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G300 Installation Manual – Installation Overview

Page 1-5

190-00921-01

Revision A

1.6

Wiring/Cabling Considerations

Use MIL-W-22759/16 (or other approved wire) AWG #24 or larger wire for all connections unless
otherwise specified. The standard pin contacts supplied in the connector kit 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, length 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 unless it is specified on aircraft manufacturer approved drawings.

Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference.
Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and
routing near aircraft control cables.

RG400 or RG142 coaxial cable with 50

Ω

nominal impedance and meeting applicable aviation

regulations should be used for the installation.

Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and
routing near aircraft control cables. Cabling for the G300 should not be routed near components or
cabling which are sources of electrical noise. Route the GPS antenna cable as far as possible away from
all COM transceivers and antenna cables.

1.6.1

Wiring Harness Installation

Allow adequate space for installation of cables and connectors. The installer shall supply and fabricate all
of the cables. 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.

CAUTION

Check wiring connections for errors before connecting any wiring
harnesses. Incorrect wiring could cause internal component damage.

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Summary of Contents for GMU 44

Page 1: ...190 00921 01 March 2009 Revision A G300 Installation Manual ...

Page 2: ... 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 151st Street Olathe KS 66062 USA T...

Page 3: ...0 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 VII Subchapter C and which may not be exported released or disclosed to foreign nationals inside or outside the United States without first obtai...

Page 4: ...tion Considerations 2 4 2 6 Mounting Requirements 2 4 2 7 Unit Installation 2 4 2 8 Continued Airworthiness 2 4 3 GMU 44 3 1 3 1 Equipment Description 3 1 3 2 Electrical Specifications 3 1 3 3 Environmental Specifications 3 2 3 4 Installation Requirements 3 2 3 5 Installation Considerations 3 2 3 6 GSU 73 GMU 44 Interconnect Harness Fabrication Instructions 3 5 3 7 Mounting Instructions 3 6 3 8 Co...

Page 5: ...M Activation 8 1 8 1 Configuration Mode 8 1 8 2 Software Audio Data Identification 8 1 8 3 Software Loading Procedure 8 3 8 4 Configuration Procedure 8 6 8 5 Garmin Database Updates 8 7 8 6 XM Activation Instructions GDU 375 only 8 9 9 Post Installation Checkout and Calibration Procedures 9 1 9 1 Required Test Equipment 9 2 9 2 GDU 37X Test Procedure 9 2 9 3 GSU 73 GMU 44 Post Installation Checkou...

Page 6: ...Installation 1 7 2 1 GDU 37X 2 1 2 2 GDU 37X Mounting Accessories 2 4 3 1 GMU 44 3 1 4 1 GSU 73 Unit View 4 1 4 2 GSU 73 Air Hose Fitting Locations 4 5 4 3 GSU 73 Orientation Calibration 4 6 5 1 GTP 59 5 1 6 1 Recommended Antenna Placement 6 2 9 1 Softkey Positions 9 1 9 2 Aircraft Alignment 9 10 10 1 Heading Failure Indication Full Screen PFD 10 2 10 2 Attitude Air Data and Engine Airframe Failur...

Page 7: ...3 B 4 1 GTP 59 O A T Probe Wiring Detail B 15 LIST OF TABLES TABLE PAGE 1 1 G300 LRU Part Numbers 1 3 1 2 G300 LRU Power Requirements 1 3 1 3 G300 LRU Physical Specifications 1 3 1 4 G300 LRU Environmental Forms 1 4 1 5 Pin Contact and Crimp Tools Part Numbers 1 6 2 1 GDU 37X Supply Voltages 2 2 2 2 GDU 37X Power Requirements 2 2 2 3 GDU 37X GPS Specifications 2 2 2 4 GDU 37X Recommended Antennas ...

Page 8: ...lation 5 2 7 1 SL40 Required Equipment 7 1 7 2 SL40 Installation Kit w Out Connectors 013 00121 20 7 1 7 3 SL40 Installation Kit D Sub 15 Pin 013 00121 30 7 1 7 4 SL40 Installation Kit RF Plug 013 00121 40 7 1 7 5 GTX 327 Required Equipment 7 2 7 6 Contents of GTX 320 327 Connector Kit 011 00651 01 7 2 7 7 Contents of Transponder Back Plate w Hex Kit 011 00677 01 7 2 9 1 Post Installation Calibrat...

Page 9: ...ETHER 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 ...

Page 10: ... 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 SO...

Page 11: ...lock diagram is given to aid in the understanding of the system This section also contains generic information that pertains to all components of the G300 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 the GMU...

Page 12: ...t panel or in a separate avionics bay if desired This design greatly eases troubleshooting and maintenance of the G300 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...

