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GRS 77/GMU 44 Installation Manual

Page 2-1

190-00303-10

Revision L

2 INSTALLATION

OVERVIEW

2.1 Introduction

This section provides hardware equipment information for installing the GRS 77 AHRS and GMU 44
Magnetometer. Installation of the GRS 77/GMU 44 must follow the aircraft TC or STC requirements.
Cabling is fabricated by the installing agency to fit each particular aircraft. The guidance of FAA
advisory circulars AC 43.13-1B and AC 43.13-2B, where applicable, may be found useful for making
retro-fit installations that comply with FAA regulations. Refer to the G1000 System Installation Manual,
Garmin part number 190-00303-00 for further details on the mechanical aspects.

2.1.1 Unit

Configurations

Model

Applicable

LRU Software
Part Numbers

Installation

Rack

Garmin P/N

GRS 77, (011-00868-00)

All

006-B0223-0(_)

and

006-B0223-1(_)

and

006-B0223-2(_)

and

006-B0223-B(_)

and

006-B0223-C(_)

and

006-B0223-FA

No 010-00295-00

GRS 77, (011-00868-00)

All

006-B0223-0(_)

and

006-B0223-1(_)

and

006-B0223-2(_)

and

006-B0223-B(_)

and

006-B0223-C(_)

and

006-B0223-FA

Yes 010-00295-01

GRS 77 HIRF, (011-00868-10)

All

006-B0223-0(_)

and

006-B0223-1(_)

and

006-B0223-2(_)

and

006-B0223-B(_)

and

006-B0223-C(_)

and

006-B0223-FA

No 010-00295-10

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Summary of Contents for GRS 77

Page 1: ...190 00303 10 March 2010 Revision L GRS 77 GMU 44 Installation Manual ...

Page 2: ...ion of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 U S A Telephone 913 397 8200 Aviation Dealer Technical Support Line Toll Free 888 606 5482 www garmin com Garmin Europe Ltd Liberty House Bulls Copse Road Hounsdown Business Park Southampton SO40 9RB UK Telephone 44 0 8708501241 RECORD OF REVISIONS Revision Revision Dat...

Page 3: ... Number s Section Number Description of Change L 2 5 2 5 1 Added paragraph concerning installation of multiple AHRS DOCUMENT PAGINATION Section Page Range Table of Contents i viii Section 1 1 1 1 8 Section 2 2 1 2 8 Section 3 3 1 3 6 Section 4 4 1 4 6 Section 5 5 1 5 18 Appendix A A 1 A 12 Appendix B B 1 B 4 ...

Page 4: ... 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 WARNING This product its packaging and its com...

Page 5: ...allation Approval Considerations for Pressurized Aircraft 2 3 2 3 Wiring 2 4 2 4 Cooling Air 2 4 2 5 Aircraft Mounting Requirements for GRS 77 GMU 44 2 4 3 INSTALLATION PROCEDURE 3 1 3 1 Unpacking Unit 3 1 3 2 Electrical Connections 3 1 3 3 Backshell Assembly 3 2 3 4 GRS 77 GMU 44 Interconnect Harness Fabrication Instructions 3 3 3 5 GRS 77 and GMU 44 Mounting Instructions 3 4 3 6 GRS 77 Rack to U...

Page 6: ...ircraft Leveling 5 4 5 4 Calibration Procedure A 2 Zero Pitch Roll Offsets by Manual Entry 5 5 5 5 Calibration Procedure B Magnetometer Calibration 5 7 5 6 Calibration Procedure C Heading Offset Compensation 5 10 5 7 Calibration Procedure D Engine Run Up Vibration Test 5 11 5 8 Calibration Procedure E Magnetometer Interference Test 5 13 5 9 Site Evaluation of Magnetic Disturbances for Magnetometer...

Page 7: ...tion Interconnect Wiring Diagram B 3 LIST OF TABLES TABLE PAGE 2 1 Required Distance from Magnetic Disturbances 2 6 3 1 Pin Contact Part Numbers 3 1 3 2 Recommended Crimp Tools 3 1 3 3 Parts Needed for GMU 44 Installation 3 3 3 4 GMU 44 Connector Kit 011 00871 00 Contents 3 3 4 1 P771 Pin Assignments 4 1 4 2 P441 Pin Assignments 4 3 4 3 Aircraft Power Pin Assignments P771 and P441 4 3 4 4 RS 232 P...

