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190-01639-00

GSU 75 ADAHRS Installation Manual

Revision 6

Page A-3

APPENDIX A ASSEMBLY AND INSTALLATION DRAWINGS

Figure A-3 GMU 44 (-00) Mounting Rack

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The document reference is online, please check the correspondence between the online documentation and the printed version.

Summary of Contents for GSU 75 Series

Page 1: ...190 01639 00 May 2017 Revision 6 GSU 75 ADAHRS Installation Manual 340095 The document reference is online please check the correspondence between the online documentation and the printed version...

Page 2: ...or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151st Street Olathe KS 66062 USA Telephone 913 397 8200 Aviation Panel Mount Technical Support Line Toll Free 1 888 606 5...

Page 3: ...s Proposition 65 If you have any questions or would like additional information please refer to our web site at www garmin com prop65 The following tables identify hardware modification Mod Levels for...

Page 4: ...ION 1 N A N A Operating high temperature reduced to 65 C MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE...

Page 5: ...GMU 44 P N 011 00870 20 HARDWARE MOD LEVEL HISTORY MOD LEVEL SERVICE BULLETIN NUMBER SERVICE BULLETIN DATE PURPOSE OF MODIFICATION 340095 The document reference is online please check the corresponde...

Page 6: ...2 5 2 11 Mounting Requirements 2 6 Section 3 INSTALLATION PROCEDURE 3 1 3 1 Unpacking Unit 3 1 3 2 Wiring Harness Installation 3 1 3 3 Backshell Assembly and Installation 3 3 3 4 GSU 75 GMU 44 Interco...

Page 7: ...ero Pitch Roll Offsets by Manual Entry 5 4 5 5 Calibration Procedure B Magnetometer Calibration 5 5 5 6 Calibration Procedure C Heading Offset Compensation 5 7 5 7 Calibration Procedure D Engine Run U...

Page 8: ...ctor J441 4 3 Section 5 POST INSTALLATION CONFIGURATION AND CHECKOUT PROCEDURE5 1 Figure 5 1 Fixed wing and Helicopter Position Examples 5 5 Appendix A ASSEMBLY AND INSTALLATION DRAWINGS A 1 Figure A...

Page 9: ...ble 2 6 Contents of GSU 75 Connector Kit 011 03109 00 2 2 Table 2 7 Contents of GTP 59 OAT Probe Kit 011 00978 00 2 2 Table 2 8 Recommended Distance from Magnetic Disturbances 2 8 Section 3 INSTALLATI...

Page 10: ...tem ID Connections 4 9 Table 4 16 GSU 75 System ID Inputs 4 9 Section 5 POST INSTALLATION CONFIGURATION AND CHECKOUT PROCEDURE5 1 Table 5 1 Post Installation Calibration Procedure Summary 5 1 Table 5...

Page 11: ...es 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 Feder...

Page 12: ...ity is 250 s However ARINC 429 angular rate output messages are limited to 128 per second Bank error and pitch error are within 1 0 in static conditions and 2 5 under dynamic and flight conditions Hea...

Page 13: ...n Integrated Avionics Units 2 RS 232 AHRS Inputs Outputs from GIA 6X Garmin Integrated Avionics Units 2 PPS Inputs 4 Discrete Inputs 2 System ID Program pins 2 Aircraft Power Inputs 1 4 Technical Spec...

Page 14: ...excluding pigtail 3 35 inches 85 1 mm diameter including flange Table 1 3 Physical Characteristics GMU 44 011 00870 20 Specification Characteristic GMU 44 Weight 0 37 lbs 0 17 kg unit only 0 52 lbs 0...

Page 15: ...Aircraft Pressure Altitude Range 1 400 feet to 55 000 feet Aircraft Vertical Speed Range 20 000 feet per minute to 20 000 feet per minute Aircraft Airspeed Range 20 Knots to 435 Knots Aircraft Mach R...

Page 16: ...5 1 TSO ETSO Compliance Table 1 6 TSO ETSO Authorizations for GMU 44 Function TSO ETSO SAE RTCA EUROCAE Category Applicable LRU SW Part Numbers Applicable Custom Logic Device Part Numbers Direction In...

Page 17: ...d for Environmental Conditions and Test Procedures for Airborne Equipment 5 Garmin has been granted a deviation from TSO C106 to modify the requirement in SAE AS 8002A paragraph 9 2 e to allow the uni...

Page 18: ...2 Garmin was granted a deviation from TSO C6d to use RTCA DO 178B instead of RTCA DO 178A to demonstrate compliance for the verification and validation of the computer software 3 Garmin was granted a...