Page 13: ...nts LRU Supply Voltage Current Draw GDU 37X 9 29 Vdc 1 07 Amp 14Vdc 0 54 Amp 28Vdc GMU 44 12Vdc from GSU 73 Inc in GSU Current Draw GSU 73 9 29 Vdc 1 75 Amp 14Vdc Max 0 80 Amp 28Vdc Max 1 4 3 Physical Specifications All width height and depth measurements are taken with unit rack if applicable and connectors Table 1 3 G300 LRU Physical Specifications LRU Width Height Depth GMU 44 Diameter includin...

Page 14: ...SU 73 should be mounted in a location that provides adequate airflow to comply with the maximum outer case temperature listed in Section 4 NOTE Avoid installing the G300 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 b...

Page 15: ...ear aircraft control cables RG400 or RG142 coaxial cable with 50 Ω nominal impedance and meeting applicable aviation regulations should be used for the installation Check that there is ample space for the cabling and mating connectors Avoid sharp bends in cabling and routing near aircraft control cables Cabling for the G300 should not be routed near components or cabling which are sources of elect...

Page 16: ...G 336 00022 01 Positronic P N 9502 5 M81969 1 04 for size 22D pins and M81969 1 02 for size 20 pins M22520 2 01 NOTES 1 Insertion Extraction tools from ITT Cannon are all plastic others are plastic with metal tip 2 Non Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice 1 6 2 Cable Location Considerations Use cable meeting the applicable avi...

Page 17: ...for the 50 62 and 78 pin connectors must be crimped onto the individual wires of the aircraft wiring harness Table 1 5 list contact part numbers for reference and recommended crimp tools 1 6 4 Backshell Assemblies Connector kits include backshell assemblies The backshell assembly houses the configuration module and a thermocouple reference junction if applicable Garmin s backshell connectors give ...

Page 18: ...ntenna 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 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 anten...

Page 19: ... 1 Flight Instrument Functions Display of attitude pitch and roll rate of turn slip skid heading airspeed altitude and vertical speed information single display installation or on an MFD in reversionary mode Display of engine and airframe instrumentation single display installation on a PFD in reversionary mode or on an MFD 2 1 2 Navigation Functions Display of position and ground speed Display of...

Page 20: ...5 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 WAAS enabled high sensitivity GPS receiver that continuously tracks and uses up to 12 satellites to compute and update it s 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 a...

Page 21: ...7X has an Operating Temperature Range of 20 C to 60 C 2 4 Installation Requirements 2 4 1 Required Accessories Each of the following accessories is provided separately from the GDU 37X unit and is required to install the unit Figure 2 2 Table 2 5 GDU 37X Required Accessories Item Garmin P N Quantity GDU 37X Connector Kit 011 01921 00 1 Configuration Module w Sockets Jackscrew required for PFD only...

Page 22: ...nate shield grounds at the backshell housing The instructions needed to install the Jackscrew Backshell 190 00313 11 and Configuration Module 190 00313 10 can be downloaded from the Dealer portion of the Garmin website www garmin com 2 6 Mounting Requirements Refer to Appendix B 1 for outline and installation drawings 2 7 Unit Installation The GDU 37X is installed by holding the unit flush with th...

Page 23: ...ong life solid state sensing technology the GMU 44 Magnetometer uses magnetic field measurements to create an electronically 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 GMU 44 to GSU 73 Interfac...

Page 24: ... Considerations 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 re...

Page 25: ...c 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 interfer...

Page 26: ...ame 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 ...

Page 27: ...ional 0 Parts used depend on method chosen 2 Shield Extension Wire 0 M22759 16 22 3 4 9 GMU 44 Connector Kit 1 011 00871 00 5 3 Conductor Cable 0 M27500 22TE3T14 6 2 Conductor Cable 0 M27500 22TE2T14 Table 3 7 lists material in the GMU 44 connector kit and the associated reference number as shown in Figure B 2 4 The GMU 44 magnetometer has an attached pigtail with male polarity The harness connect...

Page 28: ...MU 44 Place the connector at least 2 inches 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 NOTE If the GMU 44 is ever removed t...

Page 29: ...ing 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 Operation is not...

Page 30: ... AHRS Engine Airframe Magnetic Heading 28 Analog inputs including those allocated as per below Pitch Angle Dedicated Ammeters 2 Roll Angle Constant Current Source Capability 6 Linear Accelerations Divider Circuits to handle large input voltages 12 Pitch Roll Yaw Rotation Rates Frequency Counter Inputs 4 Discrete I O 4 In 2 Out 4 2 Electrical Specifications Table 4 1 GSU 73 Supply Specifications Ch...