Page 8: ...Garmin provided user name and password GRS 77 P N 011 00868 00 HARDWARE MOD LEVEL HISTORY MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION 1 N A N A This modification improves the reliability of certain GRS 77 LRUs 2 N A N A Improves circuit reliability and robustness with the use of improved circuit components 3 N A N A Improves vibration immunity GRS 77 P N 011 008...

Page 9: ...OD LEVEL HISTORY MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION 1 N A N A This modification improves the reliability of certain GMU 44 LRUs GMU 44 P N 011 00870 10 HARDWARE MOD LEVEL HISTORY MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION ...

Page 10: ...Page viii GRS 77 GMU 44 Installation Manual Revision L 190 00303 10 This page intentionally left blank ...

Page 11: ...rovide measurement of Roll Pitch and Heading angles The Garmin AHRS and magnetometer replace traditional rotating mass instruments Using long life solid state sensing technology the GRS 77 AHRS and GMU 44 Magnetometer combine 3 axis angular rate linear acceleration and magnetic field measurements to create an electronically stabilized AHRS The GRS 77 provides the following information in ARINC 429...

Page 12: ...U 44 See Section 4 and Appendix B for connection details GMU 44 to GRS 77 Interface Power RS 232 RS 485 19 200 baud ARINC 429 Input From GDC 74 Air Data Computer low speed 2 ARINC 429 Outputs to GDU 104X PFD MFD high speed 2 ARINC 429 Outputs to GIA 63 W Integrated Avionics Units high speed 2 RS 232 Inputs From GIA 63 W Integrated Avionics Units 19 200 baud 2 Aircraft Power Inputs 1 4 Technical Sp...

Page 13: ...are GRS 77 software versions 3 00 and later RTCA DO 178B Level A GRS 77 software versions prior to 3 00 RTCA DO 178B Level B GMU 44 all software versions RTCA DO 178B Level B Operating Temperature Range 55 C to 70 C Altitude 55 000 Feet 1 4 4 Power Requirements Specification Characteristic Power Requirements Including GMU 44 Supply Voltage 14 28 Vdc See the Environmental Qualification Form for det...

Page 14: ...ight Deck 1 5 1 GMU 44 TSO ETSO Compliance Function TSO ETSO SAE RTCA EUROCAE Category Applicable LRU SW Part Numbers Applicable Custom Logic Device Part Numbers Direction Instrument Magnetic Gyroscopically Stabilized TSO C6d ETSO C6d AS8013A All 006 B0224 __ except 006 B0224 Z _ All 006 C0048 0 _ 1 5 2 GRS 77 and GRS 77H TSO ETSO Compliance The following table applies to both the GRS 77 and the G...

Page 15: ...iation from ETSO C4c to use SAE AS 8001 instead of SAE AS 396B for Minimum Performance Standards and Environmental Standards 2 Garmin was granted a deviation from SAE Aerospace Standard AS 8001 to use RTCA DO 160D instead of RTCA DO 138 as the standard for Environmental Conditions and Test Procedures for Airborne Equipment ETSO C4c GRS 77 3 Neither ETSO C4c nor SAE Aerospace Standard AS 8001 speci...

Page 16: ...r installing the GRS 77 and GMU 44 Before installing the unit the technician should read all referenced materials along with this manual Part Number Document 190 00303 00 G1000 System Installation Manual 190 00303 04 G1000 Line Maintenance and Configuration Manual 190 00313 03 SPIDER Installation Instructions 190 00313 09 Shield Block Installation Instructions ...

Page 17: ...ERCHANTABILITY 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 INCIDE...

Page 18: ...Page 1 8 GRS 77 GMU 44 Installation Manual Revision L 190 00303 10 This page intentionally left blank ...

Page 19: ...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 2 1 1 Unit Configurations Model Applicable LRU Software Part Numbers Installation Rack Garmin P N GRS 77 011 00868 00 All 006 B0223 0 _ and 006 B0223 1 _ and 006 B0223 2 _ and 006 B0223 B _ and 006 B0223 C _ and 006 B0223 FA No 0...

