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Garmin C510 GPS Receiver User Manual

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1. b TEM 5 47 E 33 72 139 1 T 93 E 98 7 6 32 CAPTIVE 3 41 E gt 7 3 SC REW aa 8 86 7 237 Y ea ess o i ur L 2X 2 34 l mel T E 1 7 83 M FR L XM E 1 198 8 CONN I i 7 25 E 1 i iy 184 2 GPs H I CONN 113 109 298 _ 27 7 192 a 58 Coy x 59 148 7 1534 E 150 _ 34 108 _ 86 7 27 5 NOTES 1 DIMENSIONS INCHESIMM 2 DIMENSIONS ARE SHOWN FOR REFERENCE ONLY Figure C 1 1 GDU 37X Outline Drawing G3X Installation Manual Outline amp Installation Drawings Page C 1 Page C 2 blank 190 01115 01 Revision A APPENDIX C OUTLINE amp INSTALLATION DRAWINGS Drawing is not to scale Use for dimensions only 19 PANEL CUTOUT R 39 4X 160 149 10 0 4 1 TYP _ _ _ _ 011 01
2. 4X 00 203 3X 00 625 4X R0 25 3 50 88 9 F 6X 3 20 81 3 d x A 2 2 55 64 8 Om 2X 2 24 56 9 F 2X 1 75 44 5 G 2X 1 27 32 3 O 2 0 95 24 1 b 6X 0 30 7 6 O a 9 A 0 063 1 60 dw K AN i 3 85 9 oo o 5 at M oco cg x N 0 i i D E d XX X xx x 0 688 17 48 1 2 3 4 0 344 8 74 2X 0 098 THRU CS K 0 172 X 100 120 203 DETAIL A 4 PLCS MS21047L3 NUTPLATE 4X FARSIDE 8 MS20426AD3 4 RIVET 8X ES DIMENSIONS INCHES mm MATERIAL 0 063 THICKNESS 2024 13 ALUMINUM AMS QQ A 250 5 TOLERANCE 0 030 0 010 REMOVE BURRS AND BREAK SHARP EDGES OPTIONAL GA55A ANTENNA INSTALLATION 16 MS21059L3 MAY BE USED IN PLACE OF MS21047L3 Figure 6 15 Doubler Design ARINC 743 Footprint Antenna Skin Thickness 0 049 to 0 051 G3X Installation Manual Antennas Page 6 17 190 0 1115 01 Revision A FORWARD 16X 20 128 23 26 4X 20 203 3X 0 625 4X R0 25 3 50 88 9 6X 3 20 81 3 O A O d I 2X 2 55 64 8 fo O 2X 2 24 56 9 0 2X 1 75 44 5 T 2X 1 27 32 3 O 2X 0
3. G3X Installation Manual 190 01115 01 Page v Revision A FIGURE PAGE 6 26 Example Bracket Antenna Mounting Under 1 1 6 24 6 27 Example Non structural Antenna Mounting Under Glareshield 6 25 6 28 Example Teardrop Antenna Installation in Airframe Under Fabric Skin 6 26 6 29 Example ARINC 743 Footprint in Airframe Under Fabric 6 26 6 30 Example Non structural Antenna Mounting on Airframe sese 6 27 6 31 Example Teardrop Footprint Antenna Mounting Under Fabric Skin 6 28 8 l Softkey Positions ute Hh ee ede He EU EA ed Be Eee edie 8 1 6 2 Aircraft Alignment 5 ener deemed heat ancien e te ee e e bete tia 8 10 9 1 Heading Failure Indication Full Screen PFD nana 9 2 9 2 Attitude Air Data and Engine Airframe Failure Indication essere 9 5 9 3 Attitude Failure Indication PED L L un sunan waya Dau enne 9 5 9 4 AHRS Align Message PED uu u a iere etre ii AA pa da ete ias 9 6 9 5 No Into tor TAS Ee u uq 9 7 9 6 Airspeed and Altitude Failure Indications n anasu 9 7 9 7 Attitude Heading Air Data and Engine Airframe 9 9 9 8 CONFIG GSU Pages sa aan t PURI a ainsi
4. ees 6 14 6 7 Minimum Distance Required Between Tube Structure and Antenna esee 6 28 8 1 Post Installation Calibration Procedure Summary eese rene 8 4 8 2 Data Validity Requirements for AHRS Calibration Procedures eee 8 5 8 3 Configuration Mode GSU Page Status Boxes enne enne enne en 8 5 8 4 Magnetometer Interference Test Sequence Example eee 8 23 9 1 GSU 73 AHRS Operating Mode 9 3 9 2 GSU 73 AHRS Pitch Bank Limitations for Cold Start While Airborne 9 3 B 1 Thermocouple 011 00981 00 neret enne B 1 2 GPN 011 00979 20 Kit W EEPROM and pins enne enne B 3 B 3 GPN 011 00979 22 Kit W EEPROM and B 3 B 4 Parts supplied for a Shield Block Installation Figure B 6 B 5 Parts NOT supplied for a Shield Block Installation B 6 B 6 Shielded Cable Preparations for Garmin Connectors esee nene B 8 B 7 Shielded Cable Preparations Quick Term enne B 14 B 8 Shielded Cable Preparations for Garmin Connectors eese ene B 16 B 9 Parts supplied for a Circular Connector Installation Figure 15 B 19 B
5. enne enne nennen enne B 16 B 13 Method C 2 Double Shield Termination eere nnne B 17 B 14 D Sub Spliced Signal Wire B 18 B 15 Circular Connector Install 19 contact example enne B 20 B 16 Standard Shield Termination u l l a uu G SS a B 20 Page vi G3X Installation Manual Revision A 190 01115 01 FIGURE PAGE B 17 Insulation Contact Clearance 23 18 Daisy Chain Shield Termination ttai etre eee He ete Ee B 24 B 19 Quick Term Shield e e e nennen nennen nennen nnns B 25 B 20 Daisy Chain Quick Term Shield Termination B 27 B 21 Daisy Chain Shield Termination between Methods A and B 28 C l l GDU 37X Outline Dr wing eee eere en dno pe ete eec eoe Ree ie aee Eee ger erede C 1 C 1 2 GDU 37X Panel Cutout Drawing e o tt e e s tee esed C 3 C21 GMU 44 Mounting Rack una p n m Qu n iere edente ce tied C 5 C 2 2 GMU 44 Top Mounted C 7 2 3 GMU 44 Bottom Mounted C 9 C24 GMU 44 Wiring Detail ierit ere eric e EH DRE RE ush heared C 11 31
6. 1 00 25 4 bd 1 12X 90 129 THRU SKIN TO MATCH DOUBLER 1 EE ra lh x 4 aN 011 01032 00 2X 3 30 83 8 O E ANTENNA OUTLINE i uu 1 o NOTES UN te DOUBLER OUTLINE 1 DIMENSIONS INCHES mm 2 DIMPLE SKIN FOR INSTALLATION OF FLUSH HEAD RIVETS Figure 6 18 Skin Cutout Detail ARINC 743 Footprint Antenna Skin Thickness 0 032 to 0 049 G3X Installation Manual Antennas Page 6 19 190 01115 01 Revision A va og BR 8 Blue oc qd 0 70 17 7 2 0 0 0 2 HOLES 09 O 1 00 25 4 A x i ny gt 2X 3 30 83 8 O O Site occ n NOTES 1 DIMENSIONS INCHES mm 4X 90 220 THRU SKIN TO MATCH DOUBLER 00 625 THRU SKIN 16X 20 129 THRU SKIN TO MATCH DOUBLER 011 01032 00 j ANTENNA OUTLINE DOUBLER OUTLINE 2 DIMPLE SKIN FOR INSTALLATION OF FLUSH HEAD RIVETS Figure 6 19 Skin Cutout Detail ARINC 743 Footprint Antenna Skin Thickness 0 049 to 0 051 0 65 16 5 0 70 17 7 0 80 20 3 0 0 0 2 HOLES 4X 0 220 THRU SKIN TO MATCH DOUBLER 0 625 THRU SKIN 46X 0 129 THRU SKIN TO MATCH DOUBLER C SK 0 225 X 100 011 01032 00 ANTENNA OUTLINE
7. 2 Atone end of a shielded cable item 2 measure a distance between Window Min to Window Max Table B 6 and cut a window max size 0 35 in the jacket to expose the shield Figure B 6 Use caution when cutting the jacket to avoid damaging the individual braids of the shield When dealing with a densely populated connector with many cables it may prove beneficial to stagger the windows throughout the Window Min to Window Max range If staggering is not needed the Ideal Window length is recommended Suggested tools to accomplish the window cut Coaxial Cable Stripper e Thermal Stripper e Sharp Razor Blade Page B 8 G3X Installation Manual Appendix B Revision A 190 01115 01 3 Connect a Flat Braid item 4 to the shield exposed through the window of the prepared cable assembly item 2 from step 2 The Flat Braid should go out the front of the termination towards the connector It is not permitted to exit the rear of the termination and loop back towards the connector Figure B 6 Make this connection using an approved shield termination technique NOTE FAA AC 43 13 1B Chapter 11 Section 8 Wiring Installation Inspection Requirements may be a helpful reference for termination techniques Preferred Method Slide a solder sleeve item 3 onto the prepared cable assembly item 2 and connect the Flat Braid item 4 to the shield using a heat gun approved for use with solder sleeves It
8. 800 20 3 l 2X 1 600 40 64 011 01032 10 GA 57X GPS XM ANTENNA 65 16 5 2X 2X 70 17 8 253 00138 00 MOLDED GASKET 2X 0 011 01032 00 ANTENNA TLINE 1 000 25 40 99 Q m Lg TOf 19 05 e AIRCRAFT SKIN 2 350 59 69 2 2 3 300 83 82 9 k sj N mme 4x 220 5 59 FABRICATE AND INSTALL DOUBLER PLATE AS REQUIRED TO COMPLY WITH APPLICABLE AIRWORTHINESS REGULATIONS MOUNTING CUTOUT NOTES 1 DIMENSIONS INCHES mm Figure C 5 3 GA 57X Installation Drawing G3X Installation Manual Outline amp Installation Drawings Page C 21 Page C 22 blank 190 01115 01 Revision A APPENDIX D INTERCONNECT DRAWING NOTES 1 Bow 10 11 UNLESS OTHERWISE NOTED ALL STRANDED WIRE MUST CONFORM TO MIL W 22759 16 OR EQUIVALENT UNLESS OTHERWISE NOTED ALL SHIELDED WIRE MUST CONFORM TO MIL C 27500 OR EQUIVALENT UNLESS OTHERWISE NOTED ALL WIRES ARE 24 GAUGE MINIMUM SYMBOL DESIGNATIONS E M _ TWISTED SHIELDED SINGLE CONDUCTOR TWISTED SHIELDED 4 CONDUCTOR Ae SHIELD TERMINATED TO GROUND SHIELD TERMINATED TO GROUND C TWISTED SHIELDED SINGLE CONDUCTOR SHIELD FLOATS A TWISTED SHIELDED PAIR T IWST
9. G3X Installation Manual Installation Overview 190 01115 01 Page 1 3 Revision A 1 4 3 Physical Specifications All width height and depth measurements are taken with unit rack if applicable and connectors Table 1 4 G3X LRU Physical Specifications Depth GMU 44 Height Diameter Unit Weight including flange GDU 370 6 04 inches 7 83 inches 3 41 inches Unit Weight w Nutplate amp Connector Weight 153 4 mm 198 8 mm 86 7 mm SSECHE lees Do SES amuse wa iss errem mi 1 4 4 Cooling Requirements While no forced cooling air is required for the G3X system it is highly recommended that the air behind the panel be kept moving by ventilation or a fan No cooling air is required for GDU 37X Nocooling air is required for GMU 44 No cooling air is required for the GSU 73 however the GSU 73 should be mounted in a location that provides adequate airflow to comply with the maximum outer case temperature listed in Section 4 Avoid installing LRUs near heat sources If this is not possible ensure that additional cooling is provided Allow adequate space for installation of cables and connectors The installer will supply and fabricate all of the cables All wiring should be in accordance with FAA AC 43 13 1B and AC 43 13 2A Page 1 4 G3X Installation Manual Installation Overview Revision A 190 01115 01 1 5 Installat
10. In Figure B 15 AR denotes quantity As Required for the particular installation Figure B 15 Circular Connector Install 19 contact example B 4 2 Standard Shield Termination Technique Method A WINDOW MIN TO WINDOW MAX eres Sener MAS gt 5 FLOAT MIN TO FLOAT MAX 7 NU J J i 2 c Cpu 2 12 I a qd j J 0 75 INCHES MIN K F lt 0 35 INCHES MAX 0 17 INCHES em N FOR REF ONLY N n VNLT fr SEE FIGURE 2 2 um e d Figure B 16 Standard Shield Termination Page B 20 G3X Installation Manual Appendix B Revision A 190 01115 01 Table B 11 Shielded Cable Preparations for Garmin Connectors Backshell Size Insert Arrangement Float in Window Min Max Ideal Min Max Ideal 14 19 1 35 1 60 1 50 2 10 4 60 3 60 1 Atone end of a shielded cable item 4 measure a distance between Window Min to Window Max Table B 11 and cut a window max size 0 35 in the jacket to expose the shield Figure B 16 Use caution when cutting the jacket to avoid damaging the individual braids of the shield When dealing with a densely populated connector with many cables it may prove beneficial to stagger the windows throughout the Window Min to Window Max range If staggering is not needed the Ideal Window length is
11. 1 00 25 4 x V J d LL r 2X 3 30 83 8 41 RR NOTES 1 DIMENSIONS INCHES mm DOUBLER OUTLINE 2 COUNTERSINK EXTERNAL AIRCRAFT SKIN FOR INSTALLATION OF FLUSH RIVETS Figure 6 20 Skin Cutout Detail ARINC 743 Footprint Antenna Skin Thickness 0 051 to 0 063 Page 6 20 Revision A G3X Installation Manual Antennas 190 01115 01 12X MS20426AD4 x RIVETS AIRCRAFT SKIN NOTES 1 MS20426AD4 X RIVET SELECTION LENGTH AND INSTALLATION DETERMINED USING THE GUIDANCE FOUND IN AC43 13 1B Figure 6 21 Doubler Installation ARINC 743 Footprint Antenna Skin Thickness 0 032 to 0 049 16X MS20426AD4 x RIVETS TIT Qu CR le AIRCRAFT SKIN NOTES 1 MS20426AD4 X RIVET SELECTION LENGTH AND INSTALLATION DETERMINED USING THE GUIDANCE FOUND IN AC43 13 1B Figure 6 22 Doubler Installation ARINC 743 Footprint Antenna Skin Thickness 0 049 to 0 051 G3X Installation Manual Antennas Page 6 21 190 01115 01 Revision A 16X MS20426AD4 x RIVETS AIRCRAFT SKIN NOTES 1 MS20426AD4 X RIVET SELECTION LENGTH AND INSTALLATION DETERMINED USING THE GUIDANCE FOUND IN AC43 13 1B Figure 6 23 Doubler Installation ARINC 743 Footprint Skin Thickness 0 051 to 0 063
12. Indicates Active Low A 1 2 Aircraft Power AIRCRAFT POWER 1 and AIRCRAFT POWER 2 are diode ORed to provide aircraft power redundancy PinNam Connector Pin 1O PONERGROUND P3700 15 POWER GROUND COA 16 A 1 3 Mode Selections Configure the GDU 37X units per the following tables A GDU 37X can be manually placed in reversionary mode by grounding Pin 25 Grounding pin 42 will place the GDU 37X in Demo mode which is for in store demonstration use only never ground pin 42 in an aircraft installation PFD MODE 1 P3701 Pin 10 Open PFD MODE 2 P3701 Pin 9 Open GDU Mode MFD Ground Open PFD1 Open Ground PFD2 Ground PFD MODE 3 P3701 Pin 25 GDU Mode Open Auto Reversionary Ground Do Not Use PFD MODE 4 P3701 Pin 42 GDU Mode Open Normal Operation Ground Forced Reversionary Ground Demo Mode Page A 2 Revision A Installation Manual Pinouts 190 01115 01 A 1 4 Serial Data A 1 4 1 RS 232 The RS 232 outputs conform to EJA Standard RS 232C with an output voltage swing of 0 5V when driving a standard RS 232 load Pin Name Connector RS 232 IN 1 P3701 RS 232 OUT 1 P3701 RS 232 IN 2 P3701 RS 232 OUT 2 P3701 RS 232 IN 3 P3701 RS 232 OUT 3 P3701 A 1 4 2 CAN Bus This data bus conforms to the BOSCH standard for Controller Area Network 2 0 B This bus complies with ISO 11898 CAN BUS TERMIN
13. 3 5 4 1 GSU 73 Supply Specifications e A EEE 4 2 4 2 GSU 73 Environmental 5 4 3 43 0905073 Available Equipment noe eta eee ete teet regere te qe ae eee dh dese ed u 4 3 4 4 Contents of P731 Connector Kit 011 01818 00 esses eee 4 3 4 5 Contents of P732 Connector Kit 011 01818 01 4 4 31 1501859 PartsNumber et eu Pe e en ie t e ecce a t pe Ho e Me e Eo eee 5 1 5 2 GTP 59 Outside Air Temperature Kit annassa un nennen nennen nennen enne 5 1 5 3 Applicable TSO ETSOs for the GTP 59 5 2 5 4 TSO ETSO Deviations for the GTP 59 5 2 5 5 Parts Needed for GTP 59 5 3 2 5 RE c 6 1 6 2 GPS Antenna Minimum 6 1 03 SIE ERE 6 1 Page viii G3X Installation Manual Revision A 190 01115 01 TABLE PAGE 6 4 XM Satellite Radio Antenna Minimum 6 2 6 5 Teardrop Footprint Antenna Doubler Design and Installation 6 7 6 6 ARINC 743 Footprint Antenna Doubler Design and Installation
14. 7 SPARE RS 232 IN 9 H2VDCPOWER in A 2 2 Power Function Power input pins accept 14 28 VDC AIRCRAFT POWER 2 is for connecting to an alternate power source such as on aircraft with two electrical buses PinName Connector Pin VO 12 VDC POWER GMU 44 p Pt 9 h POWER GROUND GMU 44 P441 6 A 2 3 Serial Data A 2 3 1 RS 232 PinName Connector Pin VO RS 232 IN 8 A 2 3 2 RS 485 Pin Name Connecter Pin VO RS 485 OUT A G3X Installation Manual Pinouts Page A 5 190 01115 01 Revision A A 3 GSU 73 A 3 1 Connector Description The GSU 73 has one 62 pin connector J731 and one 78 pin connector J732 located on the connector end of the unit as shown below J731 and J732 are clearly marked on the connector end plate LLLALLULLTLTJ J732 GSU 73 011 01817 00 MOD LEVEL123456789 Designed and Assembled in the USA Figure A 3 Rear View of Connector End Plate A 3 2 Pin List A 3 2 1 P731 Connector 430 O O O O 062 O O O O 042 ib C d MN a Figure A 4 Rear Connector J731 Viewed from Connector End of Unit J731 pins are configured as shown in preceding figure J731 pin assignments are given in the following
15. Co I aa 1 lt 0 75 INCHES n e 0 17 INCHES FOR REF ONLY SEE FIGURE 2 2 Figure B 8 Method A 2 Daisy Chain for Shield Termination B 3 4 Shield Termination Method B 1 Quick Term If desired the drain wire termination item 3 and the floating shield termination item 5 can be effectively combined into a Quick Term This method eliminates the float in the cable insulation and moves the placement of the window which was described by the dimensions Window Min and Window Max from Method A This technique is depicted in Figure B 9 NOTE The original purpose for separating the shield drain termination item 3 from the float termination item 5 in Method A was to allow for a variety of lengths for the drain wires so that the shield drain terminations item 3 would not all bunch up in the harness and to eliminate loops in the drain wires If Method B is chosen as described in this section care must be taken to insure that all drain shield terminations can still be inspected With connectors which require a large number of shield terminations it may be best to use Method A This will allow the drain shield terminations item 3 a larger area to be dispersed across Using this method the instructions from Section B 3 2 Method A are followed except that 1 Step 2 is eliminated 2 Steps 3 and 4 are replaced by the following At the end of the shielded cable item 2 s
16. Engine Run Up Vibration Test Validate vibration characteristics of installation Procedure E is required for all installations Magnetometer Interference Test Validate no magnetic interference with GMU 44 Procedure F is required for initial installation verification 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 electrical device located in the same wing as a GMU 44 unit Likewise this test should also be repeated to verify all subsequent changes to materials within 10 0 feet of the GMU 44 Such changes include but are not limited to addition removal or modification of ferrous or electrically conductive materials located in the same wing as a GMU 44 unit 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 G3X system Page 8 4 Revision A Installation Manual Post Installation Checkout and Calibration Procedures 190 01115 01 For each Calibration Procedure Table 8 2 lists the LRU s that require valid calibration data Table 8 2 Data Validity Requirements for AHRS Calibration Procedures Pitch Roll Offset GPS or
17. GTP 59 Revision A 190 01115 01 6 Garmin GPS XM Antennas For non Garmin antennas follow the manufacturer s installation instructions If using a Garmin GA 26C or GA 26XM refer to the accompanying installation instructions 190 00082 00 or 190 00522 03 For GA 55 55A 56 or GA 57X antennas refer to this section and the drawings in Appendix Garmin recommends the antennas shown in Tables 6 1 and 6 3 However any equivalent GPS or XM antenna that meets the specifications listed in Tables 6 2 and 6 4 should work with the G3X 6 1 GPS Antennas Table 6 1 GPS Antennas Part Flange Magnetic or Suction GA 26C 011 00149 04 GPS Antenna Cup Mount for in cabin mounting Stud mount Tear drop form factor Thru mount ARINC 743 style mount 011 00134 00 GPS Antenna 0 24 Ibs 0 11 kg GA 57X 011 01032 10 GPS XM Antenna 0 47 Ibs 0 21 kg Table 6 2 GPS Antenna Minimum Requirements Frequency Range 1565 to 1585 MHz Noise Figure Nominal Output Impedance Supply Voltage Supply Current up to 50 mA Output Connector y 6 2 XM Antennas Table 6 3 XM Antennas Part Flange Magnetic or Suction 013 00268 10 XM Antenna Cup Mount for in cabin mounting Stud mount Tear drop form factor Thru mount ARINC 743 style mount Thru mount ARINC 743 style mount 011 01033 00 XM Antenna 0 25 Ibs 0 11 kg 011 01153 00 XM Antenna 0 43 Ibs 0 20 kg 011 01032 10 GPS X
18. WINDOW oc m OAT MIN ET I J m 0 75 INCHES w I 0 35 INCHES MAX 0 17 INCHES an Figure B 18 Daisy Chain Shield Termination Page B 24 G3X Installation Manual Appendix B Revision A 190 01115 01 B 4 4 Quick Term Shield Termination Method B If desired the drain wire termination item 5 and the floating shield termination item 7 can be effectively combined into a Quick Term This method eliminates the float in the cable insulation and moves the placement of the window which was described by the dimensions Window Min and Window Max from Method A This technique is depicted in Figure B 19 NOTE The original purpose for separating the shield drain termination item 5 from the float termination item 7 in Method A was to allow for a variety of lengths for the drain wires so that the shield drain terminations item 5 would not all bunch up in the harness and to eliminate loops in the drain wires If Method B is chosen as described in this section care must be taken to insure that all drain shield terminations can still be inspected With connectors which require a large number of shield terminations it may be best to use Method A This will allow the drain shield terminations item 5 a larger area to be dispersed across QUICK TERM MIN TO QUICK TERM MAX 1
19. Connector X PinName VO 1 P731 MAGNETOMETER RS 485 IN B IN 2 P731 MAGNETOMETER RS 485 IN A IN A 3 5 4 CAN Bus 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 GSU is located at the end of the bus Pin Connector Pin Name 7 P731 CAN BUS HI 8 P731 CAN BUS LO 29 P731 CAN BUS TERMINATION A 3 5 5 Configuration Module Interface Pin Connector Pin Name 1 0 20 CONFIG MODULE CLOCK 39 CONFIG MODULE DATA 59 CONFIG MODULE POWER OUT 78 CONFIG MODULE GROUND A 3 6 Discrete I O A 3 6 1 Active Low Discrete Inputs The GSU 73 has 4 configurable discrete inputs conforming to a Low 0 VDC lt Vin lt 3 5 VDC OR Rin lt 375 ohms active b High 8 VDC lt Vin lt 36 VDC OR Rin gt 100k ohms inactive Connector Pin Name DISCRETE IN 1 DISCRETE IN 2 DISCRETE IN 3 DISCRETE IN 4 Indicates Active Low Page A 12 G3X Installation Manual Pinouts Revision A 190 01115 01 A 3 6 2 Discrete Outputs INACTIVE Floating can be pulled up to externally sourced Vout in the range 0 lt Vout lt 33VDC Leakage current in the INACTIVE state is typically lt 10 uA to ground ACTIVE Vout lt 0 5VDC with lt 20 mA sink current Sink current must be externally limited to 20 mA max Pin Connector X PinNam
20. G3X Installation Manual Installation Overview Page 1 7 190 01115 01 Revision A 1 7 4 Backshell Assemblies Connector kits include backshell assemblies The backshell assembly houses the configuration module and a thermocouple reference junction if applicable see Appendix D Garmin s backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing The instructions needed to install the Jackscrew Backshell Configuration Module and Thermocouple are located in Appendix B The GDU 37X rear connector J3701 is electrically isolated For installations using shielded cables a ground pin must be tied to the connector shell Page 1 8 G3X Installation Manual Installation Overview Revision A 190 01115 01 2 GDU 37X GARMIN WPT BRG DST ETE OIL PSI 76 CHT F 380 gt m AT RPM MAN IN OIL F 196 FUEL 1880 28 1 5 HX ie co 85 PFD TI WPT WX TER XM INFO ENG MAP TERRAIN Figure 2 1 GDU 37X Unit View 2 1 Equipment Description NOTE There is no TSO ETSO applicable to the GDU G37X The GDU 37X provides a central display and user interface for the G3X system The display is mounted flush to the aircraft instrument panel using four 6 screws The GDU 37X is available in two models GDU 370 and GDU 375 The GDU 370 is a Garmin Display Unit with a VFR WAAS GPS receiver The GDU 375 provides these same features plus
21. HOLIMS 133HM 1041400 WULINIG OL 0314100 JI AINO AYYY WL NYL HOLIMS 133HA 1O31NOO TJO81N09 300801 OA33S NOY HOLIMS 133HA 1041400 WINAS AYVWIdd gt LNO S3 10 WINOLOId nao NYL HOLIMS 133HM 1041 00 8 ONINV SL V vl 8 310N 33S WINSS Zt 5314345 1 LHONAISIC Wal LL 310N 33S SNOILOANNOO X04 GSLINSNOO 38 GINOHS NOILVINSWNOOd SOON3A LOWNdOLNVY AINO 3O9N383439 404 NMOHS SLOSNNOOUSLNI 10 14010 32 Figure E 1 3 Tru Trak and Trio Auto Pilot Examples Page E 5 Page E 6 blank G3X Installation Manual External Interface Drawings 190 01115 01 Revision A
22. which is included in the G3X Installation Kit K10 00017 00 Table B 1 Thermocouple Kit GPN 011 00981 00 Figure Ref Description Qty Needed PN or MIL spec 3 Thermocouple K type 925 L0000 00 Pins 22 AWG 336 00021 00 Screw 211 60234 08 For the following steps please refer to indicated item numbers in Figures B 1 and B 2 1 Strip back approximately 0 17 inches of insulation from both the positive and negative thermocouple leads item 1 and crimp a pin item 2 to each lead 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 B 1 A INSPECTION HOLE WIRE MUST BE VISIBLE AFTER CRIMPING c 7 V I 1 64 TO 1 32 JL P Figure B 1 Insulation Contact Clearance N 2 Insert newly crimped pins and wires items 1 amp 2 into the appropriate connector housing item 4 location as specified by the installation specific wiring diagram 3 Place thermocouple item 1 body onto backshell item 5 boss Upon placing the thermocouple item 1 body orient it such that the wires exit downward 4 Attach thermocouple item 1 tightly to backshell item 5 using screw item 3 5 Attach cover item 6 to backshell item 5 using screws item 7 G3X Installation Manual Appendix B Page B
23. 1 60 t ON e ON ow om ao nr 9 s is oN ay S No x NON No e c amp AA X XX x x CON NOTES 1 DIMENSIONS INCHES 2 MATERIAL 0 063 THICKNESS 2024 T3 ALUMINUM AMS QQ A 250 5 3 TOLERANCE XX 0 030 XXX 0 010 4 REMOVE BURRS AND BREAK SHARP EDGES Figure 6 5 Doubler Design Teardrop Footprint Antenna Skin Thickness 0 049 to 0 051 G3X Installation Manual Antennas Page 6 9 190 01115 01 Revision A FORWARD gt 16X 20 128 90 625 4X RO 25 3 00 76 2 6X 2 70 68 6 d 2X 2 31 58 7 2X 1 90 48 3 o 1 90 58 1 J 4X 0 188 2X 1 10 27 9 o 2X 0 69 17 5 6X 0 30 7 6 p 0 063 1 60 eo Y c lt 1 eo nr gt wo om N NE oo SQ eo x eo 5 a a AA XX x x NOTES 1 DIMENSIONS INCHES 2 MATERIAL 0 063 THICKNESS 2024 T3 ALUMINUM AMS QQ A 250 5 3 TOLERANCE 0 030 0 010 4 REMOVE BURRS AND BREAK SHARP EDGES Figure 6 6 Doubler Design Teardrop Footprint Antenna Skin Thickness 0 051 to 0 063 FORWARD gt STRINGER Aj DOUBLER o 94 o o o o o o o o o o S BULKHEAD
24. Ensure that the aircraft has been properly positioned per the on screen instructions GSU73 CALIBRATION 1 TAXI THE AIRCRAFT TO A COMPASS ROSE 2 ENSURE THAT THE GPS AND MAGNETOMETER COMMUNICATION STATUS LIGHTS ARE GREEN MUST HAVE CLEAR VIEW OF SKY 3 ENSURE THAT THE MAGNETOMETER WILL NOT PASS WITHIN 20 FEET OF ANY MAGNETIC MATERIALS SUCH AS STEEL GRATES OR PIPES 4 MANEUVER TOWARD THE LEFT HAND SIDE OF THE COMPASS ROSE AND TURN TO A HEADING OF ROUGHLY MAGNETIC NORTH 5 DEG 5 ENSURE THE AIRCRAFT IS STATIONARY READY TO ENTER THE 65073 AHRS GROUND AUTO CALIBRATION MODE 8 Use the FMS Joystick to highlight the Calibrate button at the bottom of the display press the ENT Key to begin the calibration SELECT CALIBRATE TO BEGIN CANCEL CALIBRATE 9 The PFD advises the operator when to turn the aircraft when to stop and when to turn again 10 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 Due to the difficulties 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 instructi
25. Example Bracket Antenna Mounting Under Glareshield Page 6 24 G3X Installation Manual Antennas Revision A 190 01115 01 GLARESHIELD ANTENNA BRACKET INSTRUMENT PANEL Figure 6 27 Example Non structural Antenna Mounting Under Glareshield G3X Installation Manual Antennas Page 6 25 190 01115 01 Revision A 6 6 4 Non structural Installation to Airframe Internal Non structural Installation Figure 6 28 and Figure 6 29 show examples of under the fabric skin non structural mounting of the antenna to the airframe of a tube and fabric aircraft In Figure 6 28 a bracket is made to attach to the airframe just under the fabric for a teardrop antenna installation The doubler plate and mounting hardware described in the generic installation Section 6 6 1 are used with the bracket as the antenna mounting surface In Figure 6 29 a similar case is shown using the generic installation of the ARINC 743 footprint antenna The doubler plate is optional for this type of installation with either the Teardrop or the ARINC 743 antenna ANTENNA BRACKET 4X NAS1149FN832P AN960 8 8 WASHER 4X 210 10004 09 38 32 SELF LOCKING NUT TORQUE 12 TO 15 in Ibs ARINC 743 FOOTPRINT ANTENNA 4X 211 60212 20 10 32 PHP x 1 00 25 4 TORQUE 20 TO 25 in Ibs Figure 6 29 Example ARINC 743 Footprint In Airframe Under Fabric Skin Page 6 26 G3X Installation Manual
26. 00 _ GASKET NEOPRENE AIRCRAFT SKIN ON TOP OF FUSELAGE 115 00031 00 BACKING PLATE e 4X 210 10004 09 18 32 SELF LOCKING NUT FORWARD gt la 4 23 107 4 83 121 11 2 59 65 8 L e Tel i 1 91 48 5 60 15 2 i 22 5 6 50 12 7 4X 8 32 STUD 3 BNC CONNECTOR SIDE VIEW FRONT VIEW Ft a m LI E od m E s Y 3 00 76 2 LI X Pg o N 2x 1 625 41 28 m S pe a oo 813 20 64 ER n rm E a b 9 a 1 78 lt L N I r I 5 x M x LI E 5 o S 7 lt 625 15 88 ae i 2 59 65 8 BACKING PLATE MOUNTING CUTOUT OUTLINE ANTENNA OUTLINE Figure C 5 2 GA 56 Installation Drawing G3X Installation Manual Outline amp Installation Drawings 190 01115 01 Page C 19 Page C 20 blank Revision A APPENDIX C OUTLINE amp INSTALLATION DRAWINGS FORWARD 4 70 119 4 Y gt ro 49 12 3 1 80 Mi FEE 211 60212 20 10 32 PHP x 1 00 25 4 ORQUE 20 TO 25 in lbs XM GPS BNC emi TNC CONNECTOR
27. 10 Parts NOT supplied for a Circular Connector Installation Figure B 15 B 19 B 11 Shielded Cable Preparations for Garmin Connectors sese B 21 B 12 Shielded Cable Preparations Quick Term a B 25 G3X Installation Manual Page ix 190 01115 01 Revision A Limited Warranty for Garmin GMU 44 and GTP 59 Products The Garmin products GMU 44 and GTP 59 are warranted to be free from defects in materials or workmanship for two years from the date of purchase Within this 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 cover failures due to abuse misuse accident or unauthorized alteration or repairs THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR 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 THIS PRODUCT OR FR
