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Garmin SA01535Wi_D System Maintenance Manual

1. DUAL FED tinea BUS 1 6d ESS BUS SEC SL BLEED AIR WARN sq PFD NO 1 SEC de PPRNO 5 e CABIN PRES CTRL PFD GIA NO 1 FAN s AURAL WARN 5 ADC NO 1 SEC e ADO NO 2 r READINGTT A 5 A LANDINGGEARWARN GANGI seo od AHRS NO 2 5 e INSTR INDIRECT LT so _LENG INSTR PWR Se ANNUNCIATOR PWR SY AHRS NOA SEC O q GIA NO 2 5 OVHD 8 SUBPANEL LT oS LGENCTRL SL FUEL VENT HEAT Lp GMC CU PA 5 Y COPILOT PFD LT 5 e OUTSIDE AIR TEMP Se SURFACE DEICE ST RUDDER BOOST 5 R BLEED AIR WARN eek Sy BRAKE DEICE di CABIN AUDIO 53 LANDGEAR POS IND A 5 AVIONICS MASTER SW OR ENG INSTRU PWR J ANNUNCIATOR IND lt a a GEL 5 LENG FUEL CTRL HEAT 5 CIGARETTE LIGHTER 5 R FUEL VENT HEAT a Se L MAIN ENG ANTIICE 5 e FURNISHING MASTER SW 5 WINDSHIELD WIPER o NO SMK FSB amp CABIN LT 5
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3. ccccccesessssessssessseseeeeees Figure 3 28 GTS 8XX TAS TCAS1 Configuration c ccsssssccccceeesesssesssssssennaees Figure 3 29 Lightning System Option Configuration cccccccccccccccccccecesssseeeeesssssaees Figure 3 30 Stormscope Configuration Page cccccccssssssssssssessssssssssessssssssesseeeeees G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page v Revision 6 Fiotir 3 31 Stormscope Conti Ur sir tata 3 33 Figure 3 325 ESP Support onu A A AA 3 34 ICUS 3299 ESP SUPPO Contursi 3 35 Pieure 5 34 GDL 39 CONSUMO 3 36 PIgure 9 55 GSR OOC OM UM dan 3 37 Figure 3 36 GSM 85A Servo Mount Configuration ccccccccccccccccccceceeesseeseesssssneeeeeeeeeeeeeseeseseesssaaaaes 3 38 Figure 3 37 GSM 86 Servo Mount Configuration ccccceessssssncceeeeeeeeeeeseeeeeessnsnseeeeeeeeeeeeeeeeeeeeeeees 3 39 Figure 3 38 Servo Mount Configuration V encata 3 40 Foure oe Cban yew Enable A E E eee 3 41 Pioure 0 40 TAWS B Enabled eee 3 42 Preure a lt 4 TAWA Ba De aaa N AN 3 43 Figure 3 42 Supplemental Database Synchronization cccccceeeeeeeeesseeeseeeeeeeseesseeeseeseseeeeeeeeeeegs 3 44 Fene A Sy o Duato 3 45 Peire 14 E SP ld E AA 3 46 Pisto 5 45 Alreralt RELS trato oa 3 47 Figure 3 46 Navigation Database Synchronization ccccccnnnnnnooooooononnnnnnnnnonnnnnannnnnn noo nnnnnnnnnnnnnnnnnnnnnnnnnnnns 3 50 Fisure dad
4. GDC 74B Config Module located in GDC backshell connector Stores a copy of the GDC 74B configuration file GDC 74B The GDC 74B stores GDC configuration file internally The GDC 74B also stores factory calibration data internally Should internal memory or the configuration module fail loss of some or all air data outputs will result GDC Internal Memory Contains internal sensor calibration data that is not installation specific Data is stored from factory calibrations Figure 3 15 GRS GDC Configuration Settings Storage G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 17 190 00915 01 Revision 6 3 9 G1000 Software Configuration Procedure This section summarizes the procedures required to load software and configuration files to the G1000 It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft In sections of this manual where software is required to be reloaded these sections will make reference back to this Section for instructions The technician should use proper judgment regarding the context of maintenance required while following this section The following diagram depicts an overview of the software configuration sequence for the G1000 system This applies mostly to a new G1000 system which has not previously been powered up and is for informative purposes only GDU 1040A PFDs GDU 1500
5. ANLG IN CRNT MNTRENG TEMP BKSHELL ANNUNC DIGITAL DISCRETE COPY VERIFY the a tn ay a mm te a a Figure 3 3 G1000 Softkeys 3 1 2 FMS Knob The FMS knob is the primary control for the G1000 system Operation is similar to the Garmin 400 500 Series units To cycle through different configuration screens To change page groups Rotate the large FMS knob To change pages in a group Rotate the small FMS knob To activate the cursor for a page press the small FMS knob directly in as one would push a regular button To cycle the cursor through different data fields rotate the large FMS knob To change the contents of a highlighted data field rotate the small FMS knob This action either brings up an options menu for the particular field or in some cases allows the operator to enter data for the field To confirm a selection press the ENT key Page 3 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 To cancel a selection press the small FMS knob in again deactivating the cursor The CLR key may also be used to cancel a selection or deactivate the cursor 3 2 GCU 477 MFD Controller The MFD controls are located on the GCU 477 as show in Figure 3 4 Range pan Flight FMS Ctrl knob planning keys knob RANGE CSN S gt PUSH W PAN DFLT_ PUSH CASA Comm Nav MAP Tranponder keys Alpha entry keys SOFTKEY SELECT q IS gt Numeric Entry keys
6. 2 1 11 GMU 44 Magnetometer 2 The GMU 44 provides horizontal and vertical magnetic field information to the GRS 77 AHRS This allows heading to be calculated and provides assistance during AHRS alignment The GMU 44 units are mounted in the tailcone The units receive power directly from the GRS 77 units and communicate with the GRS 77 units via RS 485 digital interface Figure 2 11 Magnetometer G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 7 190 00915 01 Revision 6 2 1 12 GDL 69A Datalink The GDL 69A provides the interface to the GWX 68 weather radar and optional GDL59 wi fi datalink by acting as a communications hub between the MFD and GWX 68 and GDL 59 via HSDB The GDL 69A also provides XM Radio weather and music entertainment through means of a dedicated satellite data link The GDL 69A is mounted behind the instrument panel Power to the GDL 69A is received from the Avionics No 2 bus The GDL 69A sends weather data through the HSDB bus to the MFD where the data link interface is controlled Digital audio is sent directly to the GMA 1347D Audio Panel Optional remote control GRC 10 and remote control transceiver GRT 10 may be interfaced with the GDL 69A Installation of the GRC 10 and GRT 10 is in accordance with Garmin STC SA01487SE or other approved data Refer to the approved Instructions for Continued Airworthiness information for these units It is recommended that GRT 10 be powered from the Ent
7. 4 Onthe GCU press MENU With Map Setup highlighted press ENT on the GCU Rotate the small GCU FMS knob to select the Aviation group and press the ENT key on GCU 5 Turn the GCU large FMS Knob to scroll through the Aviation Group options to SAFETAXI 6 Turn the GCU small FMS Knob to display the range of distances 7 Turn the GCU FMS Knob to select 5000ft as the distance for maximum SafeTaxi display range and then press the GCU ENT key to complete the selection 8 Using the GCU range knob select a range of 5000ft or less Verify SafeTaxi display represents the current aircraft location and the airport layout If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 39 190 00915 01 Revision 6 7 19 DME Functional Check This check verifies that the DME to G1000 interface operates correctly 10 l1 2 13 NOTE Support for a single Collins DME 42 system is provided as an option in the G1000 If the DME option 1s selected the DME channel one audio level must be adjusted by the procedure contained within Collins DME 42 Transceiver Repair Manual 523 0772458 Maintenance Section 523 0772460 006118 to adjust DME channel one audio level Recommended nominal DME audio output level is 4 46 Vpp 0 10 Vpp Procedure must be accomplished by an approved repair station If DME is not displayed press the PFD softkey
8. Figure 2 21 G1000 GFC 700 Block Diagram G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 3 G1000 Control amp Operation All control and operation of G1000 equipment as normally used in flight occurs through the PFDs MFD GMC 710 GCU 477 and GMA 1347D audio panel Figure 3 1 through Figure 3 6 identify various interface buttons for these units 3 1 GDU 1040A and GDU 1500 Displays Figure 3 1 and Figure 3 2 provide identification of the GDU 1040A PFD and GDU 1500 MFD controls COM frequency Nav frequency toggle key toggle key GARMIN Nav volume COM volume ident knob squelch knob Nav frequency tuner knob COM frequency selector knob Baro selector Map panning range joystick Navigation systems controls Flight management system FMS knob Multi function softkeys numbered 1 12 left to right Figure 3 1 GDU 1040A Control Interface G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 1 190 00915 01 Revision 6 Multi function softkeys numbered 1 12 left to right Figure 3 2 GDU 1500 Control Interface 3 1 1 Softkeys Some pages have commands or selections that are activated by the GDU 1040 softkeys Ifa softkey is associated with a command that command will be displayed directly above the key A grayed out softkey shows a command that is unavailable A softkey that is highlighted shows the current active selection
9. NOTE New Terrain Obstacle cards GCU CNFG GCU Config error e als cee a Jeppesen Aviation Database and Config service req d ee g other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number Check wiring for faults ref Failed GCU FAIL GCU is inoperative The G1000 has detected a Path troubleshooting section failure in the GCU 477 Replace the GCU 477 The system has detected an Load the correct software version MANIFEST GCU software incorrect software version See Section 3 9 for the Software loaded in GCU 477 Load Procedure mismatch Communication halted G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 77 190 00915 01 Revision 6 5 20 Software Configuration Troubleshooting MFD or PFD displays do not power up Software file load fails FILE UPLOAD FAIL OK Configuration file load fails CONFIGURATION UPLOAD FAIL OK GIA1 and or GIA2 to LRU data path not working Software File Mismatch Alert appears in lower right corner of PFD when started in normal mode ALERTS MANIFEST Ee D 0m A mismatch Communication halted Page 5 78 Revision 6 Ensure that the criteria listed in Section
10. PFD 1 cooling fan is b PFD GIA FANS RIGHT i c MFD FAN PFD 2 FAN FAIL PFD 2 cooling fan 1s inoperative MFD FAN FAIL MED cooling fan is inoperative Fan Failure reset and acknowledgement Verify the above alerts extinguish 1 Reset all cooling fan circuit breakers 2 Acknowledge alerts by pressing the ALERTS softkey on PFD1 8 1 5 Standby Instrument Electrical Power Checks This section tests the standby electrical power for the standby attitude indicator the standby altimeter and the standby airspeed indicator The magnetic compass is tested in each Phase inspection during the cockpit lights check in the King Air 200 Series Maintenance Manual listed in Table 1 2 Step CCC Desired Result Remove or ensure external aircraft power Verify the STANDBY BATTERY is removed Set main battery switch to annunciator switch is not illuminated OFF Ensure the STBY ATT and STBY ALTM circuit breakers are closed Ensure the MASTER PANEL LIGHTS rocker switch in the overhead panel is in the ON position Ensure the STBY INSTR knob is turned to full bright G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 5 190 00915 01 Revision 6 Step DesiredResult 5 Select depress the STANDBY Verify the following BATTERY switch e STBY Attitude indicator motor is energized as indicated by the indicator motor and the absence of flag STBY altimeter vibrator is active as indicated by vib
11. PFD 1 DB ERR PFD 1 terrain database error exists Contact Garmin product Support The specified PFD has for further assistance if needed encountered an error in the terrain PFD 2 DB ERR PFD 2 terrain database database error exists MFD1 DB ERR MFD1 obstacle The MFD has encountered an database error exists error in the obstacle database Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard PFD 1 DB ERR PFD 1 obstacle Contact Garmin product Support database error exists The specified PFD has for further assistance if needed encountered an error in the PFD 2 DBERR PFD 2 obstacle Obstacle database database error exists The MFD has encountered an error in the airport terrain Confirm supplemental data card is database inserted fully MFD1 DB ERR MFD1 airport terrain database error exists Reload the database or replace the supplemental datacard PFD 1 DB ERR PFD 1 airport Contact Garmin product Support terrain database error exists The speciiea PED nas for further assistance if needed encountered an error in the airport PFD 2 DB ERR PFD 2 airport terrain database terrain database error exists The system has found the Jeppesen aviation database Load current aviation database cycles in the PFDs and or MFD do versions to all displays not match DB MISMATCH Aviation database version mismatch Xtalk is o
12. v Ifa mismatch has occurred load correct database software files or replace the terrain card Enable TAWS system alerting by pressing the INHIBIT softkey on the TAWS system alerting is disabled MAP TAWS page Ensure valid GPS position is received from the AUX GPS GPS system integrity not high STATUS page enough to enable TAWS Check GPS antenna amp associated coaxial cabling Troubleshoot GIAs Verify GIAs are online A GPWS system failure has Verify radio altimeter input is valid occurred Verify baro altitude and vertical speed input are valid Page 5 26 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 9 5 Synthetic Vision and Pathways Troubleshooting The SVS Pathways software feature requires the following G1000 sensors data to be valid e AHRS e Heading e GPS Position e 9 Arc Second Terrain Data In the event that one the above items fails or is unavailable the SVS Pathways feature is automatically removed from the PFD The following table describes possible symptoms associated with the SVS Pathways feature and provides corresponding actions for troubleshooting Table 5 1 SVS Troubleshooting Symptom Recommended Action SYN VIS softkey does not appear on PFD softkey tier Follow the steps in Section 3 33 to reactivate the SVS Pathways feature Verify that P N 010 00330 43 terrain datacards are installed in the lower slot of the PFD and MFD
13. 17 18 19 20 pale 22 2 Verify on PFD 1 and PFD 2 that there is an ESP OFF and for installations with AOA mode an ESP DEGRADE alert message ESP OFF ad ESP DEGRADE ESP ADA mode is inoperative Remove the cover from both GPS1 and GPS2 antennas Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to OFF Wait 1 minute before re applying aircraft power Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to ON During power up and GPS satellite acquisition verify on PFD1 and PFD2 the ESP Roll Indices are displayed at 45 on the roll indicator on the Attitude Display Once AFCS PFT is complete and GPS has acquired satellites verify on PFD1 and PFD2 the ESP Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 59 190 00915 01 Revision 6 24 On the GCU rotate the inner FMS knob to activate the AUX SYSTEM SETUP page 25 On the MFD AUX SYSTEM SETUP page press the SETUP 2 softkey 26 Verify that on the MFD SETUP 2 page there 1s a window for Stability amp Protection and the status is ENABLED STABILITY amp PROTECTION STATUS 27 Verify on PFD 1 and PFD 2 that there are no ESP FAIL ESP OFF or ESP DEGRADE alert mess
14. 4 2 E A Output 15 VDC for On Ground self test to Lift Transducer Pin 8 of the transducer ACI ETT TEN CARS Low Airspeed Awareness LAA Lo This output is 0 VDC at stall warning Potentiometers 3 4 and 5 on top of the computer are used to adjust the 19 LAA Output Hi LAA outputs to 2 2 VDC Pot 3 0 flaps LAA adjustment Pot 4 flaps LAA adjustment Pot 5 full flaps LAA adjustment EXT Lift Transducer Test Point Varying voltage from Lift Transducer 24 O Lift Transducer Excitation Voltage Hi 10 VAC 700 Hz nominal 25 jo Lift Transducer Excitation Voltage Lo G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 87 190 00915 01 Revision 6 et E o pr ME E 7 Squatswitohimput Logic OpenvGround Ground In Air_ 1 Js ef o P EM p26 fl Lift Transducer Secondary Fast Input ESTA Lift Transducer Center Tap Common Lift Transducer Secondary Input into the computer 28 i Lift Transducer Secondary Slow Input 5 25 2 Lift Transducer Functional Pinout Pin VO Function Information a Or Slow Secondary Pin Hi Vane resistance Pins 6 to 7 Lo 70 ohms 2 1 Genter E Core Primary Pin Hi Fast Secondary Pins 3 to 4 Lo 320 ohms EMT Fast Secondary Pin Hi Slow Secondary Pins 1 to 4 Lo 320 ohms a Secondary Pin Lo Center E Core Primary Pins 2 to 5 Lo 140 ohms EME Center E Core Primary Pin Lo Self Test coil Pins 8 to 7
15. Figure 3 4 MFD Controls GCU 477 shown 3 3 GMC 710 AFCS Controls The dedicated AFCS controls located on the GMC 710 are discussed in detail in the G1000 CRG The following figure is provided for reference Flight director transfer key Heading mode key Navigati de k E E Altitude hold key i i Flight level change Approach Flight director mode key Vertical speed mode key mode key mode key ALT ALT SEL PUSH DIA Back Autopilot key pl i ackcourse k Lone bug deh ey Course 2 Yaw damper key Speed key selector Bard Bank IAS MACH selector sm oe Nose Dn Figure 3 5 AFCS Controls GMC 710 shown G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 3 Revision 6 190 00915 01 3 4 GMA 1347D Audio Panel Figure 3 6 provides the audio panel controls Transmitters Passenger Address ro Music Marker Beacon Mute Aircraft Navigation Radio Audio Manual Squelch Intercom System ICS ICS VOL SQ Small Knob MUSIC MUTE Transceiver Audio ls COMA PA Telephone Speaker MEA Marker Beacon Signal Sensitivity e ai Transceiver Audio el 99 PLAY Digital Recording Playback F ah 4 CABIN Cabin Intercom ICS O MSTR Master VOL Large Knob Reversionary Mode DISPLAY BACKUP Figure 3 6 GMA 1347D Controls Page 3 4 Revision 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series K
16. Figure 5 1 AUX System Status Page The AUX System Status page is the 5 page in the AUX Page Group and displays the following information for each LRU and sub function e Status A green check is displayed for properly operating LRUs A red x appears when an internal LRU fault is detected and it has taken itself offline or if the MFD can not communicate with the LRU e Serial Number Each LRU serial number is displayed functions such as GPS and GS are contained within an LRU therefore serial numbers are not shown for these e Current SW Version Loaded When troubleshooting first check to ensure that each LRU status is green and that the correct software is loaded in each unit Additional airframe and database information is also displayed on this page G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 1 190 00915 01 Revision 6 5 1 G1000 Alerting System i System Annunciators FAILED PATH A Alerts failed Window GMA2 FAIL GMA2 is inoperative GMA1 FAIL GMA is inoperative IS E EEES Alerts Softkey Annunciation Figure 5 2 Alerts 8 Annunciations The G1000 Alert System conveys alerts to the pilot using combinations of the following features Alert Window The Alert window displays alert text messages Pressing the ALERTS softkey displays the Alerts window Pressing the ALERTS softkey again removes the Alerts window from the display Softkey Annunciat
17. If the resistances are within the ranges specified check that there is a ground on TP 2 If all the resistances are within the ranges specified and there is a ground on TP 2 apply power to the Stall Warning System Lift Computer and check for the presence of 28 VDC from the aircraft circuit Breaker C B on TP 1 Hi and TP 2 Lo Page 5 86 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 If the 28 VDC is missing check the C B If 28 VDC power to the computer is present check the transducer excitation voltage on TP 24 Hi and TP 25 Lo The voltage should be 10 0 75 VAC at 720 72 Hz If the excitation voltage is not within the ranges specified replace the computer If the excitation voltage is within the ranges specified check the LAA output on TP 18 Lo and TP 19 Hi The output is a varying DC voltage based on the transducer vane position The output from the computer with the vane in neutral position depends on the flap position See table below lapso Output Full Up 0 3 to 1 3 VDC Approach 0 75 to 1 75 VDC Full Down 1 1 to 2 1 VDC If the output on TP 18 Lo and TP 19 Hi is not within the ranges specified replace the Lift Computer If the output on TP 18 Lo and TP 19 Hi is within the ranges specified check the aircraft wiring in accordance with the appropriate Garmin wiring schematic 5 25 1 Lift Computer Functional Pinout 10 Function ooo
18. PTRM Failure Check the servo wiring and connector For pitch trim check pitch trim switch operation to verify Yaw Axis Failure switch contacts are not stuck If failure condition still exists remove and replace the ROLL Roll Axis Failure ee ane If the AHRS inputs have been determined to be AHRS Monitor unreasonable while the AP is engaged in air this message Failure will be displayed until AHRS inputs are determined reasonable for 5 seconds If elevator mistrim annunciations persist check the pitch and Elevator Mis Trim pitch trim servos for proper operation Verify that the servo Down is online at the AUX SYSTEM STATUS page Check the servo wiring and connectors Ensure the servo is receiving power Elevator Mis Trim Check the aircraft control adjustments Up If mistrim condition still exists remove and replace the affected servo Page 5 28 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Aileron Mistrim Check for possible fuel imbalance Right Check aileron control adjustments If mistrim condition still exists remove and replace the roll servo Check rudder control adjustments If mistrim condition still exists remove and replace the yaw or servo Rudder Mistrim Left Allow the system to complete pre flight tests Pre Flight Test The preflight test should finish within 2 minutes If it does Fails not pass the red PFT annuncia
19. Removal 1 Gain access to the forward avionics compartment in the nose of the aircraft 2 Disconnect the AHRS connector 3 Loosen the four Phillips thumbscrews with a screwdriver until they are free from the rack 4 Gently lift the GRS 77 from the mounting rack If the mounting rack is removed the GRS 77 must be re calibrated Do not loosen mounting bolts See Section 7 7 Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage Place the GRS 77 on the mounting plate ensuring the orientation is correct Fasten the unit to the plate using the Phillips thumbscrews Connect the connector to the GRS 77 ee O Calibrate and test the GRS 77 according to Section 7 7 6 9 GMU 44 Magnetometer Removal 1 Disconnect electrical wiring harnesses and remove the tailcone 2 Loosen three screws connecting the unit to the aircraft mounting bracket using a non magnetic Phillips screwdriver 3 Remove the cable tie attaching the magnetometer pigtail harness to the shelf Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Fasten the GMU to the aircraft mounting bracket using a non magnetic Phillips screwdriver 3 Attach the magnetometer pigtail harness to the shelf with a cable tie 4 Reinstall tailcone and connect the electrical wiring harnesses 5 Calibrate and test the GMU 44 according to Section 7 7 6 10 GDL69A Remo
20. is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD Km air LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ES Figure 3 29 Lightning System Option Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for GIA 2 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 32 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 19 Stormscope WX 500 Configuration Load Confirmation 1 With PFD1 in configuration mode use the PFD1 large FMS knob to select OTHER and the Stormscope configuration page STORMSCOPE DATA STATUS HEADING FLAG MODE HEADING STAB ANT MOUNT HEADING VALID HEADING FORMAT SYNC ANGLE HDG FLAG SENSE SYNC REF TEST FAULTS MODE STRIKE COUNT STATUS TRIGGER COUNT STORMSCOPE MODE y STRIKE RATE HEADING y l HDG REF DISABLED Figure 3 30 Stormscope Configuration Page 2 Activate the cursor to highlight the DATA field Use the small FMS knob to open the drop down menu then select Config and press ENT key on the PFD1 oTORMSCOPE DATA Figure 3 31 Stormscope Configuration 3 Verify that the DATA window shows the following Hdg None Hdg Valid Flag Flag Sense J3 4 H