Page 20: ... No 010 00296 00 GMU 44 011 00870 00 All 006 B0224 __ except 006 B0224 Z _ Yes 010 00296 01 GMU 44 011 00870 10 All 006 B0224 __ except 006 B0224 00 and 006 B0224 BA and 006 B0224 FA and 006 B0224 Z _ No 010 00296 10 GMU 44 011 00870 10 All 006 B0224 __ except 006 B0224 00 and 006 B0224 BA and 006 B0224 FA and 006 B0224 Z _ Yes 010 00296 11 Garmin recommends the GMU 44 011 00870 10 with Installati...

Page 21: ...e cabin pressure vessel by connector holes and or mounting arrangements For needed engineering support pertaining to the design and approval of such pressurized aircraft installations it is recommended that the installer proceed according to any of the following listed alternatives 1 Obtain approved installation design data from the aircraft manufacturer 2 Obtain an FAA approved Supplemental Type ...

Page 22: ...ontacts ensure that no two extended barrel 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 n...

Page 23: ... aircraft leveling and offset setting procedure carried out prior to flight This procedure is described in Section 5 Alternatively if the mounting rack can be guaranteed level to within 0 25 of the aircraft level reference the aircraft leveling and offset setting procedure is not required The GRS 77 mounting rack s forward direction must be aligned in heading to within 1 0 of the aircraft forward ...

Page 24: ...feet 3 0 meters 3 feet 1 0 meter Electrical devices drawing less than 100 mA current 2 feet 0 6 meter Magnetic measuring device e g installed flux gates even if not powered 2 feet 0 6 meter Electrical conductors passing less than 100 mA current must be twisted shielded pair if within 10 feet 3 0 meters 1 3 feet 0 4 meter Ensure that any electrical conductor that comes within 10 feet 3 0 meters of ...

Page 25: ...2 5 2 helicopter installations of the GMU 44 must use the 115 00481 10 installation rack using Hole Set B for high vibration installations The Hole Set B instruction drawing is Figure A 2 Sheet 2 on page A 5 2 5 2 2 Consideration for Wing Grounded Lighting Fixtures The following installation practices are recommended when installing the GMU 44 in a wing 1 The wing tip lights should not have a powe...

Page 26: ...Page 2 8 GRS 77 GMU 44 Installation Manual Revision L 190 00303 10 This page intentionally left blank ...

Page 27: ... characteristics of all input and output signals Required connector and associated hardware are supplied in the GRS 77 connector kit P N 011 00869 00 01 and GMU 44 connector kit P N 011 00871 00 See Figures B 1 and B 2 for interconnect wiring diagrams CAUTION Check wiring connections for errors before inserting connectors into the GRS 77 or GMU 44 pigtail Incorrect wiring could cause internal comp...

Page 28: ...rmin for information regarding connector crimp positioner tooling 3 3 Backshell Assembly The GRS 77 connector kit includes a Garmin backshell assembly The backshell assembly houses the configuration module Garmin s backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing using one of two methods available To assemble the backshell ...

Page 29: ...tension Wire 0 M22759 16 22 3 4 9 GMU 44 Connector Kit 1 011 00871 00 5 3 Conductor Cable 0 M27500 22TE3T14 6 2 Conductor Cable 0 M27500 22TE2T14 7 Spider Shield Block Kit 0 011 00980 01 011 01169 00 8 Cast Housing from GRS 77 Connector Kit 0 125 00083 00 Grounding kit is based on airframe and TC STC requirements Table 3 4 lists material in the GMU 44 connector kit The GMU 44 magnetometer has an a...

Page 30: ...r Calibration If the GMU 44 is ever removed the anti rotation properties of the mounting screws must be restored This may be done by replacing the screws with new Garmin PN 211 60037 08 If original screws must be re used coat screw threads with Loctite 242 blue thread locking compound Garmin PN 291 00023 02 or equivalent Important Mounting screws must be brass 3 6 GRS 77 Rack to Unit Flatness Chec...

Page 31: ...failed test gap on unfastened end of unit not within the range of 0 010 inch to 0 070 inch these possibilities must be examined and any deficiencies corrected to pass this check before the installation is acceptable MEASURE GAP MEASURE GAP AT UNFASTENED END AT UNFASTENED END Figure 3 1 Measuring GRS 77 to Mounting Rack with Feeler Gauge 3 7 Post Installation Inspection After the installation is co...