28. 25 P732 ANALOG IN 14 HI IN 5 P732 ANALOG IN 14 LO IN 64 P732 ANALOG IN 15 HI IN 44 P732 ANALOG IN 15 LO IN 26 P732 ANALOG IN 16 HI IN 45 P732 ANALOG IN 16 LO IN 65 P732 ANALOG IN 17 HI IN 6 P732 ANALOG IN 17 LO IN 71 P732 ANALOG IN 18 HI IN 51 P732 ANALOG IN 18 LO IN 32 P732 ANALOG IN 19 HI IN 12 P732 ANALOG IN 19 LO IN 31 P732 ANALOG IN 20 HI IN 11 P732 ANALOG IN 20 LO IN 69 P732 ANALOG IN 21 HI IN 49 P732 ANALOG IN 21 LO IN continued Page A 14 Installation Manual Pinouts Revision A 190 01115 01 Connector Pin Name ANALOG IN 22 HI ANALOG IN 22 LO ANALOG IN 23 HI ANALOG IN 23 LO ANALOG IN 24 HI ANALOG IN 24 LO ANALOG IN 25 HI ANALOG IN 25 LO ANALOG CURRENT MONITOR IN 1 HI ANALOG CURRENT MONITOR IN 1 LO ANALOG CURRENT MONITOR IN 2 HI ANALOG CURRENT MONITOR IN 2 LO THERMOCOUPLE REF IN HI THERMOCOUPLE REF IN LO A 3 8 Temperature Inputs Temperature input is used for Outside Air Temperature OAT computations The temperature input is a three wire temperature probe interface OAT Power Out and OAT High are connected internally at the OAT probe A GTP 59 or other supported temperature probe is required for the GSU 73 installation The Connector Pin Name P732 OAT PROBE IN HI P732 OAT PROBE POWER OUT P732 OAT PROBE IN LO A 3 9 Frequency Counter Inputs Digital signals are updated to the display at a rate of 10 times per second 10 Hz Digit
29. 4 G3X Installation Manual GMU 44 Revision A 190 01115 01 3 6 1 Consideration for Wing Grounded Lighting Fixtures The following installation practices are recommended if the required GMU 44 mounting bracket is located in the wing 1 The wing tip lights should not have a power ground referenced to the chassis of the light assembly that would then be referenced back to the airframe ground via the light assembly mounting 2 A dedicated power ground should be used and returned as a twisted pair with the power source back into the fuselage for a wing mounted GMU 44 These installation practices will prevent magnetically interfering currents from 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 Refer to Appendix C for outline and installation drawings 3 7 GSU 73 GMU 44 Interconnect Harness Fabrication Instructions Table 3 8 lists parts needed for the GMU 44 interconnect harness Some of the parts for installation are included in the GMU 44 Connector Installation Kit Other parts are provided by the installer Reference numbers refer to item bubble numbers shown in Figure C 2 4 Table 3 8 Parts Needed for GMU 44 Installation Qty Included Shield Termination Parts used depend on method method optional chosen Figure
30. AX 211 60212 20 10 32 PHP x 1 00 25 4 TORQUE 20 TO 25 in Ibs mn ud ARINC 743 FOOTPRINT ANTENNA W NC s 253 00138 00 25 MOLDED GASKET em 1 1 c c c m ex E a gt eum l c S ni lt AIRCRAFT SKIN WITH DOUBLER INSTALLED Figure 6 24 Installation of ARINC 743 Footprint Antenna Page 6 22 G3X Installation Manual Antennas Revision A 190 01115 01 6 6 Non Structural Mount Installation This section provides installation examples and considerations for non structural mounting of teardrop and ARINC 743 footprint antennas Typical installations may be below a non metallic glareshield under the composite or fabric skin or on an external non structural surface Other non structural installations may exist but are not presented in this manual 6 6 1 Generic Non structural Antenna Installation Figure 6 25 shows the generic non structural installation for the ARINC 743 footprint GA55A GA 57X antenna The teardrop footprint antennas GA55 GA56 stud mount can also be installed in this manner For mounting the teardrop style antenna GA 55 or GA56 a doubler plate similar to Figure 6 4 or P N 115 00846 10 can be used with the mounting surface to support the antenna Rivets used to secure the doubler plate to the mounting surface are optional in a non structural installation Screws washers and locking nuts as shown in Appendix C are required
31. G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 5 When the update process is complete the screen updates the database status UPDATE DATABASES 6 Once the database s have been updated the SD card can be removed from the unit PRESS THE RESTART SOFTKEY TO FINISH RESTART 7 The unit must be restarted by pressing the Restart softkey 8 Repeat steps 1 7 for each installed GDU 37X 7 5 2 Available Databases Jeppesen Aviation Data NavData The Jeppesen database contains the general aviation data NavData used by pilots Airports VORs NDBs SUAs etc and is updated on a 28 day cycle Terrain The terrain database contains the elevation data which represents the topography of the earth This database is updated on an irregular basis Basemap The basemap contains data for the topography and land features such as rivers lakes and towns It is updated only periodically with no set schedule There is no expiration date Obstacle The obstacle basemap contains data for obstacles such as towers that pose a potential hazard to aircraft Obstacles 200 feet and higher are included in the obstacle database It is very important to note that not G3X Installation Manual Software Configuration Databases and XM Activation Page 7 13 190 01115 01 Revision A all obstacles are necessarily charted and therefore may not be contained in the obstac
32. GSU 73 Outline Drawing irte cii o Rer o CIR eU e Re HERES LIOS C 13 4 1 GTP 59 O A T Probe Installation Drawing n enne nren rennen C 15 C 5 1 GA 55 55A Installation Drawing C 17 5 2 GA 56 Installation 19 5 3 GA 57X Installation Drawing 2 e e ero pedet ie aaa C 21 D 1 1 Notes 14V Power and Antenna D 1 1 2 GDU 37X and GSU 734 deiode ien pectet test te o na pe e bte ER EP Ug HOO e de D 3 E 1 1 Notes GDU 37X RS 232 and Audio E 1 E 1 2 GSU 73 RS 232 and ARINC 429 Examples esee eren E 3 E 1 3 TruTrak and Trio Auto Pilot Examples neret ener E 5 G3X Installation Manual Page vii 190 01115 01 Revision A LIST OF TABLES TABLE PAGE IL ERU PartNuribers 2 ne ae rettet ets eee p eo Pee Ee da dete eee eue oet Ce aaa deo 1 3 1 2 Contents of GDU 37X Assembly 010 00667 XX0 enne enne enne netten 1 3 1 3 G3X ERU Power Requirements 52 n eret ee Hte d HO as 1 3 1 4 G3X LRU Physical 1 4 1 5 Contents of Installation Kit K
33. MS35338 42 Flat Washer Stainless 8 032 thick 174 ID 375 OD NAS1149CN832R Flat washer Cad plated Steel 8 032 thick 174 ID 375 OD NAS1149FN832P Silicon Fusion Tape Drain Wire Shield Termination method optional Page B 6 G3X Installation Manual Appendix B Revision A 190 01115 01 In Figure B 5 AR denotes quantity As Required for the particular installation Figure B 5 Shield Install onto a Jackscrew Backshell 78 pin example NOTE G3X Installation Manual Appendix 190 01115 01 Page B 7 Revision A B 3 2 Shield Termination Technique Method A 1 Standard NOTE For the following steps please refer to the drawings showing the installation of a Jackscrew Backshell 1 The appropriate number of Jackscrew Backshells will be included in the particular LRU connector kit WINDOW MIN TO WINDOW MAX gt N DI AAT nr RN 2 LOAT MIN FLOAT M uH 2 N 4 J 0 75 INCHES MIN 0 17 INCHES FOR REF ONLY SEE FIGURE 2 2 gt a Figure B 6 Method A 1 for Shield Termination Table B 6 Shielded Cable Preparations for Garmin Connectors Backshell Number Float Float Ideal Float Window Window Ideal Size of Pins Min Max Min Max Window Std HD inches inches hohes inches inches inches
34. MUERE A 9 11 A 1 View of J3701 Connector from Back Of Unit A 1 A 2 View of J441 Connector Looking at Rear A 5 3 ReasrView ot Connector Plate eh eee idt hs eae bbs A 6 A 4 Rear Connector of J731 Viewed from Connector End of Unit A 6 5 Rear Connector of J732 Viewed from Connector End A 8 B21 Insulation Contact Clearance ge a HU uha LIS ont HE aa aulas B 1 B 2 Jackscrew Backshell Thermocouple Installation aa B 2 B 3 Insulation Contact B 4 B 4 Jackscrew Backshell Installation esee B 5 B 5 Shield Install onto a Jackscrew Backshell 78 pin B 7 B 6 Method A 1 for Shield Termination nennen enne ennt enne tenens B 8 B 7 Insulation Contact Clearance q k k enne nnne enne h kaspa tenerent ne enne B 10 B 8 Method A 2 Daisy Chain for Shield Termination esses B 12 B 9 Method B 1 Quick Term for Shield Termination B 13 B 10 Method B 2 Daisy Chain Quick Term for Shield Termination B 14 B 11 Daisy Chain between Methods and B 15 B 12 Method C 1 Double Shield Termination
35. PFD OR MFD GDU 375 AIRCRAFT POWER 1 POWER GROUND AIRCRAFT POWER 2 POWER GROUND XM ANTENNA GSU 73 AIRCRAFT POWER 1 POWER GROUND AIRCRAFT POWER 2 POWER GROUND BACKUP PWR Figure D 1 1 Notes 14V Power and Antennas G3X Installation Manual Interconnect Drawings 190 01115 01 Page D 1 Page D 2 blank Revision A APPENDIX D INTERCONNECT DRAWING 8 310N 335 0 90900 210 310QON 9SI3NOO 8 310N 33S SY GNNOYD TWwNOIS GNNOYD M3MOd M3MOd OQAZL NI S8 SY aNnoW9 TYNOIS 110 6587 58 v 100 S8p SM OO O cO ro ANNOYS WNOIS IH Sn8 8 IH SNG NILH N Atl Ql WALSAS nao Wvs9ONd Ql WALSAS NO TWNOIS 90 01 W31SAS NGO NvsSO3Sd 01 WALSAS 100 NOILVNINYSL SNE NVO O1 Sn8 NYO IH Sn8 NVO cd add XLE nao WNOLLdO QNnO3N9 WNOIS IH 509 NILH N IH v AV3903d 01 WALSAS NAO Ql WALSAS 100 01 W3ISAS 100 NV3903d GI WALSAS 100 NOILVNINYSL 509 NVO O1 Sn8 IH 509 NVO XZE nao WNOlLdO NOILVNINYSL 509 NVO O1 SNE NVO IH 5 NVO QNNOYS WNOIS IH SNE IH SNG AVL Ql WALSAS 100 Wvsg9ONd Ql WALSAS nao WvU9Odd 01 W31SAS 100 NvsSO3Sd 01 WALSAS 100 WNOIS 49010 3101001
36. Revision A 8 Use the FMS Joystick to highlight the Calibrate button at the bottom of the display press the ENT Key to begin the calibration 9 The operator should carry out the actions called for in the prepared test sequence It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence 10 After the calibration is finished a Done button will appear at the bottom of the display ensure thata MAG INTERFERENCE TEST PASSED message appears at the bottom of the display press the ENT Key to return to the GSU Status Page Page 8 22 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 Table 8 4 Magnetometer Interference Test Sequence Example Elapsed Time Since Start of Test min secs Test begins Aileron full right Aileron full left Aileron level Flaps down Flaps up Landing gear up Landing gear down Speed brake up Speed brake down Navigation lights on Navigation lights off Landing lights on Landing lights off Taxi lights on Taxi lights off Landing Taxi lights on Landing Taxi lights off Strobes on Strobes off Recognition lights on Recognition lights off Turn on all wing tip lights simultaneously typically will include navigation lights recognition lights and strobe Turn off all wing tip lights simultaneously Beacon on Beacon off Pitot heat on Pitot
37. STEREO AUDIO OUT LO ALERT 1 AUDIO IN HI MONO AUDIO OUT HI ALERT 1 AUDIO IN LO MONO AUDIO OUT LO Figure E 1 1 Notes GDU 37X RS 232 and Audio Examples G3X Installation Manual External Interface Drawings 190 01115 01 Page E 1 Page E 2 blank Revision A APPENDIX E EXTERNAL INTERFACE DRAWING EXAMPLE ONLY 8 110 687 V 110 687 8 110 687 V 110 687 91 NI 687 VL NI 687 91 NI 687 VL NI 687 8 110 687 v 110 687 8 110 687 v 110 687 LL 8 6 310N 33S S310N 33S ce oe 9c Sc 8c LC LL ONY OL SALON 33S 14 110 66 ONIl3V 110 6 ONIYV AVN 8 NI 6z ONIYV AVN NI 6 ONIMNV 549 8 NI 62 549 VE NI 67 91 100 62 VI 10 6 ONN 549 81 NI 625 549 VL NI 67 AVN 9 NI 627 AVN NI 627 110 Z S3 QNnO39 TWNOIS INO 262 534 QNhON9 IVN9SIS Figure E 1 2 GSU 73 RS 232 and ARINC 429 Examples Page E 3 Page E 4 blank G3X Installation Manual External Interface Drawings Revision A 190 01115 01 APPENDIX E EXTERNAL INTERFACE DRAWING EXAMPLE ONLY WNSIS 3313831 OIGNV WOOM3INI YO TANVd OIGNV OL SOINOIAV Ol31 lOMINOO 23 193NNOOSIQ 0435 vl p 193NNOOSIQ OAYSS QNnO39 VN3SIS NI 7 435 599 dv vsL nas 09 NO dV
38. The GSU 73 should not be at the low point of the pitot or static plumbing lines to avoid moisture or debris collecting at or near the unit Ensure that no 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 4 5 2 Pneumatic Connections The following steps should be used to aid in the fabrication of pneumatic hose connections and in attaching the aircraft pitot pressure source and aircraft static pressure source to the GSU 73 Check pneumatic connections for errors before operating the GSU 73 Incorrect plumbing could cause internal component damage Observe the following cautions when connecting pneumatic lines 1 Make sure the aircraft static 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 73 The installer must fabricate any additional mounting equipment needed Use outline and installation drawings in Appendix C for reference G3X Installation Manual GSU 73 Page 4 5 190 0
39. VO 13 P731 DISCRETE OUT 1 OUT 14 P731 DISCRETE OUT 2 OUT Indicates Active Low A 3 7 Analog Input Configuration Some analog inputs are multi purpose capable and have several configuration options These inputs are configured automatically at power on by a configuration file stored in the GDU The following table summarizes the configuration options Configurable Parameter Description Characteristic Resistive Divider Resistive Divider can be enabled or disabled for Analog Input channels 14 25 Enabling amp Disabling is achieved via software configuration When Disabled Hardware scaling is 1 1 and input impedance is greater than 10 MO When Enabled Hardware scaling is approximately 45 1 and input impedance is approximately 100 kQ Voltage Measurement Ranges There are six voltage measurement ranges for analog inputs 25mV 55 mV 100 mV 1 0 2 5 Vdc and 5 0 Applies to both 1 1 and 45 1 scaling Effective voltage range in 45 1 mode e 1 125 Vdc 2 475 4 5 Vdc and 45 Bipolar Unipolar Each analog input can be configured to measure Bi Polar positive and negative or Uni Polar positive only voltages All analog inputs are differential Constant Current Source Analog Input channels 12 13 22 23 24 amp 25 can be configured to supply a 250 pA constant current source CCS from the positive differential input used to measure resistive sensors The negative LO side
40. a GPS antenna This location results in the aft fuselage shading the antenna ANTENNA BRACKET N a a PANEL Figure 6 3 Glare Shield Buried Antenna Area Due to the excessive temperature environment and large areas of signal blockage caused by the fuselage mounting the antenna under the engine cowling forward of the firewall is not recommended and likely will not provide adequate GPS reception 6 3 4 Antenna Doubler Backing Plate The antenna installation must provide adequate support for the antenna considering a maximum drag load of 5 lbs at subsonic speed When penetrating the skin with a large hole i e for the coax connector a doubler plate is required to re instate the integrity of the aircraft skin Never weaken the aircraft structure when choosing a mounting area Make use of any available reinforcements where appropriate 6 3 5 Antenna Grounding Plane Although no ground plane is required the antennas typically perform better when a ground plane is used The ground plane should be a conductive surface as large as practical with a minimum diameter of 8 inches To use an antenna in aircraft with fabric or composite skin a ground plane is recommended It is usually installed under the skin of the aircraft below the antenna and is made of either aluminum sheet or of wire mesh 6 3 6 Antenna Grounding The antenna is grounded through the mounting hardware and the coax connection The mounting hardware w
41. an XM receiver 2 1 1 Navigation Functions Display of position and ground speed Display of stored navigation and map databases Area navigation functions using the determined position velocity and stored navigation data Advisory approach navigation functions and associated databases G3X Installation Manual GDU 37X Page 2 1 190 01115 01 Revision A 2 1 2 Interface Summary The GDU 37X uses CAN and RS 232 communications interfaces The GDU 37X communicates with the following Garmin LRUs e Other GDU 37X GSU 73 SL30 Nav Comm Transceiver SL40 Comm Transceiver GNS 400 500 Series Units GTX 327 330 Transponder 2 2 Electrical Specifications 2 2 1 Electrical Characteristics Table 2 1 GDU 37X Supply Voltages Characteristics Specifications Power Requirements 14 28 VDC 2 2 2 Power Consumption Table 2 2 GDU 37X Power Requirements 14V Maximum 14V Typical 28V Maximum 28V Typical GDU 370 15W 1 10 Amp 8 5W 600 Amp 15W 0 540 Amp 8 5W 300 Amp GDU 375 15W 1 10 Amp 9 5W 675 Amp 15W 0 540 Amp 9 25W 330 Amp 2 2 3 GPS Specifications The GDU 37X uses a high sensitivity GPS receiver that continuously tracks and uses up to 12 satellites to compute and update its position Table 2 3 GDU 37X GPS Specifications Characteristics Specifications Acquisition Time a Warm Start position known to 10 nm time known to 10 minutes with valid almanac and ephemeris Less than 5 seconds b Co
42. and Installation Aircraft Skin Thickness 0 032 to 0 049 0 049 to 0 051 0 051 to 0 063 Doubler Design Figure Figure 6 4 Figure 6 5 Figure 6 6 Number of Rivets Required 12 16 16 Type of Rivets Required MS20426AD4 x MS20426AD4 x MS20426AD4 x Skin Preparation for Rivets Dimple Dimple Countersink Doubler Preparation for Rivets Countersink Countersink None Skin Cutout Detail Figure Figure 6 8 Figure 6 9 Figure 6 10 Doubler Installation Figure Figure 6 11 Figure 6 12 Figure 6 13 Notes 1 Rivet length determined at installation dependent on thickness of material rivet length grip length 1 5 rivet diameter Refer to Figure B 2 X for Garmin Antenna installation drawings 6 4 1 Preparation of Doubler 1 Use Garmin P N 115 00846 10 or refer to Table 6 5 for guidance on selecting the appropriate doubler drawing based on the thickness of skin at the antenna location Make the doubler from 2024 T3 Aluminum AMS QQ A 250 5 0 063 sheet thickness 2 For installation in aircraft skins of thickness less than 0 051 countersink the rivet holes in the doubler for use with flush head rivets MS20426AD4 x 3 When using Garmin P N 115 00846 10 doubler sixteen rivet holes exist in the part For installation of Garmin P N 115 00846 10 in skins of thickness between 0 032 and 0 049 only the rivets identified for use through the skin cutout detail Figure 6 8 and doubler installation
43. away from the aircraft under test At the site align the aircraft to a heading of magnetic north 5 It is best to offset the aircraft position to the left west of the North South axis to allow turning clockwise around the site as indicated in Figure 8 2 N w E 5 Figure 8 2 Aircraft Alignment With the aircraft stationary initiate the GSU 73 AHRS magnetometer calibration procedure as follows 1 Enter configuration mode by holding down the left hand softkey while powering on GDU 37X if needed 2 Use the FMS Joystick to select the GSU Page if needed CONFIG GSU MAIN Page 8 10 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 3 Unlock the GSU Page by pressing softkeys 2 3 4 in order if needed 4 Ensure that all the required status boxes are checked Tables 8 2 and 8 3 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view of the sky or a GPS repeater to produce positive status indications GSU STATUS MAGNETOMETER AIR DATA GPS 5 the GSU Status Page use the FMS Joystick to select MAGNETOMER 65073 CALIBRATION T CALIBRATE 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key 65073 CALIBRATION G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 11 190 01115 01 Revision A 7
44. evidence of damage incurred during shipment If any component of the G3X system 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 1 2 Introduction This manual provides all of the mechanical and electrical information required for the installation of the G3X system The Garmin G3X system includes products like the GDU 37X and the GSU 73 that are not TSO certified products and have received no FAA approval or endorsement Consequently the G3X system is not suitable for installation in type certificated aircraft The following outline describes the organization of this manual Section 1 This section contains a basic overview of the G3X system and interface A Block diagram is given to aid in the understanding of the system This section also contains generic information that pertains to all components of the G3X system such as mounting wiring and antenna location Section 2 This section describes the mechanical electrical and installation aspects of the GDU 37X Section 3 This section describes the mechanical electrical and installation aspects of t
45. from the date of purchase Within this 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 cover failures due to abuse misuse accident or unauthorized alteration or repairs THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR 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 THIS 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 the unit 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 To obtain warranty service contact your local Garmin Authorized Service Center For assistance in locating a Service Center near you call Garmin Customer Servic
46. hoses NOTE When mounting the GSU 73 to the airframe it is important to ensure that fastening hardware is tight for proper unit operation G3X Installation Manual GSU 73 Page 4 7 190 01115 01 Revision A 4 8 Maintenance Per Part 43 Appendix 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 paragraph iv Friction and vi Barometric Scale Error are not applicable because the digital outputs of the GSU 73 are not susceptible to these types of errors A GSU 73 Field Calibration Tool not yet available can be used to adjust the calibration of GSU 73 units that have failed the 14 CFR Part 43 Appendix E tests due to altitude drift The GSU 73 utilizes an Earth magnetic field model which is updated once every five years This IGRF International Geomagnetic Reference Field update is expected to be available from Garmin by July 1 of each of the following years 2010 2015 and every five years thereafter so long as the GSU 73 remains a Garmin supported product The model can be updated by the end user via the internet it is not necessary to return the GSU 73 to Garmin for this update Otherwise maintenance of the GSU 73 is on condition only Page 4 8 Installation Manual GSU 73 Revision A 190 01115 01 5 GTP 59 Figure 5 1 GTP 59 5 1 Equipment Description The Garmin GTP 59 is an outside mounted
47. information all displayed on one two or three color screens The G3X system is composed of several sub units or Line Replaceable Units LRUs LRUs have a modular design and can be installed directly behind the instrument panel or in a separate avionics bay if desired This design greatly eases troubleshooting and maintenance of the G3X system A failure or problem can be isolated to a particular LRU which can be replaced quickly and easily Each LRU has a particular function or set of functions that contributes to the system s operation For additional information on LRU functions see the applicable section of this manual 1 3 1 System Architecture Figure 1 1 illustrates an example block diagram of a G3X installation The flexibility of system allows the installer to determine the architecture that best fits each installation SL ELT GMA 240 iid RS 232 ah AUDIO Config Module 34 GDU 37X PFD1 GDU 37X MFD GDU 37X PFD2 Autopilot Rs 232 1711 1 2 i RS 232 RS 232 429 GMU 44 Rz 7 2322 GTX 330 59 gt ene Config Module 3 5 3 5 Notes 8 20 1 Maximum of 2 COM NAV units installed 2 GDU 37X to 8140 is TX only GNS arpaa gt GNS 430 W Rs252 430 W Figure 1 1 G3
48. intermittent circuit breakers Have ground power put on the aircraft Turn on the G3X and record the system software level on the GDU start up page After the system is initialized note any Red X s on the displays ALERT messages and Red X s on the GDU If the failure cannot be verified proceed to the following physical inspection Turn off the G3X and remove the interior panels to gain access to the GSU 73 Inspect the physical installation of the GSU 73 Check that the connectors are fully seated and that the jack screw connectors are fully tightened on both sides of the GSU 73 connector Check for a loose wire harness that is able to move around during flight This condition may cause the wire to pull on or vibrate the connector making intermittent connections Ensure that the GSU 73 is mounted securely If any doubt exists use a screwdriver to check the tightness of the four mounting screws Look in the vicinity of the GSU 73 for any heavy objects that may not be fastened tight to the structure that could induce GSU 73 vibration Look for evidence of water or fluid contamination in the area around the GSU 73 Unplug the GSU 73 connector and check for bent pins Inspect the wire harness clamp on the rear of the connector to verify that it is not too tight and smashing shorting the wires If the wire clamp is installed upside down it has sharp edges that can cut into the wires Also verify the presence of protective wire
49. may prove beneficial to use a solder sleeve with a pre installed Flat Braid versus having to cut a length of Flat Braid to be used The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the Flat Braid item 4 to be attached Solder Sleeves with pre installed Flat Braid A preferred solder sleeve would be the Raychem 503 Series with the thermochromic temperature indicator S03 02 R 9035 100 S03 03 R 9035 100 S03 04 R 9035 100 These solder sleeves come with a pre installed braid and effectively take the place of items 3 and 4 For detailed instructions on product use reference Raychem installation procedure RCPS 100 70 Raychem recommended heating tools HL1802E AA 400 Super Heater CV 1981 MiniRay IR 1759 Individual solder sleeves and Flat Braid Solder Sleeves Reference the following MIL Specs for solder sleeves M83519 1 1 M83519 1 2 M83519 1 3 M83519 1 4 M83519 1 5 Flat Braid If the preferred Raychem sleeves are not being used the individual flat braid selected should conform to ASTMB33 for tinned copper and be made up of 36 AWG strands to form an approximately 19 20 AWG equivalent flat braid A circular mil area range of 1000 to 1300 is required The number of individual strands in each braid bundle is not specified e g QQB575F36T062 NOTE Flat Braid as opposed to insulated wire is specified in order to allow continuing air worthiness by allowing
50. of a CCS configured input must be tied to unit ground to provide a current path to ground Miscellaneous Sensor e Update Rate Configuration Parameters Voltage Translation Equations Minimum Maximum Values for Sensors Hysteresis Value Digital Filtering Value G3X Installation Manual Pinouts Page A 13 190 01115 01 Revision A If installing an ungrounded thermocouple to an Analog In input a DC reference must be added to the LO input This can be accomplished by adding a resistance of 1 MQ or less between ground and the Analog In LO input that the ungrounded thermocouple is installed on Connector Pin Name 61 P732 ANALOG IN 1 HI IN 41 P732 ANALOG IN 1 LO IN 21 P732 ANALOG IN 2 LO IN 1 P732 ANALOG IN 2 LO IN 2 P732 ANALOG IN 3 HI IN 22 P732 ANALOG IN 3 LO IN 60 P732 ANALOG IN 4 HI IN 40 P732 ANALOG IN 4 LO IN 73 P732 ANALOG IN 5 HI IN 53 P732 ANALOG IN 5 LO IN 33 P732 ANALOG IN 6 HI IN 13 P732 ANALOG IN 6 LO IN 63 P732 ANALOG IN 7 HI IN 43 P732 ANALOG IN 7 LO IN 23 P732 ANALOG IN 8 HI IN 3 P732 ANALOG IN 8 LO IN 24 P732 ANALOG IN 9 HI IN 4 P732 ANALOG IN 9 LO IN 62 P732 ANALOG IN 10 HI IN 42 P732 ANALOG IN 10 LO IN 30 P732 ANALOG IN 11 HI IN 29 P732 ANALOG IN 11 LO IN 34 P732 ANALOG IN 12 HI IN 14 P732 ANALOG IN 12 LO IN 72 P732 ANALOG IN 13 HI IN 52 P732 ANALOG IN 13 LO IN
51. product use reference Raychem installation procedure RCPS 100 70 Raychem recommended heating tools HL1802E AA 400 Super Heater CV 1981 MiniRay IR 1759 G3X Installation Manual Appendix Page B 21 190 01115 01 Revision A Secondary Method Solder a flat braid item 6 to the shield exposed through the window of the prepared cable assembly item 4 Ensure a solid electrical connection through the use of acceptable soldering practices Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire Slide a minimum 0 75 inches of Teflon heat shrinkable tubing item 5 onto the prepared wire assembly and shrink using a heat gun The chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable and the flat braid item 6 to be attached Solder Sleeves Reference the following MIL Specs for solder sleeves M83519 1 1 M83519 1 2 M83519 1 3 M83519 1 4 M83519 1 5 Flat Braid If the preferred Raychem sleeves are not being used the individual flat braid selected should conform to ASTMB33 for tinned copper and be made up of 36 AWG strands to form an approximately 19 20 AWG equivalent flat braid A circular mil area range of 1000 to 1300 is required The number of individual strands in each braid bundle is not specified e g QQB575F36T062 Teflon Heat Shrinkable Tubing Reference the followin
