Garmin Cessna Caravan G1000 Checkout Procedure Download

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190-00682-00

January 2008

Revision 5

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G1000 / GFC 700 Post Installation Checkout Procedure

Hawker / Beechcraft King Air C90

Summary of Contents for Cessna Caravan G1000

Page 1: ...190 00682 00 January 2008 Revision 5 PRESS TO TEST ALT 2992 1013 28 300 50 100 150 200 250 30 G1000 GFC700PostInstallationCheckoutProcedure Hawker Beechcraft King Air C90...

Page 2: ...nauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151st Street Olathe KS 66062 USA Telephone 913 397 8200 www garmin com...

Page 3: ...h defects or reproductive harm This Notice is being provided in accordance with California s Proposition 65 If you have any questions or would like additional information please refer to our web site...

Page 4: ...Page ii G1000 GFC 700 Post Installation Checkout Procedure Hawker Beechcraft King Air C90 Revision 5 190 00682 00 This page intentionally left blank...

Page 5: ...tion Troubleshooting 2 21 3 G1000 INITIAL SYSTEM TESTING 3 1 3 1 Electrical Power Distribution Testing 3 1 3 2 Electrical Load Test Procedures 3 5 3 3 Display Testing 3 10 3 4 GPS Signal Acquisiton 3...

Page 6: ...tical Speed VS Mode 8 1 8 4 Pitch Mode PIT Altitude Alerting 8 2 8 5 Flight Level Change FLC Mode Altitude Capture 8 2 8 6 Altitude Hold ALT Mode Heading Select HDG Mode 8 3 8 7 Overspeed Protection M...

Page 7: ...y installed Garmin G1000 Integrated Avionics System with GFC 700 Automatic Flight Control System in the Hawker Beechcraft King Air Model C90A GT The person performing the configuration and testing sho...

Page 8: ...375 70 Wire Harness Routing Tail King Air C90 005 00375 31 Electrical Equipment Install Nose Bay King Air C90A 005 00375 34 Removal Collins AP65 Servos King Air C90A 005 00375 36 Pitot Static Vacuum L...

Page 9: ...illance Two GIA 63W Integrated Avionics Units Two GMA 1347D Audio Panels Two GTX 33 Mode S Transponders GDL 69A Datalink Sensors Two GDC 74B Air Data Computers ADC Two GRS 77 Attitude Heading Referenc...

Page 10: ...adio No 1 GTP59 OAT Probe GMC 710 AFCS Controller No 1 GMU44 Magnotometer GSA 80 Yaw Servo DME WX 500 SKY899 No 2 GIA 63W System Integration Processors I O Processors VHF COM VHF NAV LOC GPS Glideslop...

Page 11: ...2 Autopilot The autopilot operates within one GSA 81 servo pitch trim and three GSA 80 servos pitch roll and yaw Flight director data is processed within the servos and turned into aircraft flight con...

Page 12: ...received by the GMA 1347Ds is processed by and received from the GIA 63W Integrated Avionics Units IAUs 1 5 4 GRS 77 Attitude and Heading Reference System The Garmin GRS 77 is an attitude and heading...

Page 13: ...rements The GTX 33s interface with the No 1 and No 2 GIA63W G1000 LRUs via RS 232 1 5 11 GSA 80 Servo Actuator The Garmin GSA 80 Servo Actuator is an electromechanical unit that will provide pitch rol...

Page 14: ...Page 1 8 G1000 GFC 700 Post Installation Checkout Procedure Hawker Beechcraft King Air C90 Revision 5 190 00682 00 This page intentionally left blank...

Page 15: ...Reference Engine Indicating Maintenance Practices Raytheon Hawker Beechcraft King Air A B C E Series Maintenance Manual Part No 90 590012 13 Revision B11 or later section 77 00 00 Clamp On type Amp Me...

