Garmin G1000 Checkout Procedure
  1. Manuals
  2. Brands
  3. Garmin Manuals
  4. Autopilot System
  5. Cessna Caravan G1000
  6. Checkout procedure

Garmin G1000 Checkout Procedure

Post installation checkout procedure hawker / beechcraft king air c90
Hide thumbs Also See for G1000:
Table of Contents

Advertisement

Quick Links

G1000 / GFC 700 Post Installation Checkout Procedure
Hawker / Beechcraft King Air C90
PRESS TO TEST
28
ALT
2992 1013
30
50
300
100
250
150
200
190-00682-00
January 2008
Revision 5

Advertisement

Table of Contents
loading

Related Manuals for Garmin G1000

Summary of Contents for Garmin G1000

  • Page 1 G1000 / GFC 700 Post Installation Checkout Procedure Hawker / Beechcraft King Air C90 PRESS TO TEST 2992 1013 190-00682-00 January 2008 Revision 5...
  • Page 2 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...
  • Page 3 IMPORTANT All G1000 screen shots used in this document are current at the time of initial publication. Screen shots are intended to provide visual reference only. All information depicted in screen shots, including software file names, versions and part numbers, is subject to change and may not be up to date.
  • Page 4 This page intentionally left blank Page ii G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 5: Table Of Contents

    5.1 Procedure A: GRS 77 Pitch/Roll Offset Calibration ................5-1 5.2 Engine Start............................5-2 5.3 Final GRS 77/GMU 44 Calibration Procedures.................. 5-3 G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page iii 190-00682-00 Revision 5...
  • Page 6 Figure 5-4. Magnetometer Interference Test ....................5-8 Figure 7-1. Pre-Flight Test ........................7-1 LIST OF TABLES Table 1-1. Referenced Documentation .....................1-2 Table 5-1. Magnetometer Interference Test Sequence ................5-9 Page iv G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 7: Introduction

    Scope This document presents the post-installation procedures which are required to be performed after installing the G1000 Integrated Cockpit System in the Hawker Beechcraft King Air C90 series aircraft. This document and revision are effective for the following aircraft: G1000 System...

  • Page 8: Reference Documents

    Panel, Main Instrument, G1000, C90 115-00862-XX Cable Assy, GFC 700, C90 233-20006-XX Wire Harness Assy, G1000/GFC 700, King Air 320-00326-XX C90A/C90GT Table 1-1. Referenced Documentation Page 1-2 G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 9: System Description

    • GSA 80 Servos (Yaw, Pitch & Roll) • GSA 81 Servos (Pitch Trim) • GSM85 Servo Mount • GSM85A Servo Mount G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Page 1-3 190-00682-00 Revision 5...

  • Page 10: Figure 1-1. G1000 & Gfc 700 In King Air C90A/C90Gt

    Engine / Airframe Engine / Airframe Adapter Adapter PC-920 Unit Unit FF Signal Conditioner Figure 1-1. G1000 & GFC 700 in King Air C90A/C90GT G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Page 1-4 190-00682-00 Revision 5...
  • Page 11 1.4.2 GFC 700 Operation The GFC 700 is a fail-passive digital flight control system composed of multiple G1000 LRUs and servos. The following functions are provided by the GFC 700 in this installation: • Flight Director • Autopilot • Pitch Trim •...

  • Page 12: G1000 Control Interface

    1.5.5 GDC 74B Air Data Computer The Garmin GDC 74B processes data from the pitot/static system as well as the OAT probe. This unit provides pressure altitude, airspeed, vertical speed and OAT information to the G1000 system, and communicates with the on-side GIA 63W, on-side GDU 1040A and on-side GRS 77, using an ARINC 429 digital interface.
  • Page 13 GTX 33 Mode S Transponder The Garmin GTX 33 Mode S Transponder provides Mode A, C, and S capabilities for ATC, TIS and TCAS I surveillance requirements. The GTX 33s interface with the No. 1 and No. 2 GIA63W G1000 LRUs via RS-232.
  • Page 14 This page intentionally left blank Page 1-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 15: Post Installation Procedures

    Before installing hardware, the technician must first ensure that hardware part numbers are compatible with the G1000/C90 loader card that is to be used. A G1000/C90 loader card is required to install software and configuration settings to a newly installed G1000 system. The part number of this card is directly associated with the combination of software file part numbers and version levels that are defined on the card.

