Garmin 010-00296-00 Page 48 Installation Manual Download

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190-01639-00

GSU 75 ADAHRS Installation Manual

Rev. 6

Page 5-1

5 POST INSTALLATION, CONFIGURATION, AND CHECKOUT

PROCEDURE

CAUTION

Be sure to check all aircraft control movements before flight is attempted to insure
that the wiring harness does not touch any moving part.

NOTE

The following procedures reflect a Garmin Integrated Flight Deck installation.

5.1 Function Selector Switches and Display

There are no operating controls or displays on the GSU 75.

5.2 Post-Installation Calibration Procedures

After mechanical and electrical installation of the GSU 75 AHRS and GMU 44 magnetometer have been
completed, prior to operation, a set of post-installation calibration procedures must be carried out.

Table 5-1 describes the necessary calibration procedures:

Table 5-1 Post-Installation Calibration Procedure Summary

Calibration

Procedure

Procedure Name

Procedure

Description

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

Offsets by Manual

Entry

Manually enter

zeros for pitch/roll

offsets (pass-code

required)

This procedure should be used only if
leveling the aircraft is not feasible and
the AHRS is mounted to within 0.25° of
aircraft level reference

Magnetometer

Calibration

Compass Rose

Taxi Maneuver

All installations

This procedure should be repeated
following a removal or replacement of
the GMU 44 unit, or degaussing of the
area near the GMU 44 location.

Heading Offset

Compensation

Compass Rose

Alignment with

Magnetic North

Strongly recommended in installations
in which GMU 44 alignment is not
within 0.5° of aircraft forward
longitudinal direction

Engine Run-Up

Vibration Test

Validate vibration

characteristics of

installation

All installations

340095

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

Summary of Contents for 010-00296-00

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: ...l 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 5482 www garmin com Garmin Europe Ltd Liberty House Hounsdown Business Park Southampton SO40 9LR U K 44 0 370 850 1243 Garmin AT Inc 2345 Turner Rd SE Salem OR 97302 USA Telephone 503 581 8101 RECORD ...

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 the GSU 75 and GMU 44 Mod Levels are listed with the associated service bulletin number service bulletin date and the purpose of the modification The tables are current at the time of publication of...

Page 4: ...TION 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 OF MODIFICATION 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 MOD LEVEL SERVICE BULLETIN...

Page 5: ...i 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 correspondence between the online documentation and the printed version ...

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 Interconnect Harness Fabrication Instructions 3 3 3 5 GSU 75 GTP 59 Interconnect Harness Fabrication Instructions 3 4 3 6 Pneumatic Connections 3 8 3 7 Mounting Instructions 3 9 3 8 Post Installation Config...

Page 7: ...Zero 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 Up Vibration Test 5 8 5 8 Calibration Procedure E Magnetometer Interference Test 5 10 5 9 Site Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure 5 14 Appendix A ASSEMBLY AND I...

Page 8: ...ector 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 1 GSU 75 Outline Drawing A 1 Figure A 2 GSU 75 Installation Drawing A 2 Figure A 3 GMU 44 00 Mounting Rack A 3 Figure A 4 GMU 44 10 and 20 Mounting Rack A 4 Figure A 5 GMU 44 00 and 10 Top Mounted In...

Page 9: ...able 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 INSTALLATION PROCEDURE 3 1 Table 3 1 GSU 75 Pin Contact Part Numbers 3 1 Table 3 2 GMU 44 Pin Contact Part Number 3 1 Table 3 4 GMU 44 Recommended Crimp Tools 3 2 Table 3 3 GSU 75 Recommended Crimp Tools 3 2 T...

Page 10: ...stem 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 2 Fixed wing Aircraft Magnetometer Interference Test Sequence Example 5 11 Table 5 3 Helicopter Magnetometer Interference Test Sequence Example 5 12 340095 The document reference is online please che...

Page 11: ...mes 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 instal...

Page 12: ...lity 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 Heading accuracy is within 2 0 in static conditions and 6 0 in dynamic and flight conditions Operation in the following regions is not authorized due to unsuitability of the magnetic fields near the Ear...

