L3 Communications GH-3100, Pilot'S Manual

Page 1: ...Pilot s Guide for the Electronic Standby Instrument System Model GH 3100 Software Version 1 x and 3 x ...

Page 2: ...cedence over this guide Disclaimer This Pilot s Guide is subject to change without notice The illustrations in this guide are typical to the GH 3100 but may not exactly match your configuration options Export Notice This data is provided at no charge or at cost to the public and is considered publicly available No License Required NLR as defined in the Export Administration Regulations EAR Part 73...

Page 3: ...F THE BEST PARTS NO MOVING PARTS A HISTORY OF LEADING EDGE INNOVATION In addition to the GH 3100 ESIS Avionics Systems also develops and manufactures the RGC 350 Radar Graphics Computer Stormscope weather mapping systems Skywatch Traffic Advisory System TCAS I collision avoidance systems electromechanical standby attitude indicators and power conversion products Avionics Systems also maintains a g...

Page 4: ...entification Mode 17 Sensor Alignment Mode 20 Normal Operating Mode Invalidity Indications 21 Troubleshooting 26 Specifications 28 Notes 30 Pilot s Guide for the GH 3100 Electronic Standby Instrument System Software Version 1 x 3 x Part No 501 1860 xxx1 501 1860 xxx3 Copyright 2003 2007 2009 L 3 Avionics Systems Inc 5353 52nd Street S E Grand Rapids MI USA 49512 9704 Customer Support 800 453 0288 ...

Page 5: ... of display arrangements and colors are dependent on the unit s specific configuration as it is applied in specific aircraft installations The Model GH 3100 ESIS Electronic Standby Instrument System provides backup pitch roll and slip skid information and backup Air Data information airspeed altitude and vertical speed using internal sensor systems Also the system contains interface capabilities t...

Page 6: ...tion specific to the hardware and software configuration for each installation such as panel angle navigation interface aircraft heading calibration and display format When the GH 3100 is removed from the aircraft the DCM remains in the aircraft attached to the aircraft wiring harness that mates with the GH 3100 eliminating the need to re configure a replaced GH 3100 Line Replaceable Unit LRU GH 3...

Page 7: ...s of length behind the instrument panel At a maximum weight of 4 pounds the GH 3100 offers exceptional weight savings by combining the functions of three existing instruments into one The weight decrease is up to half the weight of today s typical electromechanical systems Equipment Description cont ...

Page 8: ...erts magnetic field data into a digital format for the GH 3100 indicator Heading information is displayed on a horizontal tape at the bottom of the GH 3100 display The DCM 3100 is the memory device that stores the indicator s display configuration The device remains in the aircraft to allow the removal and replacement of the GH 3100 indicator unit thus allowing automatic configuration to the repla...

Page 9: ... Button located below the Display Screen A menu listing will appear along the bottom portion of the Display Screen with four line items visible at a time Rotate the Adjustment Knob located below and to the right of the Display Screen to scroll through the Menu and highlight a Menu item Menu items that Toggle ON OFF will indicate opposite the current condition Menu Items that are followed by indica...

Page 10: ...ditional adjustments and selections To select or adjust a value in the Sub Menu rotate the Adjustment Knob To Toggle ON OFF initiate a highlighted Menu item or to finalize an adjusted value press the Adjustment Knob Menu access will terminate when a setting is initiated or by pressing the Menu Access Button Menu access termination will occur automatically after 15 20 seconds of inactivity ...

Page 11: ...press knob to initiate SET BRIGHTNESS OFFSET press knob for sub menu rotate knob to adjust press knob to finish FAST ALIGN press knob to initiate SET HEADING press knob for sub menu rotate knob to set heading press knob to NAV ON or OFF press knob to toggle for opposite of current condition NAV MODE press knob for sub menu rotate knob to select mode press knob to SET CRS press knob for sub menu ro...

Page 12: ...are made by rotating the Adjustment Knob located below and to the right of the Display Screen To establish Standard Pressure Barometric Setting 29 92 InHg 1013 HPA or MB push the Adjustment Knob STD will be indicated at the Barometric Setting window Menu access will allow the flight crew to select barometric types as Inches of Mercury in Hectopascals hPa or Millibars mb See page 5 ...

Page 13: ...u d e Information is provided in the center portion of the Display Screen Pitch and roll data is generated by internal sensors that produce recognizable attitude indications Attitude information is displayed in a manner similar to traditional Artificial Horizon and Slip Skid Indicators ...

Page 14: ...d Heading displays The GH 3100 will self correct for small Attitude errors or the flight crew may initiate a FAST ERECT from the Menu see page 7 when the aircraft has returned to straight and level non accelerated flight If the GH 3100 continues to display erroneous attitude the flight crew may then initiate a FAST ALIGN from the Menu page 7 when the aircraft has returned to straight and level non...

Page 15: ...d and Altitude information is displayed in a scrolling Tape format with Digital Readout windows available for airspeed altitude vertical speed and metric equivalent altitude dependent on unit configuration Altitude Information is located on the right side of the Display Screen The appearance of the Digital Readouts andAltitude Tapes is dependent upon the specific configuration for the GH 3100 Poss...

Page 16: ... Possible Airspeed Readouts Air Data Information cont Airspeed Information is located on the left side of the Display Screen The appearance of the Digital Readouts andAirspeedTapes is dependent upon the specific configuration for the GH 3100 ...

Page 17: ...ce with the Attitude Information Navigation displays are designed to visually match the look and format of the primary navigational systems in the cockpit Crew member inputs i e frequency and station selections are made at the source navigational units with exception to those Navigation items configured for and available through the Menu access see page 5 ...

Page 18: ...Pilot s Guide 14 GH 3100 Screen Features Navigation Information cont ...