21. 190 00915 01 MFD1 has exceeded its operating temperature range PFD 1 has exceeded its operating temperature range PFD 2 has exceeded its operating temperature range Check cooling fan and wiring for proper operation if applicable Y Replace cooling fan if unable to determine if operating correctly v If problem persists replace the MFD If problem continues contact Garmin Aviation Product Support for assistance Check cooling fan and wiring for proper operation if applicable Y Replace cooling fan if unable to determine if operating correctly v If problem persists replace the PFD1 If problem continues contact Garmin Aviation Product Support for assistance Check cooling fan and wiring for proper operation if applicable v Replace cooling fan if unable to determine if operating correctly v If problem persists replace the PFD2 e f problem continues contact Garmin Aviation Product Support for assistance Page 5 49 Revision 6 5 9 4 Key Alerts Failure Message Cause Solution S MFD1 key KEYSTK key is stuck PFD 1 key KEYSTK key is stuck PFD 2 key KEYSTK key is stuck The SYSTEM has determined a key is stuck on MFD1 The system has determined a key is stuck on the PFD 1 The system has determined a key is stuck on the PFD 2 5 9 5 Miscellaneous Alerts Failure Message Cause Solution S XTALK ERROR A flight display cr
22. 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable TAWS A Press ENT key on PFD1 4 Verify Enable TAWS A is displayed in the Item window Press LOAD CONFIGURATION ID 63FE738 SYSTEM UPLOAD LRU VERS CARD VERS CARD PART NUM SOFTHARE CONFIGURATION N A Ef Figure 3 41 TAWS A Enable 9 Monitor load progress Verify software load completes without errors as indicated by the following 5 Green PASS in Configuration column Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the TAWS A Enable Card from PFD1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 43 190 00915 01 Revision 6 3 32 Supplemental Database Loading 1 Open PFD1 PFD2 and MFD circuit breakers 2 Remove the SD card containing the supplemental databases from the lower slot of the MFD Supplemental databases include basemap Safetaxi airport terrain obstacle airport directory and terrain databases 3 Download the current supplemental databases to the SD card 4 Reinsert the SD card containing the cur
23. 2 Electrical power to the MED is also provided by the Essential Bus The displays will power up immediately with external or aircraft power or battery operation All displays are installed in the King Air panel using 4 turn fasteners Three CDU cooling fans are also installed behind the panel for PFD and MFD cooling Figure 2 1 Display Units G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 1 190 00915 01 Revision 6 2 1 2 GMA 1347D Audio Panel 2 The Garmin GMA 1347D Audio Panel integrates NAV COM digital audio intercom system and marker beacon controls The 200 B200 installation includes two GMA 1347D panels The GMA 1347D panels provide control of all cockpit intercom mic systems as well as NAV COM ILS audio The units also provide display reversion mode control through a large red button Warning and alert audio received by the GMA 1347Ds is processed by and received from the GIA 63W Integrated Avionics Units IAUs Electrical power to GMA 1 is provided from the Essential bus Electrical power to GMA 2 is provided from Avionics Bus No 1 GMA 1 will be powered immediately with external or aircraft power or battery operation GMA 2 will operate after selecting Avionics Master on The GMA 1347D units interface with the existing marker beacon antenna as well as existing mic and phone jacks and oxygen mask mic Figure 2 2 Audio Panel 2 1 3 GMC 710 AFCS Control Unit The dedicated AFCS contr
24. 3 23 GSR 56 Satellite Reciever Option Configuration Follow this procedure to enable the optional GSR 56 satellite receiver function Note that the GDL 59 wi fi data link option must be loaded per Section 3 21 prior to loading the GSR 56 option 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight GSR 56 Press ENT key on PFD 1 4 Verify GSR 56 is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A wy N A wy ECTM Exceedance Reports N A wy Figure 3 35 GSR 56 Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME GDL 59 and ECTM Exceedance Reports e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 37 190 00915 01 Revision 6 3 24 POTS Handset Configuration Follow this procedure to enable a POTS handset if installed Note that the GDL 59 wi fi data link o
25. AP DISCONNECT J HONITOR BOARD STATUS SERVO PROGRAM 1 AP DISCONNECT a SERVO PROGRAM 2 PFT PASSED SERVO PROGRAM 3 HIGH RES LOAD CELL CAL m HIGH RNG LOAD CELL CAL mi CONTROL BOARD STATUS SERVO PROGRAM 1 AP DISCONNECT SERVO PROGRAM 2 SERVO PROGRAM 3 DRIVE SERVO RPH B BBr 8 00pm CURRENT B Bin lb SLIP CLUTCH TEST RESULTS n NOSE UP NOSE DOWN CLUTCH ENGAGE STATUS _ MIN inib A m MAX ___ _In lb ESA a ENG CLCH DRY SRVO RST GAIN Figure 5 6 GFC Status Page GIA STATUS AP DISCONNECT Shows the condition of the AP DISC 28 VDC input to the GIAs and servos which is required for the Autopilot to operate A green status indicator shows the AP DISC switch 1s closed and the GFC 700 is activly receiving 28 volts A red X indicates the GIAs and servos are no longer receiving the 28 VDC AP DISC power switch open or other fault MONITOR CONTROL BOARD STATUS Shows the condition of various monitor board components SERVO PROGRAM 1 3 Servo program discretes are used to determine the HW strapping for each GSA to define the servo type This information can be cross referenced against the system interconnects to verify proper servo grounding AP DISCONNECT Same as GIA Status PFT Indicates whether the pre flight test has passed or failed HIGH RES amp HIGH RNG LOAD CELL CAL Shows the condition of the high resolution and high range load cells on the monitor board If box is black this indicates a corrupt or missin
26. Check to ensure the rear plate is not bound by the connector harness 3 Lock the GDL 59 in place using the lever locking handle Fasten the handle to the GDL 59 body using the provided Phillips screw CAUTION Start the handle screw into the hole carefully to avoid cross threading Do not apply torque in excess of 14 in lbs to the handle screw The application of torque exceeding 14 in lbs to this screw will damage the LRU case and or retaining hardware 4 Reinstall the two rack mount angles on the remote equipment shelf using retained hardware Page 6 18 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 Reinstall the cabin center floor panel 6 Ifnew unit is installed register with Garmin Flight Data Services per Section 7 27 7 Configure the GDL 59 per Section 3 21 and 3 23 Test the GDL 59 per Section 7 28 6 34 GSR 56 Satellite Receiver Removal 1 Gain access by removing the cabin center floor panel at the main entry door 2 Detach the two rack mount angles from the remote equipment shelf Retain all mounting hardware 3 Unlock the unit from the rack by loosening the ratcheting latch mechanism 4 Remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Insert the unit into the installation rack CAUTION Do not use excessive force when inserting the GDL 56 into the rack This
27. E LOLd H H S1uod ey visa USLSIILTY ABONVIS N A me i dOL ea d3JdSHIY ABUNVIS lt av3Hx Na avaHy1nd SYNSSAud LAV 34NSSI8dA GYVMYOS Figure 2 20 Pitot Static System Post G1000 STC Page 2 15 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 5 Shield Block Grounds The connectors on Garmin G1000 LRUs utilize the Shield Block grounding system to provide necessary ground reference to wire shielding and or transducers The shield block termination method allows multiple grounds to be terminated directly to a block mounted to the connector backshell assembly Shielding and grounding requirements for all other LRUs and connectors are shown in the respective install drawings 2 6 G1000 GFC700 Block Diagram Integrated Avionics Unit System Inegration Processors VO Processor VHF COM WHF ee cles ey APCS Mode Logic 1 Flight Director Calculations Sano Communication Page 2 16 Revision 6 1 GEA 71 Engine Airframe Unit No 2 GIA 63W Air Data Integrated Avionics Unit Computer bi GDL 69A Datalink System ray ash Processors Aispead Processors Altibuda Vertical Speed VHF COM VHF NAWLOC GPS GRS 77 Glidesiope AHRS WAAS VNAV Rate of Turn ee Si Skid AFCS Mode Logic 2 Flight Director Calculations Data Link Servo Communication GWX 68 WX Radar GTS 8XX GSR 56 j Receiver E 80 iE 80 GSA B E Servo Kano Servo Abi Seno
28. If the measured current is 1 2 amps 20 high from the target l amp current then the allowable voltage measurement would be 20 high 2 5 milli volts would now be 3 0 milli volts Page 4 16 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 5 4 Phase 4 Electrical Bonding Procedure 1 Connect the positive lead of the power supply to the engine compartment grounding bracket battery negative connection to the airframe Connect touch the positive lead of the voltmeter to the same point NOTE Ensure that the voltmeter and power supply probes do not touch so as not to induce contact resistance 2 Touch negative lead of power supply to each of the test points listed while performing Step 3 At each point configure the power supply to produce 1 amp before measuring voltage Use an ammeter to ensure current is within 1 amp 100 milli amp at each point 3 Set the voltmeter to measure milli volts and null the reading Measure the voltage from the engine grounding bracket step 1 to each of the following points and record the voltage Perform Step 2 at each point to ensure that 1 amp 100 milli amp is present before measuring Nose Section e GWX 68 body milli volts Nose Avionics Compartment e GIA top milli volts e GIA 2 top milli volts e GRS 77 1 metal base milli volts e GRS 77 2 metal base milli volts e Standby battery milli volts Rear Fuselage and Empennage e GMU
29. If you have any questions or would like additional information please refer to our web site at www garmin com prop65 CAUTION The GDU lens is coated with a special anti reflective coating that is very sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings IMPORTANT All G1000 screen shots used in this document are current at the time of 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 B G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 TABLE OF CONTENTS PARAGRAPH PAGE l INTRODUCTION Guau io 1 1 SL CONTENT SCOPE PURPOSE NA 1 1 L2 ORGANIZATION eee ae eat hele re tare hice E oa tate AE dando kisah ena etn nabi anak come A 1 3 ES DEPINITIONS ABBREVIATION SA A 1 4 A PUBLICATIONS htc eh cael celica lt ll 1 5 K3 REVISON AND DISTRIBUTION ld di aa ada aiii 1 6 2 OY DINA acess aaaea taae aeaaaee aaa aeaaeae aoaaa aaae i aeara aaee died 2 1 2k EQUIPMENT DESCRIPTION SAA A 2 1 22 ALDO OPUONAS INTERFACES rr A a 2 11 2 0 BLECTRICAL POWER DISTRIBUTION stations 2 12 zA A ON esd E en ne ee ee a
30. PFDs Reconnect or remove the shield from the GPS antennas and verify the MFD LOI indication and PFD TAWS N A and LOT annunciations are removed once the GPS satellites are acquired Pull PFD1 PRI and PFD1 SEC circuit breakers Re power PFD1 in configuration mode and use the PFD1 FMS knob to select the Audio Alert Configuration page Ensure cockpit speaker is selected ON Use the PFD1 FMS knob to highlight each of the following messages then select PLAY Verify each of the following audio messages are played e Too Low Terrain e Sink Rate e Pull Up e Don t Sink e Five Hundred e Caution Terrain 2X e Terrain 2X Pull Up 2X e Caution Obstacle 2X e Obstacle 2X Pull Up 2X e Terrain Ahead 2X e Terrain Ahead Pull Up 2X e Obstacle Ahead 2X e Obstacle Ahead Pull Up 2X 11 Pull the PFD1 PRI and PFD1 SEC circuit breakers and re power PFD1 in normal operating mode If no other service is to be performed continue to the return to service checks in Section 8 7 34 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Page 7 15 2 Functional Check for TAWS A 1 With the G1000 in Normal Mode use the GCU FMS knob to select the MAP group and TAWS page on the MFD 2 Verify that the title at the top of the page reads MAP TAWS A NOTE If TAWS has not been enabled the title will read MAP TERRAIN PROXIMITY or MAP TERRAI
31. Verify that the alert messages shown in Table 5 2 are not displayed on the PFD Alerts Window If so follow the solutions described in Table 5 2 3D terrain presentation does not Verify that the G1000 AHRS and heading data are valid on the PFD Verify appear on PFD that a valid GPS 3D position solution is being received Troubleshoot these systems in accordance with sections 5 10 4 and 5 15 If a terrain database update has just been performed allow the system time to initialize and verify the data When the databases have been verified the current database cycle and version are reported on the MFD AUX System Status page The following table provides SVS Pathways specific alert messages which may appear in the Alerts Window on the PFD press the ALERTS softkey on the PFD to view the Alerts Window Table 5 2 SVS Related Alert Messages Failure Message Cause Solution S Geographical operation limitations are SVS is disabled because the defined in the AFMS listed in Table 1 2 No SVS DISABLED OUPO aircraft exceeded the boundaries eee available terrain region Aine loaded terran dalabase Ensure that operations are within this geographic area Ensure the P N 010 00330 43 Terrain Cards are installed in the lower slot of SVS is disabled because a9 Arc gach display Second or better database is not SVS SVS DISABLED Terrain DB resolution too low currently loaded If terrain data has been recently updated ensu
32. serial number manufacturer and model o GSR 56 unit serial number o Gl1000 system ID number o Name of aircraft owner and contact information o Credit card information Garmin Flight Data Services will provide additional information for activation of data services To obtain the G1000 system ID number and GSR 56 unit serial number accomplish the following 1 Turn the large FMS knob on the MED to select the AUX page group 2 Turn the small FMS knob to select the SYSTEM STATUS page Record the SYSTEM ID number shown in the AIRFRAME field This number 1s unique for each G1000 system AIRFRAME S75 SOFTHARE VERSION CONFIGURATION ID CRG PART HUMBER ponpa i SYSTEM ID Number Location CHECKLIST 3 Use the large FMS knob to scroll the cursor to GSR1 if GSR 56 is installed Record the GSR 56 serial number shown in the LRU INFO field G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 63 190 00915 01 Revision 6 For previously activated systems if the GSR 56 satellite receiver unit is replaced the new unit serial number must be registered with Garmin Flight Data Services Contact Garmin Product Support and follow the activation procedure as described previously in this section For previously activated systems if the GDL 59 wi fi datalink unit is replaced the system must be registered again This can be accomplished by entering the same passcode received during the intial activation process as descr
33. to remove potential sources of audio noise for inputs that are not used If in doubt as to which buttons should be disabled reload GMA config files and other config files for optional equipment installed in the aircraft i e ADF HF etc from the loader card Verify on the GMA CONFIGURATION page that Disable Split COM has a green box Due to the closeness of the COM antennas and high power of the COM transceivers Split COM operation is not approved If the box is black indicating COM 72 button is active highlight Disable Split COM with the cursor and press the ENT key to turn the box green which will deactivate Split COM mode Reduce volume level of the item that caused the speaker to cut out when turned up A speaker protection circuit disables the speaker output if the volume is too high If the volume is not sufficient replace aircraft cabin speaker reference the Airframe Maintenance Manual Mic Audio Heard in e Reduce ICS Volume Speaker GMA XTALK GMA crosstalk error has occurred Page 5 52 Revision 6 Ensure both GMA units are receiving power Ensure both units are properly configured by verifying there are no GMA alert messages Check interconnect wiring between the GMA s for faults Replace GMA1 If problem persists reinstall GMA1 and replace GMA2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 9 7 GMA Alerts Failure Message Cause Solution GM
34. troubleshooting section Troubleshoot GIA1 2 GRS1 wiring for faults ref Failed Path troubleshooting section Replace the GRS 77 1 AHRS2 GPS AHRS2 not The GRS 77 2 is not receiving Ensure that a cell phone or a device receiving backup GPS backup GPS information from using cell phone technology is not information either GIA 63 turned on even in a monitoring AHRS2 GPS AHRS2 operating The GRS 77 2 is operating in the state in the cabin exclusively in no GPS mode absence of GPS Check GPS status for GIA 1 and 2 AHRS2 GPS AHRS2 not The GRS 77 2 is not receiving on MFD AUX GPS STATUS page receiving any GPS information GPS data from the GPS receivers li ear both GPS recolvels cannol acquire a position lock see GPS AHRS2 GPS AHRS2 using The GRS 77 2 is using the troubleshooting section backup GPS source backup GPS data path Troubleshoot GIA1 2 GRS2 wiring for faults ref Failed Path troubleshooting section Replace the GRS 77 2 AHRS MAG DB AHRS magnetic The G1000 has detected a model database version magnetic model database version mismatch mismatch Load AHRS magnetic model field in both GRS units Page 5 68 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Failure Message Cause Solutions S MAG VAR WARN Large Magnetic variance value from magnetic variance Verify all GMU 44 is not accurate course angles 5 15 3 GM
35. usage PFD 2 VOLTAGE PFD 2 has low voltage Reducing power usage MFD1 VOLTAGE MFD1 has low voltage Reducing power usage The G1000 has determined MFD1 needs service The G1000 has determined the specified PFD needs service The specified PFD supply voltage is low The MFD supply voltage is low Ensure the MFD connector is fully seated and locked If the unit was started in a very dark environment the photocells may not have enough light to initially raise the CCFT level Go to the GDU STATUS page in configuration mode ensure CCFT CRNT 1 4 2 levels are above 50 v Ifthe CCFT levels are not above 50 apply light to the photocell and observe if the CCFT level rises If the CCFT level rises disregard the message If the CCFT level does not rise replace the MFD Replace the MFD Ensure the PFD connector is fully seated and locked If the unit was started in a very dark environment the photocells may not have enough light to initially raise the CCFT level Go to the GDU STATUS page in configuration mode ensure CCFT CRNT 1 4 2 levels are above 50 v Ifthe CCFT levels are not above 50 apply light to the photocell and observe if the CCFT level rises If the CCFT level rises disregard the message If the CCFT level does not rise replace the PFD Replace the PFD Check input voltage to PFD If input voltage is ok replace PFD Check input voltage to MFD If input voltage i
36. 1 Press the push to talk switch s again to cycle its operation Check push to talk switch s and wiring Check GIA2 GMA 1347D 2 interconnect COM2 PTT COM2 push to talk i external push to talk Switch GIA1 and GIA2 to identify key is stuck PTT switch is stuck in the whether the unit or connectors wiring enabled or pressed state is at fault Both GIAs must be configured when swapped see Section 3 9 v If problem follows the unit replace GIA2 v If problem persists replace defective GMA 1347D 2 Page 5 56 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Failure Message Cause Solutions S COM1 RMT XFR COM1 remote transfer key is stuck COM2 RMT XFR COM2 remote transfer key is stuck COM1 TEMP COM1 over temp Reducing transmitter power COM2 TEMP COM2 over temp Reducing transmitter power G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 The COM1 external remote transfer switch is stuck in the enabled or pressed state The COM2 external remote transfer switch is stuck in the enabled or pressed state The specified COM transceiver is reporting a high temperature condition and is reducing transmit power to prevent damage Press the COM1 external remote transfer switch again to cycle its operation Check COM1 external remote transfer switch and wiring Switch GIA1 a
37. 1 With the ChartView Enable card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable ChartView Press ENT key on PFD1 4 Verify Enable ChartView is displayed in the Item window Press LOAD CONFIGURATION ID EBC959D4 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ES Figure 3 39 ChartView Enable 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 41 190 00915 01 Revision 6 7 De activate the cursor 8 Power down the system and remove the ChartView Enable card from PFD1 3 30 TAWS B Enable Follow this procedure to enable the TAWS Class B function A TAWS B Enable Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure 1 With the TAWS B Enable card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob o
38. 1347D Test Phase 2 and 4 GMA 1347D Qty 2 Landing Gear Aural Alert Check Phase 2 and 4 XM Audio Suppression Check Phase 2 and 4 6 3 Removal amp Replacement On Condition GEA 71 EAU Qty 2 6 4 GTX 33 Removal amp Replacement On Condition Transponder Qty 2 Special Inspection Perform GTX 33 test 24 Calendar Months Removal amp Replacement AS On Condition GDC 74B Qty 2 Special Inspection Perform Air Data Test 24 Calendar Months Special inspection for RVSM compliant aircraft only NOTE These checks required for initial RVSM 24 Calendar Months RVSM checks compliance 7 23 On Condition These checks also required when GFC700 Periodic Check GIA 63W IAU Qty 2 see note e astatic port is removed installed e the RVSM critical region is repaired or painted GRS 77 AHRS Removal amp Replacement 2 atys Magnetic variation database update 6 GMU 44 Magnetometer Qty 2 _ Removal amp Replacement G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 5 190 00915 01 Revision 6 Manual GDL 59 Wi Fi Datalink GSR 56 Satellite Receiver G1000 Cooling Fan Fail Annunciation Check Nose Avionics Compartment Fans Operational Check Instrument Panel Fans Operational Check G1000 Redundant Connection Check Removal amp Replacement Verify the operation of the fan power and fan speed monitoring circuits for GIA1 Fan GIA2 fan
39. 2 15 Za SMELO BEOCK GROUNDS arca 2 16 26 AG10007GEC 00 BEOCK DIAGRAMA ee 2 16 3 GIVOCONTROLS OPERATION lt a eee eee 3 1 a1 GDUT04Z0A AND GDU T500 DISPLAY ii aa 3 1 Le AA MFC ONTROL LER eae a ii ice 3 3 a0 GMO TIOSAFCS CONTROLS excise ieee a 3 3 DA GMA PAID ADIOPAN ccc sata natal set ahaha tun atta E tate ult 3 4 3 5 GlOOO NORMAL MODE oraraa an aa N AT a EAN A AS 3 5 107 TREE VERSION AIRY MODE iia 3 6 Sf CONFIGURATION MODE OVERVIEW sata 3 7 3 8 GLO007 GFC 700 SOFTWARE INFORMATION ida 3 11 3 9 G1000 SOFTWARE CONFIGURATION PROCEDURE cscsssecccccccceeeeeeeeeeassesssseceeeeceeccceeeeeeeeeaaaaaas 3 18 3 10 TAWS A SUPPORT CONFIGURATION ccccccccccccccccccccccccccccccccecccccecececcececceccececececeseceeeeeseees 3 24 3 11 TAWS A VOICE NO CALLOUT OPTION CONFIGURATION sssssseeeeeeeccceceeeeeeesaaaesseeeseeees 3 25 3 12 TAWS A VOICE CALLOUT OPTION CONFIGURATION ccc ssssssssseseseeeeeeccceeeeeeessaaaaaensseseeees 3 26 3 13 ADEOPTON CONFIGURATION a 3 27 3 14 DME OPTION CONFIGURATION rocas 3 28 3 15 RAD ALTFOPTION CONFIGURATION tft 3 29 3 16 NON GARMIN TRAFFIC SYSTEM OPTION CONFIGURATION ccccccccceceeeecesessseseeeeeeeeceeeeeeeees 3 30 3 17 GTS 8XX TRAFFIC SYSTEM CONFIGURATION cccccccccccccccecesesesesesseeecececcccseeeeeeaaaaaaeneseseeees 3 31 3 18 STORMSCOPE W X 500 OPTION CONFIGURATION cccccccccccsseeeecceceeecsaeeeecccceeesuaaeseeeeeess 3 32 3 19 STORMSCOPE WX 500 CONFIGURATION LOAD CO
40. 200 B200 Series King Air Revision 6 190 00915 01 Symptom Recommended Action Terrain Obstacle Safetaxi does not display Display will not track dimmer bus Keyboard will not track dimmer bus Ensure supplemental data cards are inserted correctly in the lower slots of all three GDU s Allow the system to verify the data on the cards for approximately five minutes after power up If a database does not activate reload the problem database onto the SD Card or replace the card Reload GDU configuration files If display is a PFD swap PFD1 and PFD2 to see if problem remains with display v Replace display if condition remains with the same unit v If condition remains in original position after swapping displays check GDU dimmer input to verify voltage is present If display is the MFD check dimmer input to verify voltage is present v Replace MFD if dimmer voltage is present G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 45 190 00915 01 Revision 6 5 9 GDU 104X Alerts 5 9 1 Software Configuration Alerts Failure Message Cause Solution S SW MISMATCH GDU software and or MED software versions do version mismatch Xtalk is off not match MANIFEST PFD 1 software mismatch Communication Halted The system has detected an e Load correct software version incorrect software version loaded See Section 3 9 for GDU 1040 MANIFEST PFD 2 software in the specifi