  • Page 16: G1000 Software/Configuration Procedure

    The following diagram depicts an overview of the software/configuration sequence for the G1000 system. If any problems are encountered during the loading process, see Section 2.17. It is extremely important that each LRU software load be completed successfully.
  • Page 17 “System Status” page . Do not remove power. 8. Remove the G1000/C90 Loader Card from PFD2 and insert it into the top card slot on the MFD. Repeat Steps 3 through 6 for the MFD, using the far right softkey on the MFD in lieu of the ENT key where called out in Steps 3 through 6.
  • Page 18 FMS knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” and press ENT on PFD1. Note: The PRODUCT window displays information regarding each G1000 LRU. The LRU column depicts the reported software version of the LRU, whereas the CARD VERS column shows the LRU software version stored on the Loader Card.

  • Page 19: Software Load Confirmation

    2. Select the System Status page using the small FMS knob. Activate the cursor and toggle to the LRU window. 3. Highlight each of the following items in the LRU window, and verify that the software part number and version matches the information in G1000/GFC 700 AFCS, King Air C90A/GT 005-00375-22 General Arrangement drawing. Control & Display...
  • Page 20 Arrangement drawing, or if the software is not successfully loaded, DO NOT continue with post- installation procedures. Troubleshoot and resolve the issue before continuing (see Section 2.17). Page 2-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 21: King Air C90 Airframe Configuration

    4. Use the FMS inner knob to select the correct configuration file as determined above. 5. Verify the correct configuration file is displayed in the “FILE” window (for example “King Air C90A – Config 7”) then press “LOAD”. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-7 190-00682-00...
  • Page 22 2. Activate cursor in AIRFRAME window and rotate PFD1 FMS inner knob to display drop down menu. Highlight “C90-Weight and Airspeed” and press ENT key on PFD1. Page 2-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 23 Green “PASS” in Configuration column. b. “Upload Complete………….COMPLETE” in the summary box. key to acknowledge upload complete. 7. Select PFD1 ENT G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-9 190-00682-00 Revision 5...
  • Page 24 2. Verify the correct airspeed configuration, as loaded in step 2.5.5, is displayed in the “AIRSPEED” window. Aircraft LJ-1063 through LJ-1137, and LJ-1146: Vyse = 107 kts, Vmca = 90 kts , Vs = 89 kts Page 2-10 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 25: Traffic System Option Configuration

    Follow this procedure to enable the traffic system function for the G1000 system if required. NOTE The G1000 can only be configured for TIS or TAS but not both. Performing this procedure will automatically disable the TIS function. Coordinate this configuration with section 4.3 “Traffic System Functional Check”.

  • Page 26: Stormscope (Wx-500) Option Configuration

    7. Green “PASS” in Configuration column. 8. “Upload Complete………….COMPLETE” in the summary box. 9. Select PFD1 ENT key to acknowledge upload complete. 10. Deactivate cursor. Page 2-12 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 27 No Fla Flag Sense +invld J3-4 Open Hdg Value <aircraft heading> Inhibit Line Antenna Mount Bottom J3-3 Open 2. Deactivate the cursor G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-13 190-00682-00 Revision 5...
  • Page 28 StormScope Configuration Page (Reference Only) NOTE The DATA window is only updated once every five seconds. Page 2-14 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 29: Adf - 60 Option Configuration

    7. Green “PASS” in Configuration column for GIA1, GMA PIL and GMA COPIL. 8. “Upload Complete………….COMPLETE” in the summary box. 9. Select “ENT” to acknowledge upload complete. 10. Deactivate cursor. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-15 190-00682-00 Revision 5...

  • Page 30: Flitecharts Configuration

    ADF etc will need to be re-enabled per the instruction contained in this document. NOTE The G1000 can only be configured for FliteCharts or ChartView but not both. Performing this procedure will automatically disable the ChartView function. Coordinate this configuration with section 3.17 “FliteChart Functional Checks”.

  • Page 31: Chartview Configuration

    The required ChartView databases are subscription-based and are to be procured by the installing agency directly from Jeppesen. NOTE The G1000 can only be configured for FliteCharts or ChartView but not both. Performing this procedure will automatically disable the FliteChart option. Coordinate this configuration with section 3.18 “ChartView Functional Checks”.