52. set to Auto or Manual this setting is also available in normal mode on the Display Setup page Auto Sets the backlight intensity display brightness based on the aircraft s instrument lighting bus voltage Manual Allows setting the display brightness by changing the Backlight Intensity 0 9 setting found beside the Manual setting Default Mode Can be set to Auto or Manual described above This controls the backlight mode that will be active each time the system is powered on 7 4 5 2 Automatic Backlight Control Window settings apply only to Auto setting Input Voltage Displays the current lighting bus voltage Backlight Level Displays the current backlight level 0 100906 Graph Brightness is displayed as the vertical Y axis and aircraft lighting bus voltage is displayed as the horizontal X axis The graph changes according to the auto backlight control settings and the lighting bus voltage Off Threshold Sets the lighting bus threshold voltage At the threshold voltage backlighting is turned on per the Min Brightness setting Below the threshold voltage the backlighting defaults to a Backlight Level of 100 The setting controls the range that the Off Threshold voltage is in effect Default values are 2 9V amp 0 15V Min Brightness Voltage and Percentage Sets the lower bus voltage required to turn the backlighting on to the percentage of brightness set by the Min setting Default values are 3 0
53. shield should be grounded at both ends Use nonmagnetic materials to mount the GMU 44 and replace any magnetic fasteners within 0 5 meter with nonmagnetic equivalents e g replace zinc plated steel screws used to mount wing covers or wingtips with nonmagnetic stainless steel screws In general wing mounting of the GMU 44 magnetometer is strongly preferred Fuselage mounting is strongly discouraged because of numerous potential disturbances that interfere with accurate operation Mechanical mounting fixtures for the GMU 44 must be rigidly connected to the aircraft structure Use of typical aircraft grade materials and methods for rigid mounting of components is acceptable 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 Align the GMU 44 mounting rack s forward direction to within 0 5 in heading of the aircraft forward direction longitudinal axis If it is not possible to guarantee this accuracy installation alignment to within 2 5 in heading is acceptable in combination with a post installation heading alignment of the aircraft to a precise heading to determine and set a heading offset The heading offset procedure is described in Section 8 3 4 It is strongly preferred that the GMU 44 alignment is within 0 5 of the aircraft longitudinal axis rather than using the heading offset procedure Page 3
54. table additional tables group pin connections by function Pin PinNam WO i SIGNALGROUND 0 6 PRESERVED 8 CANBUSLO OS O 9 JDISCRETEIN 1 0 o n j Indicates Active Low Page A 6 Installation Manual Pinouts Revision A 190 01115 01 Pin PinNam WO j 24 SIGNALGROUND 29 CANBUSTERMINATION 34 SIGNALGROUND 35 SIGNAL GROUND 36 SIGNAL GROUND 0 37 SIGNALGROUND 39 MAGNETOMETERGROUND f j gt 40 SIGNALGROUND 41 SPARE ee 42 SPARE T a 43 SIGNALGROUND 44 SPARE 01 0 0 0 VE 4 SPARE ee 46 SPARE mee 48 SPARE ee m 50 SPARE rr U oo oo 53 SIGNAL GROUND 54 SIGNALGROUND 5 4 c c c c c cr rC cC C t 5 SPARE S FR SPARE orr e aaao 58 SIGNAL GROUND f Soo 59 POWER GROUND 0 60 SIGNALGROUND LL j 61 POWERGROUND SPARE OO e ce G3X Installation Manual Pinouts Page A 7 190 01115 01 Revision A A 3 2 2 P732 Connector 90000000 OP O OP O O O OO O OO 1 O OOO O OP O OP O OP O O O O O OOO 21 O OOO O O O O O O 000000 0 40 O OOP 000 00000000000 0 G 60 Figure A 5 Rear Connector J732 Viewed from Connector End of Unit 6 ANALOGIN
55. temperature probe that provides raw air temperature data The temperature input device is a three wire temperature probe interface OAT Power Out and OAT High are connected internally at the OAT probe The GTP 59 is a Resistive Temperature Device RTD 5 1 1 Available Equipment The GTP 59 is available per the following part number Table 5 1 GTP 59 Part Number GTP 59 OAT Probe Kit 011 00978 00 Included in G3X LRU K10 00016 00 5 2 Installation Requirements Table 5 2 contains a list of items found in the GTP 59 Outside Air Temperature OAT Probe kit 011 00978 00 The GTP 59 probe has an attached pigtail Table 5 2 GTP 59 Outside Air Temperature Kit Garmin P N Quantity Nut 5 16 Hex Skirt 210 00055 00 Screw 4 40 x 250 PHP SS P w NYL 211 60234 08 Washer Lock Self Sealing 5 16 212 00026 00 Contact Pin Mil Crimp Size 22D 336 00021 00 GTP 59 OAT Probe 494 00022 xx Included in G3X LRU Kit K10 00016 00 G3X Installation Manual GTP 59 Page 5 1 190 01115 01 Revision A 5 2 1 Additional Equipment Required e Cables The installer will supply all system cables 5 3 TSO ETSO Compliance The following table provides a list of applicable TSO ETSOs for the GTP 59 Table 5 3 Applicable TSO ETSOs for the GTP 59 Applicable LRU Applicable CLD TSO C106 Air Data Computer ETSO C106 Not Applicable Not Applicable 5 3 1 TSO ETSO Deviations The following deviations have bee
56. the ground may consistently cause a Red X to be displayed on the heading in the same spot while taxiing this is not caused by a failure of the GMU 44 or its calibration 2 When the aircraft is taxiing on the ground with a yaw rate of less than 1 5 degrees second i e taxiing essentially in a straight line GPS track information is used to update heading information This logic is applied regardless of magnetic anomaly detection 3 The GDU may display Red X on the heading if the GSU 73 does not have GPS information or if it senses a magnetic anomaly 4 While a magnetic anomaly is detected and the aircraft is determined to be stationary the value of the heading output is frozen When either the aircraft is determined to be no longer stationary or the magnetic anomaly ceases heading will be unfrozen and determined as useable In this context the aircraft is considered to be stationary when its yaw rate is less than 1 0 degrees second and all other angular rate and acceleration values are sufficiently small moving or shaking the wings or tail for example can cause a Red X to be displayed 5 Check to see if any new equipment has been installed on the aircraft and reference Table 3 5 for minimum distances for installed equipment from the GMU 44 to prevent interference If the GMU 44 heading is not present on the GDU 37X there may be a problem with the RS 232 line between the GSU 73 and GMU 44 Troubleshoot any possible wiring connector is
57. to secure the Teardrop style antenna to the mounting surface Torque the locking nuts to 12 15 in lbs torque should be applied evenly across all mounting studs A doubler plate similar to Figure 6 14 or P N 115 00846 00 ARINC 743 style can be used with the mounting surface to support the antenna Rivets used to secure the doubler plate to the mounting surface are optional in a non structural installation Locking nuts are required to secure the ARINC 743 antenna locking nuts installed on doubler Torque the four supplied 10 32 stainless steel screws Garmin P N 211 60212 20 MS51958 67 or equivalent evenly across all mounting screws 4X 10 32 PHP x 1 00 25 4 TORQUE 20 TO 25 in lbs Bae ARINC 743 FOOTPRINT ANTENNA i RIVETS OPTIONAL ANTENNA MOUNTING SURFACE DOUBLER Figure 6 25 Generic Non structural ARINC 743 Footprint Antenna Installation G3X Installation Manual Antennas Page 6 23 190 01115 01 Revision A 6 6 2 Considerations for Non Structural Mounting External mounting of the antenna is preferred although the antenna can be mounted inside the aircraft When mounted internally the antenna does not have to be aligned with the aircraft forward direction but should be equal to the aircraft typical cruise attitude There should be a solid mechanical base in the mounting area for the antenna and existing surfaces or brackets may be used with the
58. while retaining the shield on the OAT Probe cable 3 Trim away enough to leave 0 5 of shield exposed G3X Installation Manual GTP 59 Page 5 3 190 01115 01 Revision A 10 Strip back 1 8 0 125 of insulation and crimp pins 11 to each of the conductors in the shielded cable Cut an AWG 16 8 wire to 3 long Strip back 0 5 of insulation from this cable Connect the shield of the OAT Probe cable 3 to the AWG 16 wire 8 Attach the ring terminal 9 to the backshell using the screw provided in the OAT Probe Kit 10 and one of the tapped holes on the backshell termination area Insert newly crimped pins into the D Sub connector and wires 3 11 into the appropriate connector housing location 12 7 as specified by the installation wiring diagrams Verify that all necessary pins for the GSU 73 have been attached to the cables and snapped into the proper slots of the 78 pin D Sub connector Wrap the cable bundle with Silicone Fusion Tape GPN 249 00114 00 or a similar at the point where the backshell strain relief and cast housing contact the cable bundle The smooth side of the backshell strain relief should contact the tape 5 5 Unit Installation Refer to Figure C 4 1 GTP 59 O A T Probe Wiring Detail for wiring and mounting instructions 5 6 Maintenance Maintenance of the GTP 59 is on condition only Periodic maintenance of the GTP 59 is not required Page 5 4 G3X Installation Manual
59. x RIVETS NOTES 1 MS20426AD4 X RIVET SELECTION LENGTH AND INSTALLATION DETERMINED USING THE GUIDANCE FOUND IN AC43 13 1B Figure 6 13 Doubler Installation Teardrop Footprint Antenna Skin Thickness 0 051 to 0 063 G3X Installation Manual Antennas Page 6 13 190 01115 01 Revision A 6 5 ARINC 743 Footprint Antenna Installation GA 55A GA 57X This section describes the structural mounting of the ARINC 743 footprint antenna GA 55A GA 57X installation One acceptable method is to use Garmin P N 115 00846 00 doubler plate Another acceptable method is to fabricate and install one of three doublers Figure 6 14 Figure 6 15 or Figure 6 16 depending on the thickness of the skin The three doubler designs vary only by number of rivets and hole preparation for installation with flush rivets Figure 6 24 shows installation of the ARINC 743 footprint antenna Table 6 6 provides a summary of design and installation details for the antenna doubler Figure 6 17 shows an example of the doubler installed between stringers on the top fuselage skin just off centerline The location should be flat with no gaps between the skin and doubler to keep from deforming the skin during installation Table 6 6 ARINC 743 Footprint Antenna Doubler Design and Installation Skin Thickness 0 032 to 0 049 0 049 to 0 051 0 051 to 0 063 Doubler Design Figure Figure 6 14 Figure 6 15 Figure 6 16 Number of Rivets Req
60. 011 01747 Figure 2 2 GDU 37X Mounting Accessories Page 2 4 G3X Installation Manual GDU 37X Revision A 190 01115 01 2 5 Installation Considerations Fabrication of a wiring harness is required Sound mechanical and electrical methods and practices are recommended for installation of the GDU 37X Refer to Section 1 6 for wiring considerations and to Appendix A for pinouts Connector kits include backshell assemblies Garmin s backshell connectors give the installer the ability to quickly and easily terminate shield grounds and install a configuration module PFD1 only at the backshell housing The instructions needed to assemble the backshell connector w Shield Block grounding system and configuration modules are located in Appendix B The GDU 37X rear connector J3701 is electrically isolated For installations using shielded cables a ground pin must be tied to the connector shell 2 6 Mounting Requirements Refer to Appendix C for outline and installation drawings 2 7 Unit Installation The GDU 37X is installed by holding the unit flush with the instrument panel and fastening the four captured 3 32 hex socket head screws to the panel as shown in Figures C 1 1 and C 1 2 2 8 Maintenance Maintenance of the GDU 37X is on condition only Periodic maintenance of GDU 37X is not required Instructions for Continued Airworthiness ICA are not required for this product under 14 CFR Part 21 since the GDU 37X
61. 01115 01 Revision A 8 3 6 Calibration Procedure F Magnetometer Interference Test Calibration Procedure F is required for initial installation verification 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 electrical device located in the same wing as a GMU 44 unit Likewise this test should also be repeated to verify all subsequent changes to materials within 10 0 feet of the GMU 44 Such changes include but are not limited to addition removal or modification of ferrous or electrically conductive materials located in the same wing as a GMU 44 unit This procedure validates that no electronic device is interfering with the operation of the GMU 44 magnetometer which directly impacts the determination of attitude and heading by the GSU 73 AHRS Calibration Procedures A through E are not required prior to this execution 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 G3X system 1 Enter configuration mode by holding down the left hand softkey while powering on the GDU 37X if needed 2 Use the FMS Joystick to select the GSU Page if needed CONFIG GSU 3 Un
62. 1 190 01115 01 Revision A Figure B 2 Jackscrew Backshell Thermocouple Installation Page B 2 G3X Installation Manual Appendix B Revision A 190 01115 01 B 2 Jackscrew Configuration Module Installation into a Jackscrew Backshell Tables B 2 amp B 3 list parts needed to install a Jackscrew Configuration Module with pins or with sockets Parts for these installations are included in the 011 00979 20 and 011 00979 22 kits which are included in the G3X Installation Kit K10 00017 00 Configuration modules are to be installed in the backshells of the P732 connector for the GSU 73 and the P3701 connector for the GDU 37X designated as PFD1 Table B 2 011 00979 20 Kit and pins Description Qty Needed GPN or MIL spec Potted Module w EEPROM and Temp sensor 9105179100 4 cond Cable harness 325 00122 00 Pins Size 22D 336 00021 00 Pan head screw 211 60232 07 Description GPN or MIL spec Potted Module w EEPROM and Temp sensor A De 4 cond Cable harness 325 001 22 00 Socket Size 20 26 30 AWG 336 00022 01 Pan head screw 211 60232 07 G3X Installation Manual Appendix Page B 3 190 01115 01 Revision A NOTES For the following steps please refer to Figures B 3 amp B 4 1 Strip back approximately 0 17 inches of insulation from each wire of the four conductor wire harness item 3 and crimp either a pin item
63. 10 00017 00 a 1 5 1 6 Contents of G3X LRU Kit 10 00016 00 1 5 1 7 Pin Contact and Crimp Tools Part Numbers rennen nennen nennen nenne 1 6 221 37X Supply Voltages a uir RODEO DPI ORO DEI ORO EORR ege 2 2 2 2 Power Requirermients e t Pene eH eee ete eee Pe HE eee ass 2 2 2 3 GDU 37X GPS Specifications iti 2 2 2 4 GDU 37X Supported Antenrias a tree re e Renee eee e nce e lebe A 2 3 2 5 Contents of GDU 37X Connector Kit 011 01921 00 2 4 3 1 44 Electrical 3 1 3 2 GMU 44 Environmental 3 2 3 3 qTSO BEISO Compliance uet eerte teet reet eet ea 3 2 3 4 LISO ETSO Deviations neri Rt t a Petre peo ieri betae Pe i eoe eee obit cd 3 2 3 5 GMU 44 Part Nuinbets 1 s ER et Ee Hiec aide He ER tei eta eed eg 3 3 3 6 GMU 44 ACCESSOTIES eee te t eet tae UR OR Tea oe ere 3 3 3 7 Required Distance from Magnetic 3 4 3 8 Parts Needed for GMU 44 3 5 3 9 44 Connector Kit 011 00871 00 Contents Reference Figure C 2 4
64. 1115 01 Revision A 4 6 Mounting Requirements Mount the GSU 73 with the connectors aligned within 1 0 deg of either the X or Y axis of the aircraft The direction of the unit will be accounted for during the calibration procedure as shown in Figure 4 3 GSU73 CALIBRATION SELECT THE DIRECTION THE GSU 3 CONNECTORS ARE FACING AFTER INSTALLATION FROM THE FOLLOWING LIST TAIL a SELECT AHRS MOUNT ORIENTATION SELECT OK TO CANCEL Figure 4 3 GSU 73 Orientation Calibration The GSU 73 includes an extremely sensitive strap down inertial measurement unit It must be mounted rigidly to the aircraft primary structure preferably to a metallic structure to conduct heat away from the unit Do not mount the GSU 73 in an enclosed area it should be mounted in a location that provides adequate airflow to comply with the maximum outer case temperature listed in Section 4 3 Page 4 6 G3X Installation Manual GSU 73 Revision A 190 01115 01 Do not use shock mounting to mount the GSU 73 Shock mounts used for other types of inertial systems are not acceptable for the GSU 73 AHRS The mounting system must have no resonance with the unit installed Excessive vibration may result in degraded accuracy The supporting plate must be rigidly connected to the aircraft primary structure through strong structural members capable of supporting substantial loads Avoid areas that are prone to severe vibration Th
65. 17LO in 8 ANAOGIN23LO in 9 THERMOCOUPLE REFINLO in 18 SIGNALGROUND 37 SIGNAL GROUND Indicates Active Low Page A 8 Installation Manual Pinouts Revision A 190 01115 01 Pin PinNam WO OPARE 2 ee ee O 56 TRANSDUCER POWER OUT LO GROUND 57 TRANSDUCER POWER OUT LO GROUND gt 60 ANALOGIN4H i 66 ANALOG IN25HE dn 68 ANALOG CURRENTMONITORIN2LO h 69 ANALOG IN21HE m 74 TRANSDUCER POWER OUT LO GROUND EN RESERVED FUEL SENSOR PULL UP 2 ANALOG IN 15 RESERVED FUEL SENSOR PULL UP 1 ANALOG IN 14 CONFIG MODULE GROUND Indicates Active Low G3X Installation Manual Pinouts Page A 9 190 01115 01 Revision A A 3 3 Power I O A 3 3 1 Aircraft Power The GSU 73 has four inputs for aircraft power bus inputs of 14 28Vdc Connector Pin Name AIRCRAFT POWER 1 AIRCRAFT POWER 2 POWER GROUND POWER GROUND A 3 3 2 Transducer Output Power The GSU 73 supplies output power for engine airframe sensors that may require supply voltage excitation The GSU 73 outputs voltage levels of 5 10 and 12 Vdc Connector Pin Name 12VDC TRANSDUCER POWER OUT TRANSDUCER POWER OUT LO GROUND 10VDC TRANSDUCER POWER OUT TRANSDUCER POWER OUT LO GROUND 5VDC TRANSDUCER POWER OUT TRANSDUCER POWER OUT LO GROUND
66. 2 B 1 B 2 C 1 and 2 Figure B 14 D Sub Spliced Signal Wire illustration Page B 18 G3X Installation Manual Appendix B Revision A 190 01115 01 B 4 Circular Connector Installation Instructions B 4 1 Pigtail Installation Parts Table B 9 provides a list of parts needed to install a circular connector with backshell Parts for this installation are included in the pigtail connector kits and some are to be provided by the OEM installer Table B 9 Parts supplied for a Circular Connector Installation Figure B 15 3 Circular Backshell Non Magnetic includes 2 self tapping 330 90005 01 screws and circular connector Table B 10 Parts NOT supplied for a Circular Connector Installation Figure B 15 Figure Ref GPN or MIL spec 19 MS3474L14 19SW Multiple Conductor Shielded Cable 2 conductor Reference Installation Wiring shown in Figure B 15 Diagrams 8 Wire Shield Termination method Pars used PA metod F Flat 19 20 AWG equivalent tinned plated copper strands 36 AWG Circular Mil Fans used on mathod Area 1000 1300 Floating Shield Termination method optional Pans used bes Ring terminal 6 insulated 18 22 AWG MS25036 102 Ring terminal 6 insulated 14 16 AWG MS25036 107 Ring terminal 6 insulated 10 12 AWG MS25036 111 G3X Installation Manual Appendix Page B 19 190 01115 01 Revision A NOTE
67. 2X 5 50 139 8 2X 7 33 186 2 Figure C 3 1 GSU 73 Outline Drawing Page C 13 Page C 14 blank Revision A APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 03 x 45 02x 45 CHAMFER CHAMFER 5 16 32 UNEF 2A i JS an 1 57 57 0 50 050 SEE NOTE 2 E W SEE NOTE 3 SEE NOTE 4 NOTES DIMENSIONS INCHES MAX HEIGHT OF INCOMPLETE THREAD 0 050 CABLE M27500 22TE3V14 CABLE LENGTH BE 10 FEET 6 INCHES 16 AWG WIRE M22759 16 16 LENGTH OF WIRE OUTSIDE OF CASE TO BE 3 5 INCHES 0 25 0 SOLDER TERMINAL MS25036 109 SHIELD OF CABLE ELECTRICALLY CONNECTED TO 16 AWG WIRE BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLE 5 3 Figure C 4 1 GTP 59 O A T Probe Installation Drawing G3X Installation Manual Outline amp Installation Drawings Page C 15 Page C 16 blank Revision A 190 01115 01 APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GA 55 STUD MOUNT GA 55A FLANGE MOUNT gORWARP 289 011 00134 00 o8 ANTENNA AVIATION GA 55 T 4X 211 60212 20 10 32 PHP x 1 00 25 4 OR 20 TO 25 lb 253 00002 00 TORQUE T in lbs GASKET NEOPRENE 011 01153 00 GA 55A XM ANTENNA 253 00138 00 MOLDED GASKET AIRCRAFT SKIN ON TOP OF FUSELAGE AIRCRAFT SKIN 115 00031 00 e BACKING PLATE A 4X 210 10004 09 FABRICATE AND INSTALL DOUBLER PLATE 8 32 SE
68. 3 Available Equipment Garmin P N Quantity Configuration Module w EEPROM and Jackscrew Kit 011 00979 20 Thermocouple Kit 011 00981 00 Unit Assembly GSU 73 011 01817 00 P731 Connector Kit GSU 73 011 01818 00 P732 Connector Kit GSU 73 011 01818 01 Included in G3X LRU Kit K10 00016 00 Included in Installation Kit K10 00017 00 Table 4 4 Contents of P731 Connector Kit 011 01818 00 Garmin P N Quantity Sub Assy Backshell w Hdw Jackscrew 011 01855 03 Connector Hi Dens D Sub Mil Crimp 62ck 330 00185 62 Contact Pin Mil Crimp Size 22D 336 00021 00 Included in Installation Kit K10 00017 00 Installation Manual GSU 73 Page 4 3 190 01115 01 Revision A Table 4 5 Contents of P732 Connector Kit 011 01818 01 Garmin P N Quantity Sub Assy Backshell w Hdw Jackscrew 011 01855 04 Connector Hi Dens D Sub Mil Crimp 78ck 330 001 85 78 Contact Pin Mil Crimp Size 22D 336 00021 00 Included in G3X Installation Kit K10 00017 00 4 4 2 Additional Equipment Required e Cables The installer will fabricate and supply all system cables e Hardware 10 32 pan or hex head screw 4 ea and 10 32 self locking nut 4 ea Air hoses and fittings to connect pitot and static air to the GSU 73 The GSU 73 has a female 1 8 27 ANPT fitting for each pitot and static port Use appropriate aircraft fittings to connect to pitot and static s
69. 4 or a socket item 9 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 B 3 INSPECTION HOLE WIRE MUST BE VISIBLE AFTER CRIMPING N l fo 3 1 64 TD 1 32 _ _ 3 Figure B 3 Insulation Contact Clearance 2 Insert newly crimped pins or sockets and wires items 3 and 4 into the appropriate connector housing item 5 location as specified by the installation specific wiring diagram 3 Attach the module item 1 to backshell item 6 using screw item 10 4 Plug the four conductor wire harness item 3 into the connector on the module item 1 Orient the connector housing item 5 so that the inserted four conductor wire harness item 3 is on the same side of the backshell item 6 as the module item 1 as shown in drawing 6 Attach cover item 7 to backshell item 6 using screws item 8 Page B 4 G3X Installation Manual Appendix B Revision A 190 01115 01 Figure B 4 Jackscrew Backshell Installation Page B 5 Revision A G3X Installation Manual Appendix 190 01115 01 Jackscrew Backshell Installation Instructions B 3 1 Shield Block Installation Parts Tables B 4 and 5 list the parts needed to install a Shield Block Parts li
70. 4 00 010 10040 01 Screw GA 57X Mount 2 ARINC 743 Footprint Garmin 011 01032 10 010 11370 10 1 The GPS antenna connector is TNC type The VHF COM antenna connector is BNC type The GPS antenna should provide a gain of 16 to 25dB and requires a 4 5V to 5V supply voltage that can provide 50mA max 2 3 Environmental Specifications The GDU 37X has an Operating Temperature Range of 20 C to 60 C G3X Installation Manual GDU 37X 190 01115 01 Page 2 3 Revision A 2 4 Installation Requirements 2 4 1 Accessories The GDU 37X Connector Kit is provided with the GDU 37X unit and is required to install the unit Figure 2 2 The GDU 37X Nutplate 115 01054 00 is also supplied with the unit to reinforce the panel cutout in thin panel installations The contents of the GDU 37X Connector Kit are listed in Table 2 5 One kit is required for each GDU 37X installed Table 2 5 Contents of GDU 37X Connector Kit 011 01921 00 Garmin P N Quantity Sub Assy bkshl w Hdw Jackscrew 011 01855 04 Conn Rcpt D Sub Crimp Socket C 330 00625 50 Contact Sckt D Sub Crimp Size 20 336 00094 00 2 4 2 Additional Equipment A 3 32 hex drive tool is required to secure the GDU 37X to the panel as described in Section 2 7 Unit Installation CONNECTOR KIT 011 01921 00 D D D D D D D D bag icu 22 GDU 37x UNIT
71. 5 5 Parts Needed for GTP 59 Installation Figure C 4 1 Description Qty Included Ring Terminal 3 Conductor Cable 494 00022 xx OAT Sensor Nut 1 210 00055 00 Washer 1 212 00026 00 1 Prepare the surface The metal body of the OAT probe should be grounded to the aircraft The installation requirements vary depending on the airframe material composition a Aluminum airframe When a mounting location has been found prepare the inside surface of the aircraft Remove all paint from the contacting area and clean with a degreaser b Composite airframe If possible mount the OAT probe through a grounded metal strap or band Otherwise mount the OAT probe in an area of the airframe that has a significant amount of underlying metal foil or mesh To ensure adequate conductivity it may be necessary to mount the OAT probe through a metal doubler Use fasteners that allow a conductive path to the airframe 2 Mount the OAT probe on the prepared surface Place the ring terminal 2 over the end of the OAT probe 4 Insert the probe and ring terminal into the hole in the skin of the aircraft Place the washer 6 over the end of the OAT probe on the outside skin of the aircraft Thread the nut 5 onto the OAT probe Holding the OAT probe on the inside tighten the nut 5 to 100 inch Ibs 20 inch Ibs 3 Route the OAT probe cable 3 to the GSU 73 4 Cutthe OAT Probe cable 3 to the required length Strip back 2 0 to 3 5 of jacket
72. 73 CALIBRATION _ CALIBRATE 5 Ensure that all the required status boxes are checked Tables 8 2 and 8 3 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have a clear view of the sky or a GPS repeater to produce positive status indications GSU STATUS MAGNETOMETER AIR DATA GPS Page 8 14 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key T 7 nnn HEADING OFFSET CALIBRATE 7 Ensure that the aircraft has been properly positioned per the on screen instructions GSU73 CALIBRATION 1 ENSURE THAT THE AIRCRAFT IS ON A CALIBRATED COMPASS ROSE 2 ENSURE THAT THE GPS AND MAGNETOMETER COMMUNICATION STATUS LIGHTS ARE GREEN MUST HAVE CLEAR VIEW OF SKY 3 MANEUVER THE AIRCRAFT SO THAT ITS ACTUAL HEADING IS WITHIN 0 5 DEG OF MAGNETIC NORTH 4 ENSURE THE AIRCRAFT IS STATIONARY READY TO ENTER THE 65073 AHRS GROUND HEADING OFFSET CALIBRATION MODE 8 Use the FMS Joystick to highlight the Calibrate button at the bottom of the display press the ENT Key to begin the calibration SELECT CALIBRATE TO BEGIN EE C UN NE CANCEL CALIBRATE 9 The PFD display advises the operator when to turn the aircraft to a cardinal heading when to stop and when to turn to another heading During the procedure the operator tur
73. 747 3 67 d E GDU 37x OUTLINE 93 1 REF 2X 3 58 91 1 50 NOTES 1 DIMENSIONS INCHES mm 38 0 2 DIMENSIONS SHOWN FOR REFERENCE ONLY 0 0 0 CONNECTOR KIT 011 01921 00 2X 3 58 o 91 1 AX 45 3 67 93 1 wN at aS ON No o oj No Oo No GDU 37x UNIT amp amp 011 01747 Figure C 1 2 GDU 37X Panel Cutout Drawing Page C 3 Page C 4 blank Revision A G3X Installation Manual Outline amp Installation Drawings 190 01115 01 APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GMU 44 MOUNTING RACK AIRCRAFT HOLES 3X 213 OPTIONAL CLEARANCE 3 370 85 60 HOLES FOR HOLD DOWN SCREWS gl 3X 164 4 17 2 520 64 01 THRU IN THIN MATERIAL USING LOCKING NUTS OR DRILL AND TAP 6 32 UNC IN MATERIAL THICKER THAN 3 16 4 8 3 PLCS 2 175 55 25 120 2X 1 485 2 51 63 75 P 2 49 63 25 115 00481 00 0 061 1 54 1 256 31 90 2 511 63 79 2 572 65 33 NOTE 1 DIMENSIONS IN INCHES mm 2 SEE SECTIONS 3 AND 4 FOR MOUNTING INSTRUCTIONS OF THE GSU 73 AHRS AND GMU 44 MAGNETOMETERUNIT 3 FOLLOW FORWARD AND TOP INDICATIONS ON UNIT AND RACK Figure C 2 1 GMU 44 Mounting Rack G3X Installation Manual Outline amp Installation Drawings Page C 5 Page C 6 blank 190 01115 01 Revision A AP
74. 7X does not interfere with its own GPS receiver However placement of the GPS antenna relative to a COM transceiver and COM antenna ELT antenna and DF receiver antenna is critical Use the following guidelines in addition to others in this document when locating the GDU 37X and its antennas e GPS Antenna Locate as far as possible from all COM antennas and all COM transceivers 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 transceiver antenna output e Locate the GDU 37X as far as possible from all COM antennas 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 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 GDU 37X unit VHF COM and a good ground 3 Shield the VHF COM wiring harness Page 6 2 G3X Installation Manual Antennas Revision A 190 01115 01 6 3 2 GPS XM Antenna Mounting Location The GPS antenna is a key element in the overall system performance and integrity for a GPS 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 ens