41. 3 Select Technical Tools then select Software Downloads 4 Inthe Keyword s filter enter 0985 and click on the Go button 5 A screen similar to the one shown below will appear The numbers shown are for example only Download symbol Type Publish Date y G1000 King Air 200 300 Version Software Jun 17 2011 F E 0985 04 Summary Support Content Name Type Size kb G1000 King Air 200 300 Version 0985 04 006 B0985 04 La SB0920 pdf pdf 123 6 Click on the download symbol for the appropriate software version part number based upon the information provided in Garmin GA Drawing 005 00421 03 and save the file to the local hard drive Page 3 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 Double click the exe file that was downloaded The following window will pop up on the screen Ensure that there is an empty SD card in the card reader and then click Setup WinZip Self Extractor 006 B0985 04_0A exe 1000 Software Update To install software press Setup WinZip Self Extractor 006 B0965 04_0A exe 61000 Software Update To install software press Setup Unzipping grm avr sye gca NOTE When the extraction begins the program automatically deletes all current files on the SD card and copies the selected files to it regardless of the file format on the SD card Ensure files are not necessary or card is empty before proceeding 9 G1000 S
42. 4 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 B AHRS and ADC data path check 1 Verify there are no AHRS loss of data messages such as e AHRS not receiving any GPS information e AHRS not receiving backup GPS information e AHRS using backup GPS source 2 Place the G1000 in configuration mode 3 Inthe GIA page group go to the GIA RS 232 ARINC 429 CONFIG page 4 With GIA 1 selected in the SELECT UNIT window verify the RS232 Channel 1 GDC74 1 and RS232 Channel 6 GRS77 1 indicators are green Ref Section 5 2 1 2 5 With GIA selected in the SELECT UNIT window verify the ARINC 429 INS GDC74 1 and ARINC 429 IN6 GRS77 1 indicators are green Ref Section 5 2 1 2 6 With GIA2 selected in the SELECT UNIT window verify the RS232 Channel 1 GDC74 2 and RS232 Channel 6 GRS77 2 indicators are green Ref Section 5 2 1 2 7 With GIA2 selected in the SELECT UNIT window verify the ARINC 429 INS GDC74 2 and ARINC 429 IN6 GRS77 2 indicators are green Ref Section 5 2 1 2 8 Inthe GDU page group go to the GIA RS 232 ARINC 429 CONFIG page 9 With PFD1 selected in the SELECT UNIT window verify the ARINC 429 IN1 GRS77 1 and ARINC 429 IN2 GDC74 1 indicators are green Ref Section 5 2 1 1 10 With PFD2 selected in the SELECT UNIT window verify the ARINC 429 IN1 GRS77 2 and ARINC 429 IN2 GDC74 2 indicators are green Ref Section 5 2 1 1 11 Re
43. 5 20 1 are fulfilled for the applicable situation Ensure power is present at display backshell connector Troubleshoot per the Blank Display GDU section Ensure that criteria listed in Section 5 20 1 are fulfilled for the applicable situation Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wiring as needed Retry software file load or try using a different card Ensure that the MFD is not touched during the loading process Ensure that LRU part number is compatible with software version and Card Loader Refer to the General Arrangement Drawing and to Section 3 8 of this document Replace LRU Ensure that the criteria listed in Section 5 20 1 are fulfilled for the applicable situation Ensure that LRU is reporting data on System Status page LRU is ONLINE Check data path wiring as needed Retry configuration file load or try using a different card Ensure that the MFD is not touched during the loading process Ensure that LRU part number is compatible with Card Loader Refer to the General Arrangement Drawing and to Section 3 8 of this document Replace LRU Ensure that the criteria listed in Section 5 20 1 are fulfilled for the applicable situation Ensure GIA1 and GIA2 are configured correctly Check wiring connectors amp pins as needed Ensure that proper software file part number and version were loaded to LRU Refer to the General Arrangemen
44. 6 190 00915 01 7 23 4 RVSM Air Data System Check Perform the Air Data Test per Section 7 6 1 If either the pilot or copilot air data system does not meet the tolerances specified have maintenance checks performed on the air data system or the pitot static system IMPORTANT RVSM operations are prohibited until the air data system meets all test conditions G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 47 190 00915 01 Revision 6 7 23 5 RVSM In Flight Altitude Hold Check RVSM operation requires that the autopilot system accurately maintain the acquired altitude during non turbulent non gust cruise conditions The autopilot must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1 3 The autopilot must be shown to meet the performance specification of the following in flight altitude hold test 1 Verify the following conditions normal RVSM cruise flight e Altitude FL290 to FL350 e Altimeter setting 29 92 in Hg 1013 HPA e Autopilot altitude hold engaged e Non turbulent non gust conditions 2 Record the data from the primary cockpit displays as specified by Table 7 9 every 5 minutes for a minimum flight segment of 30 minutes in length The maximum altitude deviation shown on the display throughout the test should not exceed 65 feet If the aircraft fails to hold altitude to this tolerance repeat the test ensuring that the airspeed remains constant and the air r
45. 7 2 Configuration Prompts When configuration settings are changed the technician receives on screen prompts and or confirmations such as those shown in Figure 3 12 Section 7 shows other prompts encountered during the configuration process CONFIGURING GIA 1 GIA 1 CONFIGURED OK Figure 3 12 Configuration Status 3 3 Data Transmission Indicators Several configuration screens utilize an indicator light system to show discrete ON OFF data and or hardware component status Unless otherwise noted the following applies to all such status indicators e Green Checkmark Expected data is successfully received and is ON A green check could also indicate that the parameter component is working correctly e Red X Expected data is not received A red X could also indicate that a parameter component is invalid e White N A Expected data is OFF or no data is expected GDU STATUS ALLINA BASE MAF ETHERNET 1 ETHERNET 2 ETHERNET 3 ETHERNET 4 Ro 232 1 Ra 2s2 2 IRDA Figure 3 13 Data Transmission Indicators G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 9 190 00915 01 Revision 6 3 4 Configuration Mode Navigation Using the FMS knob as described in Section 3 1 2 a user can navigate through different pages and page groups in the Configuration Mode For complete description and breakdown of each page refer to the G1000 System Maintenance Manual listed in Table 1 3 System Page Group 1
46. 835 Emergency Power Supply during test This test is performed with the battery removed from the aircraft A Press and hold TEST SWITCH Figure 4 5 Item 4 If no OUTPUT VOLTAGE MONITOR LED s come on 1 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 5 Item 5 to the ON position 2 Press and hold TEST SWITCH Figure 4 5 Item 4 and observe the INDIVIDUAL CELL MONITOR LED s Figure 4 5 Item 1 a If all INDIVIDUAL CELL MONITOR LED s come on except DS12 the unit is damaged and requires repair at an authorized repair station b If all INDIVIDUAL CELL MONITOR LED s are on a low battery voltage condition exists B Perform the Charging Procedure 4 16 4 Charging Procedure Constant Voltage Charging Method Locally manufacture a power cable using 16AWG wire and the appropriate mating connector Include a Diode 15 Adc min 50 0 PIV or greater to prevent battery discharge in case of loss of power from the power source Using the external power supply apply 30 0 Vdc 10A maximum current limited to J1 connector pins 11 and 7 and charge the unit for 16 hours The batteries should reach 80 capacity within 1 hour and full charge at 16 hours PS 835 Power Supply Power Supply J1 pin 7 ground Figure 4 6 Power Supply Connection G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 33 190 00915 01 Revision 6 4 17 Power Bus Check 4 17 1 Power Bus Feeder Check This procedure
47. AFCS status alerts 1 Ensure the G1000 is in normal mode autopilot is not engaged and the mode controller XFR key is selected to the pilot side 2 Press the left part of the pilot s pitch trim switch upwards for approximately 10 seconds and verify that the red PTRM annunciation is displayed on both PFD 1 and PFD 2 3 Release the switch and wait for the PT RM annunciation to clear 4 Press the left part of the pilot s pitch trim switch downwards for approximately 10 seconds and verify that the red PTRM annunciation is displayed on both PFD 1 and PFD 2 5 Release the switch and wait for the PTRM annunciation to clear 6 Repeat Steps 2 through 5 for the right part of the pilot s pitch trim switch 7 Repeat Steps 2 through 6 for the copilot s pitch trim switch 8 Select copilot side by pressing the XFR key on the mode controller changes active GIA to GIA 2 9 Repeat Steps 2 through 7 and verify annunciations are displayed on both PFD 1 and PFD 2 10 Re select pilot side by pressing XFR key on the mode controller changes active GIA back to GIA 1 11 Hold the control yoke in the center position and center the pitch trim wheel 12 Press the Go Around button on the throttle and engage the autopilot Apply a forward load on the control yoke Verify that the pitch trim wheel rotates in the UP direction 13 Disconnect the autopilot by pressing the AP DISC button G1000 GFC 700 System Maintenance Manual 200 B200 Serie
48. AOA mode is inoperative e Troubleshoot Safe Flight lift computer Refer to Section 5 25 ESP DEGRADE ESP IAS mode is inoperative e Ensure ADC1 and ADC2 circuit breakers are closed and units are providing valid airspeed data e Ensure that the ESP Support Option has been installed per Section 3 20 e Ensure that the Enhanced AFCS unlock card has been ESP CONFIG ESP config error Config service installed per Section 3 34 req d e lf the ESP option needs to be removed reload the baseline configuration for the specific airframe and all applicable options as described in Section 3 9 Reloading the baseline configuration disables all previously enabled options NOTE From this point forward all message advisory alerts presented are common to all G1000 systems and are not specific to the King Air 200 B200 Messages are grouped according to LRU G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 25 190 00915 01 Revision 6 5 4 TAWS Troubleshooting Annunciation Cause _ Solution If message occurred on the first power up after unlocking TAWS cycle power to initialize TAWS Ensure each GDU contains the correct database data card Ensure the G1000 is configured for TAWS A TAWS system failure has v Ifthe system is not configured TAWS FALL occurred for TAWS reconfigure per Section 3 9 6 Verify GIAs are online Ensure a database or GDU SW mismatch has not occurred
49. Annunciator Switch STBY Battery Switch legends illuminates and reflects STANDBY BATTERY in white ARM in green and ON in amber e For the Prop Synch Annunciator Switch Prop Synch Switch legends illuminates and reflects PROP SYNC in white and ON in green 3 Release cockpit annunciator Press To Test switch 4 If further maintenance is not required proceed to Section 8 6 24 L 3 Avionics BF Goodrich PS 835 C or D Model Emergency Battery Removal 1 Gain access to the forward avionics compartment in the nose of the aircraft 2 Unscrew the knurled hold down nut to allow it to move free of the unit 3 Remove the unit from the rack Reinstallation 1 Install the emergency battery in accordance with the Electrical Equipment Install Nose Bay drawing refer to Master Drawing List listed in Table 1 2 for specific drawing number Refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 for access requirements as needed 2 If further maintenance is not required proceed to Section 8 Page 6 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 25 Standby Airspeed Indicator Removal 1 Remove MFD per Section 6 1 2 Disconnect pitot static plumbing from the back of the standby airspeed indicator Take necessary precautions to prevent foreign object debris from entering the pitot static lines during maintenance 3 Disconnect th
50. B200 Series King Air Revision 6 190 00915 01 Table 4 5 Pilot s Compartment Visual Inspection Procedure A Hem Description Procedure _Initials _ Locate equipment in the aft pedestal for the following inspection a Inspect the GCU 477 unit and connector for corrosion or other defects Check the GCU 477 integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Inspect the ADF control unit and connector for corrosion or other defects Check the integrity of the SHIELD ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Inspect all visible wire harness for chafing damage proper routing of wire bundles Pedestal Wiring and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 ADF control unit relocated by STC Inspect the GTP 59 units and connectors for corrosion or other defects Check the integrity of the SHIELD ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GTP 59 Qty 2 Inspect wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing li
51. B200 Series King Air Page 7 11 190 00915 01 Revision 6 7 5 GTX 33 Transponder Original GTX 33 _ is Reinstalled No software or configuration loading is required if the removed GTX 33 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to GTX 33 Test Section 7 5 2 Original GTX 33 _ Installed in Opposite Locations for Troubleshooting No software loading is required if the original GTX 1 and GTX 2 are installed in opposite locations Continue to Transponder Configuration Section 7 5 1 New Repaired or Exchange GTX 33 _ is Installed If a new repaired or exchange GTX 33 is installed the correct software and configuration files must be loaded to the unit per Section 3 9 Continue to Transponder Configuration Section 7 5 1 7 5 1 Transponder Configuration 1 If not applied apply power to the G1000 system 2 With PFD1 in configuration mode select the GTX page group then select the TRANSPONDER CONFIGURATION page on PFD1 3 The ADDRESS TYPE default is US TAIL To enter a non US Mode S registration number set the ADDRESS TYPE field to HEX ID 4 Activate the cursor and highlight the MODE S ADDRESS field Use the small large FMS knobs to enter the US aircraft registration number or other Mode S registration number TRANSPONDER CONFIGURATION XPDR 1 ACTIVE XPDR 2 ACT
52. Backshell Connector P681 ccccceeeeeessssssssseesssesseeseesseeeeeseseeseeseeeeeeseeeees 5 83 Figure 5 19 GTS 820 850 Mating Connectors P8001 and P8002 cccceeeseseseeessssssseseeseeseeeeens 5 83 Figure 5 20 GTS 820 850 Mating Connector ESOO ed acest ated ela 5 83 Prieure 5 21 GPA 65 Matine Connector POSI ieee ee ee 5 84 Figure 5 22 Signal Conditioner 1PVIB1 and 2PVIB1 ooooooooooooccnnnnncnnnccononanananonononnnnnnnnnnncncnonnninanannns 5 84 Facute d225 lt a Di 59 Natio Connector UPD OA aia 5 84 Figure 5 24 GSR 56 Mating Connector 1 PIO das 5 84 Fistre 0 SEO ista lada 6 6 Figure 6 2 Configuration Module Installation cocinada cedida 6 9 PISULS 025 GEA Backshell Thermocouples a 6 11 Figure 715 GrPO00 Normal Mode Check a a iin cesnaaivalsaelenmocsiales 7 2 Ficute 7 2 Marker Beacon Symbolo Os shorts AA AA 7 4 Figure 7 3 AUX GPS STATUS Page MEFD 2 0 c ccsccecccesesesacssecscascnecssassserscasensnesacssacecaeensnssees 7 6 Figure 7 4 Normal Engine Instrument Markings MFD 00oooooooonnccncccnononanononononnnnnnnnnnnnnccnnnnnananannnnnnnnnnoss 7 9 Page vi G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 FOULS J gc NICU ANG Robo 7 12 Pisto 76 Encino RUUD Tetra dolia 7 24 Foure 7 Normal Mode AHRS CHECK sind eea a e ea raa Tenian 7 25 Figure 7 8 Low Speed Awareness Band Symbolization ccccccceeesesesesssseses
53. Bulls Copse Road Hounsdown Business Park Southampton SO40 9RB UK Phone 44 0 23 8052 4000 Fax 44 0 23 8052 4004 RECORD OF REVISIONS ECO 4 6 09 Revise Table 1 1 to 0985 01 61175 7 17 09 Added GSM 86 TAWS A Radio Altimeter 62341 11 1 10 Added GDL59 GSR 56 GTS 8XX and ESP 76618 options 5 11 12 Updated procedures for software version 0985 04 90414 NS 7119 12 EN GA drawing reference error in Section arre DOCUMENT PAGINATION Section Pagination EJES 1 2 16 3 1 3 52 4 1 4 36 i i i i i i r 1 6 20 1 7 66 8 1 8 16 2 5 1 5 90 6 7 Page A G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 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 obtaining an export license The preceding statement is required to be included on any and all reproductions in whole or in part of this manual WARNING This product its packaging and its components contain chemicals known to the State of California to cause cancer birth defects or reproductive harm This Notice is being provided in accordance with California s Proposition 65
54. Bus The Entertainment Bus is a new bus added by this STC It is powered from the No 2 Avionics bus via a newly installed Entertainment Bus relay This relay is controlled via the existing Cabin Furnishing switch so that bus can be easily shed by pilot using single switch action along with the other cabin equipment Emergency Standby Battery The Standby Emergency Battery STBY BATT system in the King Air 200 B200 is designed to provide uninterrupted DC power to the Standby Attitude indicator gyro motor the Standby Altimeter vibrator and internal instrument lighting for the standby attitude indicator standby altimeter and the standby airspeed indicator from the L 3 PS 835 C or D Model Emergency Standby Battery This standby battery power is independent from the normal electrical system and provides redundant power for the standby instruments in the event that all other electrical power is lost Page 2 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Page 2 13 Revision 6
55. CLR key Deactivate cursor 3 39 Clearing Default User Settings 1 Remove power from PFD1 PFD2 and MFD by pulling the PFD1 PRI PFD1 SEC PFD2 and MED circuit breakers 2 While holding the CLR button on PFD1 reset PFD1 PRI and PFD1 SEC circuit breakers 3 While holding the CLR button on PFD 2 reset the PFD2 circuit breaker 4 While holding the second key from the right side of the MFD beginning on the right side of the MED count 2 keys to the left reset the MFD circuit breaker 5 When prompted to clear user settings select the YES softkey on each unit G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 51 190 00915 01 Revision 6 This page intentionally left blank Page 3 52 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 Instructions for Continued Airworthiness 4 1 Airworthiness Limitations The G1000 Integrated Flight Deck including the GFC 700 AFCS is airworthy when installed configured and maintained in accordance with this section The G1000 and GFC 700 systems possess the following maintenance airworthiness limitations The intervals for the airworthiness limitations are shown in maximum number of hours between checks as required for certification Table 4 1 aligns these requirements with the King Air Phase Inspection Program These limitations were derived from the certification data GFC 700 Limitations e Every 220 hours perform a
56. E gt E P lt _LSTBY ENG ANTIICE oe R GEN CTRL RENG FUEL CTRL HEAT c MFD STBY LT FS FIRE DETECT En 5 R MAIN ENG ANTLICE oq PILTPFDLT x pats EPA z E a 0 k L CHIP DETECTOR ee L E 2 R STBY ENG ANTI ICE 5 PROP BALANCE SYNG 5 R CHIP DETECTOR 4 AUTO FEATHER 1 i t 1 STBY INSTR ESSENTIAL AVIONICS AVIONICS BUS BUS BUS 1 BUS 2 FJ STBY BATTERY Sef PFD NO 1 PRI cdo AFCS To GDL 69 dl STBY ATT od GIA NO 1 PRI cme GMA NO 2 To TRAFFIC A STBY ALTM o A COMMNO B COMMNO 2 Sd STORMSCOPE S AHRS NO1 PRI cane GTX NO 2 To ADF i ADC NO 1 PRI NS RADAR 5 RADIO ALTIMETER GTX NO 1 cane DME Sd GMANO 1 S ENTERTAINMENT BUS y ES sy GDL 59 by En SD GSR 56 MFD FAN 5 LPITOTHEAT Figure 2 19 G1000 Component Power Sources Page 2 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Pitot Static System The following schematic shows the pitot static system as modified by this installation 2 4 sng v1va NIVYa NIVEd 39808d 1YO Pe Si o A e 18Od 1SVIN OILVLS 31VN83 7V LOLId HA ANWA YOL937138 OILVLS 31VN83 7V norog did LOMA OO HALNdWOO lt fo o 3gOHd V1VO HIV 14 S18Od 1WO OILVLS HA oe eee dOL 7 E 1 YHALNdWOO ddd LO1d09 _ A WOLLOG 1SVIN
57. Failure Condition For a dual GIA failure the following shall occur Open GIA1 primary and secondary CBs e COM1 NAV1 8 COM2 NAV2 fields flag invalid IA 2 CB ee GPS CDI flags LOI on PFD Check for desired results a NAV1 8 NAV2 CDI loses deviation bar XPDR field flags invalid on PFD Engine Instrument field flags invalid on MFD All AHRS ADC fields remain valid Red AFCS status annunciation given Restore power to both GIA units TAWS FAIL annunciation given ADF DME windows flag invalid If equipped G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 3 190 00915 01 Revision 6 8 1 3 Display Failure Test Step oC Desired Result MFD Failure Condition 1 Open MFD CB 2 Verify desired results 3 Close MFD CB PFD2 Display Failure Condition 1 Open PFD 2 CB 2 Verify desired results 3 Close PFD 2 CB PFD1 Display Failure Condition Open PFD 1 PRI and PFD1 SEC circuit breakers Verify desired results Close PFD 1 PRI and PFD1 SEC circuit breakers Page 8 4 Revision 6 For an MFD failure condition the following shall occur MFD goes blank All PFD1 and PFD2 primary flight information is retained The COM 1 2 and NAV 1 2 tuning fields 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 For a PFD2 failure condition the following shall occur PFD2
58. Failures Failure Message Cause Solutions S Determine which data path has failed See Section 8 1 6 A communications data path status is not being received by the Check wiring continuity for the failed G1000 path FAILED PATH A data path has failed Swap or replace the affected LRU G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 43 190 00915 01 Revision 6 5 8 GDU 104X Troubleshooting 5 8 1 GDU 104X Common Problems Symptom Recommended Action Display is blank Display resets Display flickers SD card is stuck in GDU A button knob joystick does not appear to function Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Cycle power v If GDU recovers observe display for yellow text containing error information at the top of the screen If message indicates software need to be re loaded then re load software Otherwise replace the GDU Use a bright light to verify LCD is active v Adjust avionics dimmer control full clockwise v Manually turn up backlight on the PFD and load configuration files to the GDU Ensure slide lock is fully engaged with the locking tabs on the back of the unit v If slide lock is not fully engaged remove connector and verify the locking tabs on the GDU are perpendicular to the connector If necessary straighten them before reseating connector Ensure GDU is receiv
59. Flight into terrain gear Too Low Gear voice to ea te x a TAWS Caution alert GPWS mode 4B Flight into terrain flaps not Too Low Flaps voice ene Sink Rate voice TAWS Caution alert GPWS mode 1 Excessive Descent Rate TAWS Warning alert GPWS mode 1 or 2 Excessive Descent Rate Pull Up voice Or Excessive Closure Rate Don t Sink voice or TAWS Caution alert GPWS mode 3 altitude loss after takeoff or Too Low Terrain voice go around Glide Slope voice or TAWS Caution alert GPWS mode 5 Glide Slope Path deviation Glide Path voice Five Hundred voice or Four Hundred voice or TAWS voice callout GPWS mode 6 voice callout as appropriate Three Hundred voice or per altitude Two Hundred voice or One Hundred voice Caution Obstacle Caution Obstacle voice or TAWS Caution alert Reduced required obstacle clearance Obstacle Ahead Obstacle Ahead voice Or Imminent impact with obstacle Obstacle Obstacle Pull Up Pull Up voice or TAWS Warning alert Imminent impact with obstacle Obstacle Ahead Pull Up Obstacle Ahead Pull Up voice TAWS System Failure voice TAWS status alert Terrain failure TAWS Not Available voice TAWS status alert Terrain not available TAWS System Test OK voice If passed or TAWS status alert Terrain self test TAWS System Failure voice If
60. G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 9 1 MFD amp PFD Software Load Follow this procedure to load software to either PFD or the MFD 1 With the G1000 and GFC 700 powered on pull the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Insert the software loader card into top card slot in the desired PFD or MFD See Section 3 8 for information on creating or obtaining a software loader card NOTE If loading software to all displays it is preferred to load PFD 2 first followed by the MED and then PFD 1 3 While holding the ENT key on the display restore power by closing the appropriate circuit breaker s 4 When the words MINA Sty ERE eS appear in the upper left corner of the display release the ENT key 5 Press the ENT key or the sofkey labeled YES to acknowledge the following prompt see also note below for MFD DO YOU WANT TO UPDATE SYSTEM FILES NO WILL BE ASSUMED IN 30 SECONDS NOTE For the MFD use the far right soft key on the MFD in lieu of the ENT key where called out in Steps 3 through 6 The ENT key for the MFD is located on the GCU 477 FMS controller and may not function prior to software load 6 The following screen is displayed DO YOU WANT TO UPDATE SYSTEM FILES NO WILL BE ASSUMED IN 30 SECONDS UPDATING SYSTEM FILES PLEASE WALT 7 New software is loaded to the display and the following screen is displayed DO YOU WANT TO UPDATE