Page 31: ...e 450 Knots Aircraft Mach Range 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 1 Required Equipment Table 4 3 lists the kits available for the GSU 73 Table 4 3 GSU 73 Available Equipment Item Garmin P N Quantity Configuration Module w EEPROM and Jackscrew Kit 011 00979 20 1 ...

Page 32: ... appropriate aircraft fittings to connect to pitot and static system lines 4 5 Installation Considerations Fabrication of a wiring harness is required Sound mechanical and electrical methods and practices are required for installation of the GSU 73 Refer to Section 1 6 for wiring considerations Appendix A 3 for pinouts Connector kits include backshell assemblies The backshell assembly houses the c...

Page 33: ... for any flight condition Refer to part 43 Appendix E for approved practices while installing hoses and connections 4 5 2 Pneumatic Connections The installer is required to fabricate pneumatic hose connections and attach the aircraft pitot pressure source and aircraft static pressure source to the GSU 73 CAUTION Check pneumatic connections for errors before operating the GSU 73 Incorrect plumbing ...

Page 34: ...n in Figure 4 3 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 ma...

Page 35: ...ft 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 B 3 of this manual 1 Assemble the wiring harness and backshell connectors 2 Assemble the pneuma...

Page 36: ...Page 4 8 G300 Installation Manual GSU 73 Revision A 190 00921 01 This page intentionally left blank ...

Page 37: ...owing part number Table 5 1 GTP 59 Part Number Item Garmin Part Number GTP 59 OAT Probe Kit 011 00978 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 Item Garmin P N Quantity Nut 5 16 Hex Skirt 210 00055 00 1 Screw 4 40 x 2...

Page 38: ... 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 3 2 GTP 59 OAT Probe Installation NOTE The following instructions are general guidance Table 5 3 contains a list of parts needed for the GTP 59 installation and interconnect harness Reference numbers in the table and instructions refer...

Page 39: ... probe Holding the OAT probe on the inside tighten the nut 5 to 100 inch lbs 20 inch lbs 3 Route the OAT probe cable 3 to the GSU 73 4 Cut the OAT Probe cable 3 to the required length Strip back 2 0 to 3 5 of jacket while retaining the shield on the OAT Probe cable 3 Trim away enough to leave 0 5 of shield exposed 5 Strip back 1 8 0 125 of insulation and crimp pins 11 to each of the conductors in ...

Page 40: ... 190 00921 01 5 4 Unit Installation Refer to Figure B 4 1 GTP 59 O A T Probe Wiring Detail for wiring and mounting instructions 5 5 Continued Airworthiness Maintenance of the GTP 59 is on condition only Periodic maintenance of the GTP 59 is not required ...

Page 41: ...he 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 4a The GPS antenna should be 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 frequ...

Page 42: ...Page 6 2 G300 Installation Manual Antennas Revision A 190 00921 01 Figure 6 1 below shows the recommended placement of antennas Figure 6 1 Recommended Antenna Placement ...

Page 43: ...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 4 Antenna Grounding The antenna is grounded through the mounting hardware and the coax ...

Page 44: ...Page 6 4 G300 Installation Manual Antennas Revision A 190 00921 01 This page intentionally left blank ...

Page 45: ... Installation Kit D Sub 15 Pin OEM 013 00121 30 1 SL40 Installation Kit RF Plug OEM 013 00121 40 1 Table 7 2 SL40 Installation Kit w Out Connectors 013 00121 20 Item Garmin P N Quantity Cable Tie 202 0001 2 Shoulder Bushing 204 2100 2 4 40 x SS pan head Phillips machine screw w lock washer 221 0400 4 4 40 x SS flat head Phillips machine screw 224 0404 6 Mounting frame 310 5181 01 1 Connector mount...

Page 46: ...ck 115 00431 00 1 Table 7 6 Contents of GTX 320 327 Connector Kit 011 00651 01 Item Garmin P N Quantity Nut Plate D Sub 25 Pos 125 00046 00 1 Screw 4 40x 500 FLHP100 SS P Nyl 211 63234 12 2 Tubing Ht Shrink Tfl FEP 093 ID 312 00005 05 6 Conn D Sub Mil Crp Sckt 25 ckt 330 00184 25 1 Bkshl D sub Metal 25Pos 330 00220 25 1 Cont Sckt Mil Crp Size 20 336 00022 00 28 Cont Sckt Mil Crp Sz 20 18 AWG 336 0...

Page 47: ... To enter configuration mode hold down the left hand softkey while powering on the GDU 37X In a two display system hold down the left hand softkey on the PFD while powering on the unit 8 2 Software Audio Data Identification 8 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 configuration mode 2 Use the FMS Joystick...