75. 913 VIVO FINGOW 923 2 43MOd JINON SISNOO QNnos9 JINON 9SIJNOO L add nao LOZ d O1 NI 338 31dn020WH3HL 00 00001 626 TET ASSY IH NI 333 3dAL 8 10 33S A NBO HO Bi 01 NI 380Nd dil ma maT IH NI 380Nd dial V THM THM lt INO Y3MOd 380Md dW3l THM IHR 32019 31000 B JINGOW 9 d3s M3MOd 9lJNOO 358 Y GNNOYD 9 A ma m8 EE ANNOY YILINOLIN VN NYO NO 100 YIMOd 3313 OL3NOVW E H L 100 Z Z SH THM UW THM SZ A 8 98 53 e V L NI 8 58 I THM S 8 3LON 335 B NOLIVNINM31 NVO sng lt IH Sn8 AN C NV OI SILON 335 c 5 A Poo NV OI SILON 335 l 310N 335 AN LL OL S3LON 33S LHM LH ES dau ALON 43S 0Z S0900 Z10 JINON 9SIJNOO Figure D 1 2 GDU 37X and GSU 73 Page D 3 Page D 4 blank G3X Installation Manual Interconnect Drawings 190 01115 01 Revision A APPENDIX E EXTERNAL INTERFACE DRAWING EXAMPLE ONLY NOTES 1 UNLESS OTHERWISE NOTED ALL STRANDED WIRE MUST CONFORM TO MIL W 22759 16 OR EQUIVALENT UNLESS OTHERWISE NOTED ALL SHIELDED WIRE MUST CONFORM TO MIL C 27500 OR EQUIVALENT UNLESS OTHERWISE NOTED ALL WIRES ARE 24 GAUGE MINIMUM SYMBOL DESIGNATIONS dr C TWISTED SHIELDED SINGLE CONDUCT
76. 95 24 1 eo 6X 0 30 7 6 0 i 0 063 1 60 e dg SR SN 5 Dm E XN o S5 8 uo Bo 8 qo x o no o LL RS oo oco x o a i AX xx x 0 688 17 48 0 344 8 74 2X 0 098 THRU CS K 20 172 X 100 90 203 DETAIL A 4 PLCS 52104713 NUTPLATE 4X FARSIDE B MS20426AD3 4 RIVET 8X NOTES 1 DIMENSIONS INCHES mm 2 MATERIAL 0 063 THICKNESS 2024 T3 ALUMINUM AMS QQ A 250 5 3 TOLERANCE 0 030 0 010 4 REMOVE BURRS AND BREAK SHARP EDGES 5 OPTIONAL GA55A ANTENNA INSTALLATION 8 MS21059L3 MAY BE USED IN PLACE OF MS21047L3 Figure 6 16 Doubler Design ARINC 743 Footprint Antenna Skin Thickness 0 051 to 0 063 Page 6 18 G3X Installation Manual Antennas Revision A 190 01115 01 FORWARD gt STRINGER AIRCRAFT p DOUBLER C TX o o o o o S BULKHEAD STRINGER VIEW LOOKING DOWN SKIN OMITTED FOR CLARITY A Figure 6 17 Sample Doubler Location ARINC 743 Antenna Metal Skin Aircraft 0 80 20 3 2X 1 60 40 6 0 65 16 5 0 0 0 2 HOLES 5 0707 4X 0 220 THRU SKIN gh UN TO MATCH DOUBLER 0 0 0 2 HOLES 0 625 THRU SKIN
77. A GARMIN G3X Installation Manual GARMIN DST ETE OIL PSI 76 CHT F _ 380 WPT BRG h MT a RPM MAN IN OIL F 196 FUEL E 1880 28 1 t WPT WX TER XM INFO ENG 190 01115 01 August 2009 Revision Copyright 2009 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 permission 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 151 Street Olathe KS 66062 USA 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 Description Date A 08 26 09 I
78. A 3 3 3 Magnetometer Power The GSU 73 outputs supply voltage to the GMU 44 via pins 38 amp 39 Pin Connect Pin Name P731 MAGNETOMETER POWER OUT s P731 MAGNETOMETER GROUND A 3 4 GSU System ID Program Pins 4 amp 5 must be left open floating for proper G3X configuration Pin Connector _ PinName_______ Wo P731 GSU SYSTEM ID PROGRAM 1 IN 5 P731 GSU SYSTEM ID PROGRAM 2 IN Indicates Active Low Page A 10 Installation Manual Pinouts Revision A 190 01115 01 A 3 5 Serial Data Electrical Characteristics A 3 5 1 ARINC 429 Input Output The ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers Connector Pin Name ARINC 429 OUT 1A ARINC 429 OUT 1B ARINC 429 OUT 2A ARINC 429 OUT 2B ARINC 429 IN 1A ARINC 429 IN 1B ARINC 429 IN 2A ARINC 429 IN 2B ARINC 429 IN 3A ARINC 429 IN 3B ARINC 429 IN 4A ARINC 429 IN 4B A 3 5 2 RS 232 Input Output The RS 232 outputs conform to Standard RS 232C with an output voltage swing of at least 5V when driving a standard RS 232 load Connector Pin Name MAGNETOMETER RS 232 OUT RS 232 IN 2 RS 232 OUT 2 RS 232 IN 3 RS 232 OUT 3 G3X Installation Manual Pinouts Page 11 190 01115 01 Revision A A 3 5 3 RS 485 Input The GSU 73 contains one channel of RS 485 serial data communications Pin
79. ATION should be connected to CAN BUS LO for the GDU that is located at the end of the bus farthest from the GSU 73 Pin Name Connector CAN BUS HI P3701 CAN BUS LO P3701 CAN BUS TERMINATION P3701 A 1 4 3 Configuration Module In multiple GDU 37X installations it is only necessary to connect a configuration module to PFD1 PinName CC Pin VO CONFIGMODULEGROUND P3701 49 A 1 5 Lighting The GDU 37X display and keys can be configured to track 28 VDC or 14 VDC lighting busses using these inputs PnName Connecor Pin VO 14V LIGHTING BUS HI P3701 43 In 28V LIGHTING BUS HI P3701 26 In G3X Installation Manual Pinouts Page A 3 190 01115 01 Revision A A 1 6 Audio A 1 6 1 Mono Audio Pin Name Connector Pin VO MONO AUDIO OUT HI P3701 1 Out MONO AUDIO OUT LO P3701 A 1 6 2 Stereo Audio Pin Name Connector STEREO AUDIO OUT LEFT STEREO AUDIO OUT LO STEREO AUDIO OUT RIGHT STEREO AUDIO OUT LO The left and right common pins pins 2 and 20 may be tied together or only one may be used It is not necessary to use both common pins Page A 4 G3X Installation Manual Pinouts Revision A 190 01115 01 2 GMU 44 21 P441 Connector Figure A 2 View of J441 Connector Looking at Rear of Unit SIGNAL GROUND 2 RS 485 OUT B 3 SIGNAL GROUND 4 RS 485 OUT A 5 SPARE POWER GROUND
80. Air Data Magnetic Calibration GPS or Magnetometer GPS or Air Data Magnetometer always required Engine Run Up GPS or Air Data GPS or Air Data Magnetometer always required Mounting Orientation Identification None Heading Offset Magnetometer Interference Test Table 8 3 lists the type of valid calibration data required to be output by each LRU for the Calibration Procedures listed in Table 8 2 Table 8 3 Configuration Mode GSU Page Status Boxes GPS 3D or 3D Differential GPS solution available Air Data True Airspeed TAS available NOTE A valid outside air temperature OAT measurement is required for TAS to be valid Magnetometer Measurement of local 3D magnetic field available The GSU Page status boxes referred to in Table 8 3 are shown in the following figure STATUS MAGNETOMETER AIR DATA GPS If removal and replacement of a GMU 44 unit is required after post installation calibration has been completed the GMU 44 mounting rack must not be moved If the mounting screws that secure the GSU 73 unit or the GMU 44 mounting rack are loosened for any reason a new post installation calibration procedure A B C and E plus D if required initially must be carried out before the aircraft can be returned to service Any GMU 44 removal and replacement requires repeating the magnetometer calibration and if applicable the heading offset compensation The addition removal or modif
81. Antennas Revision A 190 01115 01 External Non structural Installation Figure 6 30 is an example of an external non structural mounting of the antenna in a tube and fabric aircraft The antenna support bracket shown should be made of 2024 T3 Aluminum with a minimum material thickness 0 032 and maximum distance between airframe tubes of 36 The bracket is installed to the airframe under the fabric and the antenna is mounted externally to the bracket The generic installation of the Section 6 6 1 antenna is used with the antenna support bracket as the mounting surface Follow the applicable gasketing and sealant instructions in Section 6 4 2 Teardrop style or Section 6 5 2 ARINC 743 style 2 8 ARINC 743 FOOTPRINT ANTENNA AIRFRAME 36 in MAX DISTANCE _ ju 0 032 MIN THICKNESS BLIND RIVETS V ANTENNA SUPPORT BRACKET Figure 6 30 Example Non structural Antenna Mounting On Airframe Installation Manual Antennas Page 6 27 190 01115 01 Revision A Minimum Distance from Metal Tube Structure Requirements Figure 6 31 shows minimum distance from metal tube structure requirements for internal non structural mounting of the antenna Table 6 7 presents minimum distance requirements between the tube structure and the antenna for cases where the antenna sits underneath the fabric in a metal tube struc
82. B 2 4 Ref Description GPN or MIL Spec 1 Included in G3X Installation Kit K10 00017 00 Table 3 9 lists material in the GMU 44 connector kit and the associated reference number as shown in Figure C 2 4 The GMU 44 magnetometer has an attached pigtail with male polarity The harness connector for the GMU 44 has female polarity Table 3 9 GMU 44 Connector Kit 011 00871 00 Contents Reference Figure C 2 4 Garmin P N Quantity Figure C 2 4 Ref Screw 6 32x 250 PHP BR w Nyl 211 60037 08 Conn Circular Female 9 Ckt 330 00360 00 Backshell Circular Kit SS 330 90005 01 Cont Sckt Mil Crp Size 20 336 00022 00 Included in G3X Installation Kit K10 00017 00 G3X Installation Manual GMU 44 Page 3 5 190 01115 01 Revision A 3 8 Mounting Instructions After evaluation of the mounting location has been completed and ensuring that requirements are met assemble the GMU 44 mounting plate kits according to the dimensions given in Appendix C Install the unit assemblies Mount the GMU 44 to its mounting plate taking care to tighten the mounting screws firmly Use of non magnetic tools e g beryllium copper or titanium is recommended when installing or servicing the GMU 44 Do not use a screwdriver that contains a magnet when installing or servicing the GMU 44 The metal components in the GMU 44 s connector may slightly affect the magnetic field sensed by the GMU 44 Place the connector at least 2 in
83. Backshell Do not violate the guidelines presented in Step 8 regarding ring terminals 11 It is recommended to wrap the cable bundle with Silicone Fusion Tape item 11 GPN 249 00114 00 or a similar version at the point where the backshell clamp and cast housing will contact the cable bundle NOTE Choosing to use this tape is the discretion of the installer 12 Place the smooth side of the backshell clamp item 12 across the cable bundle and secure using the three screws item 13 Warning Placing the grooved side of the clamp across the cable bundle may risk damage to wires 13 Attach the cover item 14 to the backshell item 1 using the two screws item 15 G3X Installation Manual Appendix Page B 11 190 01115 01 Revision A B 3 3 Shield Termination Technique Method A 2 Daisy Chain In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal Figure B 8 All other restrictions and instructions for the shield termination technique set forth for Method A 1 are still applicable NOTE The maximum length of the combined braids should be approximately 4 inches WINDOW MAX gt WINDOW MIN emn 1 1 SS M u FLOAT MIN TO FLOAT MAX
84. E External Interface Drawing Example Only eene E 1 Page iv G3X Installation Manual Revision A 190 01115 01 LIST OF ILLUSTRATIONS FIGURE I L 1 a La ued te e aaa deca e aede Cea 1 2 Coaxial Cable Installation n u i au h unu us 21 GDU 37X Unt VIeW init ure uet pe eot e D ge 2 2 GDU 37X Mounting Accessories essent ener en rennen eren 3 1 GMU 4AL UMIT VIEW e et dete eed eere gen ides 21 90 V3 Umt VIew su oc Retenir PORE 4 2 GSU 73 Air Hose Fitting 5 4 3 GSU 73 Orientation Calibration Dad GTP 59 ise maban tena e e OR Ee Me 6 1 Recommended Antenna Placement esee nennen 6 2 Carbon Glass Buried Antenna 6 3 Glare Shield Buried Antenna Area n eene 6 4 Doubler Design Teardrop Footprint Antenna Skin Thickness 0 032 to 0 049 6 5 Doubler Design Teardrop Footprint Antenna Skin Thickness 0 049 to 0 051 6 6 Doubler Design Teardrop Footprint Antenna Skin Thickness 0 051 to 0 063 6 7 Sample Doubler Location Teardrop Footprint Antenna Metal Skin Aircraft 6 8 Skin Cutout Detail Teardrop Footprint Antenna Skin Thickness 0 032 to 0 049 6 9 Skin Cutout Detail Teardrop Footprint Antenna Skin Thickness 0 049 t
85. ED SHIELDED 4 CONDUCTOR GW SHIELD TERMINATED TO GROUND a FLOATS I N TWISTED SHIELDED PAIR N GARMIN SHIELD BLOCK GROUND SHIELD FLOATS N AIRCRAFT GROUND E TWISTED SHIELDED 3 CONDUCTOR Ld SHIELD TERMINATED TO GROUND E WIRE SPLICE CONNECTION gt N C COAXIAL CABLE _ TWISTED SHIELDED 3 CONDUCTOR SHIELD FLOATS NO CONNECTION UNLESS OTHERWISE NOTED ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE WIRE COLORS ARE NOTED FOR ADVISORY PURPOSES ONLY EXCEPT FOR THE CONFIG MODULE AND GTP 59 INSTALLATION INSTRUCTIONS FOR OAT PROBE GMU 44 GND HARNESS CONFIGURATION MODULES AND THERMOCOUPLES ARE PROVIDED IN THE G3X INSTALLATION MANUAL RESERVED OPTIONAL INTERFACE THE GDU 37X CAN BE CONFIGURED TO ACCEPT A 14V OR 28V LIGHTING BUS INPUT FOR DETAILS ON CONFIGURATION AND SETUP OF A LIGHTING CURVE SEE THE G3X INSTALLATION MANUAL ONLY ONE GDU 37X GPS ANTENNA CONNECTION IS REQUIRED FOR THE G3X SYSTEM ADDITIONAL ANTENNAS CAN BE ADDED SEE THE INSTALLATION MANUAL FOR DETAILS REGARDING GDU 37X GPS ANTENNA CONFIGURATION FOR REDUNDANCY IF DESIRED THE CAN BUS SHOULD ONLY BE TERMINATED AT ONE GDU 37X GDU 370 PFD OR MFD P3701 GDU 370 AIRCRAFT POWER 1 POWER GROUND SEE NOTE 10 AIRCRAFT POWER 2 POWER GROUND GPS ANTENNA GDU 375
86. ENGER WING FUEL REAR PASSENGER BAGGAGE EDIT STATION S NAME UNITS MAX ARM LOADING LIMITS MIN WEIGHT MAX WEIGHT MIN CG MAX CG 2 Use the FMS Joystick to select the desired configurable item and make the desired change then press the ENT Key or use the FMS Joystick to select the next item 3 To create a new station press the NEW softkey enter the name units max weight and arm then highlight DONE and press the ENT key 4 To edit or delete a station highlight the desired station then press the edit or delete softkey 5 Press the FMS Joystick to move the cursor to the page selection menu when finished Page 7 6 G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 7 4 4 UNITS Configuration Page The Units Configuration Page allows selection of the desired displayed units for the listed items in the Units Configuration window The various settings for Location Format Map Datum and Heading can be accessed in the Position Configuration window See the G3X Pilot s Guide for a description of Location Format and Map Datum 1 Inconfiguration mode use the FMS Joystick to select the UNITS Page CONFIG UNITS GSU ACFT W B 93 SOUN 2 Use the FMS Joystick to select the desired configurable item and make the desired change Then press the ENT Key or use the FMS Joystick to select the next item Press the FMS Joystick to move the cursor
87. Figure 6 11 are required G3X Installation Manual Antennas Page 6 7 190 01115 01 Revision A 6 4 2 Antenna Installation Instructions Refer to Table 6 5 and the drawings in Appendix C for guidance on selecting the appropriate mounting cutout Drill or punch the holes to match the mating part doubler Install a doubler plate to reinforce the aircraft skin as required Refer to Section 6 4 1 for doubler preparation and Table 6 5 for additional guidance on the doubler installation Dimple aircraft skin when the skin thickness is less than 0 051 for installation of flush head rivets Countersink aircraft skin when the skin thickness is between 0 051 and 0 063 for installation of flush head rivets For the stud mount teardrop footprint antenna place install gasket on top of aircraft skin using the four screw holes to align the gasket Washers and locking nuts are required to secure the antenna Torque the four 8 32 stainless steel locking nuts 12 15 in lbs Torque should be applied evenly across all mounting studs or screws to avoid deformation of the mounting area Ensure that the antenna base and aircraft skin are in continuous contact with the gasket or o ring as appropriate to the antenna model Seal the antenna and gasket to the fuselage using Dow Corning 738 Electrical Sealant or equivalent Run a bead of the sealant along the edge of the antenna where it meets the exterior aircraft skin Use caution to ensure th
88. Included in G3X LRU Kit K10 00016 00 Table 3 6 GMU 44 Accessories Hem GarminP N Quantity Sub Assy Connector Kit GMU 44 011 00871 00 GMU 44 Universal Mount 011 01779 01 1 optional Installation Rack GMU 44 115 00481 10 Included in Installation Kit K10 00017 00 Refer to Magnetometer Installation Considerations 190 01051 00 from www garmin com 3 6 Installation Considerations If the requirements listed in Table 3 7 cannot be met a magnetometer interference test must be performed to ensure proper operation of the G3X system Refer to the AHRS Magnetometer Installation Considerations document 190 01051 00 available from the Garmin website www garmin com The following guidelines describe proper mechanical installation of the Garmin GMU 44 Magnetometer The guidelines include requirements for proper location selection in the aircraft requirements for supporting structure and mechanical alignment and restriction on nearby equipment Fabrication of a wiring harness is required Sound mechanical and electrical methods and practices are required for installation of the GMU 44 Refer to Section 1 6 for wiring considerations and to Appendix A for pinouts The instructions needed to assemble the circular connector are located in Appendix B The GMU 44 is an extremely sensitive three axis magnetic sensor It is more sensitive to nearby magnetic disturbances than a flux gate magnetometer For t
89. LATION MANUAL FOR 5 232 INPUT OUTPUT CONFIGURATION GUIDANCE PROVISIONAL INTERCONNECT SHOWN TO SUPPORT FUTURE ENHANCEMENTS DETAILS ARE SUBJECT TO CHANGE REFERENCE SHEET 4 FOR MORE DETAILED INFORMATION ON CONNECTION OF THIRD PARTY AUTOPILOTS AIR DATA AND GPS INFORMATION OUTPUT TO THE TRANSPONDER OPTIONAL INTERFACE THE GMA 240 IS SHOWN HERE FOR REFERENCE ONLY OTHER INTERCOM AUDIO PANEL PRODUCTS MAY BE COMPATIBLE WITH THE GDU 37X THE ALERTS GENERATED BY THE GDU 37X CAN BE CONFIGURED TO TRANSMIT ON MONO AND STEREO AUDIO LINES OR MONO ONLY SEE THE G3X INSTALLATION MANUAL FOR ADDITIONAL DETAILS ON CONFIGURATION OF THE GDU 37X ALERT OUTPUT P3701 GDU 37X SEE NOTES 7 9 AND 11 AUTOPILOT TN RS 232 OUT 1 SIGNAL GROUND SIGNAL GROUND RS 232 IN GNS 430 530 1 P4001 P5001 RS 232 OUT 56 mE TEN RS 232 IN 2 BLU BLU SIGNAL GROUND N SL30 RS 232 OUT 5 mn RS 232 IN 2 SIGNAL GROUND H T T SIGNAL GROUND Rs 232 IN 4 we ORN RS 232 OUT 2 RS 232 IN CN WHT WHT 7 BLU Bul SIGNAL GROUND SIGNAL GROUND K lt ACK 04 406 MHZ ELT RS 232 IN eran SI RS 232 OUT 3 SIGNAL GROUND BLU BLU SIGNAL GROUND GTX 330 MODE S 65232 OUT 1 25 HMHI WHT cs RS 232 IN 3 51 _ BLU BLU SIGNAL GROUND LL y GMA 240 MUSIC 2 IN RIGHT STEREO AUDIO OUT RIGH MUSIC 2 IN LEFT STEREO AUDIO OUT LEFT SIGNAL GROUND MUSIC 2 IN LO CJ STEREO AUDIO OUT LO
90. LF LOCKING NUT AS REQUIRED TO COMPLY WITH APPLICABLE AIRWORTHINESS REGULATIONS lt FORWARD 4 70 119 4 FORWARD 21 1 2 37 60 2 me 4 23 107 4 1 91 48 5 T 2 59 65 8 m a 60 15 2 83 y 22 5 6 i i ING GONNEOTOR 50 12 7 AX 48 32 STUD BNC CONNECTOR SIDE VIEW FRONT VIEW E Tt lt ra m n 5 Ed C e I OS 122 ET D T 20 17 8 N S lt lt OY ue 3 00 76 2 O 2 0 r 1 _ 2x 1 625 41 28 a I F N ret ue 813 20 64 I NE ANTENNA OUTLINE 1 1 1 8 1 I m lt r3 _ r3 x i 1 Ehe d a 4X 188 4 78 S T 625 15 88 2 350 59 69 4 P x s be d uel z I N JE 2 2x 3 300 83 82 99 z 625 15 88 pa ax 220 5 59 1 1 L L ___ J 2 59 65 8 MOUNTING CUTOUT BACKING PLATE MOUNTING CUTOUT NOTH S OUTLINE ANTENNA OUTLINE 1 DIMENSIONS INCHES mm Figure C 5 1 GA 55 55A Installation Drawing G3X Installation Manual Outline amp Installation Drawings Page C 17 Page C 18 blank 190 01115 01 Revision A APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GA 56 STUD MOUNT 011 00134 00 co ANTENNA AVIATION lii GA 56 ED 253 00002
91. M Antenna 0 47 105 0 21 kg G3X Installation Manual Antennas Page 6 1 190 01115 01 Revision A Table 6 4 XM Satellite Radio Antenna Minimum Requirements Characteristics Specifications Frequency Range 2332 5 to 2345 MHz Gain Typical 24 dB 12 d8 Operating Temperature Gain For each 1 dB gain over 24 dB add 1 dB of attenuation into the antenna cable path between the antenna and the GDU 375 It is the installer s responsibility to ensure that their choice of antenna meets FAA standards according to the specific installation This installation manual discusses only the antennas listed in Tables 6 1 and 6 3 Other antennas may be acceptable but their installation is not covered by this manual There are several critical factors to take into consideration before installing an antenna for a satellite communications system These factors are addressed in the following sections 6 3 Antenna Mounting Considerations The information in this section does not pertain to in cabin internal mounted antennas such as the GA 26C refer to the accompanying installation instructions 190 00082 00 No special precautions need be taken to provide a bonding path between the GPS Antenna and the aircraft structure 6 3 1 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 GDU 3
92. OM 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 the unit 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 To obtain warranty service contact your local Garmin Authorized Service Center For assistance in locating a Service Center near you call Garmin Customer Service at one of the numbers shown below Products sold through online auctions are not eligible for rebates or other special offers from Garmin 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 Garmin International Inc Garmin Europe Ltd 1200 East 151 Street Liberty House Bulls Copse Road Olathe Kansas 66062 U S A Hounsdown Business Park Phone 913 397 8200 Romsey SO40 9RB U K FAX 913 397 0836 Phone 44 0 870 8501241 Phone 44 0 870 8501251 Page x G3X Installation Manual Revision A 190 01115 01 Limited Warranty for GSU 73 and GDU 37X Products The Garmin products GSU 73 and GDU 37X are warranted to be free from defects in materials or workmanship for one year
93. OMETER AIR DATA 5 Use the FMS Joystick to select AHRS ORIENTATION if not already selected AHRS ORIENTATION 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key 7 Determine the direction the connectors of the GSU 73 are facing per the on screen instructions 8 Use the FMS Joystick to highlight the Calibrate button at the bottom of the display press the ENT Key to begin the calibration SELECT CALIBRATE TO BEGIN CANCEL CALIBRATE Page 8 6 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 9 Use the FMS Joystick to select the direction of the GSU 73 connectors per the on screen instructions select OK and press the ENT Key to continue GSU73 CALIBRATION SELECT THE DIRECTION THE GSU73 CONNECTORS ARE FACING AFTER INSTALLATION FROM THE FOLLOWING LIST L imawas SELECT AHRS MOUNT ORIENTATION THEN SELECT OK 10 After a few minutes the calibration will finish and Done button will appear at the bottom of the display ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display press the ENT Key to return to the GSU Status Page CALIBRATION SUCCESSFUL Installation Manual Post Installation Checkout and Calibration Procedures Page 8 7 190 01115 01 Revision A 8 3 2 Calibration Procedure B Pitch Roll Offset Compensation by Aircraft Leveling 1 Enter
94. OR 7 TWISTED SHIELDED 4 CONDUCTOR 7 SHIELD TERMINATED TO GROUND SHIELD TERMINATED TO GROUND CN TWISTED SHIELDED SINGLE CONDUCTOR I V4 SHIELD FLOATS P EEN TWISTED SHIELDED PAIR TT TWISTED SHIELDED 4 CONDUCTOR SHIELD TERMINATED TO GROUND p SHIELD FLOATS wx mr 35 s p IWITED SHIELDED PAIR NZ GARMIN SHIELD BLOCK GROUND SHIELD FLOATS AIRCRAFT GROUND L1 TWISTED SHIELDED 3 CONDUCTOR SHIELD TERMINATED TO GROUND WIRE SPLICE CONNECTION N COAXIAL CABLE L1 TWISTED SHIELDED 3 CONDUCTOR HIELD FLOAT HAL N C NO CONNECTION UNLESS OTHERWISE NOTED ALL SHIELD GROUNDS MUST BE MADE TO THE RESPECTIVE UNIT BACKSHELLS ALL OTHER GROUNDS SHOULD BE TERMINATED TO AIRCRAFT GROUND AS CLOSE TO THE RESPECTIVE UNIT AS POSSIBLE RESERVED AT THIS TIME THE RS 232 INTERFACE FROM GNS 400 500 SERIES SUPPORTS FLIGHT PLAN DATA TRANSFER TRANSFER OF HSI INFO FROM AN EXTERNAL NAV SOURCE WILL BE SUPPORTED VIA PROVISIONAL WIRING AND FUTURE SOFTWARE UPDATES GDU 37 RS 232 OUTPUTS SHOWN HERE ALLOW FREQUENCIES TO BE TRANSFERRED FROM THE GDU 37X TO THE CONNECTED NAV COM OR NMEA DATA TO BE PASSED TO A SERIAL AUTOPILOT OR ELT DEVICE 5 232 INPUT OUTPUT LINES CAN ONLY BE CONNECTED TO ONE DEVICE A TIME RS 232 CHANNEL ASSIGNMENTS ARE SHOWN FOR REFERENCE ONLY CONNECTIONS CAN BE REASSIGNED TO DIFFERENT CHANNELS OR TO CHANNELS ON AN OPTIONAL SECOND OR THIRD DISPLAY SEE THE G3X INSTAL
95. PENDIX C OUTLINE AND INSTALLATION DRAWINGS 4 214 3 8 1 AIRCRAFT MOUNTING SURFACE 1 84 46 61 2 E G3X Installation Manual Outline amp Installation Drawings 190 01115 01 2 10 53 3 GMU 44 INSTALLATION FROM ABOVE PREFERRED AIRCRAFT MOUNTING RACK 6 32 PAN HEAD BRASS SCREWS 0 24 6 1 MAX THREAD LENGTH WITHOUT CLEARANCE HOLES 6 32 100 FLAT HEAD BRASS SCREWS REQUIRED NOTES 1 DIMENSIONS IN INCHES mm Figure C 2 2 GMU 44 Top Mounted Installation Page C 7 Page C 8 blank Revision A APPENDIX C OUTLINE AND INSTALLATION DRAWINGS GMU 44 INSTALLATION FROM BELOW NOT PREFERRED AIRCRAFT MOUNTING RACK AIRCRAFT MOUNTING SURFACE 8 4 214 3 370 85 60 gt AA I f 6 32 HEAD BRASS SCREWS 3 8 aE KAJ 0 24 6 1 MAX THREAD LENGTH i WITHOUT CLEARANCE HOLES 2 23 56 52 No A 2 38 60 33 G3X Installation Manual Outline amp Installation Drawings 190 01115 01 NOTES 1 DIMENSIONS IN INCHES mm 6 32 100 FLAT HEAD BRASS SCREWS REQUIRED Figure C 2 3 GMU 44 Bottom Mounted Installation Page C 9 Page C 10 blank
96. Positioner M22520 2 08 Daniels K13 1 GSU 73 011 00979 20 Config module w EEPROM kit 011 00981 00 thermocouple kit Pin Mil Crimp Size 22D 336 00021 00 Positronic P N 9502 4 ITT P N M22520 2 09 Daniels P N K42 GMU 44 Socket Mil Crimp Size 20 336 00022 00 M22520 2 08 Daniels K13 1 011 00979 22 Config module w Sockets amp Jackscrew kit Socket Mil Crimp Size 20 26 30 AWG 336 00022 01 Positronic P N 9502 5 1 Insertion Extraction tools from ITT Cannon are all plastic others are plastic with metal tip Recommended Insertion Extraction Tool M81969 1 04 for size 22D pins and M81969 1 02 for size 20 pins Recommended Hand Crimping Tool M22520 2 01 2 Non Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice Page 1 6 Revision A G3X Installation Manual Installation Overview 190 01115 01 1 7 2 Cable Location Considerations Use cable meeting the applicable aviation regulation for the interconnect wiring Any cable meeting specifications is acceptable for the installation When routing cables observe the following precautions e All cable routing should be kept as short and as direct as possible e Check that there is ample space for the cabling and mating connectors e Avoid sharp bends in cabling e Avoid routing near aircraft control cables e Avoid routi
97. Repeat steps 1 through 7 as needed for the remaining shielded cables Page B 26 G3X Installation Manual Appendix B Revision A 190 01115 01 8 Terminate the ring terminals to the circular backshell item 3 by placing items on the provided pan head screw in the following order flat washer provided with circular backshell first ring terminal second ring terminal third ring terminal if needed before finally inserting the screw into the grounding hole on the circular backshell and securing with the provided locking nut Do not violate the guidelines presented in step 7 regarding ring terminals B 4 5 Daisy Chain Quick Term Shield Termination Method B In situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal Figure B 20 other restrictions and instructions for the shield termination technique set forth for Method 1 are still applicable NOTE The maximum length of the combined braids should be approximately 4 inches 6 PES O gt SSS FO Ire SS i Ly A O F QUICK TERM MIN TO QUICK TERM MAX l4 V C E ERN jes J J wi pt 0 17 INCHES NE INCHES MAX FOR REF ONLY 5 SEE FIGURE 2 2 x Figure B 20 Da
98. Revision A APPENDIX C OUTLINE AND INSTALLATION DRAWINGS NOTE 1 BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLES 3 6AND 3 7 7 N N uA dm Figure C 2 4 GMU 44 Wiring Detail G3X Installation Manual Outline amp Installation Drawings Page C 11 Page C 12 blank 190 01115 01 Revision A APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 2X 5 00 127 0 2 8 71 m 40 10 2 2X 25 6 4 4 25 108 0 4 50 114 3 4X 210 5 33 SEE NOTE 3 IH 4 46 113 2 PITOTAIR FITTING 1 1 8 27 ANPT FEMALE THREAD pS P732 p 1 96 49 8 P731 STATIC AIRFTIING Ki 1 8 27 ANPT FEMALE THREAD 3 96 100 6 87 22 1 2X 1 17 29 7 5 50 139 7 NOTES 1 DIMENSIONS INC HES mm 2 DIM ENSIO NS ARE SHOWN FOR REFERENC E ONLY 3 MOUNTING HO LES FOR 10 PAN HEAD OR HEX HEAD FASIENERS 4 CENTER OF GRAVITY LOCATION INCLUDES UNIT WITH CONNECTOR KITS G3X Installation Manual Outline amp Installation Drawings 190 01115 01 CONFIGURATION MODULE KIT THERMOCOUPLE KIT P732 CONNECTOR KIT 011 01818 01 NOT SHOWN 011 00979 20 NOTSHOWN 011 00981 00 GSU 73 UNIT P731 CONNECTOR KIT 011 01817 00 011 01818 00 1 8 46 1 45 36 7
99. S Pitch Bank Limitations for Cold Start While Airborne Sensor Inputs Available and Valid 1 Mode of Operation Entered All Air Data Bank Limit Pitch Limit Following Initialization Inertials internal in Degrees in Degrees Reversion No GPS Reversion No Mag 5 0 Reversion No Mag No Air 50 G3X Installation Manual Troubleshooting Page 9 3 190 01115 01 Revision A 9 3 1 Attitude Heading Failure Troubleshooting Prior to troubleshooting an Attitude Failure on board the aircraft gather information from the pilot by asking the following questions 1 9 What specifically was the nature of the failure Was it a Red X of only heading only pitch roll or both If there was a Red X of pitch or roll information did the PFD display the AHRS Align Keep Wings Level message which is indicative of an AHRS reset or the Attitude Fail message which is indicative of either AHRS invalidating its output or a communication path failure What exactly was the aircraft doing in the two minutes that preceded the failure taxing on the ground flying straight and level flight turning climbing etc If the problem occurred on the ground was it within 100 feet of a hanger using GPS repeaters How long did the failure last Was it brief or sustained Was it repetitive in nature If it was repetitive about how many times did it happen Did it happen on more than one day Was the problem correlated with a specific man