61. GTX 33 1 configuration files e Swap GIA and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 CHNL 2 White N A output only GTX 33ES CHNL 5 o Replace original GIA1 if box turns green after swapping units e Check the GIA1 GTX 33 1 interconnect wiring for faults 1 w TIS Replace GTX 33 1 if problem remains Amber GIA1 GTX 33 1 data path functionality is unknown Reload GIA1 configuration files Page 5 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 GIA1 RS 232 continued GIA1 GRS 77 1 data path is functioning correctly GIA1 GRS 77 1 data path is not functioning correctly e Load GIA1 configuration files e Swap GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA1 if box turns green after CHNL 6 GRS 77 1 Swapp Mie HANS Swap GRS1 and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the GIA1 GRS 77 1 interconnect wiring for faults GIA1 GRS 77 1 data path functionality is unknown Reload Amber l GIA 1 configuration files GIAI GMA 1347D 1 data path is functioning correctly GIA1 GMA 1347D 1 data path is not functioning correctly e Load GIAI and GMA 1347D 1 configuration files e Swap GMA 1347D 1 and
62. INDIVIDUAL CELL MONITOR LED DS12 is the only LED not illuminated proceed to the Cell Isolation Test 3 Connect Digital Voltmeter leads to J1 connector pins 11 and 7 Page 4 32 Revision 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 4 5 6 7 8 9 10 Connect the Load Resistor across J1 connector pins 11 and7 and start timing the discharge period with a stopwatch Monitor and plot voltage values at 10 minute intervals At 48 0 minutes note voltage on Digital Voltmeter This voltage must be greater than 20 0 Vdc a All INDIVIDUAL CELL MONITOR LED s Figure 4 5 Item 1 must remain on b Any LED that does go OFF will represent a defective individual cell which must be replaced Remove the Load Resistor from J1 connector pins 11 and 7 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 5 Item 5 to the OFF position Compare the voltage vs time plot created during this test to that of curve identified as typical for the External Load test method on the chart above If the plot reveals a discharge curve that meets or exceeds the MINIMUM ACCEPTABLE DISCHARGE CURVE the unit is considered satisfactory If unit discharge plot is satisfactory and no other failures were revealed perform the Charging Procedure within 2 hours of completion of the discharge test Return the unit into service 4 16 3 Cell Isolation Test NOTE No power should be applied to PS
63. INSTR buses which after this STC are powered from Dual Fed Bus No 1 and No 2 respectively On these aircraft the No 1 Engine Signal Conditioner receives power from Dual Fed Bus No 1 via the L ENG INSTR bus and the No 2 Engine Signal Conditioner receives power from Dual Fed Bus No 2 via the R ENG INSTR bus Page 2 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 1 20 Standby Airspeed Indicator A Standby Airspeed indicator Aerosonic part number 25030 0184 is installed between PFD 1 and the MFD Due to varying airspeed marking requirements four marking options are used To determine the appropriate option for a specific aircraft configuration refer to the General Arrangement drawing Garmin Document 005 00421 03 The standby airspeed indicator does not require electrical power for normal operation except for internal instrument lighting which is powered from Dual Fed No 1 Bus and the emergency standby battery This unit is connected to the right hand pitot static system 2 1 21 Standby Altimeter A standby altimeter Aerosonic part number 16650 1172 or Thommen part number 3A43 22 35F 28 1 FU is installed between PFD 1 and the MFD This unit incorporates a vibrator to ensure accurate display altitude information The vibrator is powered by the new Standby Instrument Bus and the emergency standby battery Internal lighting of this unit is powered from Dual Fed No 1 Bus and the emergency s
64. King Air 0985 02 Updated GDU and GIA software 200 B200 Series King Air 0985 03 Updated GDU and GIA software 200 B200 Series King Air 0985 04 Updated GDU and GIA software This STC allows multiple configurations for the King Air 200 B200 series The correct configuration for a particular aircraft is loaded by choosing the applicable airframe engine propeller configuration Refer to Table 6 of the General Arrangement Drawing Garmin Part Number 005 00421 03 for configuration information for eligible engine and propeller combinations G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 1 190 00915 01 Revision 6 IMPORTANT If the technician is unsure of an aircraft s STC configuration perform the following After acknowledgement of the splash screen use the FMS knob on the GCU 477 controller to go to the AUX SYSTEM STATUS page on the MFD In the AIRFRAME section upper right corner the display shows the current G1000 airframe configuration and system software version number The airframe configuration is shown in the AIRFRAME field and the system software version number is shown in the following format SYS SOFTWARE VERSION XXXX XX It correlates to the software image used to load the software to the system EXAMPLE System Software Version 0985 01 Software Image P N 006 B0985 01 Restart the MFD in configuration mode see section 3 7 and use the FMS knob on the GCU 477 controller to go to the
65. MED for any axis repeat the test twice in the failed axis If the test does not pass the servo gearbox must be removed from the aircraft and tested adjusted per the Servo Gearbox Adjustment Fixture Procedure in Section 4 9 3 Page 4 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 9 2 Manual Slip Clutch Test Procedure SW version 0985 03 and earlier l Dn WON 8 9 With PFD1 in Configuration Mode go to the GFC Page Group and select the GFC STATUS Configuration Page using the FMS knob C STATUS SELECT GIA UNIT SELECT SERVO AXIS GIA 1 PITCH SERVO GIA STATUS AP DISCONNECT 3 HONITOR BOARD STATUS SERVO PROGRAM 1 m AP DISCONNECT J SERVO PROGRAM 2 J PFT PASSED SERVO PROGRAM 3 J HIGH RES LOAD CELL CAL mi HIGH RNG LOAD CELL CAL mi CONTROL BOARD STATUS SERVO PROGRAM 1 AP DISCONNECT SERVO PROGRAM Z PFT PASSED SERVO PROGRAM 3 DRIVE SERVO SERVO DATA RPH 0 00rpm SPEED 0 00rpm CURRENT TORQUE 0 Din lb CLUTCH e SLIP CLUTCH TEST RESULTS NOSE UP NOSE DOWN IN ___ _In lb tn MAX ___ _In lb Tr Figure 4 4 GFC Status Page IMPORTANT It is highly recommended that the following test be performed at temperatures between 50 F and 120 F Use the FMS knob to select the desired servo Verify that the PFT status field shows PASSED Verify that the aircraft control surface to be checked is free to travel throughout its range of motion Press t
66. PFD1 and PFD2 with an altitude reference equal to the aircraft altitude within the nearest 20 feet Press the FD key and verify that the mode annunciations and command bars are removed from the display 3 2 3 Autopilot Clutch Overpower Check NOTE The GFC 700 uses electronic torque limiting as well as mechanical slip clutches to limit the maximum servo effort When the system is on the ground the electronic torque limiting 1s removed allowing manual checks of the slip clutch settings Engage the Autopilot by pressing the AP key on the AFCS mode controller Manually overpower the autopilot clutches in pitch roll and yaw If the Autopilot clutches cannot be overpowered check the GSM 85A clutch torque settings or GSM 86 clutch cartridge Refer to the servo installation drawing listed in Table 1 2 as applicable Actuate and hold PITCH TRIM switch in either the NOSE UP or NOSE DOWN direction to disconnect the autopilot While the trim is running restrain the aircraft pitch trim wheel and verify that the trim clutch can be overpowered If it cannot be overpowered check the GSM 85A clutch torque setting or GSM 86 clutch cartridge Refer to the pitch trim servo installation drawing listed in Table 1 2 Engage the autopilot by pressing the AP key on the AFCS mode controller Actuate and hold the manual electric trim switch in either the up or down direction to disconnect the autopilot Verify that the trim wheel moves smoothly in both dire
67. PFD1 fan MFD fan and PFD2 fan and fan fail messages Functional test of the GIA1 and GIA2 ported fans Verify airflow from all fan ports Functional test of the PFD1 MFD and PFD2 cooling fans Verify airflow from each fan Verify PRI and SEC power sources for PFD 1 GIA 1 GRS 1 GDC 1 Verify secondary paths for AHRS ADC engine parameters and GPS data Verify the operation of PFD and MFD Ethernet connections Verify ARINC connection between ADC1 and MFD and between GRS1 and MFD Verify DISPLAY BACKUP button function E On Condition NS ER iniii e f a e o Engine Data Check Verify engine data is available and Phase 4 GIA 1 or 2 Inoperative accurate with GIA 1 or GIA 2 inoperative Trim Annunciator Verify trim annunciators function G1000 Miscompare Verify AHRS airspeed and altitude Phase 4 Check miscompare monitors function properly Power Bus Feeder Check Verify availability of power bus feeders essential bus No 1 dual feed bus No 2 dual feed bus 4 17 1 Phase 2 and 4 Dual Bus Feeder Diodes Check Inspection of dual bus feeder diodes 4 17 2 G1000 Alerts GPS WAAS Antennas Diversity Transponder Antenna Wi Fi Antenna GA 58 Traffic Antennas Check for and troubleshoot any alerts provided in the alert window per the referenced manual section Removal 8 Replacement Refer to Master Drawing List listed in Table 1 2 for installation drawings Flaps in motion Test th
68. RS 232 RS 485 No 1 GEA 71 Contains ACTIVE settings Uses PFD internal configuration files for backup Page 3 16 Revision 6 Figure 3 14 G1000 LRU Configuration File Storage to GMC 710 Contains ACTIVE settings Uses PFD internal configuration files for backup RS 232 RS 232 HIGH SPEED DATABUS ETHERNET GDU 1500 MFD Contains ACTIVE MFD settings The MFD uses PFD internal configuration files for backup No 2 GDU 1040A PFD Contains ACTIVE PFD settings Represents SET column for all LRUs Stores all configuration files in internal memory Uses master configuration module for backup t No 1 GIA 63W Contains ACTIVE settings Uses PFD internal configuration files for backup RS 232 N eN N ag No 1 GTX 33 Contains ACTIVE settings Uses PFD internal configuration files for backup settings Uses PFD internal configuration files GCU 475 Contains ACTIVE for backup No 2 GIA 63W Contains ACTIVE settings Uses PFD internal configuration files for backup RS 232 RS 232 RS 485 No 2 GTX 33 Contains ACTIVE settings Uses PFD internal configuration files for backup GDL 69A Contains ACTIVE settings Uses PFD internal configu
69. S TEM TESTING a e ias 8 2 9 2 GEC 700 GROUND CHECO a tome sions 8 12 0 MAINTENANCE RECORDS oa 8 17 Page 1v G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 LIST OF ILLUSTRATIONS FIGURE Froure Zal Display Unitaria Eisuret2 2 AUdIO Pane Duruelo Figure 205 APES Controller ais Feie 224 FMS Controller aaa Foie AS PON idas Figure 220 LA UNE aonair a EEE Fiene 2 GEA a o rate 2 62 Nir Data COMpul iia Pietro 29 OAT POD pas Figure 210 AT RS iaa Fiewe NIE A A A A E talents men EREN igure 2212 GDL07A Data lk sa T Figure 2 10 GDESI WietiDa alinea Fisure 214 GSR 6 Satellite RECI jols Freire 2 15 GTS 3XA Trafe ys nda Fiure 216 Weather Radar E A AA A netteat E Figure 2 18 200 B200 Electrical Distribution Post G1000 STC eeeeeeeeeees Figure 2 19 G1000 Component Power SQUTCES ccccccnnnnononooonoonnnnnnnnnnncnnnnnnnanann non nnnonnos Figure 2 20 Pitot Static System Post G1000 STC ceeeeseeseeeseseeseeeeeeeeeeeeeens Figure 2 21 G1000 GFC 700 Block Diagramn ccsseeessecteccceecsecsseeosessasenscenses Figure 3 1 GDU TOAA Control tera an ds Figure 3 2 GDU 1500 Control Interface coccccccnnnnnnooooonononnnnnnnnncncnnnononanannnnonnononnos Paeine es El ODO SONK YS and s ra Figure 3 4 MFD Controls GCU 477 SMO Wit ad Figure 3 5 AFCS Controls GMC 710 sShown 0 000cccccsssssssesssessssesssssesseeeeeeees Figure 3 6 GMA DAID Co
70. Section 3 9 and then continue to GDC 74B Test Section 7 6 1 New GDC 74B Configuration Module is Installed The correct configuration files must be loaded if the GDC 74B configuration module has been replaced See Section 3 9 and then continue to GDC 74B Test Section 7 6 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 13 190 00915 01 Revision 6 7 6 1 Air Data Test GDC 74B The G1000 system must be maintained in accordance with the G1000 System Maintenance Manual listed in Table 1 3 and appropriate regulations When the GDC 74B is tested in accordance with 14 CFR Part 43 Appendix E note the following exceptions e For paragraph b 1 1 Scale Error use Table 7 5 of this section instead of Appendix E Table I e Do not perform paragraph b 1 iv Friction e Do not perform paragraph b 1 vi Barametric Scale Error The following Air Data Test is to be performed in addition to or in conjunction with any other regulated tests This test must be performed on both pilot and copilot systems with a calibrated Air Data Test Set ADTS with a combined accuracy repeatability specification of less than 20 feet for the test altitude range 1 Perform pitot static system leak check of each system as described in the King Air 200 Series Maintenance Manual 34 00 00 with the following changes a For the pitot leak check set the air data test unit to an indicated airspeed of 200 knots with the static system ve
71. Series King Air Revision 6 190 00915 01 7 13 Non Garmin Traffic System Functional Check l Ze Select the TRAFFIC MAP page on the MFD Verify that the STANDBY OPERATE TEST and ALT MODE soft keys are available on the bottom of the MFD Verify that an operating mode STANDBY OPERATE or TEST not TAS FAIL is displayed in the upper left corner of the traffic map Verify that NO DATA is not displayed in yellow in the center of the display over the aircraft symbol NOTE If the ALT MODE softkey is not displayed the G1000 has not been properly configured for the traffic system Reference Section 3 15 Traffic System Option to enable the traffic system Press the OPERATE soft key and verify that OPERATING is displayed in the upper left corner of the traffic map Press the STANDBY soft key and verify that STANDBY is displayed in the upper left corner of the traffic map Press the TEST soft key and verify that TEST is displayed in the upper left corner of the traffic map and a traffic test pattern is displayed Upon completion of the test verify that TAS SYSTEM TEST OK is heard over the cockpit speaker NOTE This annunciated traffic system test message may be different from the traffic system installed on subject aircraft Open the TRFC circuit breaker on the avionics circuit breaker panel On the MFD verify that NO DATA 1s displayed in yellow after several seconds Close the TRFC circuit breaker on the avionics cir
72. System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 53 190 00915 01 Revision 6 5 10 GIA 63 Troubleshooting 5 10 1 COM Symptom Recommended Action e Switch GIA1 and GIA2 to verify location of problem v If problem follows unit replace GIA v If problem does not follow unit check COM antenna and cabling for faults Weak COM transmit power e Switch GIA1 and GIA2 to verify location of problem Weak COM receiver v If problem follows unit replace GIA v If problem does not follow unit check COM antenna and cabling for faults e Switch GIA1 and GIA2 to verify location of problem v If problem follows unit replace GIA v If problem persists replace GMA1 with a known good unit v If problem persists reinstall original GMA1 and replace GMA2 No COM sidetone 9 10 2 NAV Symptom Recommended Action e Setup a NAV COM Ramp Test Set to radiate a test signal e Switch GIA1 and GIA2 to verify location of problem Weak NAV receiver v If problem follows unit replace GIA v f problem does not follow unit check NAV antenna coupler and cabling for faults 9 10 3 G S Symptom Recommended Action e Setup a NAV COM Ramp Test Set to radiate a test signal e Switch GIA1 and GIA2 to verify location
73. The following publications are recommended to be on hand during the performance of maintenance activities Table 1 3 Reference Publications 190 00915 02 Airplane Flight Manual Supplement G 1000 Integrated Avionics System and GFC 700 AFCS in Hawker Beechcraft 200 B200 King Air 190 00929 01 G1000 King Air 200 B200 Cockpit Reference Guide 190 00355 04 GDL 69 69A XM Satellite Radio Activation Instructions Generic installation manuals for individual Garmin LRUs are also available through the Dealer Resource Center section of the Garmin web site refer to Section 1 5 for details 1 5 Revison and Distribution This document is required for maintaining the continued airworthiness of the aircraft When this document is revised every page will be revised to indicate current revision level Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center website Owner operators may obtain the latest revision of this document from the https fly garmin com Support page or by contacting a Garmin dealer contacting Garmin Product Support at 913 397 8200 toll free 866 739 5687 or using around the world contact information on https fly garmin com A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant Page 1 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2
74. Trim Annunciator Check per Section 4 12 e For installations with the GSM 85A Servo Gearbox every 420 hours perform a GSM 85A Slip Clutch Torque Check per Section 4 9 e For installations with the GSM 86 Servo Gearbox every 3 000 hours perform a GSM 86 Slip Clutch Torque Check per Section 4 9 G1000 Limitations e Every 220 hours perform a Weight on Wheels and Low Speed Awareness Band Check per Section 7 22 e Every 220 hours perform a G1000 Redundant Connection Check per Section 4 10 e Every 220 hours perform a G1000 Cooling Fan Fail Annunciation Check per Section 8 1 4 e Every 620 hours perform a Power Bus Feeder Check per Section 4 17 1 e Every 820 hours perform a Nose Avionics Compartment Fans Operational Check per Section 4 14 e Every 820 hours perform an Instrument Panel Fans Operational Check per Section 4 15 e Every 820 hours perform an Engine Data Check GIA 1 or GIA 2 Inoperative per Section 4 11 e Every 820 hours perform the G1000 Miscompare Checks per Section 4 13 At 10 000 cycles and every 1 000 cycles thereafter perform an exterior skin inspection around antennas for cracks per the King Air 200 Series Maintenance Manual section 53 10 00 chart 201 Other Limitations e Every 220 hours perform the Standby Instrument Electrical Power Checks per Section 8 1 5 e Every 220 hours or 6 Calendar Months whichever occurs first perform Standby Battery Charge Check per Section 4 16 1 There are no other
75. Verify that GIA 1 is selected in the SELECT UNIT field 19 Observe the data indicators for all configured RS 485 channels 20 Verify all DATA indicators are GREEN indicating the channels are receiving data as shown CAN RS 485 CONFIGURATION SELECT GIA UNIT GIA CAN CHANNEL INPUT DATA OUTPUT DATA DATA SET ACTIVE ACTIVE ACTIVE CHNL 1 GOFF OFF OFF CHNL 2 GOFF OFF OFF CHANNEL INPUT DATA OUTPUT DATA DATA SET ACTIVE SET ACTIVE CHNL 1 mGEA 1 GEA 1 GEA 1 GEA 1 CHNL 2 _JOFF OFF OFF OFF CHNL 3 GOFF OFF OFF OFF CHNL 4 m6GFC700 GFC 788 GFC 708 GFC 788 OFF OFF OFF CHANNEL INPUT OUTPUT DATA SET ACTIVE CHNL 1 OFF OFF ESA O Ps Figure 8 3 GIA Data Verification RS 485 21 Activate the cursor and select GIA2 in the SELECT UNIT field and then press the ENT key 22 Repeat Steps 18 and 19 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 9 190 00915 01 Revision 6 8 2 GFC 700 Ground Checkout The following procedures verify the proper operation of the GFC 700 AFCS after maintenance has been performed The technician performing these checks should be thoroughly familiar with the G1000 and GFC 700 Information on the installation and operation of the GFC 700 can be found by referring to Sections 6 11 6 14 and the G1000 in King Air 200 B200 Cockpit Reference Guide listed in Table 1 2 NOTE In the sections that follow an Autopilot disconnect should be accompanied by an aural alert two second tone u
76. Verify the fan is running and the unit mounting location is getting adequate ventilation TCAS Equipage Fault Broken wire improper configuration Verify configuration settings on the transponder and the GTS Ensure proper wiring between the transponder and the GTS Radio Altitude Fault Radio Altimeter is not powered on or Verify that the radio altimeter has improper wiring power and is properly wired Improper configuration settings Verify the configuration is correct Red X on a data port on the Improper wiring wrong port or speed Ensure the port is properly wired to configuration page selected the GTS 8XX and the correct settings are selected on the configuration page Page 5 90 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 Equipment Removal amp Installation This section describes how to remove and replace equipment in the King Air 200 B200 associated with this STC After removal and replacement LRUs must be configured and tested as described in Section 7 CAUTION When removing and or replacing any G1000 component always ensure that aircraft power is off Unplug any auxiliary power supplies Before performing maintenance it is required that the technician verify the LRU software part number and version number matches the software configuration listed in the General Arrangement drawing listed in Table 1 2 To check an LRU software part number and or version follow
77. Weather Radar page 2 Select the MODE softkey 3 Select the STANDBY softkey to initiate the one minute warm up period Verify the radar enters the standby mode after the warm up is complete 4 Select the MODE softkey 5 Select the WEATHER softkey After reading the CAUTION statement turn the large FMS knob to select YES Press the GCU ENT key 6 Select the STAB ON softkey to activate antenna stabilization or select the STAB OFF softkey to deactivate Verify the current stabilization condition is shown in the upper right of the weather radar display 7 Select the BACK softkey 8 Select the VERTICAL softkey 9 Select the TILT softkey to activate the cursor in the TILT field 10 On the GCU turn the small FMS knob to select the desired antenna tilt angle Press the GCU ENT key Press the GCU FMS knob to remove the cursor 11 Select the GAIN softkey to activate the cursor in the GAIN field 12 On the GCU turn the small FMS knob to adjust the gain for the desirable level Verify the gain setting 1s visible in the gain field as a movable horizontal bar in a flashing box and the line pointer is a reference depicting the calibrated position Press the FMS knob to remove the cursor 13 On the GCU select the GAIN softkey again to recalibrate the gain Verify CALIBRATED is displayed in the GAIN field 14 Select the MODE softkey 15 Select the OFF softkey Page 7 30 G1000 GFC 700 System Maintenance Manual 200 B200
78. X GRS 77 AHRS Configuration Module was X X X replaced G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 19 190 00915 01 Revision 6 7 2 Procedure A1 GRS 77 Pitch Roll Offset Calibration This procedure must be performed for both GRS 77 units installed in the aircraft This first procedure must be carried out with the engine off l Level the aircraft to within 0 25 of zero pitch and zero roll using a digital level Follow instructions in King Air 200 Series Maintenance Manual listed in Table 1 2 for leveling Start the G1000 system in Configuration mode Go to the GRS Page Group and select the GRS GMU Calibration page at the PFD This page is protected and the following softkey password must be entered at the PFD to continue e 9 e 10 e 11 e 12 Far Right softkey GRS GMU CALIBRATION SELECT PROCEDURE COMMUNICATION STATUS PITCH ROLL OFFSET m AIR DATA m MAGNETOMETER 3 1 Level the aircraft to within 0 25 deg of zero pitch and zero roll 3 2 Ready to enter the GRS77 AHRS Ground Pitch Roll Aircraft Level Compensation Mode CALIBRATE 4 Ensure that the No 1 GRS 77 is selected in the SELECT GRS UNIT window on the PFD 5 Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH ROLL OFFSET 6 Press the ENT key 7 Use the cursor to highlight the BEFORE CALIBRATION window 8 Follow the checklist items displayed on the PFD and press the ENT key as each