Page 48: ...ollowing steps to view the unit s current audio data information 1 Turn on the unit in normal mode 2 Press the ENT key twice to display the Main Menu 3 Use the FMS Joystick to select Database Information 4 Press the ENT key to highlight the database information 5 Use the FMS Joystick to scroll down as needed to display the audio database information ...

Page 49: ...he Garmin folder or use the provided software update application 2 Copy all configuration ini files to the Garmin config folder 8 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 A Software update window will appear on the screen highli...

Page 50: ...ernal GDU memory If the current GSU software is different than the GSU software stored in GDU memory a GSU software update message will be displayed on the MESSAGES page The MESSAGES page is accessed by pressing the MESSAGES softkey on the INFO page 2 Turn the GDU off and then back on in configuration mode An UPDATE SW softkey is shown on the GSU page in configuration mode only when an update is a...

Page 51: ...0921 01 Revision A 5 If the update is successful an UPDATE COMPLETE message appears press the ENT key to acknowledge the completion 6 An unsuccessful update is indicated by an UPDATE FAILED message Attempt the load again or reload GDU software and then attempt to load the GSU software again ...

Page 52: ... to select the FILE Page 1 Use the FMS Joystick to select Airframe if not already selected and press the ENT Key 2 Use the FMS Joystick to select Cessna 162 Baseline Configuration if not already selected and press the ENT Key 3 Use the FMS Joystick to select Yes if not already selected to load the C162 Baseline Configuration and press the ENT Key 4 Ensure that a green checkmark appears beside the ...

Page 53: ...mpatible 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 NOTE Perform the following steps on the PFD only After the data has been copied to the SD card perform the following steps 1 Insert the SD card in the car...

Page 54: ... Basemap The basemap database 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 database 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 ...

Page 55: ...D to send an activation signal that allows the G300 MFD to display weather data and 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...

Page 56: ...Page 8 10 G300 Installation Manual Software Configuration Databases and XM Activation Revision A 190 00921 01 This page intentionally left blank ...

Page 57: ...ositive 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 9 1 to select a calibration procedure Softkey 1 Softkey 2 Softk...

Page 58: ...t 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 Outdoor line of site to GPS satellite signals or GPS indoor repeater Digital Level or equivalent 9 2 GDU 37X Test Procedure Test the GPS Receiver 1 Power on unit and use the FMS Joystick to select the Info Page 2 Veri...

Page 59: ... 9 3 190 00921 01 Revision A Test the XM Receiver if applicable 1 Power on unit and use the FMS Joystick to select the XM Page 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 ...

Page 60: ...which GMU 44 alignment is not within 0 5 of aircraft longitudinal axis E Engine Run Up Vibration Test Validate vibration characteristics of installation Procedure E is required for all installations F 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 e...

Page 61: ... the heading offset compensation The addition removal or modification 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...

Page 62: ... indicate a positive state green check marks 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 Use the FMS Joystick to select AHRS ORIENTATION if not already selected 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key 7 Determine the direction the ...

Page 63: ...irection of the GSU 73 connectors per the on screen instructions select OK and press the ENT Key to continue 10 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 ...

Page 64: ...se the FMS Joystick to select the GSU Page if needed 3 Unlock the GSU Page by pressing softkeys 2 3 4 in order if needed 4 Ensure that all three status boxes indicate a positive state green check marks 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 Use the FMS Joystick...

Page 65: ... 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 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 ...

Page 66: ...ircraft 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 away from th...

Page 67: ... that all three status boxes indicate a positive state green check marks 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 On the GSU Status Page use the FMS Joystick to select MAGNETOMER 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key ...

Page 68: ...f turn from the last heading the PFD instructs the operator to stop the aircraft NOTE 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 ...

Page 69: ...imum of 2 successful stations per quadrant is required where a successful station is a full 18 second countdown followed by instruction to move Ensure that if stations are skipped at least a minimum of 2 stations per quadrant are completed Thus it may sometimes be required to dwell at a station after a countdown restart A maximum of 30 stations is allowed for the entire calibration procedure If to...

Page 70: ... 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 softke...

Page 71: ... button at the bottom of the display press the ENT Key to begin the calibration 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 turns 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...

Page 72: ...ation Procedures Revision A 190 00921 01 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 73: ...on 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 3 Unlock the GSU Page by pressing softkeys 2 3 4 in order if needed 4 Ensure that all three status boxes indicate a positive state green check marks The GMU 44 and GSU 73 units must be communicating with the GDU 37X and the GPS antenna must have clear view o...

Page 74: ... 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 ...