  • Page 32: Taws Configuration

    11. View the SUMMARY field and ensure that the item is ‘COMPLETE’. 12. De-activate the cursor. 13. Power down the system and remove the TAWS Enable card from PFD1. Page 2-18 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 33: Aircraft Registration Number Entry

    2. Insert an SD card containing current Terrain/Obstacle database cards into the lower slots of PFDs and MFD. Refer to the General Arrangement drawing for correct card part numbers. 3. Close PFD1, PFD2 and MFD circuit breakers. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-19 190-00682-00...

  • Page 34: Aviation Database Loading

    MFD, count 2 keys to the left). Re-power MFD. When prompted to clear user settings select the YES softkey. Page 2-20 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 35: Software/Configuration Troubleshooting

    Check and ensure that correct Card Loader was used during load process. Refer to the General Arrangement Drawing. • Reload software to LRU. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-21 190-00682-00 Revision 5...
  • Page 36 GIA 63Ws must be successfully configured with GIA1 and GIA2 configuration files. - GTX 33 • Data path from GIA1 to each LRU must be operational. Page 2-22 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 37: G1000 Initial System Testing

    Verify the absence of red Xs or alert messages. Select, or verify selected, on-side sensors for PFD1 and PFD2. 2. Open PFD1 PRI CB. Verify PFD1 remains powered and no other changes occur to any G1000 or G1000 interfaced system.
  • Page 38 40. Open AUDIO 1 CB. Verify GMA1 is not powered. 41. Close AUDIO 1 CB. Verify GMA1 is powered. 42. Open AUDIO 2 CB. Verify GMA2 is not powered. Page 3-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 39 • XPDR 1 57. Open AVIONICS NO 3 CB. Verify the following are not powered: • GDL 69 • Stormscope • TCAS G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-3 190-00682-00 Revision 5...
  • Page 40 • STBY ATT indicator motor • STBY ALT vibrator • STBY ATT, STBY Airspeed, and STBY ALT lighting 69. Select STANDBY BATTERY switch OFF (extended). Page 3-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 41: Electrical Load Test Procedures

    TAIL FLOOD LIGHT – OFF • PROP SYNC – OFF (extended) • STANDBY BATTERY – OFF (extended) • CABIN BAR – OFF G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-5 190-00682-00 Revision 5...
  • Page 42 • DATA LINK • RADIO ALT (if installed) • ADF • STORM SCOPE • TRFC • MFD • VOICE RECORDER • CABIN AUDIO Page 3-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 43 BEACON LIGHTS switch to ON • STROBE LIGHTS switch to ON • TAIL FLOOD LIGHT switch to ON • LEFT/RIGHT LANDING LIGHTS switch to ON G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-7 190-00682-00 Revision 5...
  • Page 44 Table 1 as DP2. 10. Turn off all switches referenced in paragraph 8. 11. Configure the aircraft to measure G1000/GFC700 system loads by making or verifying the following switch selections: 12. Ensure that the circuit breakers in paragraph 5 are closed with the exception of RADAR circuit breaker.
  • Page 45 Tune VHF COMM NO. 1 to a frequency appropriate for test transmissions. Transmit on COMM No. 1 (no modulation is necessary). 13. Observe the G1000/GFC700 DC electrical load from the amp meter and record in Table 1 as DP3. 14. Discontinue transmitting on COM 1. Disengage Autopilot 15.

  • Page 46: Display Testing

    Display Testing The G1000 system is tested while operating in the normal mode unless otherwise specified. If the system is in configuration mode, restart the displays by cycling the PFD1, PFD2 and MFD circuit breakers to start the display in the normal mode.

  • Page 47: Figure 3-2. Pfd Power-Up System Annunciations

    ALERTS softkey to view alert messages). If any MANIFEST errors appear, the correct software to the related LRU must be loaded before proceeding (refer to Section 2). G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-11...
  • Page 48 7. Close PFD1 (PRI) and PFD1 (SEC) circuit breakers and de-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD1 and MFD return to normal display modes Page 3-12 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 49: Gps Signal Acquisiton

    DIFF NAV on the MFD. (The GIA 63W units should normally acquire a 3D GPS navigation solution within 2 minutes of startup, provided the aircraft is outside or indoors with a GPS repeater). G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-13 190-00682-00...

  • Page 50: Gma 1347D Testing

    PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator on GMA1 flashes ~ once per second during PA address. Repeat using copilot hand mic. Page 3-14 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 51: Vhf Comm Operational Check

    6. During the transmit period, verify that the GPS “INTEG” flag does not come into view on either PFD and verify that GPS1 does not lose a 3-D navigation solution on the MFD. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-15...