100. TE TO BEGIN m CANCEL CALIBRATE 9 After a few minutes the calibration will finish and a Done button will appear at the bottom of the display ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display press the ENT Key to return to the GSU Status Page CALIBRATION SUCCESSFUL G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 9 190 01115 01 Revision A 8 3 3 Calibration Procedure Magnetometer Calibration Calibration Procedure must successfully completed prior to Calibration Procedure C Calibration Procedure C must be carried out at a location that is determined to be free of magnetic disturbances such as a compass rose Attempting to carry out this maneuver on a typical ramp area will not yield a successful calibration The accuracy of the AHRS cannot be guaranteed if this calibration is not performed at a magnetically clean location A method for evaluating the magnetic disturbances at a candidate site is described in Section 8 3 7 Taxi the aircraft to a site that has been determined to be free of magnetic disturbances Ensure that there are no nearby magnetic materials on or near the perimeter of the site If unavoidable maneuver the aircraft to keep 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
101. U 44 Table 3 4 TSO ETSO Deviations Deviation TSO C6d 1 Garmin was granted a deviation from TSO C6d to use RTCA DO 160D instead of RTCA GMU 44 DO 160B as the standard for Environmental Conditions and Test Procedures for Airborne Equipment 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 Manual rather than on the article itself 5 Garmin was granted a deviation from TSO C6d to list the DO 178B software level in the Installation Manual rather than on the article itself ETSO C6d 1 Garmin was granted a deviation from ETSO C6d to use RTCA DO 160D instead of SAE GMU 44 AS 8013 as the standard for Environmental Conditions and Test Procedures for Airborne Equipment 2 Garmin was granted a deviation from ETSO C6d to use SAE AS 8013A instead of SAE AS 8013 as the Minimum Performance Standard Page 3 2 G3X Installation Manual GMU 44 Revision A 190 01115 01 3 5 Installation Requirements 3 5 1 Equipment Available Table 3 5 GMU 44 Part Numbers Catalog Part Unit Part Number Installation Rack Number GMU 44 010 00296 10 011 00870 10 No
102. V and 10 Max Brightness Voltage and Percentage Sets the upper bus voltage required to turn the backlighting on to the percentage of brightness set by the Max setting Default values are 12 0V and 100 Input Type Sets the aircraft lighting bus voltage for either 12 or 24V input to match the aircraft lighting bus voltage Time Constant Adjusts the speed in seconds that the brightness level responds to changes in the input voltage level G3X Installation Manual Software Configuration Databases and XM Activation Page 7 9 190 01115 01 Revision A 7 4 6 SOUND Configuration Page The SOUND Configuration Page allows setting the parameters for various alert and message tones 1 Inconfiguration mode use the FMS Joystick to select the SOUND Page a CONFIG SOUND ACFT W B UNITS DSPL COMM 2 Use the FMS Joystick to select the desired configurable item and make the desired change Then press the ENT Key or use the FMS Joystick to select the next item Press the FMS Joystick to move the cursor to the page selection menu when finished SOUND CONFIGURATION ALERT VOLUME MESSAGE TONES TERRAIN AUDIO TIS AUDIO ALERT OUTPUT The configuration options for the SOUND Configuration Page are listed described as follows Alert Volume Controls the volume level of audio alerts settings 1 10 Message Tones Controls the volume level of message tones settings 1 10 Terrain Audio Enables disables terrain awarenes
103. X Interconnect Example Page 1 2 G3X Installation Manual Installation Overview Revision A 190 01115 01 1 4 General G3X LRU Specifications 1 4 4 Garmin LRU Part Numbers Table 1 1 G3X LRU Part Numbers GDU 370 Americas DB Unit Only Part Number 011 01747 15 Assembly Part Number 010 00667 15 GDU 370 Atlantic DB 011 01747 20 010 00667 20 GDU 370 Pacific DB 011 01747 35 010 00667 35 GDU 375 Americas DB 011 01747 30 010 00667 25 GMU 44 011 00870 10 010 00296 10 GSU 73 011 01817 00 010 0069 1 00 GTP 59 011 00978 00 Included in G3X LRU Kit 10 00016 00 NA Table 1 2 Contents of GDU 37X Assembly 010 00667 XX GDU 37X Garmin P N 011 01747 XX Quantity GDU 37X Connector Kit 011 01921 00 GDU 37X Nutplate 115 01054 00 SD Card Dummy 145 00561 00 Important Safety and Product Information 190 00720 50 GDU 37X Quick Reference Guide 190 01055 00 Jeppesen Free Single Update 190 10003 03 1 4 2 Power Specifications All LRUs are capable of operating at either 14 or 28 VDC Table 1 3 lists current draw specifications Table 1 3 G3X LRU Power Requirements GDU 37X Supply Voltage 10 29 Current Draw 1 10 Amp 14Vdc 0 55 Amp 28Vdc GMU 44 12Vdc from GSU 73 Inc in GSU Current Draw GSU 73 10 29 Vdc 1 75 Amp 14Vdc Max 0 80 Amp 28Vdc Max
104. YCLE 0872 AmeRIcas AOPA DB CYCLE 0901 BASEMAP VERSION 2 00 GPS SW VERSION CONFIG MAIN GSU ACFT W B UNITS DSPL SOUNI Page 7 4 G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 7 4 2 Configuration Page The Aircraft Configuration Page allows setting the parameters for Flight Planning Aircraft Identifier and Map Symbol The aircraft s cruise speed fuel flow aircraft identifier and map symbol can be entered on this page The flight planning fields let you adjust the default values cruise speed and fuel flow used for flight planning calculations Aircraft Identifier The aircraft identifier can be entered using FMS Joystick Map Symbol The aircraft symbol that is displayed on the Map page can be selected 1 Inconfiguration mode use the FMS Joystick to select the ACFT Page CONFIG ACFT MAIN GSU WZB UNITS DSPL SOUN 2 Usethe FMS Joystick to select the desired configurable item and make the desired change Then press the ENT Key or use the FMS Joystick to select the next item Press the FMS Joystick to move the cursor to the page selection menu when finished FLIGHT PLANNING CRUISE SPEED FUEL FLOW AIRCRAFT IDENTIFIER MAP SYMBOL G3X Installation Manual Software Configuration Databases and XM Activation Page 7 5 190 01115 01 Revision A 7 4 3 W B Weight Balance Configuration Page The W B Configuration Pa
105. able 1 Power on unit and use the FMS Joystick to select the XM Page XM AUDIO PAGE WPT WX TER 1 INFO INFO CATEGORY CHANNEL FAVORITE VOLUME 2 Verify that the XM receiver is functioning correctly as indicated by the green signal strength bars See Section 8 6 for XM Activation Instructions if needed NOW PLAYING S G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 3 190 01115 01 Revision A 83 GSU 73 GMU 44 Post Installation Calibration Procedures After mechanical and electrical installation of the GSU 73 AHRS and GMU 44 magnetometer have been completed prior to operation a set of post installation calibration procedures must be carried out Table 8 1 describes the necessary calibration procedures Table 8 1 Post Installation Calibration Procedure Summary Calibration Procedure Procedure Name AHRS Orientation Procedure Description Validate GSU 73 Orientation Installations Requiring Procedure Procedure A is required for all installations Pitch Roll Offset Compensation Level Aircraft Procedure B is required for all installations Magnetometer Calibration Compass Rose Taxi Maneuver Procedure C is required for all installations Heading Offset Compensation Compass Rose Alignment with Magnetic North Installations in which GMU 44 alignment is not within 0 5 of aircraft longitudinal axis
106. age are listed described as follows Garmin Data Transfer The proprietary format used to exchange data with a PC NMEA Out Supports the output of standard NMEA 0183 version 3 01 data at a baud rate of 4800 Aviation In The proprietary format used for input to the G3X baud rate of 9600 from an FAA certified Garmin panel mount unit Allows the G3X to display a Go To or route selected on the panel mount unit which eliminates the need to enter the destination on both units Aviation In NMEA amp VHF Out Receives aviation data and transmits out both NMEA data at 9600 baud and VHF frequency tuning information to a Garmin Nav Comm radio TIS In Receives TIS data from a Garmin Mode S transponder TIS In NMEA amp VHF Out Receives TIS data and transmits out both NMEA data at 9600 baud and VHF frequency tuning information to a Garmin Nav Comm radio SL30 Nav Comm RS 232 format Outputs frequency tuning and course selection data to an SL30 and receives VOR ILS signals to be displayed on the PFD G3X Installation Manual Software Configuration Databases and XM Activation Page 7 11 190 01115 01 Revision A 7 5 Garmin Database Updates The GDU 37X database updates can be obtained by visiting the flyGarmin website www fly garmin com The flyGarmin website requires the unit s System ID to update databases this allows the databases to be encrypted with the unit s unique System ID when copied to t
107. al inputs are low when the signal is lt 2 Vdc or the resistance to ground is lt 375 and high when the signal is gt 3 5 Vdc or the resistance to ground is gt 100 k Q Digital inputs can also be configured as discrete inputs Connector Pin Name FREQUENCY COUNTER IN 1 FREQUENCY COUNTER IN 2 FREQUENCY COUNTER IN 3 FREQUENCY COUNTER IN 4 Indicates Active Low G3X Installation Manual Pinouts Page 15 190 01115 01 Revision A The following table lists the minimum frequency maximum frequency and duty cycles for each of these inputs Pin Name Minimum Frequency Maximum Frequency FREQUENCY COUNTER IN 1 500 Hz 100 KHz FREQUENCY COUNTER IN 2 500 Hz 100 KHz FREQUENCY COUNTER IN 3 500 Hz 100 KHz FREQUENCY COUNTER IN 4 500 Hz 100 KHz Each frequency counter channel will be configured for a high or low speed input based on the signal being measured A 3 10 Fuel Select Outputs Pin Connector PinName WO 76 P732 RESERVED FUEL SENSOR PULL UP 2 ANALOG IN 15 OUT 77 P732 RESERVED FUEL SENSOR PULL UP 1 ANALOG IN 14 OUT Page A 16 G3X Installation Manual Pinouts Revision A 190 01115 01 APPENDIX B Connector Installation Instructions B 1 Thermocouple Installation into a Backshell Table B 1 lists parts needed to install a Thermocouple Parts for this installation are included in Thermocouple Kit 011 00981 00
108. ame 28 Analog inputs including those allocated as per below Dedicated Ammeters 2 Constant Current Source Capability 6 Divider Circuits to handle large input voltages 12 Frequency Counter Inputs 4 Discrete I O 4 In 2 Out Table 4 1 GSU 73 Supply Specifications Characteristic Specification Input Voltage Range 10 29 Power Input 1 75 Amp 14 Vdc Max 0 80 Amp 28 Vdc Max Garmin recommends using a Mod GSU 73 in aircraft that exclusively use 28V supply Page 4 2 Revision A G3X Installation Manual GSU 73 190 01115 01 4 33 Environmental Specifications The GSU 73 is non TSO d product Table 4 2 lists general environmental specifications The GSU 73 may require a warm up period of 15 minutes to reach full accuracy 30 minutes if the environmental temperature is less than 0 C Table 4 2 GSU 73 Environmental Specifications Characteristic Specification Aircraft Pressure Altitude Range 1 400 feet to 50 000 Feet Aircraft Vertical Speed Range 20 000 feet per minute to 20 000 feet per minute Aircraft Airspeed Range 450 Knots Aircraft Mach Range lt 1 00 Mach Aircraft Total Air Temperature Range 85 C to 85 C Unit Operating Temperature Range 40 C to 70 C Max Outer Case Temperature 73 C 4 4 Installation Requirements 4 4 4 Required Equipment Table 4 3 lists the kits available for the GSU 73 Table 4 3 GSU 7
109. as the electrical load increases Ifa temperature probe shorts usually where the bayonet is crimped a ground loop is created forcing the reference low side to increase which causes the temperature reading to decrease Does the EGT temperature slowly drift up and eventually flag This is an indication of an electrical open in the temperature probe or wiring Is the air data information on the PFD intermittently Red X ing If the GSU 73 5VDC transducer power supply is shorted to ground it will cause an intermittent air data Red X issue to occur If the AMP indication Red X d check the Alternator Shunt for correct resistance Refer to the applicable aircraft manual 10 If the Trim Indication is Red X d check the Elevator Trim Pot Sensor and wiring Page 9 8 Installation Manual Troubleshooting Revision A 190 01115 01 ENG HRS 3 8 ENGINE PAGE PFD MAP WPT WX TER XM INFO Figure 9 7 Attitude Heading Air Data and Engine Airframe Failure Reversionary or Split Screen PFD G3X Installation Manual Troubleshooting Page 9 9 190 01115 01 Revision A 9 5 Troubleshooting On board the Aircraft 1 Review the airframe logbook to verify if any G3X or other avionics or electrical maintenance had been performed recently that may have contributed to the failure Check for loose wire terminals on the circuit breaker connections on the power wire s causing intermittent power connections Also check for
110. ashers and nuts and doubler plate should make contact with an unpainted grounded surface ensuring proper antenna grounding Itis important to have good conductivity between the coaxial shield and the ground plane The bottom of the antenna does not need to make contact with the ground plane i e the surface may be painted The antenna will capacitively couple to the ground plane beneath the paint or aircraft cover Page 6 6 G3X Installation Manual Antennas Revision A 190 01115 01 6 4 Teardrop Footprint Antenna Installation GA 55 and GA 56 This section describes the structural mounting of the teardrop footprint antenna installation An acceptable installation method is to use Garmin P N 115 00846 10 doubler plate with the GA 55 or GA 56 stud mount antennas Another acceptable method is to fabricate and install one of three doublers Figure 6 4 Figure 6 5 and Figure 6 6 depending on the thickness of the skin The three doubler designs vary only by number of rivets and hole preparation for installation with flush rivets Table 6 5 provides a summary of design and installation details for selecting the appropriate antenna doubler backplate Figure 6 7 shows an example of the doubler installed between stringers on the top fuselage skin just off centerline The location should be flat with no gaps between the skin and doubler to keep from deforming the skin during installation Table 6 5 Teardrop Footprint Antenna Doubler Design
111. at the antenna connectors are not contaminated with sealant 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 Page 6 8 G3X Installation Manual Antennas Revision A 190 01115 01 6 4 3 Reference Figures FORWARD gt 12X 0 128 CS K 20 225 x 100 20 625 AX R0 25 3 00 76 2 d 6X 2 70 68 6 d 2 2 31 58 7 2X 1 90 48 3 1 50 38 1 2X 1 10 27 9 2X 0 69 17 5 6X 0 30 7 6 0 U m a 0 063 1 60 a Y e o gt o nr e 10 won eas ea N N 09 x N A c c 8 x x N NOTES 1 DIMENSIONS INCHES 2 MATERIAL 0 063 THICKNESS 2024 T3 ALUMINUM AMS QQ A 250 5 3 TOLERANCE 0 030 0 010 4 REMOVE BURRS AND BREAK SHARP EDGES Figure 6 4 Doubler Design Teardrop Footprint Antenna Skin Thickness 0 032 to 0 049 FORWARD gt 16X 0 128 CS K 0 225 x 100 0 625 4X R0 25 3 00 76 2 4 6X 2 70 68 6 af 9 2 2 31 58 7 2X 1 90 48 3 e 1 50138 S 4X 00 188 2X 1 10 27 9 2X 0 69 17 5 e 6X 0 30 7 6 Q 0 U 0 063
112. ated wire 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 7 3 Insert newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams 4 Atthe end opposite the pin on the 22 AWG insulated wire strip back 0 2 inches of insulation Terminate this end via the ring terminals with the other Flat Braid per Steps 8 and 11 pertaining to shield termination If this ground strap is only wire to terminate attach a Ring terminal 8 insulated 18 22 AWG MS25036 149 G3X Installation Manual Appendix B Page B 17 190 01115 01 Revision A B 3 10 Splicing Signal Wires NOTES Figure B 14 illustrates that a splice must be made within a 3 inch window from outside the edge of clamp to the end of the 3 inch max mark WARNING Keep the splice out of the backshell for pin extraction and outside of the strain relief to avoid preloading Figure B 14 shows a two wire splice but a maximum of three wires can be spliced If a third wire is spliced it is located out front of splice along with signal wire going to pin Splice part numbers Raychem D 436 36 37 38 MIL Spec MIL S 81824 1 This technique may be used with shield termination methods A 1 A
113. ave clear view of the sky or a GPS repeater to produce positive status indications CONFIG MODE MAGNETOMETER AIR DATA GPS 5 Use the FMS Joystick to select ENGINE RUN UP TEST 65073 CALIBRATION CALIBRATE 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key 65073 CALIBRATION ENGINE RUN UP TEST G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 17 190 01115 01 Revision A 7 Ensure that the aircraft has been properly positioned per the on screen instructions f GSU73 CALIBRATION A ENGINE RUN UP TEST 8 Use the FMS Joystick to highlight the Calibrate button at the bottom of the display press the ENT Key to begin the calibration _ ANCEL 9 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 If failures are indicated the engine run up test may be repeated up to three times If the test does not pass after three attempts the installation should be considered unreliable until the source of the vibration problem is identified and remedied If the engine run up test fails repeatedly record the values that are reported to be out of range for future reference The following are potential causes for failure of the engine run up test a Excessive flexibility of GSU 73 and or GMU 44 mechanical mounting wit
114. be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal Figure B 10 All other restrictions and instructions for the shield termination technique set forth for Method B 1 are still applicable NOTE The maximum length of the combined braids should be approximately 4 inches an 4 3 N xJ 7 A A TS Me En gt lt gt l b t 17 7 V J 4 QUICK TERM MIN TO QUICK TERM MAX jo D Ludo N m IE n hr i TT s 0 17 INCHES w 0 35 INCHES MAX FOR REF ONLY SEE FIGURE 2 2 nd Figure B 10 Method B 2 Daisy Chain Quick Term for Shield Termination Page B 14 Revision A G3X Installation Manual Appendix B 190 01115 01 B 3 6 Daisy Chain between Methods A and B In rare situations where more braids need to be terminated for a connector than three per ring terminal and a mixture of Methods A and B have been used it is allowable to daisy chain a maximum of two shields together from a Method A termination to a Method B Figure B 11 All other restrictions and instructions for the shield termination technique set forth for Method A an
115. ches from the body of the GMU 44 to minimize this effect After attaching the GMU 44 s connector to its mate in the aircraft wiring secure the connector in place using good installation practices This will ensure that any remaining magnetic effect can be compensated for using Calibration Procedure C Magnetometer Calibration Section 9 3 3 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 9 Maintenance Maintenance of the GMU 44 is on condition only Periodic maintenance of the GMU 44 is not required Page 3 6 G3X Installation Manual GMU 44 Revision A 190 01115 01 4 GSU 73 41 Equipment Description There is no TSO ETSO applicable to the GSU 73 The GSU 73 is intended for the LSA light sport aircraft and experimental aircraft markets The Garmin GSU 73 Sensor Unit is not a TSO certified product and has received no FAA approval or endorsement The GSU 73 is intended to be used as a part of the G3X system and it is not suitable for installation in type certificated aircraft The GSU 73 is an LRU that provides AHRS and Air Data information as well as an interface to Engine Airframe sensors in a single mechanical pa
116. ckage The GSU 73 interfaces to a remote mounted GMU 44 for heading information and also computes OAT and TAS from inputs provided by the GTP 59 The GSU 73 is capable of maneuvers through a range of 360 in bank and pitch The rotation rate capability is 200 per second Bank error and pitch error are within 1 25 over the range of 30 bank left and right and 15 pitch nose up and nose down Heading is accurate to within 2 in straight and level flight Due to unsuitability of the magnetic fields near the Earth s poles operational accuracy is unknown north of 70 North latitude and south of 70 South latitude In addition operational accuracy is unknown in the following two regions 1 North of 65 North latitude between longitude 75 W and 120 W Northern Canada 2 South of 55 South latitude between longitude 120 E and 165 E Region south of Australia and New Zealand Figure 4 1 GSU 73 Unit View G3X Installation Manual GSU 73 Page 4 1 190 01115 01 Revision A 4 1 1 Features Summary Air Data Pressure Altitude Density Altitude Vertical Speed Mach Number Indicated Airspeed True Airspeed AHRS Magnetic Heading Pitch Angle Roll Angle Linear Accelerations Pitch Roll Yaw Rotation Rates 4 2 Electrical Specifications Interfaces CAN 1 RS 232 2 2 RX ARINC 429 4 RX 2 TX OAT Probe GTP 59 Magnetometer GMU 44 1 RS 232 TX 1 RS 485 RX Engine Airfr
117. configuration mode by holding down the left hand softkey while powering on the GDU 37X if needed 2 Usethe FMS Joystick to select the GSU Page if needed CONFIG GSU 3 Unlock the GSU Page pressing softkeys 2 3 4 in order if needed 4 Ensure that all the required status boxes are checked Tables 8 2 and 8 3 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view of the sky or a GPS repeater to produce positive status indications 5 I CoNFIG MODE MAGNETOMETER AIR DATA GPS 5 Use the FMS Joystick to select PITCH ROLL OFFSET 4 PITCH ROLL OFFSET amu oa c nd CALIBRATE 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key LS EI PITCH ROLL OFFSET CALIBRATE Page 8 8 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 7 Ensure that the aircraft has been properly leveled per the on screen instructions GSU73 CALIBRATION FOR CALIBRATION THE OPERATOR MUST VERIFY THAT EACH OF THE FOLLOWING STATEMENTS IS TRUE 1 THE AIRCRAFT PITCH IS LEVEL 2 THE AIRCRAFT ROLL IS LEVEL 3 THE AIRCRAFT IS MOTIONLESS SELECT CALIBRATE TO ACKNOWLEDGE THE CALIBRATION STATUS WILL THEN BE DISPLAYED 8 Use the FMS Joystick to highlight the Calibrate button at the bottom of the display press the ENT Key to begin the calibration SELECT CALIBRA
118. correct software version Section 7 2 is required If the correct software version is not installed load the GMU 44 software contained in the G3X system software which is loaded to the displays Section 7 Following a successful magnetometer calibration and software verification the Return to Service Procedure is complete Page 10 2 G3X Installation Manual Return to Service Revision A 190 01115 01 APPENDIX A G3X Pinouts A 1 GDU 37X A 1 1 P3701 Connector PIN1 17 000000000000000 k gt N NS ANE E pu NIA ET a Los 18 PIN AA PIN 34 PIN 50 Figure A 1 View of J3701 Connector from Back of Unit Pin PinNam WO i 2 STEREO AUDIO OUTLO doo 4 SPARE SPARE SPARE CDU SYSTEM ID PROGRAM 2 In 1 6 8 9 11 RESERVED FOR FUTURE DEVELOPMENT DO NOT USE Out 15 POWERGROUD L j Out 18 MONOAUDIOOUTIO Out 20 STEREOAUDIOOUTLO j 27 SIGNALGROUND 0 Out In In Indicates Active Low G3X Installation Manual Pinouts Page A 1 190 01115 01 Revision A Pin PinName c rc c c r WO j 34 SIGNALGROUND 35 SIGNALGROUND 36 SIGNAL GROUND 0 37 SIGNALGROUND 0 44 SIGNALGROUND 49 CONFIGMODULEGROUND
119. d B are still applicable NOTE The maximum length of the combined braids should be approximately 4 inches WINDOW T lt 0 35 INCHES MAX CSS gt 7 gt M dd LL c I CI fr N A T a LOAT MIN TO FLOA 7 sock An a La INCHES 0 75 INCHES MN 0 35 INCHES MAX FOR REF ONLY SEE FIGURE 2 2 Figure B 11 Daisy Chain between Methods A and B G3X Installation Manual Appendix B Page B 15 190 01115 01 Revision A B 3 7 Double Shield Termination Technique Method C 1 In rare situations where double shielding may be necessary the outer shield should be grounded at both ends while the inner shield should be grounded only at one end All other restrictions set forth for in Table B 8 are applicable NOTE The maximum length of the braids should be approximately 4 inches p 7 BRAIDS NO LONGER THAN 4 INCHES 4 226 0 17 INCHES T 7 2 I FOR REF ONLY 4 SEE FIGURE 2 2 P 2 7 0 75 INCHES MIN F It FLOAT MIN TO FLOAT MAX WINDOW MIN WINDOW MAX Figure B 12 Method C 1 Double Shield Termination Table B 8 Shielded Cable Preparations for Garmin Connectors Backshell Size Number of Pins Std HD Float Min inches Float Max inches Ideal Float inches Wind
120. d for use with solder sleeves It may prove beneficial to use a solder sleeve with a pre installed flat braid versus having to cut a length of flat braid to be used The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the flat braid item 6 to be attached NOTE Reference Section B 3 2 for recommended solder sleeves and heating tools The same recommendations are applicable to this technique Secondary Method Solder a flat braid item 6 to the folded back shield on the prepared cable assembly item 4 Ensure a solid electrical connection through the use of acceptable soldering practices Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire Slide a minimum of 0 75 inches of Teflon heat shrinkable tubing item 5 onto the prepared wire assembly and shrink using a heat gun The chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable as well as the flat braid item 6 to be attached NOTE Reference Section B 3 2 for recommended solder sleeves flat braids and heat shrinkable tubing The same recommendations are applicable to this technique 3 Strip back approximately 0 17 inches of insulation from each wire of the shielded cable item 4 and crimp a contact item 2 to each conductor It is the responsibility of the installer to
121. 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 B 17 4 Insert newly crimped contacts and wires into the appropriate connector housing location as specified by the installation wiring diagrams 5 Cut the flat braid item 6 to a length that with the addition of a ring terminal will reach the grounding hole of the circular backshell item 3 Figure B 15 An appropriate amount of excess length without looping should be given to the flat braid item 6 to allow it to freely move with the wire bundle 6 Guidelines for terminating the newly cutoff flat braid s item 6 with insulated ring terminals item 9 The grounding hole on the circular backshell item 3 may accommodate a max of 4 ring terminals item 9 tis preferred that only two Flat Braid s item 6 be terminated per ring terminal Two flat braids per ring terminal will necessitate the use of a 6 ring terminal 14 16 AWG MS25036 107 If only a single flat braid is left or if only a single flat braid is needed a 6 ring terminal 18 22 AWG MS25036 102 can accommodate a single flat braid If more braids exist for this connector than two per ring terminal it is permissible to terminate three braids per ring terminal This will necessitate the use of a 6 ring terminal 10 12 AWG 525036 111 7
122. doubler plate Alternately non structural brackets may be fabricated in the field as necessary to mount the antenna Brackets should be made of minimum 0 032 thickness aluminum and should span as short a distance as possible Some fabric aircraft include aluminum paste in the fabric finishing process often referred to as silver coats Presence of thick fabric and or heavy silver coats may degrade the signal strength of the antenna 6 6 3 Non structural Installation to Glareshield Figure 6 26 shows an example of a bracket created to support an antenna mounted on the underside of the glare shield Figure 6 27 shows the non structural mounting of the antenna under the glareshield with the bracket assembly shown in Figure 6 26 4X 10 32 PHP x 1 00 25 4 TORQUE 20 25 in Ibs TEARDROP FOOTPRINT ANTENNA ANTENNA SUPPORT BRACKET RIVETS OPTIONAL S ARINC 743 FOOTPRINT ANTENNA lt ANTENNA SUPPORT go i ont LN DOUBLER lt 4X NAS1149FN832P D AN960 8 8 WASHER 4X 210 10004 09 8 32 SELF LOCKING NUT TORQUE 12 TO 15 RIVETS OPTIONAL 0 9 DOUBLER EXAMPLE INSTALLATION COMPOSITE AIRCRAFT EXAMPLE INSTALLATION COMPOSITE AIRCRAFT STUD MOUNT TEARDROP FOOTPRINT ANTENNA ARINC 743 FOOTPRINT ANTENNA SURROUNDING STRUCTURE NOT SHOWN FOR CLARITY SURROUNDING STRUCTURE NOT SHOWN FOR CLARITY Figure 6 26