Page 75: ...of balance NOTE In some aircraft attempting the engine runup test on a day with very strong and or gusty winds may cause the test to occasionally fail However windy conditions should not be taken as evidence that the test would pass in calm conditions an actual pass is required before the installation can be considered adequate 10 After a few minutes the calibration will finish and a Done button w...

Page 76: ... 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 GRS 77 AHRS Calibration Procedures A through D are not required prior to this execution of this procedure NOTE Garmin recommends this test be performed at least once every 1...

Page 77: ... 190 00921 01 Revision A 5 Use the FMS Joystick to select MAGNETOMETER INTERFERENCE TEST 6 Use the FMS Joystick to highlight the Calibrate button press the ENT Key 7 Ensure that the aircraft has been properly prepared per the on screen instructions See Table 9 2 for a sample test sequence ...

Page 78: ...perator should carry out the actions called for in the prepared test sequence NOTE 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 that a MAG INTERFERENCE TEST PASSED message appears at the bottom of the display ...

Page 79: ...ously 4 20 Beacon on 4 30 Beacon off 4 40 Pitot heat on 4 50 Pitot heat off 5 00 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 t...

Page 80: ...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 2 ...

Page 81: ... counter clockwise directions for the site to be considered acceptable More than one failure out of ten attempts in a given direction would be sufficient reason to conclude the site is not acceptable A site that is used repeatedly to perform the Magnetometer Calibration Procedure should be re evaluated every 12 months and after any significant construction or placement of magnetic objects above or...

Page 82: ...Page 9 26 G300 Installation Manual Post Installation Checkout and Calibration Procedures Revision A 190 00921 01 This page intentionally left blank ...

Page 83: ...ility especially if there is more than one label on the card This is usually caused by the card sticking 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...

Page 84: ... 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...

Page 85: ...lid Valid Reversion No GPS Bad Good Good Valid Valid Valid Reversion No Mag Good Bad or anomaly Good Invalid Valid Valid Reversion No Mag No Air Good Bad or anomaly Bad Invalid Valid Valid Coast On Gyros Bad Either or Both Bad Invalid Invalid Invalid Output Unreliable Bad Either or Both Bad Invalid Invalid Invalid For complaints concerning GSU 73 realignments performed while in the air i e the pil...

Page 86: ... the problem occurred on the ground was it within 100 feet of a hanger using GPS repeaters 4 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 5 Was the problem correlated with a specific maneuver or a specific geographic area 6 Can the problem be repeated reliably 7 Were an...

Page 87: ...nstallation Manual Troubleshooting Page 10 5 190 00921 01 Revision A Figure 10 2 Attitude Air Data and Engine Airframe Fail Indication Reversionary or Split Screen PFD Figure 10 3 Attitude Fail Indication PFD ...

Page 88: ...alibrated 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 are 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 fl...

Page 89: ...and or OAT indications are dashed out as shown in Figure 10 5 NOTE TAS information can only be displayed at speeds greater than 20 Knots i e TAS is invalid when the aircraft is sitting still Figure 10 5 No info for TAS OAT 1 Check the GTP 59 OAT probe wiring and connection for faults 2 Check GSU 73 configuration module wiring for damage Replace if any is found 3 Replace the GTP 59 OAT probe 4 If t...

Page 90: ...couple reference or applicable thermocouple is defective Check the wiring and replace the configuration module or applicable thermocouple 6 Are there one or more temperatures that drop as the electrical load increases If a temperature probe shorts usually where the bayonet is crimped a ground loop is created forcing the reference lo side to increase which causes the temperature reading to decrease...

Page 91: ...G300 Installation Manual Troubleshooting Page 10 9 190 00921 01 Revision A Figure 10 7 Attitude Heading Air Data and Engine Airframe Failure Reversionary or Split Screen PFD ...

Page 92: ... 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 4 Ensure that the GSU 73 is mounted securely If any doubt exists use a screwdriver to check the tightness of the four mounting screws 5 Look in the vicinity of the GSU 73 for any heavy objects that may not be fastened tight to the str...

Page 93: ...n the GSU Page config mode must indicate a positive state green check marks before performing any calibration procedures Section 9 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 Figure 10 8 CONFIG GSU Page ...

Page 94: ...Page 10 12 G300 Installation Manual Troubleshooting Revision A 190 00921 01 This page intentionally left blank ...

Page 95: ...ses If the correct software version is not installed update the displays to the current G300 system software available on the web No configuration is required as a long as the configuration module is still operational Continue to Section 11 2 11 1 4 New GDU 37X PFD Configuration Module Installed Ensure that a new configuration module is obtained for the replacement installation If a new configurat...

Page 96: ...ws 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 11 3 1 GMU 44 is Reinstalled Any time a GMU 44 is reinstalled a new magnetometer calibration is required Section 9 2 6 Continue to Section 11 3 2 11 3 2 New GMU 44 Installed If a new GMU...