Page 32: ...Page 3 6 GRS 77 GMU 44 Installation Manual Revision L 190 00303 10 This page intentionally left blank ...

Page 33: ...ID PROGRAM 1 In 3 AHRS SYSTEM ID PROGRAM 2 In 4 RESERVED 5 SPARE 6 GPS 2 RS 232 IN In 7 RESERVED 8 SPARE RS 232 IN 1 In 9 MAGNETOMETER POWER OUT Out 10 MAGNETOMETER RS 232 OUT Out 11 GPS 1 RS 232 IN In 12 ARINC 429 OUT 3 A CDU 1 high speed Out 13 ARINC 429 OUT 2 A GIA 2 high speed Out 14 ARINC 429 OUT 1 A GIA 1 high speed Out 15 ARINC 429 IN 1 A AIR DATA low speed In 16 CONFIG MODULE DATA I O 17 C...

Page 34: ... 29 ARINC 429 OUT 1 B GIA 1 high speed Out 30 ARINC 429 IN 1 B AIR DATA low speed In 31 CONFIG MODULE CLOCK Out 32 SPARE 33 ARINC 429 OUT 3 A CDU 2 high speed Out 34 SPARE 35 SIGNAL GROUND GPS 2 36 SPARE 37 SIGNAL GROUND 38 SIGNAL GROUND MAGNETOMETER 39 MAGNETOMETER RS 485 IN B In 40 MAGNETOMETER GROUND 41 SIGNAL GROUND GPS 1 42 SIGNAL GROUND CDU 1 43 SIGNAL GROUND AFCS 44 SIGNAL GROUND AIR DATA A...

Page 35: ...OWER 2 is for connecting to an alternate power source such as on aircraft with two electrical buses Refer to Figures B 1 and B 2 in Appendix B for power connections and Section 1 4 4 for lightning level note Table 4 3 Aircraft Power Pin Assignments P771 and P441 Pin Pin Name Description I O P771 18 AIRCRAFT POWER 1 GRS 77 Unit Power In P771 20 AIRCRAFT POWER 2 GRS 77 Unit Power In P771 9 MAGNETOME...

Page 36: ...ARE RS 232 OUT 1 Data Out Out P771 10 MAGNETOMETER RS 232 OUT Data Out Out P441 8 RS 232 IN Data In In The RS 232 outputs conform to EIA TIA 232C with an output voltage swing of at least 5 V when driving a standard RS 232 load Refer to Figures B 1 and B 2 in Appendix B for the RS 232 serial data interconnections 4 3 2 RS 485 Input Output Table 4 5 RS 485 Pin Assignments P771 and P441 Pin Pin Name ...

Page 37: ...t Out 29 ARINC 429 OUT 1 B GIA 1 high speed Data Out Out 28 ARINC 429 OUT 2 B GIA 2 high speed Data Out Out 43 SIGNAL GROUND AFCS Ground 15 ARINC 429 IN 1 A AIR DATA low speed Data In In 30 ARINC 429 IN 1 B AIR DATA low speed Data In In 44 SIGNAL GROUND AIR DATA Ground 41 SIGNAL GROUND GPS 1 Ground 35 SIGNAL GROUND GPS 2 Ground 37 SIGNAL GROUND Ground 4 3 4 Configuration Module Connections The con...

Page 38: ...ce of the GDC 74A ARINC 429 labels in a system with more than one GRS 77 The GRS 77 System ID can be set to All Call 1 2 or 3 for such purposes Table 4 8 identifies which pins on connector P741 are used to select the desired System ID 4 3 7 GRS 77 System ID Strapping By hard strapping the program pins listed in Table 4 8 to ground or open the GRS 77 is assigned a System ID The System ID is include...

Page 39: ... NOTE The following procedures reflect a Garmin G1000 installation 5 1 Function Selector Switches and Display There are no operating controls or displays on the GRS 77 GMU 44 5 2 Post Installation Calibration Procedures After mechanical and electrical installation of the GRS 77 AHRS and GMU 44 magnetometer have been completed prior to operation a set of post installation calibration procedures mus...