Page 13: ...in 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 Specifications 1 4 1 Environmental Qualification Form The Environmental Qualification Forms are available directly from Garmin under the following part numbers GSU 75 Environmental Qualification Form Gar...

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 24 kg installed with rack and connectors Physical Dimensions GMU 44 Height 2 10 inches 53 3 mm excluding pigtail 3 35 inches 85 1 mm diameter including flange excluding pigtail 340095 The document re...

Page 15: ...s 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 Range 1 00 Mach Aircraft Total Air Temperature 85 C to 85 C Unit Operating Temperature 55 C to 70 C Maximum Days of Continuous Operation 49 If the ambient temperature is 45 or less a warm up period of...

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 Instrument Magnetic Gyroscopically Stabilized TSO C6d ETSO C6d AS8013A All 006 B0224 __ except 006 B0224 Z _ All 006 C0048 0 _ Table 1 7 TSO Authorizations for GSU 75 011 03094 X0 Function TSO ETSO SAE...

Page 17: ...rd 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 unit to be legibly and permanently marked with a serial number and not the date of manufacture 6 Garmin has been granted a deviation from TSO C106 to modify the requirement in SAE AS 8002A section 9 2 t...

Page 18: ...t 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 deviation from TSO C6d to use SAE AS 8013A instead of SAE AS 8013 as the Minimum Performance Standard 4 Garmin was granted a deviation from TSO C6d to list this secondary TSO in the Installation Man...

Page 19: ...00 010 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 Unit 011 00870 10 010 00296 10 GMU 44 Unit 011 00870 20 010 00296 20 Garmin recommends the GMU 44 011 00870 10 011 00870 20 with Installation Rack 115 00481 10 for new TC STC approvals Garmin does no...

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 01855 04 1 Heat Shrink Tubing FEP 093 ID 312 00005 05 6 78 pin High Density D Sub Connector Male Str Military Crimp Sealed w Ground Indents 330 00776 78 1 22D Military Crimp Contact Pins 336 00021 00 77...

Page 21: ...of 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 Electrical equipment supporting brackets and racks should be electrically bonded to the aircraft s main structure Refer to SAE ARP 1870 Section 5 when surface preparation is required to achieve electrical b...

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 Appendix E for approved practices while installing hoses and connections Figure 2 1 GSU 75 Air Hose Fitting Locations 2 8 Cooling Air No cooling air is needed for the GSU 75 or GMU 44 2 9 GTP 59 Icing The ...

Page 23: ...roved 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 Certification Office in the appropriate Region and request identification of FAA Designated Engineering Representatives DERs who are authorized to prepare and approve the required installation engine...

Page 24: ...f 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 leveled to within 8 in aircraft longitudinal direction pitch and 4 in aircraft lateral direction roll with the unit oriented such that the rack is on the bottom and an aircraft leveling and offset setting...

Page 25: ...GSU 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 printed version ...

Page 26: ...ble 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 mounted with its mounting rack s forward direction aligned in heading to within 2 5 with the forward longitudinal direction of the aircraft Furthermore alignment to within 0 5 with the forward longitudi...

Page 27: ...om 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 for adequate protection against direct attachment of lightning 2 11 2 2 GMU 44 Location Survey Tool Refer to AHRS Magnetometer Installation Considerations 190 01051 00 for details regarding the deter...

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 characteristics of all input and output signals Required connectors and associated hardware are supplied with the applicable connector kit Refer to Section 2 3 See Appendix B for examples of intercon...

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 Extracting the 18 and 20 contact requires that the expanded wire barrel be cut off from the contact It may also be necessary to push the pin out from the face of the connector when using an extractor due to t...

Page 30: ...hields 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 into a Jackscrew Backshell 190 00313 10 document 3 4 GSU 75 GMU 44 Interconnect Harness Fabrication Instructions Refer to the GMU 44 Interconnect Harness Fabrication Instructions 190 00313 04 document 3...