Page 19: ...0 010 01127 00 GSU 75H Unit 011 03094 20 010 01127 20 GSU 75B Unit 011 03094 40 010 01127 40 Table 2 2 GMU 44 Part Numbers Item Garmin Catalog Part Number GMU 44 Unit 011 00870 00 010 00296 00 GMU 44...

Page 20: ...115 00481 10 Table 2 6 Contents of GSU 75 Connector Kit 011 03109 00 Item Garmin Number Quantity Configuration Module w EEPROM Jackscrew 011 00979 20 1 50 78 pin Backshell w Hardware Jackscrew 011 018...

Page 21: ...f heat or RF 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 2 6 Electrical Bonding Electri...

Page 22: ...deformations of the airframe surface have been made that would affect the relationship between static air pressure and true ambient static air pressure for any flight condition Refer to part 43 Append...

Page 23: ...oved installation design data from the aircraft manufacturer 2 Obtain an FAA approved Supplemental Type Certificate STC pertaining to and valid for the subject installation 3 Contact the FAA Aircraft...

Page 24: ...gravity The mounting location for the GSU 75 should be protected from rapid thermal transients in particular large heat loads from nearby high power equipment The GSU 75 mounting rack should be level...

Page 25: ...SU 75 ADAHRS Installation Manual Rev 6 Page 2 7 Figure 2 2 GSU 75 with Mounting Rack 340095 The document reference is online please check the correspondence between the online documentation and the pr...

Page 26: ...le so long as adequate measures are taken to ensure a stiffened mounting structure Align the GMU 44 mounting rack to within 3 0 of the aircraft level reference in pitch and roll The GMU 44 must be mou...

Page 27: ...m flowing in the wing skin that encloses the GMU 44 Electrically isolating the light assembly should not be used as an alternative to item 1 above unless the isolated light assembly has been analyzed...

Page 28: ...one 78 pin d sub connector see Figure 4 1 Connections to the GMU 44 Magnetometer are made through a 9 pin connector Figure 4 2 Connector detail is shown in Figure 3 2 Section 4 defines the electrical...

Page 29: ...Positronic 9507 9502 11 M81969 1 04 9502 4 M81969 1 04 AMP 601966 1 N A 91067 1 601966 6 91067 1 Daniels AFM8 K774 M81969 1 04 K42 M81969 1 04 Astro 615717 N A M81969 1 04 615725 M81969 1 04 Extractin...

Page 30: ...ields To assemble the backshell refer to the Jackscrew Backshell Installation Instructions 190 00313 11 document To assemble the Configuration Module refer to the Configuration Module Installation int...

Page 31: ...an appropriate degreaser b Composite Airframe Refer to the appropriate lightning certification document for zone requirements and current levels to determine an acceptable mounting location for the s...

Page 32: ...ip back approximately 0 17 inches of insulation from each wire of the 3 conductor cable item 3 and crimp a pin socket item 11 to each conductor It is the responsibility of the installer to determine t...

Page 33: ...ation item 12 as shown in Figure B 1 9 Connect the 16 AWG pigtail wire item 8 to connector item 12 Join the ring terminal item 9 to the strain relief item 7 using the screws item 10 provided in the GS...

Page 34: ...DAHRS Installation Manual Rev 6 Page 3 7 Figure 3 3 GTP 59 Outline and Installation Drawing 340095 The document reference is online please check the correspondence between the online documentation and...

Page 35: ...tic pressure port is plumbed directly to the unit static pressure input port and the aircraft pitot pressure port is plumbed directly to the unit pitot pressure input port 2 Seal the threads of pneuma...

Page 36: ...ning magnetic effect can be compensated for using Calibration Procedure B Magnetometer Calibration If the GMU 44 is ever removed the anti rotation properties of the mounting screws must be restored Th...

Page 37: ...nit on the remote rack 2 Slide the GSU 75 back until the feet are fully engaged with the remote rack 3 Push down and simultaneously turn each retention screw clockwise Torque each retention screw to 1...

Page 38: ...pendix E paragraph b 2 Garmin specifies a test procedure equivalent to Part 43 Appendix E paragraph b 1 with two exceptions The tests of sub paragraphs iv Friction and vi Barometric Scale Error are no...

Page 39: ...32 OUT AHRS 3 Out 13 MAGNETOMETER POWER OUT Out 14 AIRCRAFT POWER 1 In 15 SIGNAL GROUND 16 AIRCRAFT POWER 2 In 17 RS 232 OUT ADC 2 Out 18 RS 232 IN ADC 2 In 19 RESERVED 20 RESERVED 21 ARINC 429 OUT AD...