Page 40: ...E Magnetometer Interference Test Validate no magnetic interference with GMU 44 Required for initial installation certification This test should also be repeated to verify all subsequent electrical changes associated with devices within 10 0 feet of the GMU 44 magnetometer Such changes include but are not limited to wiring shielding or grounding changes to any light strobe beacon or other electrica...

Page 41: ...n 10 0 feet of the GMU 44 magnetometer location after the magnetometer interference test or magnetometer calibration procedure were completed requires a repeat of both procedures Furthermore electrical changes to the installation that affect components within 10 0 feet of the GMU 44 magnetometer after the magnetometer calibration and magnetometer interference procedures were completed will require...

Page 42: ...ftkey 12 6 Press in the FMS small knob to highlight GRS 77 1 The FMS small knob can now be turned to select either GRS 77 1 or GRS 77 2 for calibration Press the ENTER key after selecting which GRS 77 unit to calibrate The Select Procedure field is now blinking 7 The FMS small knob can now be used to select which calibration validation procedure to run Select PITCH ROLL OFFSET then press the ENTER...

Page 43: ...tkey 12 3 Press the FMS small knob to highlight GRS 77 1 The FMS small knob can now be turned to select either GRS 77 1 or GRS 77 2 for calibration Press the ENTER key after selecting which GRS 77 unit to calibrate The Select Procedure field is now blinking 4 The FMS small knob can now be used to select which calibration validation procedure to run Select PITCH ROLL OFFSET then press the ENTER key...

Page 44: ...actly 0 00 using the FMS small and large knobs as described above Press the ENTER key when finished with the roll offset 12 When the RECORD OFFSETS field is blinking press the ENTER key to complete data entry 13 The result of the pitch roll offset compensation is displayed on the PFD If successful the AHRS records the required pitch and roll offsets informs the operator of a successful conclusion ...

Page 45: ... the magnetometer from passing within twenty feet 6 1 meters of such objects Additionally ensure that vehicles or other aircraft are an adequate distance forty feet 12 2 meters away from the aircraft under test At the site align the aircraft to a heading of magnetic north 5 The aircraft should be positioned to enable clockwise turning around the compass rose For fixed wing aircraft it is best to o...

Page 46: ... the procedure 9 The PFD advises the operator when to turn the aircraft when to stop and when to turn again 10 FOR FIXED WING AIRCRAFT Upon instruction to turn taxi the aircraft in a right turn After approximately 30 of turn from the last heading the PFD instructs the operator to stop the aircraft FOR HELICOPTER Upon instruction to turn lift the aircraft off the ground and maintain a level orienta...

Page 47: ...nimum of 2 successful stations per quadrant is required where a successful station is a full 18 second countdown followed by instruction to move Ensure that if stations are skipped at least a minimum of 2 stations per quadrant are completed Thus it may sometimes be required to dwell at a station after a countdown restart A maximum of 30 stations is allowed for the entire calibration procedure If t...

Page 48: ...the following steps a If the PFD is not displaying the GRS GMU CALIBRATION configuration page follow steps from calibration procedure A 1 listed previously b The FMS small knob can now be used to select which calibration validation procedure to run Select HEADING OFFSET then press the ENTER key If the HEADING OFFSET selection is still blinking press the ENTER key again c Follow the checklist items...

Page 49: ...3 When the operator has completed the engine run up and the engine is back to an idle setting press the ENTER key to indicate that the process is complete When this is done the TEST COMPLETE field stops blinking 4 The PFD informs the operator if the installation has passed or failed the vibration test If the test fails the specific measurements causing the failure are identified and numeric values...

Page 50: ... or GMU 44 not firmly secured to supporting structure h An engine propeller combination that is significantly out of balance In some aircraft attempting the engine runup test on a day with very strong and or gusty winds may cause the test to occasionally fail However windy conditions should not be taken as evidence that the test would pass in calm conditions an actual pass is required before the i...

Page 51: ...ecution of this procedure Garmin recommends this test be performed at least once every 12 months by all aircraft manufacturers on a minimum of one production aircraft for every airframe type or model equipped with the G1000 system 1 Initiate the AHRS magnetometer interference test procedure by performing the following steps a If the PFD is not displaying the GRS GMU CALIBRATION configuration page ...