79. airspeed vertical speed COMM1 COMM2 NAV1 NAV2 and engine instruments 10 De activate co pilot s side reversion mode by pushing the DISPLAY BACKUP button Verify PFD 2 and MFD return to normal display modes 11 Select the TAWS page on the MFD 12 Verify that the title at the top of the page reads MAP TAWS B or MAP TAWS A If TAWS has not been enabled the title will read MAP TERRAIN PROXIMITY or MAP TERRAIN 13 Press the MENU button and select Test TAWS from the pop up menu 14 After the TAWS test has completed verify that TAWS System Test Okay is heard over the cockpit speaker 15 If no other service is to be performed perform final return to service test as specified in Section Page 7 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 2 GMA 1347D Audio Panel Original GMA 1347D Reinstalled No software configuration loading or testing is required 1f the removed GMA 1347D is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the final return to service checks in Section 8 Original GMA 1347D Installed in Opposite Locations for Troubleshooting If the original GMA 1 and GMA 2 are installed in opposite locations configuration loading is required See Section 3 9 and then continue to the GMA 1347D Test S
80. airworthiness limitations associated with this type design change STC SA01535WI D The G1000 GFC 700 King Air 200 B200 Airplane Flight Manual Supplement defines all operating limitations for this STC The Airworthiness Limitations section is FAA approved and specifies maintenance required under 43 16 and 91 403 of Title 14 of the Code of AQUA A unless an alternative program has been FAA approved Eur 9 g 2012 FAA APPROVED Robert Murray Date STC Unit Administrator ODA 240087 CE G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 1 190 00915 01 Revision 6 4 2 Servicing Information G1000 LRU maintenance is on condition only No component level overhaul is required for this type design change 4 2 1 On Condition Servicing On Condition replacement and or servicing should occur when an item exhibits conditions symptoms and or abnormalities defined in Section 5 of this manual Replacement and or servicing should be made only after the technician troubleshoots the system to the extent determined necessary by using the guidance in this manual along with common avionics maintenance practices IMPORTANT It is impossible to provide guidance for every conceivable failure scenario within the scope of this manual Every effort has been made to provide comprehensive guidance for possible failures The information in this document should always be combined with common sense and a thorough knowledge of
81. at these 30 increments for the time recommended by the PFD should result in successful calibration 13 The PFD guides the operator to dwell at multiple headings around a complete circle NOTE Due to high winds or excessive airframe vibration the operator may encounter a condition where the PFD restarts the 18 second countdown without full completion of the previous countdown If this is encountered more than once for a given station the operator should begin turning to the next station approximately 30 A minimum of 2 successful stations per quadrant is required where a successful station is a full 18 second countdown followed by instruction to move Ensure that at least 2 stations per quadrant are completed Thus it may sometimes be required to dwell at a station after a countdown restart A maximum of 30 stations is allowed for the entire calibration procedure If too many countdown restarts are encountered the calibration will fail with the message TOO MANY STATIONS 14 Repeat the turn and stop process until the PFD advises that a successful calibration is complete The GRS 77 AHRS then enters its normal operational mode Press the ENT button on the PFD to conclude this procedure 15 Repeat steps 4 through 14 for GRS 77 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 23 190 00915 01 Revision 6 7 7 5 Procedure D Engine Run Up Vibration Procedure NOTE Calibration Procedure D is per
82. by the following o Green PASS or White N A in SOFTWARE and CONFIGURATION columns e Upload Complete COMPLETE in the summary box 8 Press PFD1 ENT key to acknowledge the Upload Complete box G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 21 190 00915 01 Revision 6 3 9 3 Software Check Anytime software and configuration loading procedures are accomplished during maintenance conduct a final software review of the system 1 Start the PFD in Configuration Mode as described in Section 3 7 2 Go to the System Status page using the FMS knob Activate the cursor and toggle to the LRU window SYSTEM STATUS a AA ONLINE GOLES mi GAA E PART NUHBER VERSION PRODUCT DESCRIPTION COPYRIGHT SERIAL NUMBER GDC2 FPGA MODEL NUMBER GOLES FUNCTIONS PRESENT STATUS T C CERT GIA C CERT GIAZ ERT PL GFC CERT P M GFC CERT PT C CERT PT H E E E ca i om a Ett if gt amp Figure 3 20 System Status 3 The PFD System Status page shows a list of LRUs in the LRU window Activate the cursor and highlight the LRU window Use the FMS knob to scroll through the list in the window and verify that the software part number and version displayed in the DATA window matches the information in General Arrangement drawing listed in Table 1 2 Record the results on the next page IMPORTANT It is essential that the software versions be checked and matched against
83. drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the antenna mounting screws 4 Remove antenna Reinstallation 1 Install antenna using retained mounting screws 2 Connect the antenna coaxial cable 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Reinstall cabin interior ceiling panel 5 Proceed to Section 7 3 1 GPS Signal Acquisition for testing 6 19 Diversity Transponder Antenna Removal 1 Gain access to the antenna coaxial cable connector and mounting hardware by removing the cabin interior ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the two nuts and washers securing the antenna 4 Remove antenna Reinstallation 1 Install antenna using retained hardware 2 Connect the antenna coaxial cable 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Reinstall cabin interior ceiling panel 5 Proceed to Section 7 5 2 for testing of the GTX33D Page 6 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 20 Iridium Antenna Removal 1 Gain access to the antenna coaxial cable connector by removing the aft cabin ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the antenna mounting screws 4 Remove antenna Reinstallation 1 In
84. equipment Any equipment wiring added that is not part of the installation data will need separate testing and verification not covered as part of this document 1 Navigate to the AUX SYSTEM STATUS page on the MFD 2 Press the RA TEST softkey and verify that RA TEST annunciation is displayed on both PFDs 3 Verify 50 feet is displayed in the RA display window on both PFDs 4 Press the RA TEST softkey again Verify the RA readout window displays 2500 feet and decreases to 0 feet on PFD1 and PFD 2 5 Pull the RADIO ALTM circuit breaker Verify on PFD 1 and PFD 2 that an RA FAIL message is displayed 6 Reset the RADIO ALTM circuit breaker G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 41 190 00915 01 Revision 6 7 22 Weight on Wheels and Low Speed Awareness Band Check This procedure will verify that the GDU air ground status uses valid Weight on Wheels WOW inputs I Ze 8 Ensure aircraft is positioned with weight on wheels Apply external power to the aircraft Set BATT and AVIONICS MASTER switches to ON and wait for all aircraft and avionics systems to complete their initialization and begin operating normally Verify there are no WOW INVALID or WOW FAULT messages Refer to Section 5 3 to troubleshoot messages Verify the Low Speed Awareness band red band is NOT displayed on the PFD1 and PFD2 airspeed tapes see Figure 7 8 NOTE This portion of the check can be accomplished
85. in Table 1 2 section 27 31 00 Stall Warning Mounting Plate or Troubleshoot in accordance with the King Air 200 Series Maintenance Vane Heater Inoperative Manual listed in Table 1 2 section 27 31 00 Only Pot 0 provides any Troubleshoot in accordance with the King Air 200 Series Maintenance adjustment for Stall Warning Manual listed in Table 1 2 section 27 31 00 points Stall Warning Self Test Will Not Troubleshoot in accordance with the King Air 200 Series Maintenance Work Properly Manual listed in Table 1 2 section 27 31 00 Flap Information to the computer Troubleshoot in accordance with the King Air 200 Series Maintenance is not working properly Manual listed in Table 1 2 section 27 31 00 Insure power is removed from the Stall Warning System With the aircraft on the ground install the SK100360 Breakout Box per Figure 7 15 Breakout Box and perform the following resistance measurements per the table below Test Points TP on SK100360 Breakout Box Expected Readings 24 25 140 28 ohms 26 27 320 64 ohms Display of ESP Alpha Floor 28 27 320 64 ohms a ae alae e If the resistances are not within the ranges specified check the aircraft wiring between the computer and the transducer in accordance with the oe appropriate Hawker Beechcraft wiring diagram Advisory Alert ESP DEGRADE ESP AOA Mode is inoperative If the wiring between the computer and the transducer is good replace the transducer
86. in conjunction with the Landing Gear Aural Alert and XM Audio Suppression Test in Section 7 2 2 Place the airplane on jacks Ref King Air 200 Series Maintenance Manual Chapter 7 00 00 with the wheels clear of the ground Verify there are no WOW INVALID or WOW FAULT messages Refer to Section 5 3 to troubleshoot messages Verify the Low Speed Awareness band red band appears at the low end of the Air Speed Tape on the PFD1 and PFD2 see Figure 7 8 Remove airplane from jacks If no other service is to be performed continue to the return to service checks in Section 8 Tas air TAS OKT Figure 7 8 Low Speed Awareness Band Symbolization Page 7 42 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 23 RVSM Checks The following are required initial and continued airworthiness checks to verify proper configuration for operation in RVSM airspace RVSM operations are prohibited until the all of the RVSM checks are completed successfully 7 23 1 RVSM Required Avionics Check With the PFD in configuration mode select the System Status page using the small FMS knob Press the small FMS knob to activate the cursor Highlight each of the following items in the LRU window and verify that the required software part number and version matches the information in the General Arrangement drawing listed in Table 1 2 Verify hardware part number by visual inspection of the units Record the
87. in the neutral position press the HDG and ALT buttons on the mode controller and center the heading bug 26 Engage the autopilot and turn the heading knob to set the heading bug to the right of center Hold the control yoke centered for approximately 10 seconds Verify that the amber AIL annunciator is displayed on both PFD 1 and PFD 2 27 Turn the heading knob to set the heading bug to the left of center Hold the control yoke centered for approximately 10 seconds Verify that the amber AIL annunciator is displayed on both PFD 1 and PFD 2 28 Disengage the autopilot and clear all modes 29 Ensure the aircraft is on the ground and the nose wheel is approximately straight 30 Engage the yaw damper and apply firm load on the right rudder pedal for approximately 20 seconds 31 Verify that the amber RUD annunciator is displayed on both PFD 1 and PFD 2 32 Apply firm load on the left rudder pedal for approximately 20 seconds 33 Verify that the amber RUD annunciator is displayed on both PFD 1 and PFD 2 34 Disengage autopilot 35 The Trim Annunciator Check is complete 4 13 G1000 Miscompare Checks This procedure will check the AHRS airspeed and altitude miscompare monitors Accomplish the following checks with the aircraft positioned where it can receive GPS signals and magnetic heading Access to AHRS1 and AHRS2 will be required during this test 1 Ensure the G1000 is operating in normal mode Page 4 28 G1000 G
88. indications are illuminated Green switch GIA1 and GIA2 to verify location of problem v If problem is resolved replace defective unit v If indication is not illuminated check for wiring faults between the GIAs and aircraft squat switch system Check configuration settings for GIA1 and PFD1 NAV1 8 COM1 LT Swap GIA1 and GIA2 to verify location of problem AA ot P v If problem follows GIA1 replace GIA1 Check Ethernet interconnect from GIA1 to PFD1 v If problem persists replace PFD NAV2 amp COM2 e Check configuration settings for GIA2 and PFD2 e Swap GIA1 and GIA2 to verify location of problem v If problem follows GIA2 replace GIA2 e Check Ethernet interconnect from GIA2 to PFD2 v If problem persists replace PFD Page 5 18 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Associated Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Check GPS1 and GPS2 signal strength on AUX page 4 Refer to GIA GPS section if GPS can not acquire a position lock for troubleshooting GPS LOI GIA1 or GIA2 Check corresponding GPS antenna and cable for faults Check Ethernet interconnect between the PFD1 to GIA1 or PFD2 to GIA2 for faults Swap GIA1 and GIA2 to verify location of problem v If problem follows the GIA replace the GIA v If problem persists replace the PFD1 or PFD2 Chec
89. information related to safe flight in the event of a display communication or hardware failure For software version 0985 04 and later the pilot s PFD automatically goes into reversionary mode when communication to the MFD is lost Manual reversionary mode allows the operator to force the pilot or copilot s PFD into reversionary mode by pressing the large red button labeled DISPLAY BACKUP on the respective GMA 1347D audio panel NOTE When the DISPLAY BACKUP button is pushed to exit reversionary mode there is a 5 second debounce or the GDU waits for 5 consecutive seconds and then returns to normal mode if no other input is received If the DISPLAY BACKUP button is pushed again during this 5 second interval the timer will repeat the count le Figure 3 8 Automatic Reversion with MFD failure pi Page 3 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 7 Configuration Mode Overview Throughout this document references are made to the PFD1 PFD2 and or MFD being in configuration mode The configuration mode exists to provide the avionics technician with a means of configuring checking and calibrating various G1000 sub systems Troubleshooting and diagnostics information can also be viewed in this mode To start the G1000 system in configuration mode follow these steps 1 Apply power to the G1000 system by applying aircraft EXT power selecting the AVI
90. intruder scenario and verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co altitude read as 00 above a filled diamond indicating proximate traffic On the ramp tester toggle intruder traffic to standby or off Reposition ramp tester and reengage the same intruder scenario for 90 180 and 270 degrees Verify a target is annunciated on the MAP TRAFFIC MAP page of the MFD at the same bearing as the ramp tester If the bearing is not as anticipated or multiple targets are displayed during tests verify the following e Coax cable QMA connectors are snapped firmly in place at the GA58 antennas GTS 8XX unit and GPA 65 unit e Coax cable TNC connectors are properly secured at the bulkhead adapter fittings e Connections are made to the proper channels and color coded heat shrink is the same color on both ends of coax cables e QMA and TNC connectors are correctly installed on coax cables 7 26 2 Ramp Test The following test provides a scenario that will converge and intercept the GTS 8XX to assure proper operational and surveillance functions The GTS 8XX must be in Ground Test mode l Ze On the MAP TRAFFIC MAP page of the MFD press the OPERATE softkey Position ramp tester at 90 degrees Select the following on the ramp tester Intruder type ATCRBS Intruder Start Distance 10 nm Intruder Start Altitude 50 000 ft Vertical Speed 0 fpm Ve
91. key on PFD1 3 Rotate the small FMS knob to highlight DME Option Press ENT key on PFD 1 4 Verify the DME Option is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ES N A A GMA COPIL N A al Figure 3 25 DME Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for GIA1 GMA PIL and GMA COPIL e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 28 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 15 RAD ALT Option Configuration This section loads the necessary configuration files for those aircraft equipped with a radio altimeter 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight RAD ALT Option Press ENT key on PFD 1 4 Verify the RAD ALT Option is displayed in the Item window Press LOAD CONFIGURATION ID 35718604 SYSTEM UPLOAD LRU VERS CARD VERS CARD PART NUM SOFTHARE CONFIGUR
92. of problem Weak G S receiver v If problem follows unit replace GIA v If problem does not follow unit check NAV antenna coupler and cabling for faults Page 5 54 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 10 4 GPS Symptom Recommended Action Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Using the MFD AUX GPS Status page verify the signal strength bars are not erratic If so this indicates outside interference is affecting the GPS receivers Find and remove the source of interference i e cell phones FBO datalink antennas etc Check date and time on Date Time Setup Page v If date and time are incorrect enter the correct date and time Switch GIA1 and GIA2 to verify location of problem v If problem follows unit clear the GPS almanac by performing the following steps Using the PFD in config mode go to the GIA RS 232 ARNIC 429 Config Page Will Not Acquire Satellites At the top of the screen select the GIA that can not acquire satellites GIA1 or GIA2 and press the ENT key Press the CLR NV softkey at the bottom of the screen Select OK in the Clear GIA nonvolatile memory pop up window Next reload GIA Audio and Config files from a loader card see Section 4 3 and on for instructions Be sure to reload the config files for any optional equipment i
93. pointing arrow on the AFCS mode controller next to the XFR button Repeat step 5 using CRS2 knob while coupled to PFD2 7 Set CRS1I and CRS2 course pointers to aircraft heading 8 Simulate a Localizer Glideslope signal Tune this signal on NAV 1 and NAV 2 receiver Set the PFD1 HSI to LOCI and PFD2 HSI to LOC2 by pressing CDI soft key until LOC1 and LOC2 is selected Use the test equipment to center the deviation bars localizer and glideslope on PFD1 and PFD2 9 Press the APR key on the AFCS mode controller Verify that the LOC and PIT annunciations are green and ALTS and GS are white on PFD1 and PFD2 Apply right left and up down localizer glideslope signals using the test equipment Verify that the Flight Director and flight controls respond appropriately 10 Couple FD to PFD1 by pressing the XFR button on the AFCS mode controller Verify FD is coupled to PFD1 as indicated by a left pointing arrow on the AFCS mode controller next to the XFR button 11 Repeat step 9 while coupled to PFD1 If no other service 1s to be performed continue to the return to service checks in Section 8 Page 7 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 4 GEA 71 Engine Airframe Unit Original GEA 71 Reinstalled No software or configuration loading is required if the removed GEA 71 is re installed This does not include units that were returned for repair as their software and configuration files a
94. pressed move the control wheel to its aft limit Release the CWS button and apply continuous forward pressure slowly moving the control wheel After a brief delay verify the trim wheel begins moving in a trim up direction 8 Grip the control wheel 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 begins to trim down Relieve pressure on the wheel and verify the trim motion stops Check that the trim wheel is free to turn Hold the control wheel and press the AP YD DISC TRIM INTRPT switch to disconnect the autopilot G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 13 190 00915 01 Revision 6 8 2 6 VOR LOC GS Test Perform the following test using ramp test equipment Operate the equipment according to the test equipment manufacturer s instructions 10 IT NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency 1s tuned Ensure FD is coupled to PFD1 as indicated by a left pointing arrow next to the XFR button Simulate a VOR signal on a radial equivalent to the aircraft heading Tune the NAV 1 and NAV 2 receivers to the simulation frequency Set the HSI on PFD1 to VOR 1 by pressing the CDI soft key until VOR 1 is selected Set the HSI on PFD2 to VOR2 by pressing the CDI soft key until VOR2 is selected Rotate CRS1 and CRS2
95. rack Lock the handle to the GTX 33 body using the Philips screw Reinstall the remote equipment shelf or two rack mount angles using the retained hardware Reinstall the cabin center floor panel py A A E ae A Configure and test the GTX 33 according to Section 7 5 6 6 GDC 74B Air Data Computer Removal 1 Gain access by removing the appropriate GDU 1040A display unit see Section 6 1 2 Disconnect the pitot static plumbing from the rear of the unit Disconnect the single connector 3 Loosen each thumbscrew on the hold down clamp and remove the clamp 4 Carefully remove the unit from its mount Reinstallation 1 Inspect the connector and pins for damage Inspect the pitot static plumbing for damage Repair any damage Place the unit in the mounting tray Position the locking clamp and fasten using the thumbscrews Connect the backshell assembly and pitot static plumbing to the unit Configure and test the GDC 74B according to Section 7 6 Reinstall the GDU 1040A display unit So oe ee 6 7 GTP 59 OAT Probe Removal 1 Using a deep socket to hold the probe in place on the outside of the aircraft loosen the GTP 59 mounting nut and remove the GTP 59 Reinstallation 1 Installation is the reverse of removal 2 No configuration is required for the GTP 59 Test according to Section 7 6 3 Page 6 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 8 GRS 77 AHRS
96. removing the appropriate GDU 1040A display unit see Section 6 1 2 Unlock the GEA 71 handle by unscrewing the Phillips screw 3 Firmly grasp the GEA 71 handle and pull it up vertically This unlocks the unit from the rack 4 Gently remove the GEA 71 from its rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Gently insert the GEA 71 into the rack The handle should engage the dogleg track 3 Press down on the handle to lock the unit into place 4 Lock the handle to the GEA 71 body using the Philips screw 5 Configure and test the GEA 71 according to Section 7 4 6 Reinstall the GDU 1040A display unit G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 3 190 00915 01 Revision 6 6 5 GTX 33 Transponder Removal 1 Gain access by removing the cabin center floor panel at the main entry door 2 Remove the remote equipment shelf Alternately detach the two rack mount angles from the shelf Retain all mounting hardware 3 Unlock the GTX 33 handle by loosening the Phillips screw on the handle 4 Pull the handle upward to unlock the GTX 33 Gently remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage Gently insert the GTX 33 into its rack The handle should engage the dogleg track Press down on the GTX 33 handle to lock the unit into the
97. results in Table 7 8 HARDWARE DESCRIPTION ITEM GIA 63W IAU 1 GIA 63W IAU 2 g GDU 1040A PFD PART NUMBER GDU 1040A PFD GDU 1500 MFD GDC 74B AIR DATA COMPUTER GDC 74B AIR DATA f COMPUTER GTX 33 TRANSPONDER GTX 33D OPTIONAL gt GTX 33 TRANSPONDER GTX 33D OPTIONAL SOFTWARE DESCRIPTION PART NUMBER A or o Corswas enone CERTIFICATION GANS wan sus svstem o OPSMARS NOME CERTIFICATION GANS ssm A ssm IE DE ae a an system Dae ssm IS MU sons ssm IE Mi a GTX 33 SYSTEM GTX 33 SYSTEM ES EA E E LSS La E ASE A MANO EA SNS UNO ES E Table 7 8 RVSM Required Avionics G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 SYSTEM STATUS REPORT GIA1 GIA1 AUDIO GPS1 GFC CERT GIA 1 GIA2 GIA2 AUDIO GPS2 GFC CERT GIA 2 PFD1 PFD1 FPGA PFD2 PFD2 FPGA MFD1 MFD FPGA GDC1 GDC1 FPGA GDC2 GDC2 FPGA GTX1 Page 7 43 Revision 6 7 23 2 RVSM Critical Region Visual Inspection The RVSM critical region is a 24 x 24 inch area around the static ports on both sides of the airplane The corners of the RVSM critical region are to be marked on the aircraft with placards or paint of a contrasting color see Figure 7 9 The RVSM critical region must meet the following visual inspection criteria 1 The fuselage skin must be free from damage All skin repairs within the RVSM critical region must be f