123. e GSU 73 should be mounted within 13 feet 4 0 meters longitudinally and 6 5 feet 2 0 meters laterally of the aircraft center of gravity In cases where the longitudinal distance from the CG is planned to be greater than 6 5 feet 2 0 meters it is preferable to mount the GSU 73 forward of the aircraft center of gravity if possible to enable better acceleration outputs for autopilot use The mounting location for the GSU 73 should be protected from rapid thermal transients in particular large heat loads from nearby high power equipment The GSU 73 must be leveled to within 3 0 of the aircraft level reference and an aircraft leveling and offset calibration procedure carried out prior to flight This procedure is described in Section 9 Alternatively if the GSU 73 can be guaranteed level to within 0 25 of the aircraft level reference the aircraft leveling and offset calibration procedure is not required Avoid placing the GSU 73 within 1 inch of magnetically mounted antennas speaker magnets or other strongly magnetic items 4 7 Unit Installation For final installation and assembly refer to the outline and installation drawings shown in Appendix C of this manual 1 Assemble the wiring harness and backshell connectors 2 Assemble the pneumatic hoses and connectors 3 Mount the unit to a suitable mounting location using 10 32 pan or hex head screws 4 ea per the requirements in Section 4 6 4 Connect backshell connector and
124. e at one of the numbers shown below Products sold through online auctions are not eligible for rebates or other special offers from Garmin 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 Garmin International Inc Garmin Europe Ltd 1200 East 151 Street Liberty House Bulls Copse Road Olathe Kansas 66062 U S A Hounsdown Business Park Phone 913 397 8200 Romsey SO40 9RB U K FAX 913 397 0836 Phone 44 0 870 8501241 Phone 44 0 870 8501251 G3X Installation Manual Page xi 190 01115 01 Revision A GSU 73 HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification Mod Levels for the GSU 73 LRU 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 SERVICE SERVICE PURPOSE OF MODIFICATION BULLETIN BULLETIN NUMBER DATE Improved HSCM accuracy when using 28V supply Page xii G3X Installation Manual Revision A 190 01115 01 1 G3X Installation Overview 1 4 Unpacking Unit Carefully unpack the equipment and make a visual inspection of the unit for
125. ectronically stabilized AHRS The GMU 44 magnetometer provides magnetic information to support the function of the GSU 73 The GSU 73 provides operating voltage to the GMU 44 Magnetometer 3 1 1 Interface Summary The following is an interface summary for the GMU 44 e 44 to GSU 73 Interface Power RS 232 RS 485 19 200 baud 3 2 Electrical Specifications Table 3 1 GMU 44 Electrical Specifications Specification Characteristic Power Requirements Supply Voltage 14 28 VDC See Table 1 3 for current specifications G3X Installation Manual GMU 44 Page 3 1 190 01115 01 Revision A 3 3 Environmental Specifications Table 3 2 lists general environmental specifications Table 3 2 GMU 44 Environmental Specifications Specification Characteristic Regulatory Compliance RTCA DO 160D Environmental Conditions and EUROCAE ED 14D Unit Software RTCA DO 178B Level Operating Temperature Range Altitude 55 000 Feet 55 C to 70 C 3 4 GMU 44 TSO ETSO Compliance Table 3 3 TSO ETSO Compliance Applicable Custom Logic Device Part Numbers Applicable LRU Category SW Part Numbers All 006 B0224 __ All except 006 C0048 0 _ 006 B0224 Z TSO ETSO SAE RTCA EUROCAE Direction Instrument Magnetic Gyroscopically Stabilized TSO C6d ETSO C6d AS8013A 3 4 1 TSO ETSO Deviations The following table provides a list of applicable TSO and SAE deviations for the GM
126. emoved 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 B 17 Page B 22 G3X Installation Manual Appendix B Revision A 190 01115 01 INSPEC WIRE MUS E VISIBLE AFTER CRIMPING E 1 32 E Figure B 17 Insulation Contact Clearance 5 Insert newly crimped contacts and wires into the appropriate connector housing location as specified by the installation wiring diagrams 1 64 6 Cut the flat braid item 6 to a length that with the addition of a ring terminal will reach the grounding hole of the circular backshell item 3 Figure B 15 An appropriate amount of excess length without looping should be given to the flat braid item 6 to allow it to freely move with the wire bundle NOTE Position the window splice to accommodate a flat braid item 6 length of no more than 4 inches 7 Guidelines for terminating the newly cutoff flat braid s item 6 with insulated ring terminals item 9 e The grounding hole on the circular backshell item 3 may accommodate a max of 4 ring terminals item 9 e tis preferred that only two Flat Braid s item 6 be terminated per ring terminal Two flat braids per ring terminal will necessitate the use of a 6 ring terminal 14 16 AWG 525036 107 If only a single flat bra
127. euver or a specific geographic area Can the problem be repeated reliably Were any of the following message advisory alerts observed must navigate to the INFO page and press the MSG softkey to see them within an hour of the occurrence of the problem AHRS not receiving airspeed AHRS not receiving any GPS information AHRS magnetic field model out of date AHRS extended operation in no GPS mode Did the onset of the problem occur shortly after a software upload to one or more of the G3X LRU s or shortly after a repeat of the magnetometer calibration procedure Was a cell phone on in the aircraft at the time 10 Were there any GPS Alert messages or loss of position lock Page 9 4 Installation Manual Troubleshooting Revision A 190 01115 01 BRG h DST NM ETE __ OIL PSI CARB F OIL F Figure 9 2 Attitude Air Data and Engine Airframe Failure Indication Reversionary or Split Screen PFD BRG237 DST 132mm ETE Figure 9 3 Attitude Fail Indication PFD G3X Installation Manual Troubleshooting Page 9 5 190 01115 01 Revision A Figure 9 4 AHRS Align Message PFD 9 3 2 Heading Pitch Roll Troubleshooting The GSU 73 may not be able to provide valid heading pitch roll data for the following reasons 1 The GSU 73 external memory module in the harness that stores the installation configuration parameters is either not present or n
128. excess length without looping should be given to the Flat Braid item 4 to allow it to freely move with the wire bundle NOTE Position the window splice to accommodate a Flat Braid item 4 length of no more than 4 inches 8 Guidelines for terminating the newly cutoff Flat Braid s item 4 with insulated ring terminals item 7 e Each tapped hole on the Jackscrew Backshell item 1 may accommodate only two ring terminals item 7 e tis preferred that only two Flat Braid s item 4 be terminated per ring terminal Two Flat Braids per ring terminal will necessitate the use of a Ring terminal 8 insulated 14 16 AWG MS25036 153 If only a single Flat Braid is left or if only a single Flat Braid is needed for this connector a Ring terminal 8 insulated 18 22 AWG MS25036 149 can accommodate this single Flat Braid If more braids exist for this connector than two per ring terminal it is permissible to terminate three braids per ring terminal This will necessitate the use of a Ring terminal 8 insulated 10 12 AWG MS25036 156 9 Repeat steps 2 through 8 as needed for the remaining shielded cables 10 Terminate the ring terminals to the Jackscrew Backshell item 1 by placing items on the Pan Head Screw item 8 in the following order Split Washer item 9 Flat Washer item 10 first Ring Terminal second Ring Terminal if needed before finally inserting the screw into the tapped holes on the Jackscrew
129. for visual inspection of the conductor G3X Installation Manual Appendix Page B 9 190 01115 01 Revision A Secondary Method Solder a Flat Braid item 4 to the shield exposed through the window of the prepared cable assembly item 2 Ensure a solid electrical connection through the use of acceptable soldering practices Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire Slide a minimum 0 75 inches of Teflon heat shrinkable tubing item 3 onto the prepared wire assembly and shrink using a heat gun The chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable and the Flat Braid item 4 to be attached Teflon Heat Shrinkable Tubing Reference the following MIL Spec for Teflon heat shrinkable tubing M23053 5 X Y 4 At the same end of the shielded cable item 2 and ahead of the previous shield termination strip back Float Min to Float Max Table B 6 length of jacket and shield to expose the insulated center conductors Figure B 6 The Ideal Float length may be best to build optimally Preferred Method The jacket and shield should be cut off at the same point so no shield is exposed Slide 0 75 inches minimum of Teflon heat shrinkable tubing item 5 onto the cable and use a heat gun to shrink the tubing The chosen size of heat shrinkage tubing must accommodate t
130. g MIL Spec for Teflon heat shrinkable tubing M23053 5 X Y NOTE Flat Braid as opposed to insulated wire is specified in order to allow continuing air worthiness by allowing for visual inspection of the conductor 3 Atthe same end of the shielded cable item 4 and ahead of the previous shield termination strip back Float Min to Float Max Table B 11 length of jacket and shield to expose the insulated center conductors Figure B 16 The Ideal Float length may be best to build optimally Preferred Method The jacket and shield should be cut off at the same point so no shield is exposed Slide 0 75 inches minimum of Teflon heat shrinkable tubing item 7 onto the cable and use a heat gun to shrink the tubing The chosen size of heat shrinkage tubing must accommodate the number of conductors present in the cable Secondary Method Leave a max 0 35 inches of shield extending past the jacket Fold the exposed 35 inches of shield back over the jacket Slide a solder sleeve item 7 over the end of the cable and use a heat gun approved for solder sleeves to secure the connection The chosen size of solder sleeve must accommodate the number of conductors present in the cable 4 Strip back approximately 0 17 inches of insulation from each wire of the shielded cable item 4 and crimp a contact item 2 to each conductor It is the responsibility of the installer to determine the proper length of insulation to be r
131. ge allows setting the weight and balance parameters for the airplane these parameters are then used on the Main Menu W B Page in normal mode Weight Balance may be used during pre flight preparations to verify the weight and balance conditions of the aircraft By entering the weight and arm values into the Aircraft window the GDU 37X can calculate the total weight moment and center of gravity CG Before entering the various figures the empty weight of the airplane and the arm or station for each weight should be determined These figures should be determined using the pilot s operating handbook for the airplane which also notes the weight limitations and fore aft CG limits Compare those figures to the values calculated by the GDU 37X Each station listed in the Station window has an editable name and arm location This allows the setting of the units of measure used for that station weight or units of avgas or jet fuel An optional maximum value can be set for a particular station e g a fuel tank might have a max capacity of 50 gallons or the max can be set to zero so that no maximum will be imposed The LOADING LIMITS window contains fields for the entry of minimum and maximum aircraft weight and the minimum and maximum CG location 1 Inconfiguration mode use the FMS Joystick to select the W B Page AIRCRAFT EMPTY AIRCRAFT EMPTY WEIGHT WEIGHT ARM ARM STATION gt ur B D ie N PILOT REAR PASS
132. gnal that allows the G3X MED to display weather data an or entertainment programming XM service should activate in 45 to 60 minutes 1 The Radio ID can be displayed by accessing the XM Audio Page and then pressing the INFO Softkey Record the Radio ID for reference during XM Activation 2 Make sure that the aircraft s XM antenna has an unobstructed view of the southern sky It is highly recommended that the aircraft be outside of and away from the hangar 3 Hook up the aircraft to external power if available The complete activation process may take 45 60 minutes or more depending on the demand on the XM activation system 4 Power on the avionics and allow the G3X to power up Do not power cycle the units during the activation process 5 Goto the XM Info Page During the activation process the unit may display several different activation levels this is normal and should be ignored When the service class Aviator Lite Aviator or Aviator Pro and all of the weather products for the class that you subscribed to are displayed the activation is complete Wait 30 seconds to allow the GDU 375 to store the activation before removing power Page 7 14 G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 8 Post Installation Checkout and Calibration Procedures The checkout procedures in this section are recommended to be performed after installing the G3X The calibration procedu
133. gth of wiring current draw on units and internal unit protection characteristics Do not attempt to combine more than one unit on the same circuit breaker RG400 or RG142 coaxial cable with 50 nominal impedance and meeting applicable aviation regulations should be used for the installation Installation Manual Installation Overview Page 1 5 190 01115 01 Revision A 1 7 1 Wiring Harness Installation Allow adequate space for installation of cables and connectors Ensure that routing of the wiring does not come in contact with sources of heat RF or EMI interference Analog Input wires routed too close to spark plugs plug wires or magnetos may result in erratic readings The installer shall supply and fabricate all of the cables Required connectors etc are provided with the G3X Installation Kit K10 00017 00 Electrical connections are made through D subminiature connectors for the GDU 37X and GSU 73 units and through a round 9 pin connector for the GMU 44 Appendix A defines the electrical characteristics of all input and output signals Required connectors and associated hardware are supplied with the connector kit Check wiring connections for errors before connecting any wiring harnesses Incorrect wiring could cause internal component damage GDU 37X Table 1 7 Pin Contact and Crimp Tools Part Numbers Contact Type Socket Mil Crimp Size 20 Garmin Contact Part Number 336 00094 00 Recommended
134. gu T L 0 17 INCHES 9 sK 2152 0 35 INCHES OF A SHIELD FOLDED FOR REF ONLY p FED SEF FIGURE 22 p gt BACK OVER JACKET 3L VUR 3 UM NZ Figure B 19 Quick Term Shield Termination Table B 12 Shielded Cable Preparations Quick Term Quick Term Max inches Quick Term Float inches Backshell Insert Quick Term Min Size Arrangement inches 1 At the end of the shielded cable item 4 strip Quick Term Min to Quick Term Table B 12 length of the jacket to expose the shield Next trim the shield so that at most 0 35 inches remains extending beyond the insulating jacket Fold this remaining shield back over the jacket 2 Connect a flat braid item 6 to the folded back shield of the prepared cable assembly The flat braid should go out the front of the termination towards the connector It is not permitted to exit the rear of the termination and loop back towards the connector Figure B 19 Make this connection using an approved shield termination technique NOTE FAA AC 43 13 1B Chapter 11 Section 8 Wiring Installation Inspection Requirements may be a helpful reference for termination techniques G3X Installation Manual Appendix B Page B 25 190 01115 01 Revision A Preferred Method Slide a solder sleeve item 5 onto the prepared cable assembly item 4 and connect the flat braid item 6 to the shield using a heat gun approve
135. h respect to airframe See Section 2 6 entitled Aircraft Mounting Requirements for GSU 73 GMU 44 b Vibrational motion of GSU 73 and or GMU 44 caused by neighboring equipment and or supports c Mounting of GSU 73 at a location that is subject to severe vibrations example close to an engine mount d Mounting screws and other hardware for GSU 73 and or GMU 44 not firmly attached Page 8 18 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 e Absence of mounting supports recommended by the aircraft manufacturer f GSU 73 connector not firmly attached to unit g Cabling leading to GSU 73 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 run up 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 installation can be considered adequate 10 After a few minutes the calibration will finish and a Done button will appear at the bottom of the display ensure that a ENGINE RUN UP TEST PASSED message appears at the bottom of the display press the ENT Key to return to the GSU Status Page Installation Manual Post Installation Checkout and Calibration Procedures Page 8 19 190
136. has received no FAA approval or endorsement G3X Installation Manual GDU 37X Page 2 5 190 01115 01 Revision A 2 9 Panel Cutout Template The below drawing can be used as a template when marking the panel for cutout Dimensions below are to verify accuracy of printout only see Figure C 1 2 for complete dimensions GDU 37X PANEL CUTOUT TEMPLATE IMPORTANT Cut out panel Ensure the Page Scaling setting to inside line is set to NONE when printing this page Verify dimensions of printed template accurate before cutting panel 7 33 in 186 2 mm 5 57 in 141 4 mm For corner holes center punch and drill 36 tap 6 32 to create threaded holes OR drill out with 25 drill bit and use Garmin nut plate P N 115 01054 00 Page 2 6 G3X Installation Manual GDU 37X Revision A 190 01115 01 3 GMU 44 Figure 3 1 GMU 44 Unit View 3 1 Equipment Description The Garmin GMU 44 Magnetometer is a remote mounted device that interfaces with a Garmin GSU 73 to provide flight attitude and heading data for flight instrumentation An Attitude and Heading Reference System combines the functions of a Vertical Gyro and a Directional Gyro to provide measurement of Roll Pitch and Heading angles The Garmin ADAHRS and magnetometer replace traditional rotating mass instruments Using long life solid state sensing technology the GMU 44 Magnetometer uses magnetic field measurements to create an el
137. he GMU 44 Section 4 This section describes the mechanical electrical and installation aspects of the GSU 73 Section 5 This section describes the mechanical electrical and installation aspects of the GTP 59 Section 6 This section describes the mechanical electrical and installation aspects for the GPS and XM antennas Section 7 This section describes the non G3X LRU interfaces Section 8 This section contains software configuration database and XM activation information Section 9 This section contains post installation checkout and calibration procedures for the G3X Section 10 This section contains troubleshooting information Section 11 This section contains information for ensuring the unit is suitable to be returned to service Appendix A This section contains pinout information for all G3X LRU s Appendix This section contains connector installation instructions Appendix C This section contains G3X Outline and Installation Drawings Appendix D This section contains the Interconnect Drawings Appendix E This section contains the External Interface Drawings Installation Manual Installation Overview Page 1 1 190 01115 01 Revision A 1 3 System Overview The G3X is an advanced technology avionics suite designed to integrate pilot aircraft interaction into one central system The system combines primary flight instrumentation aircraft systems instrumentation and navigational
138. he SD Card The System ID is displayed on the System Setup Menu in normal mode or on the Main Page in configuration mode Since these databases are stored internally in each GDU each GDU will need to be updated separately The SD card may be removed from the applicable GDU after installing the database s After the databases have been updated check that the appropriate databases are initialized and displayed on the splash screen during power up 7 5 1 Updating Garmin Databases Equipment required to perform the update is as follows Windows compatible PC computer Windows 2000 or XP recommended SanDisk SD Card Reader P Ns SDDR 93 or SDDR 99 or equivalent card reader Updated database obtained from the flyGarmin website SD Card 2 GB recommended Garmin recommends SanDisk or Toshiba brand After the data has been copied to the SD card perform the following steps 1 Insert the SD card in the card slot of the GDU 37X to be updated 2 Turn on the GDU 37X to be updated 3 Upon turn on a screen appears which lists the databases on the SD card A green checkbox indicates that the database already installed on the G3X is up to date an empty checkbox indicates that the database on the SD card is more current and should be installed 4 The database s can be updated by either highlighting UPDATE ALL and pressing the ENT key or by using the FMS Joystick to highlight a single database and pressing the ENT Key Page 7 12
139. he display press the ENT Key to return to the GSU Status Page Installation Manual Post Installation Checkout and Calibration Procedures Page 8 13 190 01115 01 Revision A 8 3 4 Calibration Procedure D Heading Offset Compensation Calibration Procedures B and C must have been successfully completed before Calibration Procedure D can be performed This procedure is optional and generally not recommended as it is difficult to orient the entire aircraft with an absolute accuracy of less than a few degrees This procedure is required only when the GMU 44 Magnetometer has not been installed facing forward and parallel to within 0 5 of the aircraft longitudinal axis For calibration accuracy maneuver the aircraft with assistance from outside the cockpit to precisely align the aircraft to cardinal compass heading reference lines on the compass rose In order to accomplish the necessary degree of accuracy in heading alignment it is generally required that the aircraft be physically towed by hand Towing tugs should not be used as they distort the magnetic field in their vicinity 1 Enter configuration mode by holding down the left hand softkey while powering on the GDU 37X if needed 2 Use the FMS Joystick to select the GSU Page if needed CONFIG GSU MAIN 3 Unlock the GSU Page by pressing softkeys 2 3 4 in order if needed 4 GSU Status Page use the FMS Joystick to select HEADING OFFSET 650
140. he number of conductors present in the cable Secondary Method Leave a max 0 35 inches of shield extending past the jacket Fold this 0 35 inches of shield back over the jacket Slide a solder sleeve item 5 over the end of the cable and use a heat gun approved for solder sleeves to secure the connection The chosen size of solder sleeve must accommodate the number of conductors present in the cable 5 Strip back approximately 0 17 inches of insulation from each wire of the shielded cable item 2 and crimp a contact item 6 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 B 7 d Ps 6 d INSPECTION H WIRE MUST BE VISIBLE AFTER CRIMPING E y V 1 64 1 32 a N N X S Figure B 7 Insulation Contact Clearance Page B 10 G3X Installation Manual Appendix B Revision A 190 01115 01 6 Insert newly crimped pins and wires into the appropriate connector housing location as specified by the installation wiring diagrams 7 Cut the Flat Braid item 4 to a length that with the addition of a ring terminal will reach one of the tapped holes of the Jackscrew backshell item 1 Figure B 5 An appropriate amount of
141. he site NOTE Although Section 8 3 3 indicates that the Magnetometer Calibration Procedure should be performed by making a series of clockwise turns around the site the procedure can also be performed by making counter clockwise turns for the purpose of evaluating the site for magnetic disturbances If upon completion of the Magnetometer Calibration Procedure in both the clockwise and counter clockwise directions the PFD displays the CALIBRATION SUCCESSFUL SITE IS CLEAN message then the candidate site is sufficiently free of magnetic disturbances and is acceptable for performing the Magnetometer Calibration Procedure It is important to perform the procedure in both the clockwise and counter clockwise directions to ensure that the magnetometer sweeps over a large enough area at the candidate site If upon completion of the Magnetometer Calibration Procedure in either of the two directions the PFD displays either the MAG FIELD AT SITE NOT UNIFORM or MAG FIELD AT SITE DIFFERS FROM IGRF MODEL message then the site contains magnetic disturbances that are too large Page 8 24 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 The Magnetometer Calibration Procedure must consistently report CALIBRATION SUCCESSFUL 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 atte
142. heat off End of test If the test fails the installation should be considered unreliable until the source of magnetic interference is identified and remedied 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 timestamps with the prepared test sequence to identify which action produced the problem Contact Garmin for assistance in resolving the problem Two common reasons for a failed magnetometer interference test are 1 New equipment is installed in close proximity to the GMU 44 magnetometer 2 An existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair Installation Manual Post Installation Checkout and Calibration Procedures Page 8 23 190 01115 01 Revision A 8 3 7 Site Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure As mentioned in Section 8 3 3 the Magnetometer Calibration Procedure Calibration Procedure C must be carried out at a site that is determined to be free of mag
143. his reason when choosing a mounting location for the GMU 44 observe the following distances from objects or devices that can disturb the magnetic field Table 3 7 specifies required distances from magnetic disturbances for GMU 44 location G3X Installation Manual 44 Page 3 3 190 01115 01 Revision A Table 3 7 Required Distance from Magnetic Disturbances Disturbance Source Minimum Distance from GMU 44 Electric motors and relays including servo motors 10 feet 3 0 meters Ferromagnetic structure greater than 1 kg total iron steel or cobalt materials especially landing 8 2 feet 2 5 meters gear structure Ferromagnetic materials less than 1 kg total such as control cables Any electrical device drawing more than 100 mA current Electrical conductors passing more than 100 mA current must be twisted shielded pair if within 10 3 feet 1 0 meter feet 3 0 meters Electrical devices drawing less than 100 mA current 2 feet 0 6 meter 3 feet 1 0 meter 3 feet 1 0 meter Magnetic measuring device e g installed flux gates even if unpowered 2 feet 0 6 meter Electrical conductors passing less than 100 mA current must be twisted shielded pair if within 10 1 3 feet 0 4 meter feet 3 0 meters Ensure that any electrical conductor that comes within 10 feet 3 0 meters of the GMU 44 is installed as a twisted shielded pair not a single wire conductor If possible the
144. hrough the skin of the aircraft The loss may not be apparent but under the some of the worst case signal scenarios signal availability may be affected e The materials in some aircraft are not suitable for GPS signals to penetrate care should be taken to properly modify the aircraft structure to accommodate this Modifications of this sort are not recommended or inferred by Garmin or the installation of the G3X and the installer should seek the guidance of the kit manufacture for such modifications XM FIS antennas may typically be buried without performance impact if the overlying material is fairly transparent to the satellite signal Figure 6 2 shows example areas of some mounting locations which have been used Low satellite reception and tracking are compromised in these installations due to fuselage and tail blockage It is not possible to determine the full impact of these locations however initial flight testing has not shown any significant impact to GPS signal availability your results may vary Better Forward Visibility Best Visibility Fiber TN Fiber Glass Carbon Fiber N 5 Deg Mask Angle x Horizon Line Figure 6 2 Carbon Glass Buried Antenna Area G3X Installation Manual Antennas Page 6 5 190 01115 01 Revision A Mounting the antenna under the glare shield Figure 6 3 is a good option for XM FIS antennas although it is not typically the best option for
145. ication of components that are ferrous or otherwise magnetic within 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 a repeat of the magnetometer interference test If new magnetic interference is detected it must be resolved and then the magnetometer calibration procedure must be repeated Wiring or grounding changes associated with a device located in the same wing as the GMU 44 is a good example of such a change G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 5 190 01115 01 Revision A 8 3 1 Calibration Procedure A AHRS ORIENTATION 1 Enter configuration mode by holding down the left hand softkey while powering on the GDU 37X 2 Use the FMS Joystick to select the GSU Page CONFIG GSU 2301650 3 Unlock GSU Page by pressing softkeys 2 3 4 in order 4 Ensure that all the required status boxes are checked Tables 8 2 and 8 3 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view of the sky or a GPS repeater to produce positive status indications 4 AJ CONFIG MODE MAGNET