  • Page 52: Vor/Loc/Gs Test

    A VSWR of 3:1 may result in up to a 50% loss in transmit power. Ideally, the VSWR should be 2.5:1 or less. Page 3-16 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 53: Gtx 33 Testing

    GTX 33 Testing Operation of the GTX 33 Mode-S transponder is accomplished using PFD1, PFD2 or MFD. Refer to G1000 in Hawker Beechcraft King Air C90A/GT Cockpit Reference Guide, Garmin P/N 190-00664-00, for basic operation. 1. Ensure XPDR NO 1 CB is closed and open XPDR NO2 CB. Ensure XFR on the AFCS mode controller is coupled left as indicated by a left pointing arrow.

  • Page 54: Pitot Static System Leak Checks

    30,000 ft and airspeed of 226 knots. When pitot pressure has stabilized, verify and record the cumulative leak rate is 1 knot/minute or less. AIRSPEED kts/min: Page 3-18 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 55: Gdc 74B Testing

    MFD will apply to the values displayed on PFD1 in configuration mode for both ADC1 and ADC2 regardless of the sensor selected on the MFD. The copilot's display can be ignored. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-19 190-00682-00...
  • Page 56 +/-5 28000 +/-50 +/-50 +/-170 +/-2 +/-2 +/-5 23000 +/-50 +/-50 +/-145 +/-2 +/-2 +/-5 8000 +/-60 +/-60 +/-60 +/-2 +/-2 +/-5 Page 3-20 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 57 OAT Probe Check Ensure on-side sensors for PFD1 and PFD2. Verify that the outside air temperature (OAT) measurement shown on PFD1 and PFD2 indicates ambient temperature. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-21 190-00682-00...

  • Page 58: Gdl 69A Functional Check

    6. Plug a set of headphones into the pilot and co-pilot stations and verify that you can hear the XM radio playing in both channels. Page 3-22 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 59 9. Release the stall warning transducer in the left wing leading edge, verify the following: • Stall warning tone is silenced and annunciation extinguishes. 10. Verify XM audio returns. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-23 190-00682-00...
  • Page 60 GDL69 discrete inputs from stall warning and landing gear control systems as detailed in 005-W0022-00 “Wiring Diagram, G1000 / GFC 700 King Air C90A/GT” are required for aircraft not equipped with a tone generator. This procedure is applicable to SN LJ-1268.
  • Page 61 • Stall warning tone is silenced and annunciation extinguishes. • Pilot and copilot XM audio remains muted. 16. On the MFD deselect mute softkey or adjust XM volume. Verify XM audio returns. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-25 190-00682-00...

  • Page 62: Gea Functional Check

    Air (A/B/C/E) Series Maintenance Manual Part No. 90-590012-13 Revision B11 or later, section 77-00-00. • • • • Torque and • Fuel Flow Page 3-26 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 63: Taws Functional Check

    IOI – Warning: Obstacle (2X), Pull Up (2X) 11. Pull the PFD1 PRI and PFD1 SEC circuit breakers, and re-power PFD1 in normal operating mode. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-27 190-00682-00...

  • Page 64: Flitecharts Functional Check

    7. Press the CHRT OPT softkey and verify Terminal Chart is displayed and the softkeys advance to the following: • ALL • FIT WDTH • FULL SCN • BACK Page 3-28 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 65: Chartview Functional Check

    9. Turn either GCU FMS knob to scroll through the available charts and select a chart for viewing by pressing the GCU ENT key to complete the chart selection and verify the appropriate ChartView chart is displayed. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-29 190-00682-00...

  • Page 66: Safetaxi Functional Check

    7. Using the GCU range knob, select a range of 5000ft or less. Verify SafeTaxi display represents the current aircraft location and the airport layout. Page 3-30 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 67: Aircraft Weight Configuration Functional Check

    Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to increase the CARGO weight to 110. Verify the ZERO FUEL WEIGHT value is 9010 and displayed in amber G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-31 190-00682-00...
  • Page 68 Select the EMPTY WT softkey. Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the entry. Page 3-32 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 69 Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight value to zero (0). Verify that AIRCRAFT WEIGHT value is 9650 and displayed in cyan. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 3-33...
  • Page 70 This page intentionally left blank Page 3-34 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 71: Interface Testing

    This section describes the checks that must be completed in order to verify the system interface to the G1000. The checks must be completed only for those systems that are installed. Following the interface verification with the G1000, additional system checks may be required – refer to the appropriate system installation manual for additional details.

