49 I/O Out
Outputs course datum information to AFCS. Amplitude:
Load Impedance:
Scaling:
Range:
Resolution:
Accuracy:
DC
-15 to +15 Vdc
> 5 k 0.21 Vdc per degree of course error 0 71 degrees 0.15 or better 1 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-37 DRAFT 4.10.3 Main Deviation Outputs Table 4-39. Main Lateral and Vertical Deviation Pin Name MAIN LATERAL DEVIATION +LEFT MAIN LATERAL DEVIATION +RIGHT (MAIN COMMON) MAIN VERTICAL DEVIATION +UP MAIN VERTICAL DEVIATION +DOWN (MAIN COMMON) Connector P605 P605 P605 P605 Pin 17 18 23 24 I/O Out Out Out Out The deviation output is capable of driving up to three 1000 loads with 150 mVDC 5% for full-scale deflection. The drive circuit provides for more than full-scale deflection with a maximum course deviation output voltage of 300 mVDC 5%. Table 4-40. Main Lateral and Vertical Flag Pin Name MAIN LATERAL +FLAG MAIN LATERAL -FLAG (MAIN COMMON) MAIN VERTICAL +FLAG MAIN VERTICAL FLAG (MAIN COMMON) Connector P605 P605 P605 P605 Pin 19 20 25 26 I/O Out Out Out Out The Flag output is capable of driving up to three 1000 loads. When valid information is present (Flag OUT OF VIEW) the Flag output is 375 80 mVDC. When invalid information is present (Flag IN VIEW) the Flag output is 0 25 mVDC. Table 4-41. Superflag Pin Name MAIN LATERAL SUPERFLAG MAIN VERTICAL SUPERFLAG SUPERFLAG 1A SUPERFLAG 2A SUPERFLAG 3A SUPERFLAG 4A Connector P605 P605 P605 P605 P605 P605 Pin 62 63 67 75 77 64 I/O Out Out Out Out Out Out The output supplies not less than 500 mA on a 28 volt system with the output voltage not less than
(AIRCRAFT POWER 2.0 VDC) when the flag is to be OUT OF VIEW. The output voltage with respect to ground is less than 0.25 VDC when the flag is to be IN VIEW. GIA 63 Installation Manual Page 4-38 190-00303-05 Rev. V DRAFT 4.10.4 Remote Annunciate Data Bus Table 4-42. Remote Annunciate Data Bus Pin Name REMOTE ANNUNCIATE CLOCK REMOTE ANNUNCIATE DATA REMOTE ANNUNCIATE SYNC Connector P606 P606 P606 Pin 53 54 55 I/O In In In These inputs read the remote annunciate data bus that the autopilot uses to tell its remote annunciator panel what mode it is operating in. The GIA 63 requires 4.7 k pull-up resistors to +28 VDC in the aircraft harness for each of these inputs. No pull-up resistors are required for the GIA 63W or GIA 63H. NOTE The GIA 63W and GIA 63H will function properly if the pull-up resistors are installed in the aircraft harness. 190-00303-05 Rev. V GIA 63 Installation Manual Page 4-39 DRAFT This page intentionally left blank GIA 63 Installation Manual Page 4-40 190-00303-05 Rev. V DRAFT APPENDIX A GIA 63 MAIN BOOT BLOCK UPLOADING INSTRUCTIONS NOTE This appendix applies to the GIA 63 only, and does not apply to the GIA 63W or GIA 63H. A.1 Introduction This appendix contains instructions on how to upgrade main boot block software for the GIA 63. Boot block version 4.01 is required for GIA Main Software Version 4.00 or later. CAUTION While performing this procedure ensure the aircraft is connected to and drawing power from a power cart. A loss of power during this procedure may result in a defective GIA 63. A.2 Determining Current Boot Block 1. Ensure the G1000 is powered off. 2. Insert the airframe specific approved software loader card (containing GIA main software version 4.00 or later) into the top slot of the PFD. 3. While holding the ENT key on the PFD, restore power to the PFD. 4. When the words appear in the upper left corner of the PFD, release the ENT key. 5. Press the CLR key at the DO YOU WANT TO UPDATE SYSTEM FILED? prompt. 6. Repeat step 3 and 4 for the MFD. 7. Restore power to all remaining G1000 LRUs. 8. On the MFD use the FMS knob to highlight GIA 1 on the System Status page. Figure A-1. System Status Page 190-00303-05 Rev. W GIA 63 Installation Manual Page A-1 DRAFT 9. On the PFD use the FMS knob to turn to the Software Upload page. 10. Use the FMS knob to highlight GIA 6X software. Figure A-2. GIA 6X Software 11. Press the LRU softkey and highlight GIA 1. 12. Press the ENT key to begin loading software. 