146. ications u u e u ep ei una uu ite i uu 2 3 2 4 Installation Requirements ete reet eee Crete et eee EE eee Ua te EE ee Vea Suyu 2 4 2 5 Installation Considerations eot ede et te e Pent Late tae ote ie eet be 2 5 2 6 Mounting Requirements ssena n enra i RN Re a te d eter eee det tette us 2 5 2T Unit Installation ass suede een era elena rd et eR I rers 2 5 2 8c 2 5 29 Panel Cutout Templates oe e Rn iia ddan inate 2 6 3 hasa Sas aspa Dau tai eens teely 3 1 3 1 Equipment Description cz 1 Eee Gre lcu b Le 3 1 3 2 Electrical Specifications e ee e e eles ca i E e eee hea ene 3 1 3 3 Bnvironmental Specifications u l ai La S n aas 3 2 34 44 TSO ETSO 3 2 3 5 Installation Requirements eei REL ee Ce e RUM bee Ho coe da 3 3 3 6 Installation Considerations io eps ea een d eee atq dte EU eria 3 3 3 7 GSU 73 GMU 44 Interconnect Harness Fabrication Instructions eene 3 5 3 8 Mounting Instructors in debi e hd ee ee te eene ipee bebat 3 6 3 9 i Maintenance tee eee ie DL ha a ete id iq ripe 3 6 4 GS UNS EE 4 1 41 Equipment Description u Cede du ud d dede e Le qu eeu e 4 1 4 2 Electrical Specifications iuto ceo on TORT OTT PO REPOS 4 2 4 3 En
147. id is left or if only a single flat braid is needed a 6 ring terminal 18 22 AWG MS25036 102 can accommodate a single flat braid If more braids exist for this connector than two per ring terminal it is permissible to terminate three braids per ring terminal This will necessitate the use of a 6 ring terminal 10 12 AWG MS25036 111 8 Repeat steps 1 through 7 as needed for the remaining shielded cables 9 Terminate the ring terminals to the circular backshell item 3 by placing items on the provided pan head screw in the following order flat washer provided with circular backshell first ring terminal second ring terminal third ring terminal 1f needed before finally inserting the screw into the grounding hole on the circular backshell and securing with the provided locking nut Do not violate the guidelines presented in step 7 regarding ring terminals Installation Manual Appendix Page B 23 190 01115 01 Revision A B 4 3 Daisy Chain Shield Termination Technique Method A In rare situations where more braids need to be terminated for a connector than three per ring terminal it is allowable to daisy chain a maximum of two shields together before coming to the ring terminal Figure B 18 All other restrictions and instructions for the shield termination technique set forth for Method A are still applicable NOTE The maximum length of the combined braids should be approximately 4 inches
148. in part of this manual DOCUMENT PAGINATION Table of Contents i xii Section 1 1 1 1 8 Section 2 2 1 2 6 Section 3 3 1 3 6 Section 4 4 1 4 8 Section 5 5 1 5 4 Section 6 6 1 6 28 Section 7 7 1 7 14 Section 8 8 1 8 26 Section 9 9 1 9 12 Section 10 10 1 10 2 Appendix A 1 A 16 Appendix B B 1 B 28 Appendix C C 1 C 22 Appendix D D 1 D4 Appendix E 1 E4 Installation Manual Page i 190 01115 01 Revision A TABLE OF CONTENTS PARAGRAPH PAGE 1 G3X Installation inn epigr diet aaa ee p IH 1 1 Li Unpacking Units uu a aii aaa sae ED a one en ea neha 1 1 1 25 IntroductiOD i ccc Chusu amu OP e ua ceded ERE OR I iate 1 1 13 System OVeEVISW esae ee e pateant ete ete E etr ye 1 2 14 General G3X LRU Specifications na nn e Ue ete NL SoC e Ree Dette tn 1 3 1 5 Installation Requirements neni ls t a tr E o DEO E En 1 5 EG aes 1 5 1 7 Considerations 1 5 2 GDU 37 Xs need e eed bec eene reed 2 1 2 1 Equipment Description Rees Rr Hie Hee Heer ee PEEL ee e t E rete 2 1 2 2 Electrical SpecifiCatloris iie dee e eH EPI ei He re isst Gre kala hulu 2 2 23 Environmental Specif
149. ion Requirements One GDU 37X assembly listed in Table 1 1 is required dependent upon customer s desired database region Each GDU 37X 010 00667 XX comes with all equipment needed for installation 1 5 1 Required Accessories The following kits are required for the installation of the G3X Table 1 5 Contents of G3X Installation Kit K10 00017 00 Garmin P N Quantity GMU 44 Connector Kit 011 00871 00 Config Module w EEPROM Jackscrew 011 00979 20 Config Module w Sockets Jackscrew 011 00979 22 Thermocouple Kit 011 00981 00 GSU 78 Connector Kit P9731 011 01818 00 GSU 78 Connector Kit P9732 011 01818 01 G3X Supplemental Parts 011 02347 00 GMU A4 Install Rack Modified 115 00481 10 Table 1 6 Contents of G3X LRU Kit K10 00016 00 Garmin P N GMU 44 Unit Only 010 00296 10 GSU 73 Unit Only 010 00691 00 GTP 59 Unit Only 011 00978 00 1 6 Mounting Refer to Section 2 through Section 6 for specific mounting instructions for each component of the G3X and to Appendix A for Outline amp Installation Drawings 1 7 Wiring Cabling Considerations Use MIL W 22759 16 or other approved wire AWG 24 or larger wire for all connections unless otherwise specified The supplied standard pin contacts are compatible with up to AWG 22 wire In cases where some installations have more than one LRU sharing a common circuit breaker sizing and wire gauge is based on aircraft circuit breaker layout len
150. ion errors 10 2 GSU 73 A pitot static check as outlined in 91 411 and Part 43 Appendix E must be completed if the pitot static lines are broken 10 2 1 Original GSU 73 is Reinstalled No software or configuration loading is required if the original GSU 73 is reinstalled Continue to Section 10 3 G3X Installation Manual Return to Service Page 10 1 190 01115 01 Revision A 10 2 2 New GSU 73 Installed If anew GSU 73 is installed new serial number verify the correct software version on the MAIN page in configuration mode If the correct software version is not installed load the GSU 73 software contained in the G3X system software loaded to the displays If the configuration module is operational no software configuration is required Continue to Section 10 3 10 3 GMU 44 If the GMU 44 is removed the anti rotation properties of the mounting screws must be restored This may be done by replacing the screws with new Garmin P N 211 60037 08 If original screws must be re used coat screw threads with Loctite 242 blue thread locking compound Garmin P N 291 00023 02 or equivalent Important Mounting screws must be brass 10 3 1 GMU 44 is Reinstalled Any time a GMU 44 is reinstalled a new magnetometer calibration is required Section 8 3 3 Continue to Section 10 3 2 10 3 2 New GMU 44 Installed If anew GMU 44 is installed new serial number a new magnetometer calibration Section 8 3 3 and verification of the
151. isy Chain Quick Term Shield Termination G3X Installation Manual Appendix B Page B 27 190 01115 01 Revision A B 4 6 Daisy Chain Shield Termination Between Methods A and B In rare situations where more braids need to be terminated for a connector than three per ring terminal and a mixture of Methods A and B have been used it is allowable to daisy chain a maximum of two shields together from a Method A termination to a Method B Figure B 21 All other restrictions and instructions for the shield termination technique set forth for Method A and B are still applicable NOTE The maximum length of the combined braids should be approximately 4 inches WINDOW 4 6 tea 0 35 INCHES MAX SSS gt D 4 ner f EN I f T AN LOAT MIN TO FLOAT a 16 b NC Lu INCHES 0 75 INCHES MIN 0 35 INCHES MAX 1 FOR REF ONLY SEE FIGURE 2 2 Figure B 21 Daisy Chain Shield Termination between Methods A and B Page B 28 G3X Installation Manual Appendix B Revision A 190 01115 01 APPENDIX C OUTLINE AND INSTALLATION DRAWINGS 2X 1 72 FRONT SURFACE OF PANEL
152. ld Start position known to 300 nm time known to 10 minutes with valid almanac Less than 45 seconds C AutoLocate with almanac without initial position or time Less than 60 seconds Update Rate 5 second continuous Positional Accuracy lt 10 meters Antenna Power Supply Voltage 4 5 to 5 0 current 50 mA max Page 2 2 G3X Installation Manual GDU 37X Revision A 190 01115 01 2 2 4 Antennas Table 2 4 lists Garmin and non Garmin antennas currently supported by the GDU 37X Refer to Section 6 for Garmin antenna installation information For non Garmin antennas follow the manufacturer s installation instructions NOTE Only a single GPS antenna is required for installations using more than one GDU 37X unit as the GDU 37X will share the GPS information with all GDU 37X units Table 2 4 GDU 37X Supported Antennas Antenna Part Number Antenna Type Garmin Order Mount Style Number Screw Mount Teardrop Comant 2480 201 VHF GPS Cl 2480 201 Comant 1 Footprint Comant Screw 420 10 XM Mount only ARINC 743 Antenna Footprint CI 420 10 Suction Cup Magnetic or Flange Mt GA 26C Garmin 011 00149 04 010 10052 04 Ground GA 26XM Plane Mt Garmin 013 00268 10 010 11373 00 GA 55 Stud Mount Garmin 011 01033 00 010 10600 01 GA 55A ARINC 743 Garmin 011 01153 00 010 10598 00 GA 56 Stud Mount Garmin 011 0013
153. le database This database is updated on a 56 day cycle SafeTaxi The SafeTaxi database contains detailed airport diagrams for selected airports These diagrams aid in following ground control instructions by accurately displaying the aircraft position on the map in relation to taxiways ramps runways terminals and services This database is updated on a 56 day cycle and has no expiration date FliteCharts The FliteCharts database contains terminal procedure charts for the United States only This database is updated on a 28 day cycle If not updated within 180 days of the expiration date FliteCharts will no longer be user accessible AOPA Airport Directory The AOPA Airport Directory provides data on airports and heliports throughout the U S and offers detailed information for over 5 300 U S airports along with the names and phone numbers of thousands of FBOs Look up taxi services plan an overnight and choose fuel stops plus find ground transportation lodging restaurants local attractions and more This database is updated on a quarterly cycle and has no expiration date 7 6 XM Activation Instructions GDU 375 only Follow the below instructions to activate the XM receiver in the GDU 375 Before XM Satellite Weather can be used the service must be activated by calling XM at 1 800 985 9200 Service is activated by providing XM Satellite Radio with a Radio ID XM Satellite Radio uses the Radio ID to send an activation si
154. lock GSU Page by pressing softkeys 2 3 4 in order if needed 4 Ensure that all the required status boxes are checked Tables 8 2 and 8 3 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view of the sky or a GPS repeater to produce positive status indications GSU STATUS MAGNETOMETER AIR DATA GPS Page 8 20 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 5 Use the FMS Joystick to select MAGNETOMETER INTERFERENCE TEST Bee MAG INTERFERENCE TEST 0000000 CALIBRATE 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key MAG INTERFERENCE TEST CALIBRATE 7 Ensure that the aircraft has been properly prepared per the on screen instructions See Table 8 2 for a sample test sequence GSU73 CALIBRATION 1 ENSURE THE AIRCRAFT IS ABLE TO EXERCISE ALL ELECTRONIC DEVICES ON WING AND FUSELAGE LE FLAPS LIGHTS BEACONS ETC 2 IF THE AIRCRAFT HAS RETRACTABLE LANDING GEAR IT MUST BE ON JACKS SO THE GEAR CAN BE RAISED AND LOWERED 3 PREPARE A DETAILED TEST SEQUENCE WITH PRECISE START AND STOP TIMES FOR EXERCISING ALL ELECTRONIC DEVICES 4 ENSURE THE AIRCRAFT IS STATIONARY READY TO ENTER THE 65073 AHRS MAGNETOMETER INTERFERENCE TEST MODE G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 21 190 01115 01
155. 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 interference at the L1 frequency of 1575 42 MHz An aircraft EMC check reference VHF COM interference 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 The separation requirement does not apply to GPS and COM combination antennas provided the antenna has been tested to meet Garmin s minimum performance standards The separating requirement includes the combination with an XM antenna element as well 4b 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 4c 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 mo
156. mpts 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 meters of the location Installation Manual Post Installation Checkout and Calibration Procedures Page 8 25 190 01115 01 Revision A This page intentionally left blank Page 8 26 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 9 Troubleshooting In this section the term Red X refers to a red X that appears on different areas of the display to indicate the failure of that particular function Refer to the G3X Pilot s Guide 190 01054 00 for a complete listing of System Status Messages For additional assistance contact your G3X Dealer then for further help if needed contact Garmin Aviation Product Support at US Toll Free Number 1 888 606 5482 or US 1 913 397 8200 The information in this section is for troubleshooting use only and does not supersede any approved Maintenance or Installation Manual instructions 9 1 GDU 37X 9 1 1 SD Card Slot A stuck or sticking SD card issue can sometimes be caused by the card thickness variability especially if there is more than one label on the card This is usually caused by the card s
157. n requested and granted for the GTP 59 Table 5 4 TSO ETSO Deviations for the GTP 59 1 Garmin was granted a deviation from TSO C106 to use RTCA DO 160D including changes 1 2 and 3 instead of RTCA DO 160B as the standard for Environmental Conditions and Test Procedures for Airborne Equipment 2 Garmin was granted a deviation from TSO C106 to use Society of Automotive Engineers SAE AS 8002 Rev A instead of SAE AS 8002 as the Minimum Performance Standard 1 Garmin was granted a deviation from ETSO C106 to use Society of Automotive Engineers SAE AS 8002 Rev A instead of SAE AS 8002 as the Minimum Performance Standard Page 5 2 G3X Installation Manual GTP 59 Revision A 190 01115 01 5 4 Installation Considerations 5 4 1 GTP 59 Icing The GTP 59 OAT probe has no icing protection If ice accumulates on the GTP 59 OAT probe its accuracy is unknown Consequently air temperature measurements may be incorrect if ice accumulates on the probe Furthermore computations dependent upon air temperature measurements may be affected e g true airspeed and delta ISA 5 4 2 GTP 59 OAT Probe Installation The following instructions are general guidance Do not mount the GTP 59 where aircraft exhaust gases will flow over it Table 5 5 contains a list of parts needed for the GTP 59 installation and interconnect harness Reference numbers in the table and instructions refer to item bubble numbers shown in Figure C 4 1 Table
158. netic disturbances Typically a compass rose is an acceptable location to perform the magnetometer calibration procedure However because not all compass roses are well maintained even an existing compass rose should be regularly evaluated using the method described here to determine if it is free of magnetic disturbances If evaluation of an existing compass rose indicates that magnetic disturbances are present then an alternative location must be found to perform the Magnetometer Calibration Procedure A G3X equipped airplane can be used to evaluate a candidate site for magnetic disturbances and determine whether it is a suitable location to perform the magnetometer calibration procedure The magnetometer calibration procedure itself contains the logic to simultaneously survey the location for magnetic cleanliness while it is computing the magnetometer calibration parameters The G3X equipped airplane installation used to evaluate the site must have already completed the pitch roll offset compensation procedure Procedure B However prior completion of the Magnetometer Calibration Procedure Procedure C 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 8 3 3 of this document with the exception of the direction of turns around t
159. ng cables near power sources e g 400 Hz generators trim motors etc or near power for fluorescent lighting e Route the GPS antenna cable as far as possible away from all COM transceivers and antenna cables 1 7 3 Cable Installation 1 Route the coaxial cable to the unit location Secure the cable in accordance with good aviation practices 2 Trim the coaxial cable to the desired length and install the BNC connector 330 00087 00 per the cabling instructions on Figure 1 2 If the connector is provided by the installer follow the connector manufacturer s instructions for cable preparation GASKET NUT 1 PLACE NUT AND GASKET OVER CABLE AND STRIP JACKET N TO DIMENSION SHOWN Hl al 2 COMB OUT BRAID AND TRIM DIELECTRIC TO DIMENSION SHOWN F 3 PULL BRAID WIRES FORWARD AND TAPER TOWARD CENTER CONDUCTOR PLACE CLAMP OVER BRAID AND PUSH BACK AGAINST CABLE JACKET 4 FOLD BACK BRAID OVER CLAMP AS SHOWN TRIM OFF EXCESS BRAID SOLDER CONTACT TO CENTER CONDUCTOR S INSERT CABLE CLAMP AND GASKET INTO CONNECTOR BODY MAKING SURE THAT SHARP EDGE OF CLAMP SEATS PROPERLY AND TIGHTEN NUT E Figure 1 2 Coaxial Cable Installation 3 Contacts for the 50 62 and 78 pin connectors must be crimped onto the individual wires of the aircraft wiring harness Table 1 7 lists contact part numbers for reference and recommended crimp tools
160. nitial Release Page A G3X Installation Manual Revision A 190 01115 01 This product its packaging and its components contain chemicals known to the State of California to cause cancer birth defects or reproductive harm This Notice is being provided in accordance with California s Proposition 65 If you have any questions or would like additional information please refer to our web site at www garmin com prop65 NOTE The Garmin G3X system includes products like the GDU 37X and the GSU 73 that are not TSO certified products and have received no FAA approval or endorsement Consequently the G3X system is not suitable for installation in type certificated aircraft NOTE Unless otherwise noted all installation guidance requirements and instructions apply to one display two display and three display G3X systems NOTE References to the GDU 37X throughout this manual apply equally to the GDU 370 and GDU 375 except where specifically noted 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 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
161. nna Installation GA 55 and GA 56 sese 6 7 6 5 ARINC 743 Footprint Antenna Installation GA 55A GA 57 6 14 6 6 Non Structural Mount Installation enne n sns 6 23 7 Software Configuration Databases and XM Activation a 7 1 Til Configuration Mode eant ee P eO NO OG P e PESO ER Gis 7 1 7 2 Software Audio Data TdentfiegBhon L u aaa apawaska wawaspaq enn 7 1 7 3 Software Loading Procedure eae nee dt ne ep te E P Me ie e opt e bola 7 3 14 Configuration Pages is oett eni Leste a Eee upaku u eerie 7 4 7 5 Garmin Database Updates dn eter dee hd nin dette bee 7 12 7 6 Activation Instructions GDU 375 7 14 8 Post Installation Checkout and Calibration Procedures serene 8 1 8 1 Recommended Test Equipment 1 urit eo o P CL Fm i ie HE Lee rte pe sistas 8 2 82 Test Procedures ep ee a epe eei EO en 8 2 8 3 GSU 73 GMU 44 Post Installation Calibration Procedure 8 4 9 Troubleshooting sen 5 7c ere theo ee Ee eta ihe ree eee tte e axes 9 GDU 37X zer eO eei Oe M e GE HE Oe ayasa 9 1 9 2 9 2 9 3 its deae teinte ie Rete iter t ce 9 3 94 GSU 73 Air Data Troublesh ootIn8 rennen nnne nas
162. ns to magnetic headings of 360 090 180 and 270 degrees within a tolerance of 0 25 Maneuver the aircraft with the longitudinal axis aligned with the desired heading line of the compass rose 10 Repeat the preceding steps 3 4 and 5 until a Calibration OK message is displayed G3X Installation Manual Post Installation Checkout and Calibration Procedures Page 8 15 190 01115 01 Revision A 11 After the complete calibration is finished a Done button will appear at the bottom of the display ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of the display press the ENT Key to return to the GSU Status Page Page 8 16 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 8 3 5 Calibration Procedure E Engine Run Up Vibration Test Calibration Procedure E is required for all installations to validate the vibration characteristics of the installation Calibration Procedures B through D are not required prior to this procedure 1 Enter configuration mode by holding down the left hand softkey while powering on the GDU 37X if needed 2 Use the FMS Joystick to select the GSU Page if needed CONFIG GSU 3 Unlock the GSU Page by pressing softkeys 2 3 4 in order if needed 4 Ensure that all the required status boxes are checked Tables 8 2 and 8 3 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must h
163. nt Antenna Skin Thickness 0 049 to 0 051 Page 6 11 Revision A G3X Installation Manual Antennas 190 01115 01 0 0 0 2 HOLES 2X 0 81 20 6 4X 00 188 THRU SKIN TO MATCH DOUBLER 1 DOUBLER OUTLINE UN 0 0 0 2 HOLES O 1 p L 2X 4 62 41 3 N Pu Q 1 00 25 4 I 4 23 107 4 2X 1 75 44 5 A y uns 1 ME e I 2 59 65 8 FORWARD ANTENNA OUTLINE 7 20 625 THRU SKIN NOTES 1 DIMENSIONS INCHES mm 2 COUNTERSINK EXTERNAL AIRCRAFT SKIN FOR INSTALLATION OF FLUSH HEAD RIVETS Figure 6 10 Skin Cutout Detail Teardrop Footprint Antenna Skin Thickness 0 051 to 0 063 12X MS20426AD4 x RIVETS NOTES DOUBLER 1 MS20426AD4 X RIVET SELECTION LENGTH AND INSTALLATION DETERMINED USING THE GUIDANCE FOUND IN AC43 13 1B Figure 6 11 Doubler Installation Teardrop Footprint Antenna Skin Thickness 0 032 to 0 049 Page 6 12 G3X Installation Manual Antennas Revision A 190 01115 01 a 16X MS20426AD4 x RIVETS NOTES 1 MS20426AD4 X RIVET SELECTION LENGTH AND INSTALLATION DETERMINED USING THE GUIDANCE FOUND IN AC43 13 1B Figure 6 12 Doubler Installation Teardrop Footprint Antenna Skin Thickness 0 049 to 0 051 16X MS20426AD4
164. nting cutout Drill or punch the holes to match the mating part doubler Install a doubler plate to reinforce the aircraft skin as required Refer to Section 6 5 1 for doubler preparation and Table 6 6 for additional guidance on the doubler installation Dimple aircraft skin when the skin thickness is less than 0 051 for installation of flush head rivets Countersink aircraft skin when the skin thickness is between 0 051 and 0 063 for installation of flush head rivets Place the install gasket on top of aircraft skin using the four screw holes to align the gasket Locking nuts are required to secure the antenna locking nuts installed on doubler Torque the four supplied 10 32 stainless steel screws Garmin P N 211 60212 20 MS51958 67 or equivalent 20 25 in lbs Torque should be applied evenly across all mounting studs to avoid deformation of the mounting area Ensure that the antenna base and aircraft skin are in continuous contact with the gasket Seal the antenna and gasket to the fuselage using Dow Corning 738 Electrical Sealant or equivalent Run a bead of the sealant along the edge of the antenna where it meets the exterior aircraft skin Use caution to ensure that the antenna connectors are not contaminated with sealant 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 warrant
165. o 0 051 6 10 Skin Cutout Detail Teardrop Footprint Antenna Skin Thickness 0 051 to 0 063 6 11 Doubler Installation Teardrop Footprint Antenna Skin Thickness 0 032 to 0 049 6 12 Doubler Installation Teardrop Footprint Antenna Skin Thickness 0 049 to 0 051 6 13 Doubler Installation Teardrop Footprint Antenna Skin Thickness 0 051 to 0 063 6 14 Doubler Design ARINC 743 Footprint Antenna Skin Thickness 0 032 to 0 049 6 15 Doubler Design ARINC 743 Footprint Antenna Skin Thickness 0 049 to 0 051 6 16 Doubler Design ARINC 743 Footprint Antenna Skin Thickness 0 051 to 0 063 6 17 Sample Doubler Location ARINC 743 Antenna Metal Skin Aircraft 6 18 Skin Cutout Detail GA 55A Antenna Skin Thickness 0 032 to 0 049 6 19 Skin Cutout Detail 55A Antenna Skin Thickness 0 049 to 0 051 6 20 Skin Cutout Detail 55A Antenna Skin Thickness 0 051 to 0 063 6 21 Doubler Installation ARINC 743Footprint Antenna Skin Thickness 0 032 to 0 049 6 22 Doubler Installation ARINC 743Footprint Antenna Skin Thickness 0 049 to 0 051 6 23 Doubler Installation ARINC 743Footprint Antenna Skin Thickness 0 051 to 0 063 6 24 Installation of ARINC 743 Footprint Antenna eese 6 25 Generic Non structural ARINC 743 Footprint Antenna Installation
166. on to turn as a real time indication of when to turn simply judge the 30 55 turn increments of the aircraft by using the compass rose radials Dwelling at these 30 increments for the time recommended by the PFD should result in successful calibration Page 8 12 G3X Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 01115 01 11 The PFD guides the operator to dwell at multiple headings around a complete circle Due to high winds or excessive airframe vibration the operator may encounter a condition where the PFD restarts the 18 second countdown without full completion of the previous countdown If this is encountered more than once for a given station the operator should begin turning to the next station approximately 30 A minimum 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 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 too many countdown restarts are encountered the calibration will fail with the message TOO MANY STATIONS 12 When the calibration is finished a Done button will appear at the bottom of the display ensure that a CALIBRATION SUCCESSFUL message appears at the bottom of t
167. ondary Method Solder a Flat Braid item 4 to the folded back shield on the prepared cable assembly item 2 Ensure a solid electrical connection through the use of acceptable soldering practices Use care to avoid applying excessive heat that burns through the insulation of the center conductors and shorts the shield to the signal wire Slide a minimum of 0 75 inches of Teflon heat shrinkable tubing item 3 onto the prepared wire assembly and shrink using a heat gun The chosen size of heat shrinkage tubing must accommodate both the number of conductors present in the cable as well as the Flat Braid item 4 to be attached Teflon Heat Shrinkable Tubing Reference the following MIL Spec for general Teflon heat shrinkable tubing M23053 5 X Y HF 4 QUICK TERM MIN TO QUICK TERM MAX nN 3 v 7 cc T TI m J L pen ArH H d u 0 17 INCHES Ps L 0 35 INCHES MAX Of FOR REF ONLY ss SHIELD FOLDED EP EIA IDE 5 pd BACK OVER JACKET SEE FIGURE 2 2 ss 2 ae Z Figure B 9 Method B 1 Quick Term for Shield Termination G3X Installation Manual Appendix B Page B 13 190 01115 01 Revision A Table B 7 Shielded Cable Preparations Quick Term Backshei Number of Size Pins Std HD B 3 5 Shield Termination Method B 2 Daisy Chain Quick Term In rare situations where more braids need to
168. ot wired properly If this is the case then the external installation configuration parameters will not be considered calibrated If an AHRS not Calibrated message is displayed the AHRS and or Magnetometer calibration needs to be performed or the GSU 73 configuration module is inoperative 2 The external installation configuration parameters not considered calibrated These parameters are categorized into 2 sets AHRS installation and Magnetic installation If either of these is not calibrated the GSU 73 heading pitch and roll may all be flagged as invalid and an AHRS not Calibrated message is displayed Calibrate the unit to the installation 3 There is not sufficient or valid sensor information being provided to the GSU 73 for it to compute valid attitude information Table 9 1 summarizes the inputs the GSU needs to provide Attitude and Heading information Page 9 6 Installation Manual Troubleshooting Revision A 190 01115 01 9 4 GSU 73 Air Data Troubleshooting Under normal operating conditions the GSU 73 provides the following air data information Total Air Temperature is measured Outside Air Temperature OAT Indicated Airspeed IAS True Airspeed TAS Barometric Altitude Density Altitude Pressure Altitude Static Pressure Differential Pressure If the TAS and or OAT indications are dashed out as shown in Figure 9 5 1 2 Check the GTP 59 OAT probe wiring and connection for faul
169. ow Min inches Window Max inches Page B 16 Revision A G3X Installation Manual Appendix B 190 01115 01 B 3 8 Double Shield Termination Technique Quick Term Method C 2 In addition to method C 1 described previously another suitable method for double shielding wires is presented in Figure B 13 All restrictions set forth for Method C 1 Table B 8 are still applicable NOTE The maximum length of the braids should be approximately 4 inches BRAIDS NO LONGER THAN 4 INCHES 4 lt 0 35 INCHES MAX a 2 a Se p j _ f 17 INCHES 0 35 INCHES MAX ma FOR REF ONLY SEE FIGURE 2 2 FLOAT MIN TO FLOAT MAX WINDOW MIN WINDOW n Figure B 13 Method C 2 Double Shield Termination B 3 9 ID Program Pins Strapping ID Program Pins provide a ground reference used by the hardware as a means of configuration for system identification The following instructions will illustrate how this ground strapping should be accomplished with the Jackscrew Backshell 1 Cuta4 inch length of 22 AWG insulated wire WARNING Flat Braid is not permitted for this purpose Use only insulated wire to avoid inadvertent ground issues that could occur from exposed conductors 2 Strip back approximately 0 17 inches of insulation and crimp a contact item 6 to the 4 length of 22 AWG insul