Page 16: ...software and configuration are accomplished successfully as described in these procedures The following diagram depicts an overview of the software configuration sequence for the G1000 system If any...

Page 17: ...lower right corner and may be used in lieu of the ENT key 6 The following screen is displayed 7 New software is loaded to PFD2 When complete the PFD starts in configuration mode displaying the System...

Page 18: ...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 v...

Page 19: ...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 GF...

Page 20: ...A ______ AFCS SYSTEM SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK GSA PTCH CTL _____ GSA PTCH TRM M _____ GSA YAW CTL _____ GSA PTCH MON _____ GSA ROLL CTL _____ GSA YAW MON _____ GSA PTCH TRM C...

Page 21: ...al number 1362 A C modified by SA3593NM Raisbeck STC with AFMS 86 206C Configuration to be loaded King Air C90A Config 7 Once the correct configuration is determined load the appropriate King Air C90...

Page 22: ...d Airspeed Configuration In addition to the airframe configuration loaded above certain installations will require additional steps to configure the G1000 for airframe weight and airspeed markings 2 5...

Page 23: ...C90 Airspeed LJ 1063 1137 1146 All other aircraft not included in this serial number range are not required to load this additional airspeed indication marking configuration Follow this procedure to...

Page 24: ...Load Confirmation 1 Deselect cursor if selected use the large FMS knob to select the GDU page group and the small FMS knob to select AIRFRAME CONFIGURATION page 2 Verify the correct airspeed configur...

Page 25: ...r knob to select King Air C90 Traffic System Option Press ENT 6 Verify the King Air C90 Traffic System Option configuration file is displayed in the File window Press LOAD 7 Monitor load progress Veri...

Page 26: ...n menu Highlight C90 Options and press PFD1 ENT key 3 Verify cursor drops down to the file box Rotate the inner FMS knob to view the list of available C90 Options 4 Use the FMS inner knob to select Ki...

Page 27: ...Stormscope configuration page StormScope Configuration Page Reference Only Activate the cursor to highlight the DATA field Use the small FMS knob to open the drop down menu then select Config and pres...

Page 28: ...1000 GFC 700 Post Installation Checkout Procedure Hawker Beechcraft King Air C90 Revision 5 190 00682 00 StormScope Configuration Page Reference Only NOTE The DATA window is only updated once every fi...

Page 29: ...en PASS in Configuration column for GIA2 GMA PIL and GMA COPIL 8 Upload Complete COMPLETE in the summary box 9 Select ENT to acknowledge upload complete 10 Deactivate cursor 2 9 DME 42 Option Configur...

Page 30: ...Upload page using PFD1 small FMS knob 3 Activate the cursor and use the small FMS knob to highlight C90 in the AIRFRAME field Press the ENT key to select the airframe type Ensure that the correct air...

Page 31: ...ctivate this feature Insert the ChartView Enable card in the upper slot of the PFD1 3 While holding the ENT key on PFD1 PFD2 and MFD for MFD press and hold the farthest right pushbutton restore power...

Page 32: ...rds appear in the upper left corner of the displays release the ENT key 6 On PFD1 go to the System Upload page using the small PFD1 FMS knob 7 Activate the cursor Use the small PFD1 FMS knob to select...

Page 33: ...enter the aircraft registration number 6 Once the correct registration number is entered press the ENT key The transponder is configured 7 Observe the status window 8 Press the ENT key on PFD1 to ack...

Page 34: ...ate SD Card from PFD2 7 Repeat steps 2 through 4 for the MFD then PFD1 for MFD press and hold the farthest right pushbutton 8 The aviation databases are now updated 9 Confirm that the correct update c...

Page 35: ...nfiguration file load fails Ensure that criteria listed in 2 17 1 are fulfilled for the applicable situation Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wirin...

Page 36: ...e inserted in top slot of PFD1 PFD1 and MFD must be powered on PFD1 and MFD must have correct software Load Software Configuration files to GIA 63Ws G1000 C90 SW Loader Card must be inserted in top sl...

