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190-01639-00

GSU 75 ADAHRS Installation Manual

Revision 6

Page A-8

APPENDIX A ASSEMBLY AND INSTALLATION DRAWINGS

Figure A-8 GMU 44 (-20) Bottom Mounted Installation

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

Содержание GSU 75 Series

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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...

Страница 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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