Page 52: ...ke up 1 50 Speed brake down 2 00 Navigation lights on 2 10 Navigation lights off 2 20 Landing lights on 2 30 Landing lights off 2 40 Taxi lights on 2 50 Taxi lights off 3 00 Landing Taxi lights on 3 10 Landing Taxi lights off 3 20 Strobes on 3 30 Strobes off 3 40 Recognition lights on 3 50 Recognition lights off 4 00 Turn on all wing tip lights simultaneously typically will include navigation ligh...

Page 53: ... Only 2 40 Landing lights off REAR Only 2 50 Landing lights on FWD REAR 3 00 Landing lights off FWD REAR 3 10 Strobes on 3 20 Strobes off 3 30 Turn on all lights simultaneously typically will include navigation lights recognition lights and strobe 3 40 Turn off all lights simultaneously 3 50 Pitot heat on 4 00 Pitot heat off 4 10 Air conditioning system on 4 20 Air conditioning system off 4 30 End...

Page 54: ...medied The magnetometer interference test must be repeated until passed When the magnetometer interference test fails record the three magnetometer maximum deviation values and their corresponding timestamps A maximum deviation value greater than 5 0 milliGauss in either the X or Y axes or greater than 8 0 milligauss in the Z axis indicates a problem that must be resolved Compare the corresponding...

Page 55: ...compensation procedure Procedure A 1 However prior completion of the Magnetometer Calibration Procedure Procedure B is not required In order to evaluate a candidate site the Magnetometer Calibration Procedure must be performed twice once turning clockwise around the site and once turning counter clockwise Both times the procedure should be conducted as described in Section 5 5 of this document wit...

Page 56: ...ctions for the site to be considered acceptable More than one failure out of ten attempts in a given direction would be sufficient reason to conclude the site is not acceptable A site that is used repeatedly to perform the Magnetometer Calibration Procedure should be re evaluated every 12 months and after any significant construction or placement of magnetic objects above or below ground within 50...

Page 57: ...APPENDIX A OUTLINE AND INSTALLATION DRAWINGS GRS 77 GMU 44 Installation Manual Page A 1 Page A 2 blank 190 00303 10 Revision L Figure A 1 GRS 77 Outline Drawing With Mounting Rack ...

Page 58: ...APPENDIX A OUTLINE AND INSTALLATION DRAWINGS GRS 77 GMU 44 Installation Manual Page A 3 Page A 4 blank 190 00303 10 Revision L Figure A 2 GMU 44 Mounting Rack Sheet 1 of 2 ...

Page 59: ...APPENDIX A OUTLINE AND INSTALLATION DRAWINGS GRS 77 GMU 44 Installation Manual Page A 5 Page A 6 blank 190 00303 10 Revision L Figure A 2 GMU 44 Mounting Rack Sheet 2 of 2 ...

Page 60: ...APPENDIX A OUTLINE AND INSTALLATION DRAWINGS GRS 77 GMU 44 Installation Manual Page A 7 Page A 8 blank 190 00303 10 Revision L Figure A 3 GMU 44 Top Mounted Installation ...

Page 61: ...APPENDIX A OUTLINE AND INSTALLATION DRAWINGS GRS 77 GMU 44 Installation Manual Page A 9 Page A 10 blank 190 00303 10 Revision L Figure A 4 GMU 44 Bottom Mounted Installation ...

Page 62: ...APPENDIX A OUTLINE AND INSTALLATION DRAWINGS GRS 77 GMU 44 Installation Manual Page A 11 Page A 12 blank 190 00303 10 Revision L Figure A 5 GMU 44 Wiring Detail ...

Page 63: ...APPENDIX B INTERCONNECT DRAWINGS GRS 77 GMU 44 Installation Manual Page B 1 Page B 2 blank 190 00303 10 Revision L Figure B 1 Typical GRS 77 GMU 44 Interconnect Wiring Diagram ...

Page 64: ...APPENDIX B INTERCONNECT DRAWINGS GRS 77 GMU 44 Installation Manual Page B 3 Page B 4 blank 190 00303 10 Revision L Figure B 2 Simplified GRS 77 GMU 44 Installation Interconnect Wiring Diagram ...

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