  • Page 72: Optional Stormscope Functional Check

    14. Use the F1 and F2 keys to adjust range and F3 and F4 keys to adjust heading. NOTE The WX-500 will plot data at one-half the range selected on the WX-PA Page 4-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 73 26. On the MFD, verify the positioning of test strikes within are within 10 degrees of azimuth and within 2 NM of 7.5 NM. 27. Restart the G1000 in configuration mode by opening the PFD and MFD circuit breakers. While holding the ENT keys on the PFDs and MFD, restore power by closing the PFDs and MFD circuit breakers.

  • Page 74: Optional Traffic System Functional Check

    NOTE If the ALT MODE softkey is not displayed, the G1000 has not been properly configured for the traffic system. Reference section 2.6 “Traffic System Configuration Option to enable the traffic system.

  • Page 75: Optional Dme Functional Check

    This check verifies that the DME-to-G1000 interface operates correctly. NOTE Support for a single Collins DME-42 system is provided as an option in the G1000. If the DME option is selected the DME channel one audio level must be adjusted by the procedure contained within Collins DME-42 Transceiver Repair Manual 523-0772458-00611A, Maintenance Section 523-0772460-006118 to adjust DME channel one audio level.

  • Page 76: Optional Adf Functional Checks

    5. Increment the ADF volume control from full low to full high. Verify the volume increases and decreases appropriately over pilots and copilots headset and cockpit speaker. Page 4-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 77: Grs 77/Gmu 44 Initial Alignment And Stby Compass Calibration

    Follow the checklist items displayed on PFD1 and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 5-1 190-00682-00...

  • Page 78: Engine Start

    To carry out the remaining GRS/GMU procedures, the aircraft engines must be started in accordance with Hawker / Beech C90 engine starting and operating procedures. Prior to engine start, verify all engine/airframe sensor operation by compliance with G1000 / GFC 700 Power On and Functional Checkout for Raytheon / King Air C90B 190-00682-04. Perform remaining GRS/GMU calibrations listed in Section 5.3.

  • Page 79: Final Grs 77/Gmu 44 Calibration Procedures

    Magnetometer Calibration Procedure. A G1000-equipped C90 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.
  • Page 80 CALIBRATION IS NOT PERFORMED ON A MAGNETICALLY CLEAN COMPASS ROSE OR EQUIVALENT. 4. Restart PFD1 in configuration mode. 5. Go to the GRS Page Group on PFD1. Page 5-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 81 PFD1 to conclude this procedure. 16. Repeat Steps 8 – 15 for the GRS2. 17. Proceed to Section 5.3.3 for the engine run-up procedure. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 5-5 190-00682-00...
  • Page 82 7. Press the ENT key on PFD1 to conclude this procedure. 8. Repeat Steps 2 – 7 for GRS2. 9. Proceed to Section 5.3.4. Page 5-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 83: Figure 5-3. Ahrs Information Valid

    Figure 5-3 (provided both GPS receivers have a valid position; if GPS is unavailable, AHRS initialization may take as long as 2 minutes). Figure 5-3. AHRS Information Valid G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 5-7 190-00682-00...

  • Page 84: Figure 5-4. Magnetometer Interference Test

    4. Select MAG INTERFERENCE TEST and press the PFD1 ENT key. 5. Follow the checklist items displayed on the PFD1, and press the ENT key as each one is completed or confirmed. Page 5-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 85: Table 5-1. Magnetometer Interference Test Sequence

    It is important that the “time equals zero” moment corresponds with the moment PFD1 first displays the blinking TEST COMPLETE? message. 7. The operator should carry out the actions called for in the prepared test sequence. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 5-9 190-00682-00...
  • Page 86 Any maximum deviation value greater than 5.0 milliGauss 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.

  • Page 87: Final System Checkout

    Final System Checkout The final checkout tests exercise various secondary communications paths in the G1000 to ensure that the desired backup paths are in place. Additional aircraft systems checks are also performed in this section. Perform the following steps and verify the results of each test.