Page 37: ...G1000 or G1000 interfaced system 8 Open GIA1 SEC CB Verify GIA1 is not powered by observing red Xs and or alert messages 9 Close GIA 1 PRI CB Verify GIA1 is powered by observing the absence of red Xs...

Page 38: ...alid frequency in the COMM2 tuning window 28 Open MODE CTL CB Verify GMC 710 AFCS mode controller is not powered Close AFCS CTL CB when finished 29 Open AFCS SERVOS CB Verify AFCS servos are not power...

Page 39: ...red and MFD 1 FAN FAIL alert message is displayed on PFD1 and PFD2 50 Close MFD FAN CB Verify MFD fan is powered and MFD FAN FAIL message extinguish on PFD1 and PFD2 51 Open PFD GIA FANS LEFT CB Verif...

Page 40: ...e Fed Bus 2 CB Verify the following are not powered MFD GEA2 62 Close CB Panel No 2 Triple Fed Bus 2 CB 63 On GMA1 de select DISPLAY BACKUP button button extended 64 Open CB Panel No 3 Triple Fed Bus...

Page 41: ...tructions to zero the amp meter Place meter around the ground power cart DC power cable 3 Make or verify the following switch selections Switches not listed are not required EXT PWR OFF AVIONICS MASTE...

Page 42: ...PERS OFF OVERHEAD FLOOD LIGHT CONTROL OFF INSTRUMENT INDIRECT LIGHT CONTROL OFF PILOT PFD LIGHT CONTROL OFF STBY INSTR LIGHT CONTROL OFF MFD LIGHT CONTROL OFF OVHD PED SUBPANEL LIGHT CONTROL OFF SIDE...

Page 43: ...N1 TACH L ENG INST L FUEL FLOW L OIL PRESS 6 Make the following switch selections EXT PWR ON 7 Observe the non switchable DC electrical load EXT PWR ON from the amp meter and record in Table 1 as DP1...

Page 44: ...electrical load EXT PWR ON BATT charge External lights anti ice systems from the amp meter and record in Table 1 as DP2 10 Turn off all switches referenced in paragraph 8 11 Configure the aircraft to...

Page 45: ...sions 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 Aut...

Page 46: ...he left may vary Note database versions and system software represented in the upper right corner Refer to General Arrangement Drawing 005 00375 22 drawing for the correct database and system software...

Page 47: ...valid until the units have been calibrated as described later in this chapter 5 Check that all COM NAV fields are valid in the top corners of PFD1 and PFD2 6 Check that altitude airspeed vertical spe...

Page 48: ...fy PFD1 and MFD return to normal display modes 3 Repeat Step 1 using GMA2 Ensure that PFD2 and MFD enter reversion mode and MFD displays valid altitude airspeed vertical speed COMM1 COMM2 NAV1 NAV2 an...

Page 49: ...e 1 Select the GPS status page on the MFD 4th page in AUX group Toggle between GPS 1 and GPS 2 using the two softkeys on the bottom of the display Verify that both receivers show 3D DIFF NAV on the MF...

Page 50: ...sengers or copilot 6 Deselect GMA1 pilot ICS ISOLATION 7 Repeat steps 5 6 using GMA2 for copilot 8 On GMA1 select COM1 MIC and AUDIO 9 Ensure INTR COM is deselected on GMA1 or GMA2 Verify an active gr...

Page 51: ...t equipment manufacturer s instructions Verify that each marker audio signal is present over the pilot and co pilot headphones and cockpit speaker Verify that the outer middle and inner annunciations...

Page 52: ...COM transceiver 19 On the MFD select AUX page 5 and return the COM channel spacing to 25 kHz 3 9 VOR LOC GS Test Check the VOR ILS and Glideslope functions with ramp test equipment Operate the equipm...