13. The boot block version should now appear on the MFD. 14. If GIA main boot block version is 4.00 or earlier press the CANCEL softkey on the PFD and select YES at the prompt. Continue to Section A.3 for instructions on loading GIA main boot block version 4.01. NOTE If GIA main boot block version is 4.01, do not cancel the software upload. 15. Repeat steps 7 through 13 for GIA 2. A.3 Loading Boot Block Version 4.01 1. Remove power from the PFD only. NOTE If power is removed from the entire G1000 system GIA 2 may appear as GIA 1. Insert the GIA 63 boot block version 4.01 loader card into the top slot of the PFD. 2. 3. While holding the ENT key on the PFD, restore power to the PFD. 4. When the words appear in the upper left corner of the PFD, release the ENT key. 5. Use the FMS knob to turn to the Software Upload page on the PFD. 6. Verify GIA 6X Boot Block 4.01 appears in the File List. 7. Verify GIA 1 and GIA 2 appears in the LRU window. 8. Press the FMS knob to highlight GIA 6X Boot Block 4.01. 9. Press the LOAD softkey. 10. Press the ENT key at the BEGIN FILE UPLOAD? prompt. GIA 63 Installation Manual Page A-2 190-00303-05 Rev. W DRAFT CAUTION Do not turn power off or cancel the software upload while the boot block is loading. 11. Confirm update completion and press the ENT key. 12. On the MFD use the FMS knob to turn to the System Status page. 13. Highlight GIA 1. 14. Verify G1000 GIA 6X SYS is being reported in the description field. 15. Power down the G1000. 16. Remove the GIA 63 boot block version 4.01 loader card form the PFD. 17. Continue to Section A.4. A.4 Loading GIA Main Software (only if GIA main software was cancelled in Section A.2) 1. Insert the airframe specific approved software loader card (containing GIA main software version 4.00 or later) into the top slot of the PFD. 2. While holding the ENT key on the PFD, restore power to the PFD. 3. When the words appear in the upper left corner of the PFD, release the ENT key. 4. Press the CLR key at the DO YOU WANT TO UPDATE SYSTEM FILES? prompt. 5. Repeat step 2 and 3 for the MFD. 6. Restore power to all remaining G1000 LRUs. 7. On the PFD use the FMS knob to turn to the Software Upload page. 8. Use the FMS knob to highlight GIA 6X software. Figure A-3. GIA 6X Software 9. Press the LOAD softkey. 10. Press the ENT key at the BEGIN FILE UPLOAD? prompt. 11. Confirm update completion and press the ENT key. 190-00303-05 Rev. W GIA 63 Installation Manual Page A-3 DRAFT This page intentionally left blank GIA 63 Installation Manual Page A-4 190-00303-05 Rev. W DRAFT APPENDIX B OUTLINE AND INSTALLATION DRAWINGS 190-00303-05 Rev. W Figure B-1. GIA 63(W) Modular Installation Outline Drawing GIA 63 Installation Manual Page B-1 DRAFT APPENDIX B OUTLINE AND INSTALLATION DRAWINGS 190-00303-05 Rev. W Figure B-2. GIA 63(W) Modular Installation Drawing GIA 63 Installation Manual Page B-2 DRAFT APPENDIX B OUTLINE AND INSTALLATION DRAWINGS 190-00303-05 Rev. W Figure B-3. GIA 63(W) Standalone Installation Outline Drawing GIA 63 Installation Manual Page B-3 DRAFT APPENDIX B OUTLINE AND INSTALLATION DRAWINGS 190-00303-05 Rev. W Figure B-4. GIA 63(W) Standalone Installation Drawing GIA 63 Installation Manual Page B-4 DRAFT APPENDIX B OUTLINE AND INSTALLATION DRAWINGS 190-00303-05 Rev. W Figure B-5. GIA 63H Standalone Installation Outline Drawing GIA 63 Installation Manual Page B-5 DRAFT APPENDIX B OUTLINE AND INSTALLATION DRAWINGS 190-00303-05 Rev. W Figure B-6. GIA 63H Standalone Installation Drawing GIA 63 Installation Manual Page B-6 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-1. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-1 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-2. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-2 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-3. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-3 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-4. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-4 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-5. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-5 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-6. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-6 DRAFT APPENDIX C INTERCONNECT DRAWINGS 190-00303-05 Rev. W Figure C-7. GIA 63(X) Example Interconnect GIA 63 Installation Manual Page C-7 DRAFT