  • Page 88: Gia Failure Test

    • An amber BOTH ON GPS1 is displayed on PFD1 and PFD2. • AHRS and ADC data remain valid on PFD1 and PFD2. Page 6-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 89: Display Failure Test

    IAS NO COMP illuminates on PFD1 − ALT NO COMP illuminates on PFD1 • GMA2 Fail – GMA2 is inoperative. • XPDR2 Fail – XPDR2 is Inoperative. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 6-3 190-00682-00 Revision 5...
  • Page 90 ROLL NO COMP illuminates on PFD2 − PIT NO COMP illuminates on PFD2 − IAS NO COMP illuminates on PFD2 − ALT NO COMP illuminates on PFD2 Page 6-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 91: Cooling Fan Failure Annunciations

    • The STBY attitude motor and STBY altimeter vibrator remain active. • Visible white portion of the STANDBY BATTERY switch remains illuminated full bright. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 6-5 190-00682-00 Revision 5...
  • Page 92 • The STBY altimeter vibrator is deactivated. • Visible white portion of the STANDBY BATTERY switch extinguishes. Page 6-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 93: G1000 Backup Path Tests

    8. On PFD1, activate the cursor and select MFD1 in the SELECT UNIT field and press the ENT key. 9. Repeat Steps 4 and 5. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 6-7 190-00682-00...
  • Page 94 18. Observe the data indicators for all configured RS-485 channels. 19. Verify all DATA indicators are GREEN, indicating the channels are receiving data as shown: Page 6-8 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 95 20. Activate the cursor and select GIA2 in the SELECT UNIT field, then press the ENT key. 21. Repeat Steps 18 and 19. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 6-9 190-00682-00 Revision 5...
  • Page 96 This page intentionally left blank Page 6-10 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 97: Gfc 700 Ground Checks

    The following procedure will verify the proper operation of the GFC 700 AFCS. This procedure is designed to test the installation of the AFCS only after the G1000 testing in Sections 3 through 6 has been conducted. The technician performing these checks must be thoroughly familiar with the GFC 700.

  • Page 98: Afcs Switch Checks

    AFCS Mode Controller. Press the AP/YD DISC TRIM INTRPT switch on the pilot side to disconnect the autopilot; verify the flashing amber ‘AP’ alert is displayed on PFD1 & 2. Page 7-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 99: Autopilot Clutch Overpower Check

    HDG key on the AFCS mode controller. Verify the command bars are level and the control wheel is stationary. (There may be some roll motion in the yoke if the aircraft not perfectly level.) G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 7-3...
  • Page 100 AFCS mode controller next to the XFR button. Repeat step 5 using CRS2 knob while coupled to PFD2. 7. Set CRS1 and CRS2 course pointers to aircraft heading. Page 7-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 101 PFD1 as indicate by a left pointing arrow on the AFCS mode controller next to the XFR button. 11. Repeat step 10 using while coupled to PFD2. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 7-5...
  • Page 102 This page intentionally left blank Page 7-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 103: Gfc 700, Taws And Post Modification Flight Test Procedure

    All performance tolerances specified in the following in-flight checks assume smooth air. The pilot must be thoroughly familiar with the GFC 700 by studying the following: • G1000 in Hawker Beechcraft King Air C90A/GT Cockpit Reference Guide, Garmin P/N 190- 00664-00. •...

  • Page 104: Pitch Mode (Pit) & Altitude Alerting

    (aircraft’s airspeed when the FLC button was pressed), and “ALTS” will be annunciated in white in the pitch window on PFD1 and PFD2. Page 8-2 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 105: Altitude Hold (Alt) Mode & Heading Select (Hdg) Mode

    Autopilot can track VHF NAV or GPS guidance. The navigation sensor currently displayed on the HSI dictates the NAV source that will be tracked by the autopilot. G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 8-3...
  • Page 106 This will cause “LOC” to annunciate in white to the left of “HDG”, “GS” will annunciate in white to the right of the reference altitude. Page 8-4 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...

  • Page 107: Taws 'Five Hundred' Call-Out

    TAWS ‘FIVE HUNDRED’ Call-out 1. During approach, verify that the ‘FIVE HUNDRED’ voice call-out is issued at approximately 500’ AGL (GPS altitude). G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 8-5 190-00682-00 Revision 5...
  • Page 108 This page intentionally left blank Page 8-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90 Revision 5 190-00682-00...
  • Page 109 Complete the information below. A copy of this procedure should be left with the aircraft records. Testing Completed By:_________________________________________ (Print Name) Signature:_________________________________________ Date:_________________________________________ G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 9-1 190-00682-00 Revision 5...

This manual is also suitable for:

Gfc 700

Table of Contents