Page 40: ...RS 1A In 46 ARINC 429 IN AHRS 1B In 47 ARINC 429 IN AHRS 3A In 48 SIGNAL GROUND 49 ARINC 429 OUT ADAHRS 2A Out 50 ARINC 429 OUT ADAHRS 2B Out 51 RS 232 OUT AHRS 1 Out 52 RS 232 IN AHRS 1 In 53 CONFIG...

Page 41: ...3 RS 232 AHRS 2 GROUND 74 CONFIG MODULE GROUND 75 SYS ID 1 In 76 DISCRETE IN 3 In 77 DISCRETE IN 4 In 78 DISCRETE IN 2 In Table 4 2 J441 Pin Assignments Pin Pin Name I O 1 SIGNAL GROUND 2 RS 485 OUT B...

Page 42: ...to Section 4 5 and Figure B 1 for OAT Power pin 6 J751 information Table 4 3 GSU 75 Aircraft Power Pin Name Pin I O AIRCRAFT POWER 1 14 In AIRCRAFT POWER 2 16 In POWER GROUND 34 POWER GROUND 36 AIRCR...

Page 43: ...NC 429 OUT ADAHRS 3A 8 28 Out ARINC 429 OUT ADAHRS 3B 9 29 Out ARINC 429 IN AHRS 1A 45 In ARINC 429 OUT AHRS 1A 27 Out ARINC 429 IN AHRS 1B 46 In ARINC 429 IN AHRS 2B 66 In ARINC 429 IN AHRS 3B 67 In...

Page 44: ...FIG MODULE DATA 54 I O CONFIG MODULE CLOCK 55 Out CONFIG MODULE GROUND 74 Table 4 8 GSU 75 RS 232 I O Pin Name Pin I O RS 232 IN ADC 1 70 In RS 232 OUT ADC 1 69 Out RS 232 ADC 1 GROUND 68 RS 232 IN AD...

Page 45: ...IVE Vin 3 5 VDC ACTIVE 10 Vin 33 VDC with 75 A source current Source current will not exceed 2 0 mA for a 10 33 VDC input Table 4 10 GSU 75 RS 422 I O Pin Name Pin I O RS 422 IN A 10 In RS 422 IN B 11...

Page 46: ...single ended and a differential PPS signal from the GPS The single ended PPS input accepts a 0 5V CMOS logic level signal The differential PPS input conforms to the electrical specifications of the EI...

Page 47: ...C 429 word The System ID indicates there is only a single ADC installed All Call or if multiple units are installed which ADC the data originates from 1 or 2 When a single GSU 75 is installed in the s...

Page 48: ...n Installations Requiring Procedure A 1 Pitch Roll Offset Compensation Level Aircraft Either procedure A 1 or A 2 is required for all installations Procedure A 1 is recommended A 2 Zero Pitch Roll Off...

Page 49: ...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...

Page 50: ...bration Press the following softkeys in sequence a softkey 9 b softkey 10 c softkey 11 d softkey 12 6 Press in the FMS small knob to highlight GSU 75 1 The FMS small knob can now be turned to select e...

Page 51: ...n is still blinking press the ENTER key again 5 Contact Garmin for password 6 Follow the checklist items displayed on the PFD and press the ENTER key as each one is completed or confirmed 7 When the P...

Page 52: ...icles 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 positio...

Page 53: ...iculties in executing smooth accurate turns the PFD may incorrectly interpret a station and instruct to HOLD POSITION prior to full completion of a 30 turn If this scenario is encountered it is best f...

Page 54: ...uired that the aircraft be physically towed by hand Towing tugs should not be used as they distort the magnetic field in their vicinity 1 Initiate the AHRS heading offset calibration mode by performin...

Page 55: ...The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over the course of a couple of minutes 3 When the operator has completed the engine run u...

Page 56: ...pports recommended by the aircraft manufacturer f GSU 75 connector not firmly attached to unit g Cabling leading to GSU 75 or GMU 44 not firmly secured to supporting structure h An engine propeller co...

Page 57: ...every 12 months by all aircraft manufacturers on a minimum of one production aircraft for every airframe type or model equipped with the Garmin Integrated Flight Deck system 1 Initiate the AHRS magne...

Page 58: ...n 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 Reco...

Page 59: ...50 Cyclic full back 1 00 Cyclic centered 1 10 Collective full negative 1 20 Collective full positive 1 30 Anti Torque full left 1 40 Anti Torque full right 1 50 Navigation lights on 2 00 Navigation l...