Page 31: ...h 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 sensor If possible mount the sensor through a grounded metal strap or band Otherwise mount the sensor in an area of the airframe that has a significant amount of underlying metal foil or mesh To ensur...

Page 32: ...rip 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 the proper length of insulation to be removed Wire must be visible in the inspection hole after crimping and the insulation must be 1 64 1 32 inches from the end of the contact as shown in Figure 3 1 ...

Page 33: ...cation 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 GSU 75 Connector Kit GPN 011 03109 00 Tighten the screws item 10 10 Secure cables Refer to Figure B 1 to verify that all required pins sockets have been attached to the cables and fully inserted into t...

Page 34: ...ADAHRS 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 the printed version ...

Page 35: ...atic 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 pneumatic fittings at the connector ports Use caution to ensure there are no pneumatic leaks 3 Use care to avoid getting fluids or particles anywhere within the pitot and static lines connected to the GSU ...

Page 36: ...ining 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 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 eq...

Page 37: ...unit 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 15 20 in lbs To disengage the GSU 75 refer to Figure 3 5 1 Turn each retention screw counterclockwise until they disconnect from the remote rack 2 Slide the GSU 75 unit forward to remove from the remo...

Page 38: ...ppendix 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 not applicable because the digital outputs of the GSU 75 X are not susceptible to these types of errors Other than periodic testing as required by 14CFR91 411 and in accordance with Section 3 8 herein ...

Page 39: ...232 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 ADC 3A Out 22 ARINC 429 OUT ADC 3B Out 23 ARINC 429 OUT ADC 2B Out 24 SIGNAL GROUND 25 PPS SELECT In 26 SIGNAL GROUND Indicates active low 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24...

Page 40: ...HRS 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 MODULE POWER OUT Out 54 CONFIG MODULE DATA I O 55 CONFIG MODULE CLOCK Out 56 DISCRETE IN 1 In 57 SYS ID 2 In 58 RESERVED 59 RESERVED 60 PPS IN 1 A In 61 PPS IN 2 B In 62 ARINC 429 IN ADC 3A In 63 ARI...

Page 41: ...73 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 Out 3 SIGNAL GROUND 4 RS 485 OUT A Out 5 SPARE 6 POWER GROUND 7 SPARE 8 RS 232 IN In 9 12 VDC POWER In Table 4 1 J751 Connector Pin Pin Name I O Indicates active low 340095 The document reference is...

Page 42: ...r 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 AIRCRAFT PWR1 and AIRCRAFT PWR2 are diode ORed to provide power redundancy Table 4 4 GMU 44 Input Power Pin Name Pin I O 12 VDC POWER 9 In POWER GROUND 6 Table 4 5 GSU 75 Magnetometer Power Pin Name Pin I...

Page 43: ...INC 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 ARINC 429 IN ADC 1A 42 In ARINC 429 OUT ADC 1A 1 Out ARINC 429 IN ADC 1B 43 In ARINC 429 OUT ADC 1B 2 Out ARINC 429 IN ADC 2A 44 In ARINC 429 OUT ADC 2A 3 Out ARINC 429 IN ADC 2B 64 In ARINC 429 OUT ...

Page 44: ...NFIG 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 ADC 2 18 In RS 232 OUT ADC 2 17 Out RS 232 ADC 2 GROUND 37 RS 232 IN AHRS 1 52 In RS 232 OUT AHRS 1 51 Out RS 232 AHRS 1 GROUND 32 RS 232 IN AHRS 2 72 In RS 232 OUT AHRS 2 71 Out RS 232 AHRS 2 GROUND 7...

Page 45: ...CTIVE Vin 3 5 VDC ACTIVE 10 Vin 33 VDC with 75 µA 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 In Table 4 11 GMU 44 RS 485 I O Pin Name Pin I O RS 485 OUT A 4 Out RS 485 OUT B 2 Out Table 4 12 GSU 75 Discrete Inputs Pin Name Pin I O DISCRETE IN 1 56 In DISCRETE IN 2 78 In DISCRETE IN 3 76 I...