98. side is coupled No flight director modes should be active at this time XFR gt 6 On the GCU rotate the inner FMS knob to activate the AUX SYSTEM SETUP page on the MFD 7 On the MFD AUX SYSTEM SETUP page press the SETUP 2 softkey 8 Verify that on the MFD SETUP 2 page there is a window for Stability amp Protection and the status is ENABLED STABILITY amp PROTECTION STATUS 9 Verify on PFD 1 and PFD 2 that there are no ESP FAIL ESP OFF or ESP DEGRADE alert messages 10 Cover both GPS1 and GPS2 antennas 11 Verify on PFD 1 and PFD 2 the ESP Roll Indices are displayed at 45 on the roll indicator on the Attitude Display 12 For installations with AOA mode verify on PFD 1 and PFD 2 that there is an ESP DEGRADE alert message ESP DEGRADE ESP ADA mode is inoperative 13 On the GCU press the inner FMS knob to activate the cursor then rotate the outer FMS knob to select the Stability amp Protection window on the MFD 14 Rotate the inner FMS knob to change the status to DISABLED 15 Verify that on the MFD SETUP 2 page Stability amp Protection window that the status is DISABLED STABILITY amp PROTECTION STATUS 16 Verify on PFD 1 and PFD 2 the ESP Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display Page 7 58 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01
99. steps Otherwise skip to step 10 a Inthe LRU box you may select either GIA1 or GIA2 b Inthe SERVO box choose a servo using the FMS knobs Each servo contains two logs one in the Monitor MON processor and one in the Control CTL processor You must download both for each servo separately c Inthe COMMAND box select View Maintenance Log and press the ENT key d The log will appear in the OUTPUT box It will scroll to the end automatically When it is complete repeat steps a c for the other servos in the aircraft Be sure to note the order the servos were downloaded in including the Monitor or Control logs to email to Garmin Product Support Without knowing the order in which the logs were downloaded Garmin will be unable to process them and will ask for another full download 10 Press the LG2CRD softkey to turn off the recording function 11 Wait 1 minute for the system to save the data from the download to the SD card G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 41 190 00915 01 Revision 6 12 While you are waiting for the data to be saved to the SD card record the order of the LRU s and or Servos were downloaded so that you can provide that information to Cessna or Garmin to help decipher the order of the error data 13 Power down the G1000 System and remove the SD card 14 Insert the SD card in the card reader of a laptop or desktop computer and open the diag b
100. test failed TAWS Available voice TAWS status alert Terrain available Vertical Track voice Vertical navigation alerting function G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 3 190 00915 01 Revision 6 5 2 System Annunciations If data fields become invalid due to an LRU failure the PFD MFD typically annunciates the failure with a large red X as shown in Figure 5 4 132 825 124 580 con 121 588 131 588 cone HDG NO COMP ROL NO COMP PIT NO COMP TAS NO COMP ALT NO COMP IFORI 2324 STBY A mul TMR REF NRST ADVISORY Figure 5 4 System Annunciations 5 2 1 Failed Path Messages The following message indicates there is a data path connected to the GDU PFD1 PFD1 or MFD or the GIA 63W 1 or 2 that has failed FAILED PATH A data path has failed The FAILED PATH message is triggered by a timeout of any one digital channel The channels that are checked are listed on these pages in config mode 1 GDURS 232 ARINC 429 CONFIG PFD1 2 and MFD 2 GIA RS 232 ARINC 429 CONFIG GIA1 and GIA2 3 GIA CAN RS 485 CONFIGURATION GIA1 and GIA2 IMPORTANT Once the FAILED PATH message has been triggered it will remain on the list of messages until the next power cycle This latching was implemented so that for intermittent failures the message would remain at the end of the flight to alert maintenance crew Also this keeps the crew from having to acknowledge messa
101. that the technician install correct software image part number when servicing the G1000 system Approved software image part numbers are defined on the appropriate General Arrangement drawing see Table 1 2 CAUTION Be cautious when using software loader cards during maintenance The G1000 system immediately initializes the card upon power up On screen prompts must be given careful attention in order to avoid potential loss of data Always read through procedures given in Sections 5 6 and 7 before attempting to use the software loader cards G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 11 190 00915 01 Revision 6 3 8 2 Loader Card Creation The software image is an executable self extracting file which builds the correct file structure onto an SD card for use loading software to the G1000 and GFC700 To create a software loader card follow the procedures outlined below NOTE In order to create a 200 B200 loader card the individual facility completing these procedures must be an authorized King Air 200 B200 service center to gain access to the necessary data via the Garmin website 1 Goto www garmin com and click on the Dealer Resource Center link in the lower portion of the home page Enter username and password Sign In Username Password By signing in you agree to the Garmin Confidentiality Agreement Sign In 2 Click the I Agree button on the confidentiality agreement page
102. the control surface to either the NOSE UP stop Pitch and Pitch Trim or the RIGHT stop Roll and Yaw Ifthe PITCH SERVO is selected firmly hold the control yoke in the full aft position until the NOSE UP portion of the test is completed Allow the servo to continue driving against the control stop for at least 50 seconds Observe the TORQUE values displayed in the Servo Data field and record the maximum and minimum values in Table 4 10 or in the appropriate aircraft maintenance records Manually select 0 00 rpm for the Drive Servo and press ENT Allow the servo to stop Firmly grasp the aircraft control under test and press the DIS CLCH softkey Press the STP SRVO softkey Repeat steps 2 through 18 for each servo axis shown Verify that the minimum and maximum torque values measured are within the Minimum and Maximum torque values allowed for the given axis listed in Table 4 10 Ke Diesen Min Measured Max Measured Min Allowed Max Allowed a Torque in lbs Torque in lbs Torque in lbs Torque in lbs Pitch p 28 GSM 85A 38 GSM 85A 24 GSM 86 40 GSM 86 78 GSM 85A 107 GSM 85A 66 GSM 86 112 GSM 86 52 GSM 85A 71 GSM 85A 45 GSM 86 76 GSM 86 Yaw Table 4 10 Measured Torque NOTE If the GSM 85A or GSM 86 measured values exceed the limits in Table 4 10 the servo gearbox must be removed from the aircraft and tested adjusted per the Servo Gearbox Adjustment Fixture Procedure in Section 4 9
103. the CONNECTION STATUS field on the AUX WI FI SETUP page on the MFD indicates CONNECTED G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 65 190 00915 01 Revision 6 7 29 GSR 56 Satellite Receiver Functional Check 1 Power up the PFD1 in configuration mode 2 On the PFD1 select GDL page group using the large FMS knob 3 Using the small FMS knob select the GSR56 Configuration page Verify the page can be displayed and information is available GSR56 CONFIGURATION CONF TGURA TION CONFIGURED PERMISSION LEVEL e a EONI HOHE ENABLED FUNCTIONALITY SETTINGS SET ACTIVE DEFAULT INTERNATIONAL CODE VOICE PRIORITIZED OVER DATA Figure 7 18 GSR56 Configuration Page 4 Restart the G1000 System in Normal Mode 5 Using the large FMS knob select the AUX page group on the MFD Using the small FMS knob select the AUX TELEPHONE page 6 Ensure the system is showing Iridium signal strength best if aircraft is outside 7 Press TEL button on the pilot s GMA 8 Press the DIAL softkey on the MFD 9 Enter the test phone number in the ENTER PHONE NUMBER field using the GCU keypad 10 Press the ENT key on the GCU keypad to accept the phone number 11 Press the ENT key on the GCU keypad to initiate the dialing sequence 12 When call is complete press the HANGUP softkey on the AUX TELEPHONE page on the MED to end the call DTE PHONE STATUS COCKPIT IRIDU 1 OOOO OOOO nan CO
104. the DME distance is dashed out Tune NAV 2 to the test set frequency Set NAV 1 to a frequency other than the test set frequency Verify that the DME distance on PFD1 and PFD2 match the test set If no other service is to be performed continue to the return to service checks in Section 8 Page 7 40 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 20 ADF Functional Check This check verifies that the ADF G1000 interface operates correctly l Press the PFD softkey on PFD1 and PFD2 Toggle the BRG1 and BRG2 softkey until the ADF bearing is shown on PFD1 and PFD2 Verify that the ADF window 1s not invalid no red X Using the ADF control head select a known valid local ADF Verify that the ADF bearing pointer moves towards a bearing and stabilizes Select ADF and SPKR on GMA1 and GMA2 Using the ADF control head select ANT mode Verify that the audio from the station tuned can be heard on the pilots and copilots headset and cockpit speaker 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 If no other service is to be performed continue to the return to service checks in Section 8 7 21 Radio Altimeter Check This check verifies that the G1000 radio altimeter interface is operates correctly NOTE This check only verifies the data output from the G1000
105. the LRU drop down menu and then press the ENT key to select it 6 Skip the SERVO box and move the cursor to the COMMAND box and select View Maintenance Log in the drop down menu then press the ENT key The error log data will be displayed in the OUTPUT box If you see the more press any key to continue text at the bottom of the screen you may need to reselect View Maintenance Log for GIA data to allow it to continue scrolling down the screen pressing any key will not continue disregard the text instruction you to do so Continue to scroll through all the OUTPUT data until you see the text End of Fault Log 7 Move the curser back to the LRU box select GIA2 in the LRU drop down menu and then press the ENT key to select it 8 Skip the SERVO box and move the cursor to the COMMAND box and select View Maintenance Log in the drop down menu then press the ENT key The error log data will be displayed in the OUTPUT box If you see the more press any key to continue text at the bottom of the screen you may need to reselect View Maintenance Log for GIA data to allow it to continue scrolling down the screen pressing any key will not continue disregard the text instruction you to do so Continue to scroll through all the OUTPUT data until you see the text End of Fault Log 9 Ifyou need to download Servo fault logs usually done at the request of Garmin Product Support perform the following
106. the PFD If messages illuminates check dual bus feeder circuit breaker LH No 1 associated limiter and diode 10 Close No 1 dual bus feeder circuit breaker RH No 1 oY O ae eS 11 Open No 2 dual bus feeder circuit breaker LH No 2 Verify PFD 2 remains powered If power to PFD 2 is removed check dual bus feeder circuit breaker RH No 2 associated limiter and diode 12 Open No 2 dual bus feeder circuit breaker RH No 2 Verify PFD 2 is not powered 13 Close No 2 dual bus feeder circuit breaker LH No 2 Verify PFD 2 powers up If PFD 2 remains without power check dual bus feeder circuit breaker LH No 2 associated limiter and diode 14 Close No 2 dual bus feeder circuit breaker RH No 2 15 If no other service is to performed remove aircraft power 4 17 2 Dual Bus Feeder Diodes Check Supersedes King Air 200 Series Maintenance Manual 24 50 00 periodic inspection of dual bus feeder diodes 1 Remove aircraft power by turning BATT and AVIONICS MASTER switches to OFF position 2 Remove all electrical power from the airplane 3 Remove the center aisle floorboards and covers as necessary to gain access to the power distribution panel A145 4 Remove the left isolation limiter F131 Page 4 34 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 10 11 12 13 14 15 16 Apply external power Turn BATT and AVIONICS MASTER switches to ON position Bus voltage SHOULD
107. the SVS Enable card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD 1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable SVS Dual PFD Press ENT key on PFD1 4 Verify Enable SVS Dual PFD is displayed in the Item window Press LOAD CONFIGURATION ID 48233D5E SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ES Figure 3 43 SVS Enable 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the SVS Enable card from PFD 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 45 190 00915 01 Revision 6 3 34 ESP Enable Follow this procedure to enable the Electronic Stability and Protection ESP function An Enhanced AFCS Unlock Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The G1000 has various features that require the use of unlock enable cards to activate the feature Throughout this docu
108. the data before continuing To see more of the data reselect the VIEW MAINTENANCE LOG in the COMMAND window and press the ENT key The press any key to continue function 1s not active at this time 8 Scroll through the OUTPUT list by pressing the OUTPUT softkey Page 5 32 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 9 The GIA Maintenance Log can record any of the following faults e FCS Task not started Bad gains The FCS task has not started because the gains are not present or have been corrupted Reload the gain files to correct e FCS Task not started Gain structure out of range The FCS task has not started because the gains are not compatible with the GIA software Reload the gain files to correct e PFT FAIL Timeout lt STEP gt Pre flight test has failed because the specified step has not passed in the allotted time See the GIA pre flight steps for a description of the possible values for lt STEP gt on the failed GIA and corrective actions e PFT FAIL Cross GIA Failed State lt STEP gt Pre flight test has failed on opposite GIA lt STEP gt specifies the pre flight test step on selected GIA that was in progress when the pre flight test failed on the opposite GIA See the GIA pre flight steps for a description of the possible values for lt STEP gt on the failed GIA and corrective actions e PFT FAIL lt STEP gt Pre flight has failed because the step specifi
109. the displays and GPS data availability to the AHRS with either GIA inoperative check 1 Open GIAI primary and secondary CBs 2 Verify the following NAV 1 and COMM tuning fields on PFD 1 and PFD 2 are invalid red X L R engine data remains valid XPDR1 is Inoperative GMA 1 is Inoperative AHRS is using backup GPS source AHRS2 not receiving backup GPS Information An amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2 AHRS and ADC data remain valid on PFD 1 and PFD 2 3 Close GIAI primary and secondary CBs Allow system to re acquire satellites and return to normal display modes 4 Open GIA2 CB 5 Verify the following NAV2 and COMM2 tuning fields on PFD 1 and PFD 2 are invalid red X L R engine data remains valid XPDR2 is Inoperative GMA2 Is Inoperative AHRS2 is using backup GPS source AHRSI not receiving backup GPS Information An amber BOTH ON GPS is displayed on PFD 1 and PFD 2 AHRS and ADC data remain valid on PFD 1 and PFD 2 6 Close GIA2 CB Allow system to re acquire satellites and return to normal display modes 7 Open GIA 1 primary and secondary CBs and GIA2 CB 8 Verify the following COMI NAV1 amp COM2 NAV 2 fields flag invalid GPS CDI flags DR on PFD NAVI amp NAV2 CDI loses deviation bar XPDR field flags invalid on PFD Engine Instrument field flags invalid on MFD All AHRS amp ADC fields remain valid Red AFCS status annunciation given If equipped with T
110. the listed versions in the General Arrangement drawing listed in Table 1 2 Software Configuration is a critical part of the G1000 operation and must be verified before returning an aircraft to service If any software version and or part number does not match those specified by the General Arrangement drawing or if the software is not successfully loaded DO NOT continue Troubleshoot and resolve the issue before continuing Page 3 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 SYSTEM COM 1 COM 2 GCU GDCI GDC FPGA GDC2 GDC2 FPGA GDL69 GEA GEA2 GFC CERT GIA 1 GFC CERT GIA2 GFC CERT PC GFC CERT PM GFC CERT PT C GFC CERT PT M GFC CERT RC GFC CERT RM GFC CERT YC SW VER OK SYSTEM GFC CERT YM GIA1 GIA1 AUDIO GIA2 GIA2 AUDIO GMAI1 GMA2 GMC GMU1 GMU1 FPGA GMU2 GMU2 FPGA GPS1 GPS2 GRSI GRS1 FPGA GRS2 GRS2 FPGA GSA PTCH CTL Table 3 1 Software Verification SW VER OK This item only verified when GIA p n 011 01105 20 is installed G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 SYSTEM GSA PTCH MON GSA PTCH TRM C GSA PTCH TRM M GSA ROLL CTL GSA ROLL MON GSA YAW CTL GSA YAW MON GWX GWX FPGA MFD1 MFD1 FPGA NAV 1 NAV 1 FPGA NAV 2 NAV 2 FPGA PFD1 PFD1 FPGA PFD2 PFD2 FPGA SW VER OK P
111. the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 Rotate the small FMS knob to highlight GDL 59 Press ENT key on PFD1 Verify GDL 59 is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A of SYSTEM N A MANIFEST N A GMA 1 GMA 2 GDL59 GDL59 ROUTER 006 B0736 12 GDL59 ROUTER FILE SYSTEM 006 D1112 10 6 ip 8 N A N A 006 B8 735 11 ol wy f Figure 3 34 GDL 59 Configuration Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME SYSTEM MANIFEST GMA 1 GMA 2 and GDL 59 e Green PASS in software column for GDL59 GDL59 ROUTER and GDL59 ROUTER FILE SYSTEM e Upload Complete COMPLETE in the summary box Press ENT key on PFD1 to acknowledge upload complete Deactivate cursor On the MFD verify that the GDL59 software part number and version matches the information in G1000 GFC 700 AFCS King Air 200 B200 005 00421 03 General Arrangement drawing Page 3 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01
112. the system Use sound avionics maintenance practices when working around or on G1000 equipment The remainder of this document is organized in the following fashion e Section 4 3 lists maintenance requirements related to the G1000 system e Section 6 gives instructions regarding the removal and replacement of physical G1000 equipment and parts e Section 7 gives configuration and testing instructions to be accomplished if G1000 equipment or parts are removed or replaced e Section 8 specifies system return to service procedures The beginning of Section 6 provides instructions to check the software part number and version of each LRU before removing a unit Procedures in Section 7 require the same check after LRU replacement and software loading IMPORTANT All structural repairs associated with this installation are to be addressed in accordance with the Hawker Beechcraft Structural Inspection and Repair Manual listed in Table 1 2 Page 4 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 2 2 Required Tools The following tools are needed to perform maintenance tasks on G1000 equipment Calibrated Milli ohm meter OR Agilent 34410A Ammeter or equivalent Fluke 187 Voltmeter or equivalent Variable DC Power Supply capable of providing 1 amp current 2 Non Magnetic Phillips Screwdriver 3 32 Hex tool Calibrated digital level Required for AHRS Procedure A Calibration Ca
113. turn Pot 0 CCW until the horn is OFF and then slowly turn the Pot 0 CW until the horn is ON again Press down on the vane until the horn is OFF and slowly release the vane If the horn is not ON when the vane is released turn the Pot 0 until the horn is ON Reduce the force on the vane to 0 TG and reposition the force applicator to apply a downward force on the vane d Calculate the Pot 3 TG force by adding 10 TG to the Pot 0 TG force Example If the Pot 0 force is 4 TG add 10 TG and the Pot 3 force is 6 TG e f h Install voltmeter leads between TP18 Lo and TP19 H1 of the SK100360 Breakout Box Apply the calculated Pot 3 TG force to the vane with the force applicator Adjust the Pot 3 on the lift computer until the voltage output from TP18 Lo and TP19 Hi reads 2 2 0 2 VDC on the voltmeter Return the force on the force applicator to 0 TG 10 Approach Flaps calibration a b C d Run the flaps to the APPROACH position Using the force applicator deflect the transducer vane forward UP to the Pot 1 TG force measured in step 11 in Section 7 24 1 If the stall warning horn is already ON turn the Pot 1 CCW until the horn is OFF and then slowly turn the Pot 1 CW until the horn is ON again Press down on the vane until the horn is OFF and slowly release the vane If the horn is not ON when the vane is released turn the Pot 1 until the horn is ON Reduce the force on the va
114. turn sockets 5 Configure and test the GMC 710 according to Section 7 11 6 15 GWX 68 Removal 1 Gain access by removing nose radome 2 Disconnect backshell assembly from unit 3 Use a 3 16 hex drive tool to remove each of the four mounting screws Reinstallation 1 Inspect connector for damaged pins 2 Hold unit flush with the radar mount 3 Use a 3 16 hex drive tool to tighten each of the four mounting screws 4 Connect backshell assembly to unit 5 Configure and test the GWX 68 according to Section 7 12 1 Page 6 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 16 Configuration Module Removal amp Replacement Configuration modules Item 1 shown below are located in the following LRU harness connector backshells Item 6 GDU 1040A PFD GRS 77 AHRS GDC 74B Air Data Computer and the GEA 71 Engine Airframe Unit Refer to the Master Drawing List listed in Table 1 2 for specific installation drawings Figure 6 2 Configuration Module Installation Table 6 1 Configuration Module Kit 011 00979 00 Description Qty Needed Garmin Part Number EN cong rene Module PCB Board Assembly w EEPROM amp Temp E 012 00608 00 or 02 adas Spacer Config Module A ee 213 00043 00 Cable 4 Conductor Harness 325 00122 00 Pins 22 AWG HD 336 00021 00 Removal 1 Disconnect connector from LRU 2 Remove 2 screws 8 from cover 7 and remove cover 3 Unplug connecto
115. volts e Top metal case of PFD 2 milli volts e Top metal case of MFD milli volts e Top metal case of GMA 1347D 1 milli volts e Top metal case of GMA 1347D 2 milli volts e Top metal case of GCU 477 milli volts e Top metal case of GMC 710 milli volts e GEA 71 1 body milli volts e GEA 71 2 body milli volts e GDC 74B 1 body milli volts e GDC 74B 2 body milli volts e OAT Probe base nut inside fuselage milli volts e OAT 2 Probe base nut inside fuselage milli volts e GDL 69A body milli volts e Engine Signal Conditioner 1 near mounting holes of case milli volts e Engine Signal Conditioner 2 near mounting holes of case milli volts e PFD1 Cooling fan metal base milli volts e PFD2 Cooling fan metal base milli volts e MFD Cooling fan metal base milli volts Cabin Compartment e GTX 33 1 top milli volts e GTX 33 2 top milli volts e GSA 80 Roll Servo body milli volts Ensure that at each PFD or MFD test point no more than 20 milli volts 20 mQ are present Ensure that at each other test point no more than 2 5 milli volts 2 5 mQ are present In this case voltage is equivalent to resistance Q given that precisely 1 amp reference current is present TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and 1 amp reference current Calculate the percentage difference and apply this to the voltage reading to obtain the equivalent resistance Example
116. window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A SYSTEM N A MANIFEST N A GTS 006 B0551 06 E Figure 3 28 GTS 8XX TAS TCAS1 Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME SYSTEM MANIFEST and GTS e Green PASS in Software column for GTS e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor 8 On the MFD verify that the GTS software part number and version matches the information in G1000 GFC 700 AFCS King Air 200 B200 005 00421 03 General Arrangement drawing G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 31 190 00915 01 Revision 6 3 18 StormScope WX 500 Option Configuration Follow this procedure to enable the lightning system option WX 500 for the G1000 system if required 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the System Upload page using the PFD1 small FMS knob 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD 1 3 Rotate the small FMS knob to highlight Lightning System Option Press ENT key on PFD 1 4 Verify the Lightning System Option