Page 53: ...h 0 45 sec 0 10 sec 6 Using a ramp tester evaluate XPDR1 mode S tail number interrogation Verify proper mode S reply 7 Using an air data and XPNDR ramp tester evaluate XPDR1 mode C interrogations Veri...

Page 54: ...ing at an altitude of 30 000 ft and airspeed of 120 knots When static pressure has stabilized verify and record the cumulative leak rate is 200ft minute or less ALTITUDE ft min With a pitot static tes...

Page 55: ...1 in configuration mode by pressing and holding the PFD1 ENT key while closing PFD1 PRI and PFD1 SEC circuit breakers 4 Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner o...

Page 56: ...nce Tolerance Tolerance Tolerance Tolerance ALT AS Actual Actual Actual Actual Actual Actual 20 20 20 N A N A N A 0 N A 20 20 20 2 2 5 1000 50 20 20 20 2 2 5 500 50 20 20 20 2 2 5 1000 50 25 25 25 2 2...

Page 57: ...rates shown in the table below 2 Wait for ADTS to report that target rates have been achieved 3 Verify that the Rate of Climb reported by the Vertical Speed field on PFD1 and PFD2 are within the tole...

Page 58: ...the AUX XM RADIO page on the MFD 2 Verify that you can increment and decrement the channels the white arrow to the left of the channel list indicates the currently selected channel Select channel 1 w...

Page 59: ...ration from the Systems menu by rotating the small FMS knob 5 Select PLAY for the following audio and verify XM audio is temporarily muted while alert audio is being played GEAR STALL ALERT Message 1...

Page 60: ...RCISE EXTREME CAUTION WHILE WORKING AROUND LANDING GEAR OR IN LANDING GEAR WHEEL WELLS Gear warning discrete 1 Reference Hawker Beechcraft aircraft maintenance manual 90 590012 13 and jack aircraft to...

Page 61: ...uit breaker is closed 14 While monitoring pilot and copilot XM audio actuate the stall warn transducer on the left wing leading edge in an up position verify the following Stall warning tone is active...

Page 62: ...UP button Observe MFD in reversion mode and verify all engine instruments are displayed and indicate valid values and markings Reference figure below for reversion mode EIS display Normal EIS Display...

Page 63: ...uished 7 With a GPS position acquired shield or disconnect the GPS antennas to remove the GPS signal Verify DR shows on the MFD and the TAWS N A and DR annunciations show on the PFDs 8 Reconnect or re...

Page 64: ...ts is displayed in blue text adjacent to CHART 4 Verify the FliteCharts database REGION CYCLE number EFFECTIVE EXPIRES and DISABLES dates of the subscription appear in blue text 5 Use the GCU large FM...

Page 65: ...CK 3 Press CHRT OPT softkey and verify softkeys advance to the following level of softkeys ALL HEADER PLAN PROFILE MINIMUMS FIT WDTH FULL SCN BACK 4 Return to the Navigation Map Page 5 Press the GCU M...

Page 66: ...ges where the SafeTaxi feature can be seen Navigation Map Page Inset map Weather Datalink Page Airport Information Page Intersection Information Page NDB Information Page VOR Information Page User Way...

Page 67: ...ighlight the CARGO field Turn the small FMS knob CW to increase the CARGO weight to 1210 Verify the ZERO FUEL WEIGHT value is 10110 and displayed in amber 5 Turn the small FMS knob CCW to decrease the...

Page 68: ...the CARGO field Using the GCU keypad enter a CARGO weight of 100 Press the ENT key to confirm the entry Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan 4 Turn the large FMS knob CCW t...

Page 69: ...ll FMS knob CW to increase the CARGO weight to 760 Verify the ZERO FUEL WEIGHT value is 9660 and displayed in amber 5 Turn the small FMS knob CCW to decrease the CARGO weight to 750 Verify the ZERO FU...