Page 97: ...ARE 7 SPARE 8 SPARE 9 CDU SYSTEM ID PROGRAM 2 In 10 CDU SYSTEM ID PROGRAM 1 In 11 RS 422 OUT A Out 12 RS 422 OUT B Out 13 RS 232 OUT 3 Out 14 RS 232 IN 2 In 15 POWER GROUND 16 POWER GROUND 17 CONFIG MODULE POWER OUT Out 18 MONO AUDIO OUT LO 19 STEREO AUDIO OUT RIGHT Out 20 STEREO AUDIO OUT LO 21 SPARE 22 SPARE 23 SPARE 24 SPARE 25 CDU SYSTEM ID PROGRAM 3 In 26 28V LIGHTING BUS HI In 27 SIGNAL GROU...

Page 98: ...ER 1 and AIRCRAFT POWER 2 are diode ORed to provide aircraft power redundancy Pin Name Connector Pin I O AIRCRAFT POWER 1 P3701 32 In AIRCRAFT POWER 2 P3701 31 In POWER GROUND P3701 15 POWER GROUND P3701 16 A 1 3 PFD Mode Selections Configure single display installation as PFD1 per the following table Configure the optional MFD unit as MFD per the following table PFD MODE 1 P3701 Pin 10 PFD MODE 2...

Page 99: ...n I O RS 422 OUT A P3701 11 Out RS 422 OUT B P3701 12 Out A 1 4 3 CAN Bus This data bus conforms to the BOSCH standard for Controller Area Network 2 0 B This bus complies with ISO 11898 Pin Name Connector Pin I O CAN BUS HI P3701 46 I O CAN BUS LO P3701 45 I O CAN BUS TERMINATION P3701 28 A 1 4 4 Configuration Module Pin Name Connector Pin I O CONFIG MODULE CLOCK P3701 33 I O CONFIG MODULE DATA P3...

Page 100: ...701 1 Out MONO AUDIO OUT LO P3701 18 A 1 6 2 Stereo Audio Pin Name Connector Pin I O STEREO AUDIO OUT LEFT P3701 3 Out STEREO AUDIO OUT LO P3701 20 STEREO AUDIO OUT RIGHT P3701 19 Out STEREO AUDIO OUT LO P3701 2 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 101: ... 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 Pin Name Connector Pin I O 12 VDC POWER GMU 44 P441 9 In POWER GROUND GMU 44 P441 6 A 2 3 Serial Data A 2 3 1 RS 232 The RS 232 outputs conform to EIA TIA 232C with an output voltage swing of at least 5 V when driving a standard RS 232 load Pin Name Conne...

Page 102: ...e 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 table additional tables group pin connections by function Pin Pin Name I O 1 MAGNETOMETER RS 485 IN B In 2 MAGNETOMETER RS 485 IN A In 3 SIGNAL GROUND 4 GSU SYSTEM ID PROGRAM 1 In 5 GSU SYSTEM ID PROGRAM 2 In 6 RESERVED 7 CAN BUS HI I O 8...

Page 103: ... 2 A In 28 ARINC 429 IN 2 B In 29 CAN BUS TERMINATION 30 ARINC 429 IN 3 A In 31 ARINC 429 IN 3 B In 32 ARINC 429 IN 4 A In 33 ARINC 429 IN 4 B In 34 SIGNAL GROUND 35 SIGNAL GROUND 36 SIGNAL GROUND 37 SIGNAL GROUND 38 MAGNETOMETER POWER OUT Out 39 MAGNETOMETER GROUND 40 SIGNAL GROUND 41 SPARE 42 SPARE 43 SIGNAL GROUND 44 SPARE 45 SPARE 46 SPARE 47 AIRCRAFT POWER 1 In 48 SPARE 49 AIRCRAFT POWER 2 In...

Page 104: ...3 ANALOG IN 6 LO In 14 ANALOG IN 12 LO In 15 OAT PROBE IN HI In 16 OAT PROBE POWER OUT Out 17 FREQUENCY COUNTER IN 1 In 18 SIGNAL GROUND 19 FREQUENCY COUNTER IN 2 In 20 CONFIG MODULE CLOCK Out 21 ANALOG IN 2 HI In 22 ANALOG IN 3 LO In 23 ANALOG IN 8 HI In 24 ANALOG IN 9 HI In 25 ANALOG IN 14 HI In 26 ANALOG IN 16 HI In 27 ANALOG IN 24 HI In 28 ANALOG IN 23 HI In 29 ANALOG IN 11 LO In 30 ANALOG IN ...