117. 0 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Table 7 5 Air Data System Test Test Point Nominal Altitude Tolerance Actual 20 1000 25 2000 4000 S 4000 8000 30 8000 8000 30 8000 10000 30 10000 35 11000 40 13000 14000 40 14000 16000 AS 16000 18000 45 18000 47 18983 7 18971 18958 47 18947 47 18947 47 18947 4 47 ASAS SANA NANA NN Altitude FT a Zw J gt gt ju a Zz J gt gt N Tolerance Actual 20 20 20 20 25 25 30 30 30 35 40 40 45 45 47 47 47 47 47 47 Airspeed KIAS AIR DATA 1 AIR DATA 2 Tolerance Tolerance Actual Actual 2 apa ee MO ae a a HUIR sa ae eT a ae as EEE a TENIA a INDICE a E ae AENA rs III a INIA a ENE ae ONE a ENCARA ee PUUIEAE as a ne NUS ae SSI G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 7 15 Revision 6 Air Data System Test Continued Test Point Airspeed KTS gt a O Vs AIR DATA 1 AIRDATA 2 AIRDATA 1 AIR DATA 2 Nominal Altitude Tolerance Actual oe Tolerance Actual a Tolerance Actual 72 Tolerance Actual 29000 72 28999 29000 12 28982 29000 I 12 28967 29000 12 28953 29000 I 12 28946 29000 72 1
118. 00 B200 Series King Air Page 4 23 190 00915 01 Revision 6 4 10 G1000 Redundant Connection Check Perform the following steps to verify the following A The primary PRI and secondary SEC power sources for GIA 1 GRS 1 PFD 1 and GDC 1 B The AHRS and ADC data path to PFD C PFD and MFD Ethernet connection includes ARINC connection between ADC and MFD and DISPLAY BACKUP button function D Engine data availability to the displays and GPS data availability to the AHRS with either GIA inoperative A PRI and SEC power sources for PFD 1 GIA 1 GRS 1 and GDC 1 check l Connect a ground power unit to the external power receptacle and turn on the ground power unit 2 Set the BAT and AVIONICS MASTER PWR switches to ON 3 With the G1000 system in normal mode pull the following circuit breakers on the right hand circuit breaker panel e PFD PRI e AHRS 1 PRI e ADC 1 PRI e GIA 1 PRI 4 Wait at least 5 seconds then verify the data on PFD1 remains valid and the following alert messages are not present e GIA 1 FAIL or any related message such as COM1 NAV1 XPDR1 GPS1 e AHRS FAIL e ADC 1 FAIL e FAILED DATA PATH 5 Close the circuit breakers listed in step 3 6 Repeat step 4 7 Pull the following circuit breakers on the right hand circuit breaker panel e PFD 1 SEC e AHRS 1 SEC e ADC 1 SEC e GIA 1 SEC 8 Wait at least 5 seconds then repeat step 4 9 Close the circuit breakers listed in step 7 Page
119. 00915 01 3 37 Navigation Database Loading A new navigation database cycle may be loaded before it is effective The new database will be stored on the G1000 bottom SD card until it becomes effective The G1000 will automatically update to use the new database at the first on ground power on after its effectivity date Follow this procedure to load the navigation database 1 Remove power from the PFD1 PFD2 and MFD 2 Insert an SD card containing the latest cycle Jeppesen navigation database data supplied by Jeppesen into the top slot of the MFD 3 Apply power to the PFD1 PFD2 and MFD A prompt similar to the following will be displayed on the MFD DO YOU WANT TO UPDATE THE STANDBY NAVIGATION DATABASE ON THE BOTTOM CARD THE STANDBY DATABASE WILL BE ACTIVATED UPON THE FIRST ON GROUND POWER CYCLE ON OR AFTER 00 88 SYSTEM TIME ON THE EFFECTIVE DATE FROM TO REGION WORLDWIDE WORLDWIDE CYCLE 4904 0905 EFFECTIVE 9 APR 2009 07 MAY 2009 EXPIRES 7 MAY 2089 44 JUN 2889 4 Select the YES softkey to confirm the standby navigation database update After the database is updated a prompt similar to the following will be displayed on the MFD DO YOU WANT TQ UPDATE THE ACTIVE NAVIGATION DATABASE SELECTING YES WILL QUERWRITE THE ACTIVE NAVIGATION DATABASE FROM TO REGION WORLDWIDE WORLDWIDE CYCLE 4904 0905 EFFECTIVE 9 APR 2009 47 MAY 2889 EXPIRES 7 MAY 2009 04 JUN 2089 6 Select the NO softkey to allow the syst
120. 01 and P8002 Rear View Figure 5 20 GTS 820 850 Mating Connector P8003 Rear View G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 83 Revision 6 190 00915 01 Figure 5 21 GPA 65 Mating Connector P651 Rear View Figure 5 22 Signal Conditioner 1PVIB1 and 2PVIB1 Rear View 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 00000000000000090909 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 000000000909 00090590 2 3 4 5 6 7 9 10 8 11 12 16 17 18 19 20 Figure 5 23 GDL 59 Mating Connector 1P591 Rear View 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 06000000000090909090 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 44 43 42 41 40 39 38 37 36 35 34 33 32 31 Figure 5 24 GSR 56 Mating Connector 1P561 Rear View Page 5 84 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 22 Standby Attitude Indicator Troubleshooting Symptom Recommended Action Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Warning flag pops into view indicating that the gyro motor is not receiving sufficient power to operate Unit fails to perform to specifications Remove the unit per Section 6 27 and inspect the electrical connector Check to ensure appropriate electrical power is being supplied
121. 12 6 20 AIDA TEN E e TT 6 13 6 21 WET ANTT NN ear an NUS 6 13 6 22 SIGNAL CONDONES o nea ol aie 6 13 6 23 INSTRUMENT PANEL ANNUNCIATORS PROP SYNCH AND STANDBY BATTERY 0000000008 6 14 6 24 L 3 AVIONICS BF GOODRICH PS 835 C OR D MODEL EMERGENCY BATTERY 00666 6 14 6 25 STANDBY AIRSPEED INDICATORS ardid 6 15 6 26 STANDBY ALIIME TE emer ee ee ont ae en mR Pe tC aC eg o tte e 6 15 6 27 STANDBY APTITUDE INDICATORS asada 6 16 6 28 NOSEAVIONICS BAY COOLING E ANS A A Ai iii 6 16 6 29 SB ad E Nn CORO NO en aT 6 16 6 30 Gl Bec G2 3 0 oa OE Diana 6 17 6 31 GPAOGSPA CNA UNIT A A cantata ada ad ae ed Doce EAR 6 17 6 32 ASS TRAFFIC ANTENAS eo lares o ete do a tO ne ae edna 6 18 6 33 ODLSIWELEDA TANK at 6 18 6 34 SR OO OA TELDE RECEIVER rats 6 19 7 G1000 EQUIPMENT CONFIGURATION TESTEN Go ooccoocoooccccnnonccccononoocccnnnnoocccnnnncaccccnnnoss 7 1 TL DU TO1S0OMPEDS PRD oa 7 1 a OMNIA SA ADA UDS PAN E EE E I EAN aera basta Re sieete adsense 7 3 Loa GIA63WINTEGRATED AVIONICS UNIT di TERRA 7 6 de GEA 7UENGNE AIRFRAME UNIT oreari ida 7 9 Poor TAS SF LAIN POND Eura aE A tad 7 12 TO GDCJAB ARDATACOMPUT ER eee oca 7 13 ET AGRS 77 ABRS 7 GMU 44 MAGNETOMETER 1 ecosesceccistbasscsigda ua a ais i 7 18 SS GeO DAI DATA LINK hase thers a ali 7 26 TO OSA SUS ERROR ra 7 26 7 10 GOW ATT EMS CONTROLLER A 7 27 7 11 GMC TLIOAFCSCONTROLLCER mier E tie AT I E A A teed it id 7 29 TA2 GOWA GS WEATHERRADAR a co ia 7 30 7 13 NON GARMIN TRA
122. 200 Series King Air Revision 6 190 00915 01 3 8 G1000 GFC 700 Software Information NOTE The following sections provide a detailed description of loading all G1000 software and configuration files which may be excessive for individual LRU removal and replacement If removing and replacing individual LRUs refer to Section 6 of this manual for the necessary steps 3 8 1 G1000 Software Image All software and configuration files were certified by Garmin and are considered part of FAA approved Type Design data Approved software and hardware definitions for each STC Configuration are defined on the appropriate General Arrangement drawing listed in Table 1 2 G1000 software and configuration files are controlled via the approved software image part number listed on the General Arrangement drawing listed in Table 1 2 This software image is loaded into the G1000 using a software loader card The installer shall create this software loader card by downloading the approved software image in accordance with section 3 8 2 NOTE Only SanDisk and Toshiba brand SD cards are recommended for use with the G1000 system NOTE Installers may obtain this software image already on a loader card by ordering Garmin Part number 010 00798 XX directly from Garmin Reference the General Arrangement drawing listed in Table 1 2 for part number information IMPORTANT To satisfy the G1000 GFC700 STC requirements for the 200 B200 series aircraft it is critical
123. 200 inspection program For a complete description of the King Air inspection program refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 Table 4 1 Maintenance Intervals ane Manual G1000 GFC700 Equipment Complete Visual Inspection of GWX 68 Equipment and Wiring located in Nose 4 4 Phase 4 Section Complete Visual Inspection of G1000 GFC700 Equipment and Wiring 4 4 Phase 4 located in Nose Avionics Compartment Complete Visual Inspection of G1000 GFC700 Equipment and Wiring 4 4 Phase 3 G1000 GFC700 located in Pilot s Compartment System Visual Inspections Complete Visual Inspection of G1000 GFC700 Equipment and Wiring 4 4 Phase 3 located on and behind Instrument Panel Complete Visual Inspection of G1000 GFC700 Equipment and Wiring 4 4 Phase 3 located in Cabin Complete Visual Inspection of G1000 GFC700 Equipment and Wiring 4 4 Phase 4 located in Rear Fuselage and Empennage Page 4 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 me bs Manual Verify proper operation of the GFC700 by performing the following Pre Flight Test AFCS Switch Checks Phase 2 and 4 Autopilot Operation Checks For installations with the GSM 86 servo gearbox Autopilot Clutch Overpower Check OA Periodic TAWS function check 7 15 Phase 4 Check oo oe Removal amp Replacement On Condition GDU 1500 MFD Removal amp Replacement On Condition Removal amp Replacement On Condition GMA
124. 3 Page 4 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 9 3 Servo Gearbox Adjustment Fixture Procedure This test is an alternative to the automated and manual slip clutch test procedures Only the GSM 85A servo gearbox slip clutch can be adjusted The GSM 86 servo gearbox does not have an adjustable slip clutch however the torque value can be measured using this procedure IMPORTANT This adjustment requires the use of the Garmin servo adjustment fixture P N T10 00110 01 For detailed operating instructions for the fixture refer to GSASX GSM85 A Installation Manual listed in Table 1 3 It is highly recommended that the following test be performed at temperatures between 50 F and 120 F 1 Remove the GSM 85A or GSM 86 servo gearbox as per Section 6 12 2 Place the GSM 85A or GSM 86 servo gearbox on the slip clutch adjustment fixture and secure with the toggle clamps Install the fixture cable between the capstan under test and the fixture capstan Remove the slack in the cable using the tension adjustment knob Tighten the two wingnuts on bottom of fixture while holding the top thumbscrews 3 Attach a socket to a calibrated torque wrench of appropriate range and place on top of the fixture capstan Adjust the wrench support fixture so that it contacts the handle in the appropriate location 4 Connect a 2 Amp 24 V DC power supply to the fixture 5 Place the solen
125. 32 33 34 35 36 37 38 1 o Figure 5 9 GEA 71 Backplate Connectors P13472 P13471 GMA 1347D Backplate Connectors 10 Figure 5 P331 COOLING PORT TOP ANTENNA CONNECTOR BOTTOM ANTENNA CONNECTOR Figure 5 11 GTX 33 33D Backplate Connectors Page 5 81 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Figure 5 12 GDU 1040A 1500 Backshell Connector P10401 or P15001 Figure 5 13 GRS 77 Backshell Connector P771 Figure 5 14 GDC 74B Backshell Connector P74B1 Figure 5 15 GDL 69A Backplate Connector P69A1 200 B200 Series King Air G1000 GFC 700 System Maintenance Manual Page 5 82 Revision 6 190 00915 01 Figure 5 17 GMC 710 Backshell Connector P7101 4 5 6 7 8 9 10 11 12 13 14 15 0000000000909 23 24 25 26 27 28 29 30 000090 3 1 2 0090 18 17 18 19 20 21 22 000000009090 31 32 33 34 35 36 37 38 39 40 41 42 43 44 0000000090 0009090 Figure 5 18 GWX 68 Backshell Connector P681 O 000000000000090909090 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 000000090 O 000000090 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 000000090 O 0000009090 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 00009090 00000000000909090 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 Figure 5 19 GTS 820 850 Mating Connectors P80
126. 347D 1 1 Turn the GMA 1347D 1 off by pulling the AUDIO NO 1 circuit breaker This directs all COM 1 phone audio MIC audio and MIC key to the pilot s position 2 Check the failsafe operation by exercising the COM 1 boom mic hand mic microphone key and audio over the headphones All volume control for the COM audio should be through the PFD volume control Verify proper operation of COM 1 using the failsafe operation 3 Close the AUDIO NO 1 circuit breaker to continue testing Failsafe Operation Check GMA 1347D 2 1 Turn the GMA 1347D 2 off by pulling the AUDIO NO 2 circuit breaker This directs all COM 2 phone audio MIC audio and MIC key to the co pilot s position 2 Check the failsafe operation by exercising the COM 2 boom mic hand mic microphone key and audio over the headphones All volume control for the COM audio should be through the PFD volume control Verify proper operation of COM 2 using the failsafe operation 3 Close the AUDIO NO 2 circuit breaker to continue testing Marker Beacon Test Figure 7 2 Marker Beacon Symbology 1 Using a ramp tester simulate the outer marker middle marker and inner marker signals by following the test equipment manufacturer s instructions Verify that each marker audio signal is present over the pilot and co pilot headphones and speaker 2 Verify that the outer middle and inner annunciations appear on PFD 1 and PFD 2 when the corresponding signal is applied Mark
127. 44 1 metal base milli volts e GMU 44 2 metal base milli volts e GSA 80 Pitch Servo body milli volts e GSA 80 Pitch Trim Servo body milli volts e GSA 80 Yaw Servo body milli volts TIP If 1 amp reference current cannot be maintained note the difference between the attainable current and 1 amp reference current Calculate the percentage difference and apply this to the voltage reading to obtain the equivalent resistance Example If the measured current is 1 2 amps 20 high from the target l amp current then the allowable voltage measurement would be 20 high 2 5 milli volts would now be 3 0 milli volts G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 17 190 00915 01 Revision 6 4 6 GRS 77 Earth Magnetic Field Updates The GRS 77 utilizes an Earth magnetic field model which is updated once every five years The update is expected to be available from Garmin in each of the following years 2010 2015 and every five years thereafter as long as the GRS 77 remains a Garmin supported product The G1000 system alerts the operator that the magnetic field database is out of date by issuing the message AHRS SERVICE AHRS Magnetic field model needs update Garmin will distribute update instructions when updates are available As of this writing Garmin Service Bulletin 0533 addresses the most recent update to the 2005 database Service Bulletins may be obtained from www garmin com at the Dealer R
128. 6 3 GEA Backshell Thermocouple Table 6 2 Thermocouple Kit 011 00981 00 Hem Description Qty Needed Garmin Part Number 3 Thermocouple K type 925 L0000 00 Removal Remove GEA 71 per Section 6 4 Remove GEA connector backplate Remove connector assembly J711 from the backplate Remove screws item 7 and cover item 6 from the backshell item 5 oy age Se ce Unscrew thermocouple from boss on backshell Extract the thermocouple pins from the connector G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 11 190 00915 01 Revision 6 Replacement l Crimp pins item 2 onto each of the thermocouple wires item 1 Ensure that pre stripped wire length is 1 8 prior to crimping 2 Insert newly crimped pins and wires into the appropriate connector housing location item 4 as specified by King Air 200 B200 Wiring Diagram listed in Table 1 2 3 Place thermocouple body item 1 onto the backshell boss item 5 Place the thermocouple as shown in Figure 6 3 so that the wires exit towards the bottom of the backshell 4 Fasten thermocouple tightly to backshell using the provided screw item 3 5 Fasten cover item 6 to backshell using screws item 7 6 Continue to Section 7 4 1 and verify that the ITT indications are valid on the MFD 6 18 GPS WAAS Antennas Removal 1 Gain access to the antenna coaxial cable connector by removing the cabin interior ceiling panel Refer to the Antenna Install
129. 7 24 3 for the flight calibration of the C 05606 1 Lift Computer NOTE Safe Flight P N C 05606 1 lift computers are equipped with six adjustable potentiometers in the top of the computer The potentiometers are marked 0 1 2 3 4 and 5 Ref Figure 7 14 The potentiometers marked 0 1 and 2 are used to calibrate the stall warning points for the three flap positions full up approach and full down The potentiometers marked 3 4 and 5 are used to calibrate the Low Airspeed Awareness LAA output for the three flap positions full up approach and full down which determines Electronic Stability and Protection ESP and Autopilot Underspeed Protection USP alpha floor symbol position 7 24 1 Measuring Lift Computer Stall Warning Points Prior to removal of the lift computer it is recommended that the stall warning points from the lift computer installed in the aircraft be measured This section is used to measure stall warning points of the lift computer 1 Gain access to the stall warning computer 2 Connect the breakout box P N SK100360 or equivalent between the lift computer and the airplane wiring harness see Figure 7 15 3 Make sure that the stall warning heat system is turned OFF 4 Remove the potentiometer access cover plate from the lift computer 5 Simulate an in flight condition as follows Bypass the landing gear safety switch by connecting an electrical ground to TP 7 of the breakout box This is best acc
130. 8 CONFIGURATION OF NAVIGATION MAP FOR TRAFFIC SYSTEM cooccnnoccnnocnnnccnnaronunccnnoconininnnos 3 51 3 39 CEEARING DEFAUETUSERSETUNO SS ri lista 3 51 4 INSTRUCTIONS FOR CONTINUED ATRWORTHINESG ccccsssccsssccssccsscccsccccssccescsees 4 1 El AIRWORTHINESS LIMITA TON a A 4 1 a SERVICING IN E ORNATO to 4 2 A gt JVEAINFENANGE IN DER VALS lao 4 4 AA VISUAL INSPECTION sicscs2 chc cansntecaseaivssnaayeiesaamntaesmaannsesanuanbewnannesesaaguubeseannnis saaunecceanameesenoousemanba 4 10 gt JEEBCTRICAL BONDING TEST dicos 4 15 4 6 GRS 77 EARTH MAGNETIC FIELD UPDATES cccccsscccssccessccessccessceesscessccessccessceescessccessseess 4 18 4T GSA S0GREASINGPROCEDUR E sonarai la eset 4 18 4 8 FLAPS IN MOTION DISCRETE INPUT CHECK ccccccsscccssccesccescccessceessceesccessscecceesccessccessseess 4 19 4 9 GSM 85A GSM 86 SLIP CLUTCH TORQUE CHECK PROCEDURE occonoccnnnocononiocononoccnnnccnonanononoso 4 20 4 10 G TOOO REDUNDANT CONNECTION CHECK sia 4 24 4 11 ENGINE DATA CHECK GIA 1 OR GIA 2 INOPERATIVE 0000ssssssseeeeecccceeeeeesaaeeeeessseseeees 4 27 4 12 TRIM ANNUNCIATOR CHECK cil 4 27 4 13 GTO00 NUSCOMPARE E HECKS sa cds a 4 28 4 14 NOSE AVIONICS COMPARTMENT FANS OPERATIONAL CHECK cccccsecccssccessccescceeecceescenee 4 30 4 15 INSTRUMENT PANEL FANS OPERATIONAL CHECK cccccsccesccesccescceccesscescesscessesceesceescens 4 30 4 16 STANDBY BATTERY PERIODIC CHECK Sussie lll 4 3 4 17 POWER BUS C
131. 88 28937 29000 fare 28928 87 35016 87 34996 87 34978 87 34961 87 34953 87 34946 87 34939 Aircraft S N Operator 72 i I I a N 72 2 2 72 T N T N 72 2 2 72 T No te N 72 2 2 87 2 2 87 T 2 87 2 2 87 2 2 87 2 2 87 2 2 87 2 2 ANNAN NANA NS GF ADC1 ADC2 Make Model GDC 74B Model GDC 74B Model P N 011 01110 P N 011 01110 S N S N S N Cal Date Cal Date Cal Date Leak Check Static System at 30 000 ft 300 kts pass if lt 300 ft in 1 min Pilot Feet Min Copilot Feet Min Leak Check Pitot System at 200 kts pass if lt 1 KIAS in 1 min Pilot KIAS Min Copilot KIAS Min Page 7 16 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 6 2 Static Port Vertical Speed Rate of Climb Test 1 Command ADTS to change the altitude at the 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 tolerances specified in Table 7 6 Table 7 6 Vertical Speed Table N A No VS Display 7 6 3 OAT Probe Check 1 Ensure on side sensors for PFD1 and PFD2 2 Ensure the outside air temperature OAT probes and a calibrated thermometer stabilize at a
132. A GARMIN G1000 GFC 700 system Maintenance Manual Hawker Beechcraft Model 200 B200 Series King Air Contains Instructions For Continued Airworthiness For STC SA01535WI D NN ATA Y an ne p TE u aA E ONO IV MEA EA avere O 0 0600000 m 0 E LI Ola ER E 5 ON ur man Y K ja Q_Y qe ale 190 00915 01 July 2012 Revision 6 This page intentionally left blank Copyright 2009 2012 Garmin Ltd or its subsidiaries All Rights Reserved Except as expressly provided herein no part of this manual may be reproduced copied transmitted disseminated downloaded or stored in any storage medium for any purpose without the express prior written consent of Garmin Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 WWwW garmin com Garmin Europe Ltd Liberty House
133. A1 SERVICE GMA1 needs service Return unit for repair The system has determined that the specified GMA 1347D needs e Replace GMA service Return unit for repair GMA1 FAIL GMA1 in Ensure GMA1 is receiving inoperative power Ensure both GIAs are receiving power Ensure all GDUs are receiving The system has detected a failure GMA2 FAIL GMA2 in in the specified GMA 1347D power inoperative Ensure the GMA GIA RS 232 data lines are working properly Ensure the GIA GDU Ethernet data lines are working properly Replace GMA1 MANIFEST GMA1 software mismatch Communication Halted The system has detected an Load the correct unit software See incorrect software version loaded Section 3 9 for the Software Loading MANIFEST GMA2 software in the specified GMA 1347D procedure mismatch Communication Halted GMA1 CONFIG GMA1 e Load GMA configuration files see configuration error Config service Section 3 9 req d a e Replace GMA e f problem persists replace master configuration module check config module wiring for faults and replace if necessary The system has detected a GMA NOTE 1347D configuration mismatch for New Terrain Obstacle cards Jeppesen GMA2 CONFIG E GMA2 l the specified unit Aviation Database and other optional configuration error Config service features i e TAWS unlock card will req d need to be replaced if the master configuration module is changed The G1000
134. ARNESS SEE mp THE MODEL 200 ggl SUPER KING AJR L bla 200 SERIES WIRING DIAGRAM MANUAL A rrr Figure 7 15 Breakout Box AMP 205838 3 AMP 205840 3 SOCKET PLUG G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 55 190 00915 01 Revision 6 l 6 positionar anchor tab 3 Into vane opening 5 Turn screws 2 and 6 as required to bring gage e j A biii pressure arm 7 to bear on surface of vane 8 within 2 Hook anchor tab 3 onto the mounting plate 1 32 of tip 3 K anchor tab engaged shift positioner until cone 6 Apply pressure to aft surlace of vane B for negative aa ea in the screw heads 5 tip grams and forward surface for positive tip mis 4 Tum screw 1 counterclockwise until knob cluich slips 7 Tum screw 6 to adjust force tip grams as required Figure 7 16 Force Applicator Usage Instructions Page 7 56 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 24 3 Safe Flight Lift Computer Flight Calibration NOTE This procedure 1s required only for aircraft with the optional Electronic Stability and Protection ESP feature 1 Disable the STABILITY amp PROTECTION item via the MFD AUX SYSTEM SETUP 2 page Verify that the message ESP OFF is present 2 Perform the Flight Test and Calibration procedure in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 S
135. ATION N A ES Figure 3 26 RAD ALT Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for GIA2 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 29 190 00915 01 Revision 6 3 16 Non Garmin 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 7 13 Traffic System Functional Check 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the System Upload page on PFD1 using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Traffic System Option Press ENT key on PFD1 4 Verify the Traffic System Option is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A Cf Figure 3 27 Non Garmin Traffic Syst
136. AWS TAWS FAIL annunciation given If equipped with ADF and or DME ADF DME windows flag invalid 9 Restore power to both GIA units The G1000 Redundant Connections Check is complete Page 4 26 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 11 Engine Data Check GIA 1 or GIA 2 Inoperative NOTE This procedure should be accomplished in conjunction with the engine run up Valid engine indications will be needed Do the following to verify the engine data availability and validity with GIA 1 or GIA 2 inoperative 1 Ensure the G1000 is in normal mode With engines running note the indication values for torque ITT and oil pressure On the right hand circuit breaker panel open the GIA1 PRI and GIA1 SEC circuit breakers Verify the values for torque ITT and oil pressure remain unchanged Close the GIA1 PRI and GIA1 SEC circuit breakers and wait until the COM1 and NAVI fields are valid oY A SAS Open the GIA2 circuit breaker Verify the values for torque ITT and oil pressure remain unchanged Close the GIA2 circuit breaker and wait until the COM2 and NAV2 fields are valid O A Put the G1000 in Reversionary mode 10 Repeat steps 2 through 8 verifying engine gauge indications on PFD 1 MFD and PFD 2 11 The Engine Data Check is complete 4 12 Trim Annunciator Check This procedure checks the pitch trim PTRM annunciation from both GIA 1 and GIA 2 and the mis trim