Page 60: ...nce tests Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem Contact Garmin for assistance in resolving the problem The acceptable magne...

Page 61: ...e installation used to evaluate the site must have already completed the pitch roll offset compensation procedure Procedure A 1 However prior completion of the Magnetometer Calibration Procedure Proce...

Page 62: ...FUL SITE IS CLEAN in both the clockwise and counter clockwise directions for the site to be considered acceptable More than one failure out of ten attempts in a given direction would be sufficient rea...

Page 63: ...18 54 44 11 0 2 375 010 60 33 0 25 313 7 94 3 00 76 2 2X 1 16 29 5 1 01 25 7 98 24 9 1 5 37 PITOT AIR FITTING 1 8 27 ANPT FEMALE THREAD STATIC AIR FITTING 1 8 27 ANPT FEMALE THREAD P751 NOTES DIMENSIO...

Page 64: ...75 RACK 117 00608 00 330 00776 78 NOTE 1 011 01855 04 NOTES GASKET IS PART OF 330 00776 78 INSTALL GASKET OVER PINS 1 REFER TO 190 01639 00 FOR ADDITIONAL PARTS LISTS 2 CONNECTOR KIT SEE NOTE 2 011 0...

Page 65: ...BLY AND INSTALLATION DRAWINGS Figure A 3 GMU 44 00 Mounting Rack 08 02817 1 5 25 5 1 7 3 237 21 5 1 2 6 25 2 2 1 6 5 6 5 5 7 02817 1 2 6 25 25 5 72 5 1 6 340095 The document reference is online please...

Page 66: ...17 1 2 3 77 51 6 7 02817 1 5 2 6 7 02817 1 2 6 5 86 7 7 7 51 7 5 5 7 02817 1 2 3 77 51 25 9 5 7 21 167 7 216 7 7 02817 1 5 237 21 5 1 2 6 25 2 2 1 6 5 6 86 1 2 1 1876 25 5 1 7 3 25 5 08 02817 1 5 7 51...

Page 67: ...MU 44 00 and 10 Top Mounted Installation 5 5 7 02817 1 685 0 16 216 5 120 1 1 72 5 1 6 5 08 1 167 7 21 520 29 35 55 08 25 25 5 5 7 02817 1 5 6 6 2 1 7 5 66 6 5 6 5 66 6 5 6 7 287 5 1 2 6 211 725 7 340...

Page 68: ...44 00 and 10 Bottom Mounted Installation 08 25 7 5 66 6 5 6 5 66 6 5 6 7 287 5 1 2 6 211 725 7 25 5 5 7 02817 1 5 6 6 2 1 5 5 7 02817 1 685 08 1 167 7 21 520 2 127 35 55 0 16 216 5 120 1 1 72 5 1 6 5...

Page 69: ...20 Top Mounted Installation 08 167 7 21 520 29 35 55 08 5 5 7 02817 1 5 7 5 66 6 5 6 2 6 7 5 66 6 5 6 7 287 5 1 2 6 211 725 7 0 16 216 5 120 1 1 72 5 1 6 5 02817 1 5 7 02817 1 2 6 7 5 5 7 02817 1 685...

Page 70: ...Bottom Mounted Installation 08 7 5 66 6 5 6 2 6 7 5 66 6 5 6 7 287 5 1 2 6 211 725 7 5 5 7 02817 1 5 0 16 216 5 120 1 1 72 5 1 6 5 02817 1 5 7 02817 1 2 6 7 5 5 7 02817 1 685 08 167 7 21 520 2 127 35...

Page 71: ...Revision 6 Page A 9 APPENDIX A ASSEMBLY AND INSTALLATION DRAWINGS Figure A 9 GMU 44 Connector Assembly 08 08 211 725 7 340095 The document reference is online please check the correspondence between t...

Page 72: ...mum Recommended Installation Clearance 0 1 080 5 200 1 5 1 25 0 1 080 1 5 86 2 7 08 1 7 7 5 7 21 6 520 7 08 17 5 0 1 080 5 200 1 5 1 0 1 080 5 200 1 5 1 25 0 1 080 1 5 86 2 7 08 1 685 08 81 76 21 08 8...

Page 73: ...429 OUT ADAHRS 3A 28 S S SYS ID 2 57 SYS ID 1 75 S S NC NC ARINC 429 OUT ADAHRS 3B ARINC 429 OUT ADC 2B 14 28 VDC AIRCRAFT POWER ARINC 429 OUT ADAHRS 1B RS 232 IN AHRS 1 RS 232 IN ADC 1 ARINC 429 OUT...

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