Page 105: ...UT Out 56 TRANSDUCER POWER OUT LO GROUND 57 TRANSDUCER POWER OUT LO GROUND 58 10 VDC TRANSDUCER POWER OUT Out 59 CONFIG MODULE POWER OUT Out 60 ANALOG IN 4 HI In 61 ANALOG IN 1 HI In 62 ANALOG IN 10 HI In 63 ANALOG IN 7 HI In 64 ANALOG IN 15 HI In 65 ANALOG IN 17 HI In 66 ANALOG IN 25 HI In 67 ANALOG IN 22 LO In 68 ANALOG CURRENT MONITOR IN 2 LO In 69 ANALOG IN 21 HI In 70 ANALOG CURRENT MONITOR I...

Page 106: ...32 12VDC TRANSDUCER POWER OUT OUT 56 P732 TRANSDUCER POWER OUT LO GROUND 58 P732 10VDC TRANSDUCER POWER OUT OUT 57 P732 TRANSDUCER POWER OUT LO GROUND 75 P732 5VDC TRANSDUCER POWER OUT OUT 74 P732 TRANSDUCER POWER OUT LO GROUND A 3 3 3 Magnetometer Power The GSU 73 outputs supply voltage to the GMU 44 via pins 38 39 Pin Connector Pin Name I O 38 P731 MAGNETOMETER POWER OUT OUT 39 P731 MAGNETOMETER...

Page 107: ... Pin Connector Pin Name I O 20 P731 ARINC 429 OUT 1A OUT 21 P731 ARINC 429 OUT 1B OUT 22 P731 ARINC 429 OUT 2A OUT 23 P731 ARINC 429 OUT 2B OUT 25 P731 ARINC 429 IN 1A IN 26 P731 ARINC 429 IN 1B IN 27 P731 ARINC 429 IN 2A IN 28 P731 ARINC 429 IN 2B IN 30 P731 ARINC 429 IN 3A IN 31 P731 ARINC 429 IN 3B IN 32 P731 ARINC 429 IN 4A IN 33 P731 ARINC 429 IN 4B IN A 3 5 2 RS 232 Input Output The RS 232 o...

Page 108: ...nd of the bus Pin Connector Pin Name I O 7 P731 CAN BUS HI I O 8 P731 CAN BUS LO I O 29 P731 CAN BUS TERMINATION A 3 5 5 Configuration Module Interface Pin Connector Pin Name I O 20 P732 CONFIG MODULE CLOCK OUT 39 P732 CONFIG MODULE DATA I O 59 P732 CONFIG MODULE POWER OUT OUT 78 P732 CONFIG MODULE GROUND A 3 6 Discrete I O A 3 6 1 Active Low Discrete Inputs The GSU 73 has 4 configurable discrete ...

Page 109: ...s achieved via software configuration When Disabled Hardware scaling is 1 1 and input impedance is greater than 10 MΩ When Enabled Hardware scaling is approximately 45 1 and input impedance is approximately 100 kΩ Voltage Measurement Ranges There are six voltage measurement ranges for analog inputs 25 mV 55 mV 100 mV 1 0 Vdc 2 5 Vdc and 5 0 Vdc Applies to both 1 1 and 45 1 scaling Effective voltag...

Page 110: ...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 I...

Page 111: ...32 ANALOG CURRENT MONITOR IN 2 LO IN 10 P732 THERMOCOUPLE REF IN HI IN 9 P732 THERMOCOUPLE REF IN LO IN 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...

Page 112: ... FREQUENCY COUNTER IN 1 IN 19 P732 FREQUENCY COUNTER IN 2 IN 36 P732 FREQUENCY COUNTER IN 3 IN 38 P732 FREQUENCY COUNTER IN 4 IN Indicates Active Low The following table lists the minimum frequency maximum frequency and duty cycles for each of these inputs Pin Name Minimum Frequency Maximum Frequency Duty Cycle FREQUENCY COUNTER IN 1 1 Hz 950 Hz 50 FREQUENCY COUNTER IN 2 1 Hz 100 KHz 50 FREQUENCY ...

Page 113: ...3 198 8 6 04 153 4 2 98 75 8 3 89 98 7 2X 1 72 43 7 004 0 1 1 09 27 7 86 7 3 41 59 15 0 1 08 27 5 6 32 CAPTIVE SCREW 4 PLCS 5 47 139 1 7 25 184 2 3 41 86 7 28 7 2 29 7 3 93 23 7 2X 2 34 59 4 1 92 48 7 4 50 114 4 XM CONN GPS CONN NOTES DIMENSIONS INCHES MM 1 DIMENSIONS ARE SHOWN FOR REFERENCE ONLY 2 FRONT SURFACE OF PANEL Figure B 1 1 GDU 37X Outline Drawing ...