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Page 71: ...m up is complete 4 Press the GCU FMS knob to activate the cursor in the TILT field then turn the small FMS knob to select the desired antenna tilt angle Press the GCU ENT key Press the GCU FMS knob to...

Page 72: ...weather radar Verify these systems do not cause strike data to appear on the MFD 5 Connect the WX PA cable to the WX PA antenna 6 Position the WX PA antenna on the WX 500 antenna Ensure the connectio...

Page 73: ...he F1 and F2 keys to select 120 NM range and press MENU ENTER to start the test Verify the WX 500 plots discharge points at approximately 60 NM 22 Observe the MFD to ensure the proper positioning of t...

Page 74: ...o enable the traffic system 3 Press the OPERATE softkey and verify that OPERATING is displayed in the upper left corner of the traffic map 4 Press the STANDBY softkey and verify that STANDBY is displa...

Page 75: ...can be selected by turning the small FMS knob 4 Set NAV1 and NAV2 frequencies to 108 00 and 117 00 respectively 5 On PFD1 and PFD2 select the DME NAV1 mode Verify that the DME window display is set to...

Page 76: ...y that the ADF window is not invalid no red X 3 Using the ADF control head select a known valid local ADF Verify that the ADF bearing pointer moves towards a bearing and stabilizes 4 Select ADF and SP...

Page 77: ...tate the large FMS knob to select the GRS page group on PFD1 Rotate the small FMS knob clockwise to access the GRS GMU calibration page on PFD1 1 This page is protected and requires a keystroke passwo...

Page 78: ...operator of a successful conclusion and returns to normal operation 5 Press the ENT key on PFD1 to conclude this procedure Repeat Steps 3 4 for the GRS2 6 Restart displays in normal mode and proceed t...

Page 79: ...uting the magnetometer calibration parameters The G1000 equipped C90 used to evaluate the site must have already completed the pitch roll offset compensation procedure Procedure A However prior comple...

Page 80: ...ngine instruments Operate engines in accordance with Hawker Beechcraft C90B engine starting and operating procedures Monitor engine instruments during startup for proper operation When engines and sys...

Page 81: ...sing the PFD instruction to turn as a real time indication of when to turn simply judge the 30 5 turn increments of the aircraft by using the compass rose radials Dwelling at these 30 increments for t...

Page 82: ...for the left and right engine 6 PFD1 informs the operator if the installation has passed or failed the vibration test If the test fails the specific measurements causing the failure are identified and...

Page 83: ...for final testing Restart both displays in normal mode to conduct final system checks When the PFDs power up in normal mode the AHRS attitude and heading information displayed should become valid with...

Page 84: ...terferes with the operation of the GMU 44 magnetometer Calibration Procedures A through C are not required prior to this procedure 1 Initiate the AHRS magnetometer interference test procedure by perfo...

Page 85: ...s 0 10 Navigation lights on 0 20 Navigation lights off 0 30 Landing lights on 0 40 Landing lights off 0 50 Taxi lights on 1 00 Taxi lights off 1 20 Strobes on 1 40 Strobes off 1 50 Recognition lights...

Page 86: ...ils record the three magnetometer maximum deviation values and their corresponding timestamps Any maximum deviation value greater than 5 0 milliGauss indicates a problem that must be resolved Compare...

Page 87: ...antenna 3 Place a shroud over the GPS antenna for GIA 2 to prevent signal reception Verify loss of signal on MFD AUX page 4 4 Remove shroud from the GIA 2 GPS antenna GPS Failure For each of the speci...

Page 88: ...X L R engine data remains valid XPDR1 is Inoperative GMA1 Is Inoperative AHRS1 is using backup GPS source AHRS2 not receiving backup GPS Information An amber BOTH ON GPS2 is displayed on PFD1 and PFD2...

Page 89: ...remain valid and can be tuned by rotating the tuning knobs on PFD1 and PFD2 XPDR 1 2 fields remain valid and XPDRs can adjusted via PFD softkeys PFD2 Display Failure Conditions 1 Open PFD 2 CB 2 Veri...