Page 19: ...no longer exceeds these conditions Navigation Information cont Software Versions and Navigation Configuration Options Unit with 1 x software and configured for ARINC 710 ILS Receiver will have the VOR ILS NAV Mode replaced with ILS Mode in the sub menu Unit with 3 x software and configured for ARINC 710 ILS Receiver will have the first VOR ILS NAV Mode replaced with ILS Mode in the sub menu and th...

Page 20: ...external heading source If the DG indication continues use the Menu access to select the Set Heading option and align the Heading Tape to the cockpit reference compass See page 7 The To arrow will point up on the Heading Tape at the selected course setting The From arrow points down on the tape at 180 of the course setting See page 7 for Set CRS and CRS Auto Center Menu options If the GH 3100 is c...

Page 21: ...he GH 3100 starts an automatic process of self diagnostics prior to normal operations After power application the Display Screen will be blank approximately 15 seconds while the tests are performed If no failures were detected during the Power ON Self Test Mode the Identification Screen will appear Identification Mode ...

Page 22: ...e either System Failures or Function Failures System Failures will cease the start up process where as Function Failures will complete start up process and allow the system to operate despite the loss of the affected function See Invalidities see page 20 NOTE Use the provided Notes pages see page 30 to record the date and time and error message code Report the information to aAvionics Systems auth...

Page 23: ...g Perform a Power Reset to allow unit to perform the internal diagnostics and possibly correct the fault condition A similar condition will appear with the System Test Failure and a Red X Again perform a Power Reset Repeated unsuccessful resets confirm thattheunitrequiresservice and or repair NOTE Use the provided Notes page see page 30 to record the date and time and error message code Report the...

Page 24: ...er During abnormal conditions such as motion during the Sensor Alignment Mode the indicator will reset and attempt to reach the Normal Operation Mode within six minutes of applying power If sensor alignment is unsuccessful the message will change to ALIGNMENT FAILand the system will not enter the operational mode See Troubleshooting see page 25 NOTE Use the provided Notes pages see page 30 to reco...

Page 25: ...y indications that reveal a loss of information from their associated sources The invalidities are detected during the GH 3100 s Power ON Self Test or by the continuous Background Self Test They may appear as either of the examples offered here dependent on unit configuration Air Data information will revert to normal display when invalidity conditions no longer exist The GH 3100willcontinuetooper...

Page 26: ... Attitude Failure will appear as either of the examples offered here dependent upon unit configuration The Heading Tape will always appear invalid simultaneously with ATT FAIL Heading and Attitude Invalidities internal sensor source must be reported Air Data and Navigation information will continue to display if those sources are still valid NOTE Use the provided Notes pages see page 30 to record ...

Page 27: ...ashes color dependent on unit configuration in the navigation value field Because Navigation information displayed on the GH 3100 originates from the aircraft s primary navigational units those units must be checked when invalidities occur NOTE Use the provided Notes pages see page 30 to record the date and time and error message code Report the information to aAvionics Systems authorized dealer o...

Page 28: ...ckground Self test diagnostics can not correct the condition the unit will then display the System Test Failure error message combined with the Red X Bring the aircraft to straight and level non accelerated flight then reset recycle the power to the GH 3100 Repeated unsuccessful resets confirms that the unit requires service and or repair NOTE Use the provided Notes pages see page 30 to record the...

Page 29: ...utomatically the system will prompt the flight crew to intervene to prevent any loss of display Bring the aircraft to straight and level non accelerated flight then reset recycle the power to the GH 3100 NOTE Use the provided Notes pages see page 30 to record the date and time and error message code Report the information to aAvionics Systems authorized dealer or Avionics Systems Field Service as ...

Page 30: ...orted toAvionics Systems See page 24 WARNING displays across the screen The unit is prompting the flight crew to Power Reset Attempt recycle of power at straight and level non accelerated flight to correct condition Note the error message code indicated on Identification Screen and report to Avionics Systems See page 25 Identification Screen continues to display at unit start up The unit has suffe...

Page 31: ...onal message Aligning No action is required Obvious discrepancy of pitch roll indicators to that of true flight Initiate FAST ERECT similar to Caging when the aircraft is stationary or in straight and level non accelerated flight If condition continues perform FASTALIGN approx 90 seconds Initiate either action from the unit s MenuAccess see page 10 Report to Avionics Systems if discrepancy becomes...

Page 32: ...ystems P N 563 1113 01 mates with MS3116F18 32S solder contacts or MS3126F18 32S front crimp contacts or MS3476L18 32S rear crimp contacts with M85049 52S18W strain relief Connector J2 Avionics Systems P N 563 1013 21 for interface port to DCM 3100 and diagnostic port Static Air Port IAW MS33649 05 Pitot Air Port IAW MS33649 04 Service Life Repairable by an authorized commercial instrument repair ...

Page 33: ...equirements 1 5 watts maximum operating power at 28 0 Vdc During power on tests the maximum power shall not exceed 2 5 watts Weight Not to exceed 0 5 pounds 0 23 kg Dimensions Magnetometer is approximately 2 30 inches 5 84 cm in diameter by 2 12 inches 5 38 cm high with a 2 38 inch 6 05 cm diameter mounting lip Connector P1 JT06RE 10 35P SR P1 mates with JT01RE 10 35S SR Straight Strain Relief or ...

Page 34: ...Pilot s Guide 30 Notes ...

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Page 36: ...L 3 Avionics Systems Inc 5353 52nd Street S E Grand Rapids MI USA 49512 9704 Telephone 800 453 6600 International 616 949 6600 www as l 3com com GH 3100 Software Version 1 x 3 x TP 560 Rev F 07 22 09 ...