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 EIA standard RS 422 receiver PPS SELECT pin 25 determines which PPS mode is used PPS SELECT connected to GPS PPS IN 1B or 2B input selects single ended mode PPS SELECT pin 25 floating unconnected selec...

Page 47: ...NC 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 system then the pins are left open All Call 4 8 GSU 75 System ID Inputs The system ID is determined by configuring the Sys ID pins per Table 4 16 Table 4 15 GSU 75 ARINC 429 System ID Connections Pin ...

Page 48: ...on 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 Offsets by Manual Entry Manually enter zeros for pitch roll offsets pass code required This procedure should be used only if leveling the aircraft is not feasible and the AHRS is mounted to within 0 25 ...

Page 49: ...e 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 Calibration Procedure Procedure Name Procedure Description Installations Requiring Procedure E Magnetome...

Page 50: ...ibration 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 either GSU 75 1 or GSU 75 2 for calibration Press the ENTER key after selecting which GSU 75 unit to calibrate The Select Procedure field is now blinking 7 The FMS small knob can now be used to select...

Page 51: ...on 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 PASSCODE field is blinking enter the appropriate pass code by using the FMS small knob to change the value of the first digit and the FMS large knob to move to the next digit of the pass code Press th...

Page 52: ...hicles 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 offset the aircraft position to the left west of the North South axis For helicopters it is best to posit...

Page 53: ...ficulties 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 for the operator to ignore the HOLD POSITION command and instead use outside references to complete the approximate 30 of turn Instead of using the PFD instruction to turn as a real time indication of...

Page 54: ...quired 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 performing the following steps a If the PFD is not displaying the GSU GMU CALIBRATION configuration page follow steps from calibration procedure A 1 listed previously b The FMS small knob can now be used to s...

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 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...

Page 56: ...upports 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 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 con...

Page 57: ...e 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 magnetometer interference test procedure by performing the following steps a If the PFD is not displaying the GSU GMU CALIBRATION configuration page follow steps from calibration procedure A 1 b The FMS s...

Page 58: ...on 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 lights recognition lights and strobe 4 10 Turn off all wing tip lights ...

Page 59: ...0 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 lights off 2 10 Landing lights on FWD Only 2 20 Landing lights off FWD Only 2 30 Landing lights on REAR Only 2 40 Landing lights off REAR Only 2 50 Landing lights on FWD REAR 3 00 Landing lights off F...

Page 60: ...ence 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 magnetic interference limits are defined as follows according to the system software part number 006 B1068 00 Square root of Mx 12 0 2 My 12 0 2 Mz 16 0 2 0 6 for fixed wing configuration Square root of M...

Page 61: ...ne 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 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 B...

Page 62: ...SFUL 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 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 constructi...

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 DIMENSIONS INCHES mm METRIC VALUES ARE FOR REFERENCE ONLY 1 DIMENSIONS ARE NOMINAL AND TOLERANCES ARE NOT IMPLIED UNLESS 2 SPECIFICALLY STATED MOUNTING HOLES FOR 10 PAN HEAD OR HEX HEAD FASTENERS 3 340095 Th...

Page 64: ...U 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 03109 00 CONFIGURATION MODULE NOT SHOWN 011 00979 20 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

Page 65: ...MBLY 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 check the correspondence between the online documentation and the printed version ...

Page 66: ...817 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 7 5 5 7 02817 1 2 6 2 6 7 25 9 5 7 21 167 7 216 86 1 72 5 1 6 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

Page 67: ...GMU 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 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

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 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

Page 69: ...4 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 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

Page 70: ...0 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 55 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

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 the online documentation and the printed version ...

Page 72: ...imum 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 81 76 21 340095 The document reference is online please check the correspondence between the online documentation and the printed version ...

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 ADAHRS 2B RS 232 IN AHRS 2 RS 422 IN B ARINC 429 IN 1B ARINC 429 IN 2A ARINC 429 IN 2B ARINC 429 IN 1A ARINC 429 IN 1B ARINC 429 IN 2A ARINC 429 IN 2B MAIN ARINC 429 IN 6 B RS 485 OUT B J751 P751 NOT...

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