Page 90: ...llowing illuminate on PFD2 GMA1 Fail GMA1 is inoperative XPDR1 Fail XPDR1 is Inoperative XTALK ERROR A flight display crosstalk error has occurred PFD1 and MFD Display Failure Conditions 1 Open MFD ci...

Page 91: ...otor and the absence of flag STBY altimeter vibrator is active as indicated by vibrator noise STBY attitude STBY Altimeter and STBY Airspeed indicators are illuminated dimly Amber ON is annunciated fu...

Page 92: ...titude motor and STBY altimeter vibrator remain active Visible white portion of the STANDBY BATTERY switch remains illuminated full bright 5 Remove aircraft power by selecting the battery switch to OF...

Page 93: ...l the words INITIALIZING SYSTEM appear 2 In configuration mode go to the GDU Page Group on PFD1 3 On PFD1 activate the cursor and select PFD1 in the SELECT UNIT field and press ENT 4 Observe the GRS 7...

Page 94: ...luding the GRS 77 and GDC 74 ARINC 429 channels 13 Verify all DATA indicators are GREEN indicating the channels are receiving data as shown below 14 Activate the cursor and select GIA2 in the SELECT U...

Page 95: ...Post Installation Checkout Procedure Hawker Beechcraft King Air C90 Page 6 9 190 00682 00 Revision 5 20 Activate the cursor and select GIA2 in the SELECT UNIT field then press the ENT key 21 Repeat St...

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Page 97: ...64 00 Roll Servo Install King Air C90A P N 005 00375 41 Yaw Servo Install King Air C90A P N 005 00375 42 Pitch Servo Install King Air C90A P N 005 00375 43 Pitch Trim Servo Install King Air C90A P N 0...

Page 98: ...ease the CWS switch and press the XFR key on the AFCS mode controller Verify the clutches are engaged and resist movement of the control wheel Press and hold the CWS switch and verify the control whee...

Page 99: ...hes cannot be overpowered check the servo clutch torque settings Refer to the pitch or roll servo installation drawing as applicable 3 Actuate and hold PITCH TRIM switch in either the NOSE UP or NOSE...

Page 100: ...and press the CWS button Verify trim motion stops Move the control wheel to the forward limit and release the CWS button Slowly move the control wheel aft After a brief delay verify the trim wheel be...

Page 101: ...localizer and glideslope on PFD1 and PFD2 9 Press the APR key on the AFCS mode controller Verify that the LOC and GS annunciations are green on PFD1 and PFD2 Apply right left and up down localizer gl...

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Page 103: ...vation will be held up to a maximum of 25 3 Press the AP key on the AFCS mode controller to engage the autopilot The autopilot will hold the commanded pitch attitude within 2 and the roll attitude wit...

Page 104: ...a green ALT ALT will flash for 10 seconds to indicate the transition to the new mode and the altitude reference will be displayed in green to the right of ALT 6 Verify the autopilot levels off within...

Page 105: ...T mode Synchronize the HDG bug to current aircraft heading and engage HDG mode 2 Use the HDG bug to change heading 90 The autopilot will bank the airplane at standard rate up to a maximum bank angle o...

Page 106: ...with minimal overshoot Allow the system to track the radial for five minutes Verify the autopilot tracks the selected course with minimal scalloping or oscillation 8 8 3 NAV BC and APR ILS Modes 1 Est...

Page 107: ...ormation set the course selector on the HSI to the inbound course 2 Use the HDG and ALT modes to set up 45 intercept of the selected VOR radial at least 5 miles from the final approach fix Arm the VAP...

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Page 109: ...2 00 Revision 5 9 SIGNATURES Complete the information below A copy of this procedure should be left with the aircraft records Testing Completed By _________________________________________ Print Name...

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