frequency | equipment class | purpose | ||
---|---|---|---|---|
1 | 2012-11-28 | 118 ~ 136.992 | TNB - Licensed Non-Broadcast Station Transmitter | Original Equipment |
app s | Applicant Information | |||||
---|---|---|---|---|---|---|
1 | Effective |
2012-11-28
|
||||
1 | Applicant's complete, legal business name |
Garmin International Inc
|
||||
1 | FCC Registration Number (FRN) |
0005088588
|
||||
1 | Physical Address |
1200 E. 151st. Street
|
||||
1 |
Olathe, Kansas 66062
|
|||||
1 |
United States
|
|||||
app s | TCB Information | |||||
1 | TCB Application Email Address |
t******@timcoengr.com
|
||||
1 | TCB Scope |
B3: Maritime & Aviation Radio Services equipment in 47 CFR parts 80 & 87
|
||||
app s | FCC ID | |||||
1 | Grantee Code |
IPH
|
||||
1 | Equipment Product Code |
0194500
|
||||
app s | Person at the applicant's address to receive grant or for contact | |||||
1 | Name |
D**** K********
|
||||
1 | Title |
Manager Environmental and Regulatory Affairs
|
||||
1 | Telephone Number |
91344********
|
||||
1 | Fax Number |
913 3********
|
||||
1 |
d******@garmin.com
|
|||||
app s | Technical Contact | |||||
n/a | ||||||
app s | Non Technical Contact | |||||
n/a | ||||||
app s | Confidentiality (long or short term) | |||||
1 | Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | Yes | ||||
1 | Long-Term Confidentiality Does this application include a request for confidentiality for any portion(s) of the data contained in this application pursuant to 47 CFR § 0.459 of the Commission Rules?: | No | ||||
if no date is supplied, the release date will be set to 45 calendar days past the date of grant. | ||||||
app s | Cognitive Radio & Software Defined Radio, Class, etc | |||||
1 | Is this application for software defined/cognitive radio authorization? | No | ||||
1 | Equipment Class | TNB - Licensed Non-Broadcast Station Transmitter | ||||
1 | Description of product as it is marketed: (NOTE: This text will appear below the equipment class on the grant) | AIRBORNE COMMUNICATIONS TRANSCEIVER | ||||
1 | Related OET KnowledgeDataBase Inquiry: Is there a KDB inquiry associated with this application? | No | ||||
1 | Modular Equipment Type | Does not apply | ||||
1 | Purpose / Application is for | Original Equipment | ||||
1 | Composite Equipment: Is the equipment in this application a composite device subject to an additional equipment authorization? | No | ||||
1 | Related Equipment: Is the equipment in this application part of a system that operates with, or is marketed with, another device that requires an equipment authorization? | No | ||||
1 | Grant Comments | Power output is conducted and measured at the antenna terminal. This device contains functions that are not operational in U.S. Territories. This filing is only applicable for U.S. operations. | ||||
1 | Is there an equipment authorization waiver associated with this application? | No | ||||
1 | If there is an equipment authorization waiver associated with this application, has the associated waiver been approved and all information uploaded? | No | ||||
app s | Test Firm Name and Contact Information | |||||
1 | Firm Name |
Rogers Labs, Inc.
|
||||
1 | Name |
S**** R******
|
||||
1 | Telephone Number |
913-8********
|
||||
1 | Fax Number |
913-8********
|
||||
1 |
r******@pixius.net
|
|||||
Equipment Specifications | |||||||||||||||||||||||||||||||||||||||||
---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|---|
Line | Rule Parts | Grant Notes | Lower Frequency | Upper Frequency | Power Output | Tolerance | Emission Designator | Microprocessor Number | |||||||||||||||||||||||||||||||||
1 | 1 | 87 | 118 | 136.975 | 21.7 | 5 ppm | 6K00A3E | ||||||||||||||||||||||||||||||||||
1 | 2 | 87 | 118 | 136.992 | 21.7 | 5 ppm | 5K6A3E |
some individual PII (Personally Identifiable Information) available on the public forms may be redacted, original source may include additional details
This product uses the FCC Data API but is not endorsed or certified by the FCC