170. pdate pop up will appear on the screen highlight YES and press the ENT key to begin the update NOTE If the below software update pop up does not appear select the Database Information Menu to update the software SOFTWARE UPDATE FOUND UPDATE SOFTWARE TO VERSION 2 20 3 The unit will reboot then GDU software update will begin automatically 4 Ensure power is not removed while the update is being performed 5 The unit will reboot after the update is complete 7 3 2 GSU Software Loading Procedure 1 Power on the GDU in configuration mode 2 Usethe FMS Joystick to select the GSU Page 3 Press the UPDATE SW softkey then press the ENT Key to begin the update G3X Installation Manual Software Configuration Databases and XM Activation Page 7 3 190 01115 01 Revision A 7 4 Configuration Pages 7 4 1 Main Configuration Page The Main Configuration Page is used to display LRU device specific information such as Unit and System ID s and Database information for the various databases used by the G3X This page has no user selectable options 1 Inconfiguration mode use FMS Joystick to select and view the MAIN Page Fa NI ONT LG u a DEVICE SOFTWARE PRODUCT VERSION NUMBER MFD 2 12 006 0746 PRODUCT NAME GDU 375 WS PRODUCT DESCRIPTION 2 12 UNIT ID UNASSIGNED SYSTEM ID UNASSIGNED AVIATION DB CYCLE 0901 AMERICAS CHART DB CYCLE 0901 US SAFETAXI CYCLE Ossi US OBSTACLE DB CYCLE 0981 US TERRAIN DB C
171. recommended Suggested tools to accomplish the window cut e Coaxial Cable Stripper e Thermal Stripper e Sharp Razor Blade 2 Connect a Flat Braid item 6 to the shield exposed through the window of the prepared cable assembly item 4 from step 1 The Flat Braid should go out the front of the termination towards the connector It is not permitted to exit the rear of the termination and loop back towards the connector Figure B 16 Make this connection using an approved shield termination technique NOTE FAA AC 43 13 1B Chapter 11 Section 8 Wiring Installation Inspection Requirements may be a helpful reference for termination techniques Preferred Method Slide a solder sleeve item 5 onto the prepared cable assembly item 4 and connect the Flat Braid item 6 to the shield using a heat gun approved for use with solder sleeves It may prove beneficial to use a solder sleeve with a pre installed Flat Braid versus having to cut a length of Flat Braid to be used The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the Flat Braid item 6 to be attached Recommended Solder Sleeve A preferred solder sleeve would be the Raychem 503 Series with the thermochromic temperature indicator S03 02 R 9035 100 S03 03 R 9035 100 S03 04 R 9035 100 These solder sleeves come with a pre installed braid and effectively take the place of items 5 and 6 For detailed instructions on
172. res are required to be performed after installing the G3X It is assumed that the person performing these checks is familiar with the aircraft has a working knowledge of typical avionics systems and has experience using the test equipment defined in this section The calibration procedures in this section are performed in the configuration mode To enter configuration mode hold down the left hand softkey while powering on the GDU 37X In a two display or three display system hold down the left hand softkey on the PFD while powering on the unit All three status boxes on the GSU Page config mode must indicate a positive state green check marks before performing any calibration procedures The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view of the sky or a GPS repeater to produce positive status indications The CONFIG GSU Page must be unlocked by pressing the softkeys 2 3 4 in order Figure 8 1 to select a calibration procedure CONFIG GSU Softkey 1 Softkey 3 Softkey 5 Softkey 2 Softhey 4 Figure 8 1 Softkey Positions All procedures in this section require that the GPS receiver is receiving sufficient satellite signal to compute a present position This requires outdoor line of site to GPS satellite signals or a GPS indoor repeater NOTE As these procedures involve engine run up and moving the aircraft it is recommended that the installer read this entire
173. s audio alerts TIS Audio Enables disables TIS traffic audio alerts Alert Output If set to MONO STEREO alert tones and messages will be output on both the mono and stereo outputs If set to MONO ONLY alert tones and messages will be output only on the mono output Alert Source If more than one GDU 37X is installed an Alert Source field will appear on the SOUND Configuration page The Alert Source field allows the user to select which GDU will generate the alert sounds The Alert Source options are PFD1 PFD2 MFD or Auto which will use whichever unit is present in the order PFD1 MFD PFD2 Page 7 10 G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 7 4 7 COMM Configuration Page The COMM Configuration Page allows setting the parameters for the communication ports 1 Inconfiguration mode use FMS Joystick to select the COMM Page CONFIG COMM ACFT W B UNITS DSPL SOUND 2 Usethe FMS Joystick to select the desired configurable item and make the desired change Then press the ENT Key or use the FMS Joystick to select the next item Press the FMS Joystick to move the cursor to the page selection menu when finished MFD COMM PORT CONFIGURATION RS 232 1 RS 232 2 RS 232 3 A small green dot will appear next to the name of each RS 232 port when it is receiving valid data The RS 232 comm port configuration options for the COMM Configuration P
174. section before beginning the checkout procedure NOTE Unless otherwise noted all procedures apply to both one display and two display systems CAUTION Be sure to check all aircraft control movements before flight is attempted to ensure that the wiring harness does not touch any moving part Installation Manual Post Installation Checkout and Calibration Procedures Page 8 1 190 01115 01 Revision A 8 1 Recommended Test Equipment The following test equipment is recommended to conduct and complete all post installation checkout procedures in this section All test equipment should have current calibration records Pitot static ramp tester Digital Multi Meter DMM Ground power unit capable of supplying 14 28 Vdc power to the aircraft systems and avionics e Outdoor line of site to GPS satellite signals or GPS indoor repeater e Digital Level or equivalent 8 2 GDU 37X Test Procedure Test the GPS Receiver 1 Power on unit and use the FMS Joystick to select the Info Page INFO PAGE MAP WPT WX TER XM fige MESSAGES 2 Verify that the GPS receiver is functional and able to calculate its present position GPS STATUS 3D DIFFERENTIAL DATE 18 FEB 09 TIME 4 30 37PM 22 30UTC POSITION N 38 51 395 W094 47 949 ACCURACY 11 Page 8 2 Revision A Installation Manual Post Installation Checkout and Calibration Procedures 190 01115 01 Test the XM Receiver if applic
175. ss of the installation 10 1 GDU 37X 10 1 1 Original GDU 37X is Reinstalled No software or configuration loading is required if the original GDU 37X is reinstalled Continue to Section 10 2 10 1 2 Original GDU 37X s Installed in a Different Position No software or configuration loading is required if the GDU 37X is installed in a different location Continue to Section 10 2 10 1 3 New GDU 37X s Installed If anew GDU 37X is installed new serial number verify the correct software version on the MAIN page in configuration mode Additionally verify that all installed displays have the same software version as well as NavData terrain and obstacle databases If the correct software version is not installed update the displays to the current G3X system software available on the web No configuration is required if the configuration module is still operational Continue to Section 10 2 10 1 4 New GDU 37X PFD Configuration Module Installed Ensure that a new configuration module is obtained for the replacement installation If a new configuration module is installed and no change is made to the PFD the PFD will write the required configuration information to the configuration module If the PFD and the configuration module are both replaced the system will need to be configured Section 7 Do not use a used GDU configuration module as a replacement Data that may reside on the used configuration module may cause system configurat
176. sted in Table B 4 are supplied in jackscrew backshell kits 011 01855 03 and 011 01855 04 Parts listed in Table B 5 are to be provided by the installer Table B 4 Parts supplied for a Shield Block Installation Figure B 1 or MIL spec MIL spec Ref for 011 01855 03 For 011 01855 04 von Contacts 336 00094 00 336 00094 00 Clamp 115 01078 03 115 01078 04 Screw 4 40x 375 PHP SS P w Nylon 211 60234 10 211 60234 10 Cover 115 01079 03 115 01079 04 Screw 4 40x 187 FLHP100 SS P w Nylon 211 63234 06 211 63234 06 Table B 5 Parts NOT supplied for a Shield Block Installation Figure B 1 Figure Description GPN or MIL spec Ref Multiple Conductor Shielded Cable 2 conductor shown in Figure B 1 Pans used depend on method chosen Parts used depend on method chosen Braid Flat 19 20 AWG equivalent tinned plated copper strands 36 Parts used depend AWG un Mil Area 1000 1300 on method chosen Parts used depend e Floating Shield Termination method optional On method ehos h Ring terminal 8 insulated 18 22 AWG MS25036 149 Ring terminal 8 insulated 14 16 AWG MS25036 153 Ring terminal 8 insulated 10 12 AWG MS25036 156 Screw PHP 8 32x 312 Stainless MS51957 42 Screw PHP 8 32x 312 Cad Plated Steel MS35206 242 Split Washer 8 045 compressed thickness Stainless MS35338 137 Split Washer 8 045 compressed thickness Cad plated steel
177. sues before replacing either unit Page 9 2 Installation Manual Troubleshooting Revision A 190 01115 01 93 GSU 73 GSU 73 ground operation is heavily dependent on GPS data inputs Be sure to correct any GPS performance problems i e interference caused by some types of cell phones or anything that transmits in the area before troubleshooting the GSU 73 GMU 44 For GPS data to be considered usable the receiver must be tracking at least 4 satellites and have a 3D GPS Solution GSU 73 AHRS operation needs at least two of the three inputs from the GPS receiver the GMU 44 and the Air data also part of the GSU 73 for proper operation See Table 9 1 below for the attitude and heading outputs the GSU 73 can provide based on the available data inputs Table 9 1 GSU 73 AHRS Operating Mode Table GSU 73 Mode GSU 73 Input GSU 73 Output GPS GMU44 data Air data data Heading Pitch Roll Primary Reversion No GPS Reversion No Mag Reversion No Mag No Air Coast On Gyros Output Unreliable For complaints concerning GSU 73 realignments performed while in the air i e the pilot feels that the realignment is taking too long or does not seem to be reinitializing Table 9 2 shows the pitch and roll limits that the pilot must maintain for the GSU 73 to realign itself If the pilot was performing maneuvers outside these limits the GSU 73 may not properly reinitialize Table 9 2 GSU 73 AHR
178. ticking in the overlay opening not by the card sticking to the socket inside the unit Try another card without a label if possible to confirm the problem before returning If the second card sticks the SD socket board inside the unit may be misaligned with the overlay and the GDU 37X will require repair If the thickness of the card was the cause see if more than one label was on the card If the labels weren t the cause determine what brand of SD card was being used Garmin recommends using SanDisk or Toshiba brand cards 9 1 2 Crosstalk Error Dual or Three Screen Systems Crosstalk Error messages occur if there is a mismatch in GDU 37X software versions If this occurs the GDU s will not communicate with each other and a software mismatch message will be reported on the INFO page press the MSG softkey Ensure both displays are running the same software version to clear the issue G3X Installation Manual Troubleshooting Page 9 1 190 01115 01 Revision A 9 2 GMU 44 Figure 9 1 Heading Failure Indication Full Screen PFD 9 2 1 Red X Failures If a Red X steady or intermittent is displayed on the heading Figure 9 1 check the following while the aircraft is on the ground 1 When taxiing without reliable GPS information heading performance is susceptible to the presence of magnetic anomalies metal buildings underground steel culverts steel grates in the ramp rebar Localized sources of interference on
179. to the page selection menu when finished 5 E DISTANCE NAUTICAL NM GROUNDSPEED NAUTICAL KT AIRSPEED NAUTICAL KT DIRECTION DISPLAY NUMERIC DEGREES TEMPERATURE FAHRENHEIT F ALTITUDE FEET FT VERTICAL SPEED FEET MINUTE PRESSURE INCHES HG FLUID VOLUME GALLONS US WEIGHT PouNps LBs LOCATION FORMAT HDDD MM MMM MAP DATUM WGS 84 HEADING AUTO MAG VARIATION MAG VARIATION OQ3 E G3X Installation Manual Software Configuration Databases and XM Activation Page 7 7 190 01115 01 Revision A 7 4 5 DSPL Display Configuration Page The DSPL Configuration Page allows setting the parameters for Display and Backlight Control configuration 1 Inconfiguration mode use the FMS Joystick to select the DSPL Page CONFIG DISPLAY ACFT UNITS SOUND COM 2 Use the FMS Joystick to select the desired configurable item and make the desired change Then press the ENT Key or use the FMS Joystick to select the next item Press the FMS Joystick to move the cursor to the page selection menu when finished 5 NI BACKLIGHT INTENSITY DEFAULT MODE INPUT VOLTAGE 0 0v BACKLIGHT LEVEL 100 BACKLIGHT OFF THRESHOLD 1 0v MIN BRIGHTNESS 3 0v MAX BRIGHTNESS 12 0v INPUT TYPE lev TIME CONSTANT 1 0 Page 7 8 G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 7 4 5 1 Display Configuration Window Backlight Intensity Can be
180. trip Quick Term Min to Quick Term Max Table B 7 length of the jacket to expose the shield Next trim the shield so that at most 0 35 inches remains extending beyond the insulating jacket Fold this remaining shield back over the jacket Page B 12 G3X Installation Manual Appendix B Revision A 190 01115 01 Connect a Flat Braid item 4 to the folded back shield of the prepared cable assembly The flat braid should go out the front of the termination towards the connector It is not permitted to exit the rear of the termination and loop back towards the connector Figure B 9 Make this connection using an approved shield termination technique NOTE FAA AC 43 13 1B Chapter 11 Section 8 Wiring Installation Inspection Requirements may be a helpful reference for termination techniques Preferred Method Slide a solder sleeve item 3 onto the prepared cable assembly item 2 and connect the Flat Braid item 4 to the shield using a heat gun approved for use with solder sleeves It may prove beneficial to use a solder sleeve with a pre installed Flat Braid versus having to cut a length of Flat Braid to be used The chosen size of solder sleeve must accommodate both the number of conductors present in the cable and the Flat Braid item 4 to be attached NOTE Reference Section B 3 2 for recommended solder sleeves and flat braid The same recommendations are applicable to this technique Sec
181. ts Check GSU 73 configuration module wiring for damage Replace if any is found Replace the GTP 59 OAT probe If the problem persists replace the GSU 73 with a known good unit OAT ___ F Figure 9 5 No info for TAS amp OAT TAS information can only be displayed at speeds greater than 20 Knots i e TAS is invalid when the aircraft is sitting still If the Airspeed and or Altitude is failed and shows a Red X condition as shown in Figure 9 6 Figure 9 6 Airspeed and Altitude Failure Indications G3X Installation Manual Troubleshooting Page 9 7 190 01115 01 Revision A 9 4 1 Inspect GSU73 pitot static plumbing integrity Inspect pitot static ports and associated equipment If the problem persists replace the GSU 73 with a known good unit Troubleshooting GSU 73 Engine Indication Failures See Figure 9 7 for example The following may help to determine to cause of an Engine Indication failure 1 2 Does cycling power restore operation Did the operator give it sufficient time to start and initialize Did the problem begin after a software or configuration load Did the problem happen on the ground or while airborne Is only the EGT Red X d If so the GSU 73 configuration module configuration module wiring thermocouple reference or applicable thermocouple is defective Check the wiring and replace the configuration module or applicable thermocouple Are there one or more temperatures that drop
182. ture aircraft Figure 6 31 illustrates the tube diameter d and minimum distance I references in the table x j TOP OF ANTENNA AT OR ABOVE O d CENTER OF THE TUBE STRUCTURE TOP OF ANTENNA BETWEEN CENTER AND BOTTOM OF THE TUBE STRUCTURE Figure 6 31 Example Teardrop Footprint Antenna Mounting Under Fabric Skin Table 6 7 Minimum Distance Required Between Tube Structure and Antenna Tube Diameter Minimum Distance Illustrated Case d in in Top of antenna at or above the center of the tube structure Figure 6 31 top Top of antenna between the center and bottom of the tube structure Figure 6 31 bottom Page 6 28 G3X Installation Manual Antennas Revision A 190 01115 01 7 Software Configuration Databases and XM Activation 7 1 Configuration Mode Some software loading and all configuration settings are performed in the configuration mode To enter configuration mode hold down the left hand softkey softkey 1 while powering on the GDU 37X If more than one GDU 37X is installed hold down softkey 1 on PFD 1 CONFIG MAIN WB UNITS DSPL SOUND NRST Softkey 1 7 2 Software Audio Data Identification 7 2 1 LRU Software Version Identification Do the following steps to verify the unit s current software version s 1 Turn on the unit in config
183. ua a sas 9 7 9 5 Troubleshooting On board the Aitrcraft enne nennen ener enne 9 10 9 65 GSU Pase s anan eden deeem enit ded eie e teet ende tiec benda 9 11 10 Return to Service Information seie reen orete Eea EERE Eae S ET R E ER EEE aa a 10 1 TOI GD WB Pee TS asc er a aia haus vane aa sa 10 1 102 GSU Lada 10 1 GMU AT 10 2 Installation Manual Page iii 190 01115 01 Revision A PARAGRAPH PAGE APPENDIX A G3X PitiOUtS erre esee HO TE qa ute VT LE isa A 1 PON QE 1 A2 E E 5 A3 GSU TI eit rete et Ra ec cote at de ede ee ee ae A 6 APPENDIX B Connector Installation Instructions n anus B 1 B 1 Thermocouple Installation into a Backshell aaa B 1 B 2 Jackscrew Configuration Module Installation into a Jackscrew Backshell B 3 B 3 Jackscrew Backshell Installation Instructions enne enne nene B 6 B 4 Circular Connector Installation Instructions B 19 APPENDIX C Outline and Installation Drawings enne nennen nennen C 1 APPENDIX D Interconnect D 1 APPENDIX
184. uired 12 16 16 Type of Rivets Required MS20426AD4 x MS20426AD4 x MS20426AD4 x Skin Preparation for Rivets Dimple Dimple Countersink Doubler Preparation for Rivets Countersink Countersink None Skin Cutout Detail GA 55A Figure 6 18 Figure 6 19 Figure 6 20 Doubler Installation Figure Figure 6 21 Figure 6 22 Figure 6 23 Notes 1 Rivet length determined at installation dependent on thickness of material rivet length grip length 1 5 rivet diameter 6 5 1 Preparation of Doubler 1 Use Garmin P N 115 00846 00 or refer to Table 6 6 for guidance on selecting the appropriate doubler drawing based on the thickness of skin at the antenna location Make the doubler from 2024 T3 Aluminum AMS QQ A 250 5 0 063 sheet thickness 2 For installation in aircraft skins of thickness less than 0 051 countersink the rivet holes in the doubler for use with flush head rivets MS20426AD4 x 3 When using Garmin P N 115 00846 00 doubler sixteen rivet holes exist in the part For installation of Garmin P N 115 00846 00 in skins of thickness between 0 032 and 0 049 only the rivets identified for use through the skin cutout detail Figure 6 18 and doubler installation Figure 6 21 are required Page 6 14 G3X Installation Manual Antennas Revision A 190 01115 01 6 5 2 Antenna Installation Instructions Refer to Table 6 6 and to Figures in Appendix C for guidance on selecting the appropriate mou
185. unted 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 G3X Installation Manual Antennas Page 6 3 190 01115 01 Revision A Figure 6 1 shows the recommended placement of antennas ANTENNA MASKED BY VERTICAL FIN T TAIL OR DORSAL FIN ANTENNA NOT MOUNTED LEVEL WITH RESPECT TO THE NORMAL FLIGHT ATTITUDE DISTANCE BETWEEN COM AND GPS ANTENNAS SHOULD BE GREATER THAN 2 FT SEE ITEM 4 a IN THIS SECTION FOR GPS ANTENNA LOCATION GOOD BETTER _ GREATER THAN 3 AFT OF WINDSCREEN NORMAL FLIGHT ATTITUDE SIDE VIEW o snrennamusrecon TOP OF AIRCRAFT CENTER LINE 1 TOP VIEW GPS ANTENNA OFFSET FROM CENTERLINE WITH TYPICAL DUAL GPS INSTALLATION Figure 6 1 Recommended Antenna Placement Page 6 4 G3X Installation Manual Antennas Revision A 190 01115 01 6 3 3 Buried Antenna below the skin covering or glareshield Mounting There are potential performance issues related to buried antennas that the kit builder installer should be aware of prior to electing to install a buried antenna See also Section 6 6 3 Non structural Installation to Glareshield e Some gain of the antenna may be lost as the signal needs to penetrate t
186. uration mode 2 Use the FMS Joystick to select the CONFIG MAIN page if needed CONFIG MAIN GSU W B UNITS DSPL SOUNI 3 Note the displayed software version CONFIG MAIN DEVICE SOFTWARE PRODUCT VERSION NUMBER vi MFD 2 12 006 B0746 XX G3X Installation Manual Software Configuration Databases and XM Activation Page 7 1 190 01115 01 Revision A 7 2 2 Audio Data Identification Do the following steps to view the unit s current audio data information 1 Turn on the unit in normal mode 2 Press the MENU key twice to display the Main Menu 3 Use the FMS Joystick to select Database Information MAIN MENU FLIGHT Loc TRACK LOG USER WAYPOINTS E6B CALCULATOR WEIGHT amp BALANCE DATABASE INFORMATION SYSTEM SETUP 4 Press the ENT key to display the Database Information page 5 Use the FMS Joystick to scroll down as needed to display the audio database information Page 7 2 G3X Installation Manual Software Configuration Databases and XM Activation Revision A 190 01115 01 7 3 Software Loading Procedure Software loading is performed in normal mode Sections 7 3 1 and 7 3 2 describe the GDU and GSU software load procedure 7 3 1 GDU Software Loading Procedure 1 Power on the GDU in normal mode then insert the properly formatted SD card into the SD card slot NOTE It is also acceptable to insert the SD card before powering on the unit 2 software u
187. uring that the 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 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 1 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 1 Mount the antenna on top of the aircraft in a location with an unobstructed view of the sky 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 see Section 1 7 3 for more GPS COM interference information 4a The GPS antenna should be
188. vironmental Specifications onte eit eie bed un eap E et LI Pe UTER SEES HE REEL e Fea 4 3 44 Installation Requirements ect RI enne ee ee ec e e iets reciben e E Re 4 3 45 Installation Considerations s usus ipti ed e e i dit ip dde eda 4 4 4 6 Mounting Requiremehts te ete e ee tete e lege Ua ai torpore diee 4 6 4 1 Unit Installation be ett cte PN eet tede ertet Ne Pe eed eo ote e yp Gs do 4 7 4 8 Maintenance a a SS ee EU ea d eU ER e eroi pides 4 8 Page ii G3X Installation Manual Revision A 190 01115 01 PARAGRAPH PAGE 5 RA I A IR Su 5 1 Sl Equipment 1 oni ieee Miter a tee nate eee a aoe rende 5 1 2 2 Anstallation Requirements 5 Pe pe te f e au e e EE efe eee 5 1 5 3 TSO ETSO Compliance iis ses o ee e HER HER be ta 5 2 5 4 Installation Considerations esses p q enne nnn hua a i s 5 3 5 97 Umit Installati nza ti hri ect b 5 4 5 6 c redet Peer E T ERROR ERE EA e QS bi ann deena ane Re 5 4 6 Garmin GPS XM Antennas einen denne bete en b de e 6 1 6 17 Antennas eese ede e a pe nd S 6 1 6 237 XM Antennas side ORO I PERDER ORE REPRE TERR an ein 6 1 6 3 Antenna Mounting Considerations snoeren niini ener nennen nennen pashpa kars 6 2 6 4 Teardrop Footprint Ante
189. wate SR STRINGER VIEW LOOKING DOWN SKIN OMITTED FOR CLARITY Figure 6 7 Sample Doubler Location Teardrop Footprint Antenna Metal Skin Aircraft Page 6 10 G3X Installation Manual Antennas Revision A 190 01115 01 ul 23 9 I e S x x Ce ee ee NG L i 4X 0 188 THRU SKIN i TO MATCH DOUBLER 9 iQ IQ i i 0 0 0 2 HOLES 9 1 00 25 4 E 4 23 107 4 a 2X 1 75 44 5 lt Oe 4 AG He ANTENNA OUTLINE 9 a 2 59 65 8 20 625 THRU SKIN NOTES 1 DIMENSIONS INCHES mm 2 DIMPLE SKIN FOR INSTALLATION OF FLUSH HEAD RIVETS Figure 6 8 Skin Cutout Detail Teardrop Footprint Antenna Skin Thickness 0 032 to 0 049 ES o e I amp a EA cM x DOUBLER OUTLINE 4X 00 188 THRU SKIN TO MATCH DOUBLER tO a i 0 0 0 2 HOLES En 6 1 00 25 4 9 4 23 107 4 2X 1 75 44 5 x O re UE m ANTENNA OUTLINE E 1 16 20 128 23 26 APO MC PELLE Boos THRU SKIN e 2 59 65 8 NOTES 1 DIMENSIONS INCHES mm 2 DIMPLE SKIN FOR INSTALLATION OF FLUSH HEAD RIVETS Figure 6 9 Skin Cutout Detail Teardrop Footpri
190. wrap between the wires and the clamp If the condition is not resolved by following the preceding instructions contact Garmin Product Support for additional assistance A Garmin Field Service Engineer may ask the technician to download the fault logs to a PC via the USB port on the GSU 73 and email the logs back to Garmin to help determine if the problem is in the GSU 73 or in the aircraft Page 9 10 Installation Manual Troubleshooting Revision A 190 01115 01 9 6 GSU Page All three status boxes on the GSU Page config mode must indicate a positive state green check marks before performing any calibration procedures Section 8 The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view of the sky to produce positive status indications a T NI NORMAL MODE MAGNETOMETER AIR DATA GPS GSU73 1 31 9 2005 08 GARHIN LTD OR SUBS SERIAL NUMBER 100000002 AHRS ORIENTATION CONFIG GSU MAIN eU ACFT W B UNITS DSPL Figure 9 8 CONFIG GSU Page G3X Installation Manual Troubleshooting Page 9 11 190 01115 01 Revision A This page intentionally left blank Page 9 12 Installation Manual Troubleshooting Revision A 190 01115 01 10 Return to Service Information These return to service procedures are intended to verify the serviceability of the appliance only These tests alone do not verify or otherwise validate the airworthine
191. y G3X Installation Manual Antennas Page 6 15 190 01115 01 Revision A 6 5 3 Reference Figures FORWARD 12X 20 128 CS K 20 225 x 100 AX 00 203 3 3X 00 625 AX RO 25 3 50 88 9 i 6X 3 20 81 3 _ 4 On 2X 2 55 64 8 D fo O Ii 2X 2 24 56 9 2X 1 75 44 5 a 710 2X 1 27 32 3 _1 2X 0 95 24 1 6 0 30 7 6 X9 e 0 063 1 60 ow dw io r co x N LO N Cc lt om 2 60 e 0 e o E MS gt N Oo c i EN EN x x N 0 688 17 48 0 344 8 74 20 203 2X 0 098 THRU 20 172 X 100 DETAIL 4 PLCS MS21047L3 NUTPLATE FARSIDE 5 MS20426AD3 4 RIVET 8X NOTES 1 DIMENSIONS INCHES mm 2 MATERIAL 0 063 THICKNESS 2024 T3 ALUMINUM AMS QQ A 250 5 3 TOLERANCE 0 030 0 010 4 REMOVE BURRS AND BREAK SHARP EDGES E OPTIONAL GA55A ANTENNA INSTALLATION 6 MS21059L3 MAY BE USED IN PLACE OF MS21047L3 Figure 6 14 Doubler Design ARINC 743 Footprint Antenna Skin Thickness 0 032 to 0 049 Page 6 16 G3X Installation Manual Antennas Revision A 190 01115 01 FORWARD 16X 20 129 CS K 20 225 x 100
192. ystem lines 4 5 Installation Considerations Fabrication of a wiring harness is required Sound mechanical and electrical methods and practices should be used for installation of the GSU 73 Refer to Section 1 6 for wiring considerations and to Appendix A for pinouts Connector kits include backshell assemblies The backshell assembly houses the configuration module P732 only and a thermocouple reference junction if applicable Garmin s backshell connectors give the installer the ability to quickly and easily terminate shield grounds at the backshell housing The instructions needed to install the Jackscrew Backshell Configuration Module and Thermocouple are located in Appendix B Page 4 4 Installation Manual GSU 73 Revision A 190 01115 01 4 5 1 Pneumatic Plumbing The GSU 73 has two ports that are connected to the aircraft s pitot pressure source and static pressure source The two ports are labeled on the unit see Figure 4 2 The pressure ports have 1 8 27 ANPT female threads The mating fitting must have 1 8 27 ANPT male threads LLLLLAT J732 cr Figure 4 2 GSU 73 Air Hose Fitting Locations Use appropriate air hoses and fittings to connect the pitot and static lines to the unit Avoid sharp bends and routing near aircraft control cables

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