Page 114: ...1 R 39 TYP 10 0 19 TYP 4 9 1 24 31 5 0 0 0 1 50 38 0 3 67 93 1 3 67 93 1 2X 3 58 91 1 2X 3 58 91 1 0 0 0 2 78 70 7 2X 2 69 68 4 2 78 70 7 2X 2 69 68 4 2 21 56 2 C L C L 011 01747 GDU 37x OUTLINE REF NOTES 1 DIMENSIONS INCHES mm 2 DIMENSIONS SHOWN FOR REFERENCE ONLY PANEL CUTOUT GDU 37x UNIT 011 01747 CONNECTOR KIT 011 01921 00 Figure B 1 2 GDU 37X Panel Cutout Drawing ...

Page 115: ...AFT MOUNTING INSTRUCTIONS OF THE GRS 77 AHRS AND GMU 44 MAGNETOMETER UNIT 3 FOLLOW FORWARD AND TOP INDICATIONS ON UNIT AND RACK 2 51 2 49 63 75 63 25 164 4 17 THRU IN THIN MATERIAL USING LOCKING NUTS OR DRILL AND TAP 6 32 UNC IN MATERIAL THICKER THAN 3 16 4 8 3 PLCS 3X 213 OPTIONAL CLEARANCE HOLES FOR HOLD DOWN SCREWS 3X 120 120 0 1 256 31 90 2 511 63 79 0 725 18 42 2 175 55 25 061 1 54 2 572 65 3...

Page 116: ...on A 3 37 85 60 2 10 53 34 2 38 60 33 1 84 46 61 8 4 214 3 8 AIRCRAFT MOUNTING SURFACE NOTES 1 DIMENSIONS IN INCHES mm GMU 44 INSTALLATION FROM ABOVE PREFERRED GMU 44 AIRCRAFT MOUNTING RACK 6 32 100 FLAT HEAD BRASS SCREWS REQUIRED 6 32 PAN HEAD BRASS SCREWS 0 24 6 1 MAX THREAD LENGTH WITHOUT CLEARANCE HOLES Figure B 2 2 GMU 44 Top Mounted Installation ...

Page 117: ...sion A GMU 44 6 32 100 FLAT HEAD BRASS SCREWS REQUIRED 6 32 PAN HEAD BRASS SCREWS 0 24 6 1 MAX THREAD LENGTH WITHOUT CLEARANCE HOLES AIRCRAFT MOUNTING RACK 2 23 56 52 2 38 60 33 8 4 214 3 370 85 60 3 8 AIRCRAFT MOUNTING SURFACE NOTES 1 DIMENSIONS IN INCHES mm GMU 44 INSTALLATION FROM BELOW NOT PREFERRED Figure B 2 3 GMU 44 Bottom Mounted Installation ...

Page 118: ...INGS GMU 44 G300 Installation Manual Outline Installation Drawings Page B 11 Page B 12 blank 190 00921 01 Revision A NOTE 1 BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLES 3 6 AND 3 7 Figure B 2 4 GMU 44 Wiring Detail ...

Page 119: ...LOCATION INCLUDES UNIT WITH CONNECTOR KITS 4 186 2 139 8 5 50 2X 2X 7 33 1 45 36 7 PITOT AIR FITTING 1 8 27 ANPT FEMALE THREAD 1 8 27 ANPT FEMALE THREAD P732 STATIC AIR FITTING P731 49 8 3 96 1 96 2X 100 6 22 1 29 7 1 17 87 TYP 5 50 139 7 SEE NOTE 3 210 5 33 40 25 6 4 65 16 6 127 0 5 00 2X 4 50 4X 114 3 10 2 2X 4 25 108 0 GSU 73 UNIT 011 01817 00 P731 CONNECTOR KIT 011 01818 00 P732 CONNECTOR KIT ...

Page 120: ...M27500 22TE3V14 CABLE LENGTHTO BE 10 FEET 6 INCHES 4 16 AWG WIRE M22759 16 16 LENGTH OF WIRE OUTSIDE OF CASE TO BE 3 5 INCHES 0 25 0 5 SOLDER TERMINAL MS25036 109 6 SHIELD OF CABLE ELECTRICALLY CONNECTED TO 16 AWG WIRE 7 BUBBLE NUMBERS IN THIS DRAWING REFER TO REFERENCE NUMBERS LISTED IN TABLE 5 3 255 0 57 1 57 50 050 SEE NOTE 2 5 16 32 UNEF 2A 02 x 45 CHAMFER 03 x 45 CHAMFER SEE NOTE 4 SEE NOTE 3...

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