137. BY BATTERY legend on the standby battery switch extinguishes Page 8 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 8 1 6 G1000 Backup Path Test 1 Remove power from the displays by pulling the following circuit breakers e PFDI1 PRI e PFD1 SEC e PFD2 e MFD 2 Reboot PFD1 PFD2 and MED while holding the ENT key on each display far right key on MFD until the words INITIALIZING SYSTEM appear 3 In configuration mode go to the GDU Page Group on PFD1 4 On PFD1 activate the cursor and select PFD1 in the SELECT UNIT field and press ENT 5 Observe the GRS 77 and GDC 74 DATA indicators in the ARINC 429 window 6 Verify both indicators are GREEN indicating the channels are receiving data as shown below ci 2 MCO Figure 8 1 GDU Data Verification ARINC 429 7 On PFD1 activate the cursor and select PFD2 in the SELECT UNIT field and press the ENT key 8 Repeat Steps 5 and 6 9 On PFD1 activate the cursor and select MFD1 in the SELECT UNIT field and press the ENT key 10 Repeat Steps 5 and 6 11 On PFD1 go to the GIA Page Group Go to the RS 232 ARINC 429 CONFIG page 12 Verify that GIA 1 is selected in the SELECT UNIT field 13 Observe the data indicators for all configured RS 232 and ARINC 429 channels except GIA DEBUG including the GRS 77 and GDC 74 ARINC 429 channels 14 Verify all DATA indicators are GREEN indicating the channels are receiving data as
138. CedUre oooooooonooooononnnnnnnnnnnnnononononnnnnnnnononononnnnnnnnnnnnnnnnnnos 4 10 Table 4 4 Nose Avionics Compartment Visual Inspection Procedure ooooooooooooonnnnnnncnnnnnnnnnnnnnnnnnnnoss 4 10 Table 4 5 Pilot s Compartment Visual Inspection Procedure ooooooonononoooonnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnos 4 11 Table 4 6 Instrument Panel G1000 Equipment Visual Inspection Procedure ccccccccnnnnnnnnnnnnnnnnnns 4 11 Table 4 7 Cabin Area Visual Inspection Pr io 4 13 Table 4 8 Rear Fuselage and Empennage Visual Inspection Procedure oooooooooonoonnnnnnnnnnnnncnnnnnnnnnnnss 4 14 Table 4 9 Lightning Strike Inspection Procedure sas alo 4 14 Hable 4 10 Measured Torque operan 4 22 Table 4 12 Standby Battery Required Equipment ccris ianoaaeie aeiae ea 4 31 Table ol SVS COUDES NOON ia 5 27 Fable 522 SVS Related Alen Mess ia 5 27 Table 5 3 AFCS Annunciation TroubleshootIMg occcccccnnnnnnnnnnnnnnnnnnnnnnnnononononnnnnnnnnnnnnnnnnnnnnnnnnnnnonoss 5 28 Pable 5 4 AFCS General round a 5 29 Table 5 5 Magnetometer Interference Test Sequence oooooononooooooooncnnnnnnnnnnnnnnononnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnos 5 72 Table 6 1 Configuration Module Kit 011 00979 D0 ococccccccncncnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnos 6 9 Table 6 2 Thermocouple KAOL 00981 00 a ca cetaes see ac A EA AET 6 11 Table 7 1 Fuel Flow Indication Special Equipment oooooooononoooonnncnnnnnnnonnnnnnnn
139. Check ChartView must be enabled using a ChartView Enable Card as specified in the General Arrangement Drawing listed in Table 1 2 and a current ChartView database Reference section 3 29 ChartView Configuration for enabling procedures NOTE The required ChartView databases are subscription based and are to be procured by the aircraft owner directly from Jeppesen 1 With the G1000 in Normal Mode use the GCU FMS knob to select AUX System Status page then select MFD1 DB softkey 2 Use the small FMS knob to scroll to CHART Verify ChartView is displayed in blue text adjacent to CHART 4 Verify the ChartView database cycle number is displayed in blue text and the ChartView database is current 5 Deactivate the cursor and use the large GCU FMS knob to select the Navigation Map Page then press the SHW CHRT softkey 6 Verify the airport chart is displayed and the following softkeys are displayed some softkeys may be grayed out e CHRT OPT e APR e CHRT o WX e INFO 1 e NOTAM e DP e GO BACK e STAR 7 Press CHRT OPT softkey and verify the following softkeys are displayed some softkeys may be grayed out e ALL e HEADER e PLAN e PROFILE e MINIMUMS e FIT WDTH e FULL SCN e BACK If no other service 1s to be performed continue to the return to service checks in Section 8 Page 7 38 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 18 SafeTaxi Fu
140. D according to Section 7 1 6 2 GMA 1347D Audio Panel Removal 1 Using a 3 32 hex tool turn the hex nut counter clockwise until the GMA 1347D is unlocked from its location 2 Carefully remove the GMA 1347D from its rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Gently insert the GMA 1347D into the rack until the locking tab engages the rack 3 Begin to turn the hex nut clockwise This draws the unit into the rack until seated Do not over tighten the nut 4 Configure and test the GMA 1347D according to Section 7 2 Page 6 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 3 GIA 63W Integrated Avionics Units Removal 1 Gain access to the forward avionics compartment in the nose of the aircraft 2 Unlock the GIA 63W handle by loosening the Phillips screw on the handle 3 Pull the handle upward to unlock the GIA 63W Gently remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Gently insert the GIA 63W into its rack The handle should engage the dogleg track 3 Press down on the GIA 63W handle to lock the unit into the rack 4 Lock the handle to the GIA 63W body using the Philips screw 5 Configure and test the GIA 63W s according to Section 7 3 6 4 GEA 71 Engine Airframe Unit Removal 1 Gain access by
141. ERTS GIA 1 GIA 2 GEA 1 GIA CERT 006 D1426 04 PITCH CERT 006 D1426 04 ROLL CERT 006 D1426 04 YAW CERT 006 D1426 04 Figure 3 32 ESP Support Configuration Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME MANIFEST ALERTS GIA1 GIA2 and GEA 1 e Green PASS in Software column for GIA CERT PITCH CERT ROLL CERT YAW CERT and PITCH TRIM CERT e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 34 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 21 ESP Support no AOA Option Configuration This section applies only to installations with the ESP option without AOA modes available in software version 0985 04 and later The original Safe Flight lift computer is used for this configuration The procedures outlined in this section must be followed to load the necessary configuration files required to enable ESP messages and functions An Enhanced AFCS unlock card is also required for this option see Section 3 34 NOTE If the ESP Support with AOA Option Configuration was previously loaded see Section 3 20 the baseline configuration must be reloaded before proceeding with this procedure Reload the baseline configuration for the specific airframe and all applicable opt
142. FC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 Connect a pitot static test set to the aircraft ADC1 pitot and static ports Pilot s side Do not connect the pitot static tester to ADC2 ports at this time 3 Set the baro correction on PFD1 and PFD2 to 29 92 4 Onthe AFCS mode controller press the ALT HDG and AP buttons and verify autopilot engages 5 Slowly increase the pitot static test set to simulate an ADC1 ADC2 altitude miscompare of greater than 200 ft verify the disconnected ADC altitude does not increase autopilot does not disconnect and amber comparator window text ALT MISCOMP is displayed on PFD1 and PFD2 6 Reduce ADC altitude to ambient pressure 7 Repeat Step 5 with the pitot static test set connected to the aircraft ADC2 pitot and static ports 8 Use the pitot static test set to simulate an airspeed of 40 kts for ADC1 and 55 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 9 Use the pitot static test set to simulate an airspeed of 55 kts for ADC1 and 40 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 10 Use the pitot static test set to simulate an airspeed of 85 kts for ADC1 and 95 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is disp
143. FD AUX page 4 Check for desired results Remove shroud from the GIA 2 GPS antenna Dual GPS Failure Condition 1 2 Page 8 2 Ensure GPS satellites are acquired Cover both GPS antennas Verify loss of signal on MFD AUX page 4 Check for desired results Remove shrouds from GPS antennas Allow both receivers to re acquire satellite signals before continuing Revision 6 For each of the single GPS failure conditions the following shall remain valid on the PFD throughout the procedure e Attitude and Heading from AHRS e Airspeed Altitude Vertical Soeed and OAT from Air Data Computer e GPS Course Deviation Indicator For a GIA1 GPS Failure an amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2 For a GIA2 GPS Failure an amber BOTH ON GPS1 is displayed on PFD 1 and PFD 2 For a dual GPS failure condition the following shall occur e GPS CDI flags LOI on both PFDs e Attitude and Heading remain valid from both AHRS on both PFDs Airspeed Altitude Vertical Speed and OAT remain valid from both Air Data Computers on both PFDs e LOI appears on MFD Map e TAWS N A aural alert amp annunciation given When GPS satellites are re acquired verify that the INTEG OK annunciation is given on the HSI in white for a brief period of time then disappears After 10 seconds of stable GPS position reacquisition verify the TAWS AVAILABLE aural alert is given Verify that the system
144. FFIC SYSTEM FUNCTIONAL CHECK j ccccccssecccesecccsscccesscccusscceeseceeenecens 7 31 7 14 STORMSCOPE FUNCTIONAL CHE CR it ti id 7 32 7 15 TAWSTONCTONAL CHE Css ica Raat 7 34 7 16 PTE CHAR TS UNC TION ATs CHECK ica 7 37 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 111 190 00915 01 Revision 6 7 17 CHARTY IEW FUNCTIONAL CHECK neral dd sia 7 38 7 18 SARE TAXTRUNCETONAL CHE CS A a 7 39 7 19 DMEFUNCTONALEHECR a a eb Sa eo esse 7 40 7 20 PA TOE PUNCUIONAL CE Cg tah id 7 41 7 21 RADIO AL TIME FE CHECO tench tia AE stan waltet casi puse hl ia het 7 41 1 22 WEIGHT ON WHEELS AND LOW SPEED AWARENESS BAND CHECK Q ccsccsscceccescesscescesces 7 42 den ROS VEGADEO Si O Ad mere renee 7 43 7 24 SAFE FLIGHT LIFT COMPUTER GROUND CALIBRATION o0ooccoccnccnoconccnncnnccnnconccnnconccnnconccnncnnacos 7 49 Maza ESP EUNCTONAL CHEC rd A A Ei 7 57 7 26 GTS 8XX TRAFFIC SYSTEM FUNCTIONAL CHECK ccccccsccsesccesccesccsccescccscccsecseccseecsecesees 7 61 27 ACTIVATION OF GARMIN FLIGHT DATA SERVICES cccoccnoccnnccnnccnnccnncconoconoconoconoconoconoconoconicons 7 63 7 28 GDL 59 WI FI DATA LINK FUNCTIONAL CHECK oc c ccccccccsccceccsescsstessctsscevecspscevecsversvecsverseces 7 65 7 29 GSR 56 SATELLITE RECEIVER FUNCTIONAL CHECK c csccssccsccscccsscscesccscesscsscessescessencs 7 66 8 SYSTEM RETURN TO SERVICE PROCEDURE ccccccsccccccccccccccccccccccscccssccscccsecees 8 1 Sl BACKUP PATHASY
145. FORWARD arrows are aligned and the WX PA antenna suction cups are positioned forward of center along the longitudinal axis 7 Secure the WX PA cable to the aircraft with the attached suction cup and route the cable to the cockpit 8 Connect the remaining cable end to the WX PA 9 Power up the WX PA and verify the WX 500 is in the weather mapping mode 1 e 3600 weather view at the 200 NM range 10 Set the WX 500 to STRIKE mode 100 NM range or next highest available range 11 Select the Continuous Out mode displayed on the WX PA menu and press MENU ENTER 12 Select the bottom mount antenna configuration on the WX PA keyboard A key 13 Select a cardinal bearing and a range of 120 NM 14 Use the Fl 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 7 32 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 15 16 1 18 19 20 2l 22 23 24 25 26 2T 28 Press MENU ENTER to start the test Observe the MFD to ensure the proper positioning of the strikes based on range and azimuth settings on the WX PA Change the cardinal bearings and verify correct test strikes Verify the strikes are within 10 degrees of the selected azimuth and plot at 60NM 1 2 120 NM Verify after 20 seconds of operation the strike counter reads 580 40 After testin
146. GDU AIRFRAME CONFIGURATION page In the AIRFRAME section upper right corner verify the correct configuration for SERIES ENGINE and PROP EXAMPLE For a configuration that loaded King Air B200 PT6A 42 with a McCauley 3 BLADE propeller the AIRFRAME section should display SERIES B200 ENGINE PT6A 42 PROP MCCAULEY 3 Page 1 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 1 2 Organization The following outline briefly describes the organization of this manual Section 2 System Description Provides a complete description of the type design change associated with installing the G1000 integrated cockpit system in the 200 B200 Series King Air An overview of the G1000 and GFC 700 system interface is also provided Section 3 G1000 Control amp Operation Presents basic control and operation information specifically tailored to maintenance practices Basic G1000 Configuration Mode operation is also described Section 4 Instructions for Continued Airworthiness Provides maintenance instructions for continued airworthiness of the G1000 and GFC 700 systems Section 5 Troubleshooting Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000 and GFC 700 systems Section 6 G1000 Equipment Removal Replacement Gives instructions for the removal and replacement of G1000 and GFC700 equipment Section 7 G1000 Equipment Con
147. GMA 1347D 2 reconfigure both GMA s to their new locations to confirm if the problem is in the original GMA 1347D 1 o Replace original GMA 1347D 1 if box turns green CHNL 7 ee ft i it 1347 1 after swapping units Swap GIA1 and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA1 o Replace original GIA1 if box turns green after swapping units Check the GIA1 GMA 1347D 1 interconnect wiring for faults Amber GIA1 GMA 1347D 1 data path functionality is unknown Reload GIA1 configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 11 190 00915 01 Revision 6 GIAI ARINC 429 GIA1 GDC 74 1 data path is functioning correctly GIA1 GDC 74 1 data path is not functioning correctly e Load GIAI and GDC 74 1 configuration files e Swap GIA and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA 1 IN 5 GDC 74 1 o Replace original GIA 1 if box turns green after swapping units e Check the GIA1 GDC 74 1 interconnect wiring for faults Replace GDC 74 1 1f problem remains pane GIA1 GDC 74 1 data path functionality is unknown Reload GIA1 configuration files Green Green GIAI GRS 77 1 data path is functioning correctly GIA1 GRS 77 1 data path is not functioning correctly e Load GIA1 configuration files e Swap GIA and GIA2 reconfigure both GIA s to their new locations to conf
148. GSM 85A servo gearboxes are selected press LOAD CONFIGURATION ID D2C83E0 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A PITCH TRIM SERVO N A ROLL SERVO N A YAW SERVO N A Figure 3 36 GSM 85A Servo Mount Configuration Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for PITCH SERVO PITCH TRIM SERVO ROLL SERVO and or YAW SERVO as selected e Upload Complete COMPLETE in the summary box Press ENT key on PFD1 to acknowledge upload complete Deactivate cursor 10 Verify the servo mount configuration per section 3 27 Page 3 38 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 26 GSM 86 Servo Mount Configuration For software versions 0985 04 and later the section 4 9 1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured Ifa GSM 85A servo gearbox is replaced by a GSM 86 servo gearbox follow the steps below to load the configuration It 1s not necessary to load this configuration if GSM 86 servo gearboxes are already installed for all servos default configuration 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop d
149. Gain access to the antenna coaxial cable connectors by removing the cabin interior ceiling panel Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the four coax quick lock connectors 3 Remove the antenna mounting screws 4 Remove antenna Reinstallation 1 Install antenna using retained mounting screws 2 Connect the four coax connectors Note the color coded bands which match the mating connectors 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Reinstall cabin interior ceiling panel 5 Test the GTS 8XX per Section 7 26 6 33 GDL 59 Wi Fi Datalink Removal 1 Gain access by removing the cabin center floor panel at the main entry door 2 Detach the two rack mount angles from the remote equipment shelf Retain all mounting hardware 3 Remove the Philips head screw which holds the locking lever down 4 Lift the locking lever up to unlock the unit from the mounting rack 5 Remove the unit from the mounting rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Insert the unit into the installation rack Do not use excessive force when inserting the GDL 59 into the rack This may cause damage to occur to the connectors unit and or unit rack If heavy resistance 1s felt during installation stop Remove the GDL 59 and identify the source of resistance The rear plate is designed to float in the unit rack
150. HRS magnetic field model update should be updated for the Load updated AHRS magnetic field AHRS2 SERVICE AHRS2 specified unit Appears on ground file See Section 4 6 magnetic field model needs only update GEO LIMITS AHRS1 too far north south no magnetic Operate the aircraft only within the compass Noma NEUE an limits as specified in the G1000 GFC available due to being too far 700 Kina Air 200 B200 AFMS listed north south no magnetic in Table 1 3 compass AHRS1 TAS AHRS1 not Check GRS GDC interconnect for receiving airspeed The specified GRS 77 is not faults receiving airspeed from the GDC Replace the GDC 74B AHRS2 TAS AHRS2 not 74B receiving airspeed If problem persists replace the GRS TT AHRS1 GPS AHRS1 not The GRS 77 1 is not receiving Ensure that a cell phone or a device receiving backup GPS backup GPS information from using cell phone technology is not information either GIA 63 turned on even in a monitoring AHRS1 GPS AHRS1 operating The GRS 77 1 is operating in the state in the cabin exclusively in no GPS mode absence of GPS Check GPS status for GIA 1 and 2 AHRS1 GPS AHRS1 not The GRS 77 1 is not receiving on MFD ne ao STATUS page receiving any GPS information GPS data from the GPS receivers lf one or both GPS receivers cannot acquire a position lock see GPS AHRS1 GPS AHRS1 using The GRS 77 1 is using the backup GPS source backup GPS data path
151. IVE VFR CODE 1200 1200 AIRCRAFT WEIGHT lt 15 500 LBS lt 15 500 LBS MAX AIRSPEED lt 300 KTS lt 300 KTS ADDRESS TYPE US TAIL US TAIL MODE S ADDRESS N N FLIGHT ID TYPE SAME AS TAIL SAME AS TAIL FLIGHT ID N N ENHANCED SURVEIL ENABLED ENABLED ADS B TRANSMIT PFD CONFIG PFD CONFIG AIRCRAFT WIDTH lt 23 MT lt 23 MT AIRCRAFT LENGTH lt 15 MT lt 15 MT SURVEIL INTEGRITY lt 1x1 5 ERR HR FLT lt 1x1 5 ERR HR FLT Figure 7 5 Aircraft Registration 5 For US registered aircraft the FLIGHT ID TYPE field should be set to SAME AS TAIL For other aircraft the FLIGHT ID TYPE field should be set to CONFIG ENTRY or PFD ENTRY NOTE The CONFIG ENTRY setting requires the Aircraft Registration ID number to be entered once in the FLIGHT ID field The PFD ENTRY setting allows the pilot to enter the Aircraft Registration ID number from the PFD via the TMR REF softkey Page 7 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 After each configuration setting change press the ENT key to configure the transponders 7 Press the ENT key on PFD1 to acknowledge prompt 8 After completing transponder configuration deactivate the cursor 7 5 2 GTX 33 Test Operation of the GTX 33 or GTX 33D Mode S transponder is accomplished using PFD 1 PFD 2 or the MFD Refer to G1000 in King Air 200 B200 Cockpit Reference Guide listed in Table 1 2
152. Iridium top and bottom GA 58 traffic antennas if installed To gain access for the following Inspections remove floorboards in cabin at FS 185 00 and FS 246 750 Inspect all exposed wire harness for chafing damage proper routing of wire Cabin Wiring bundles and security of attachment in accordance with AC 43 13 1B Harness Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Inspect the GTX 33 units shelf brackets and connectors for corrosion or other defects Check the integrity of the shield block ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GTX 33 Qty 2 Inspect the GDL 59 unit if installed shelf brackets and connectors for GDL 59 corrosion or other defects Check the integrity of the shield block ground wi fi option only attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Inspect the GSR 56 unit if installed shelf brackets and connectors for GSR 56 corrosion or other defects Check the integrity of the shield block ground iridium option only attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Using a flashlight inspect the roll servo servo gearbox connectors support structure and control cables to ensure that no corrosion chaffing crack
153. Lo 50 ohms EM Vane Heater Pin Hi 7 Vane Heater Pin Lo ap All resistances are 20 8 1 Self Test Coil Pin Hi Transducer Mounting Plate heater resistance is 2 1 20 ohms at ambient temperature 5 26 GDL 59 Troubleshooting Symptom Recommended Action Check power wiring and pin out of GDL 59 unit No communication with GDL 59 Ensure GDL 59 configuration option has been loaded Verify that a wi fi network is configured and available Ensure the wi fi antenna is within range of a wi fi network No or low quality wi fi signal Remove any obstacles between the aircraft wi fi antenna and the wi fi network hub that may be blocking the signal Check the wi fi antenna cable and connectors Verify antenna ground plane is adequate Activate Garmin Flight Data Services reference Section 7 27 Note that a replacement GDL 59 unit must be registered again even if the MFD already shows REGISTERED Connects to wi fi but cannot send report data Page 5 88 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 27 GSR 56 Troubleshooting Symptom Recommended Action Check power wiring and pin out of GSR 56 unit No communication with GSR 56 Ensure GSR 56 configuration option has been loaded Ensure the Iridium antenna has an unobstructed view of satellite constellation CRON a Check the Iridium antenna cable and connectors Verify antenna ground plane is adequate Check wi
154. MFD Software Load Software is first loaded to the MFD and PFDs From the factory G1000 units do not contain useable software or configuration settings Load software to PFD2 first then MFD and finally to PFD1 G1000 System Upload Selection After software is loaded to the MFD and PFDs the displays should be placed in configuration mode Using PFD1 the technician goes to the System Upload page From the System Upload page software files are selected to create an automated profile to load Once all desired files are checked the G1000 automatically loads the selected files in the correct sequence to the LRUs G1000 System Software Verification After software is loaded to the system the technician verifies that each LRU reports the correct version and software part number G1000 System Configuration Upload Selection Following G1000 system software upload and verification the aircraft specific configuration files as defined in the general arrangement drawing are loaded The aircraft general arrangement drawing will define the configuration files appropriate to the specific aircraft serial number STC modifications and applicable AFMS G1000 Configuration Verification After system configuration files are loaded the technician verifies that the correct configuration on the Airframe Configuration page Figure 3 16 Software Configuration Overview Page 3 18
155. N Refer to section 3 30 for TAWS Configuration for configuring TAWS 3 Press the GCU MENU button and select Test TAWS System from the pop up menu Verify TAWS test annunciation is displayed on the MFD and both PFDs 4 After the TAWS test has completed verify that TAWS System Test Okay is heard over the cockpit speaker if selected and the headsets 5 Press the GCU MENU button again and select Inhibit TA WS from the pop up menu and press ENT on the GCU Verify TAWS INH is displayed on PFD 1 and PFD 2 6 Press the GCU MENU button again and select Enable TAWS from the pop up menu and press ENT on the GCU Verify the TAWS INH annunciation on the PFDs has extinguished 7 Press the GCU MENU button again and select Inhibit GPWS from the pop up menu and press ENT on the GCU Verify GPWS INH is displayed on PFD 1 and PFD 2 8 Press the GCU MENU button again and select Enable GPWS from the pop up menu and press ENT on the GCU Verify the GPWS INH annunciation on the PFDs has extinguished 9 Press the GCU MENU button again and select Flap Override from the pop up menu and press ENT on the GCU Verify FLAP OVR is displayed on PFD 1 and PFD 2 10 Press the GCU MENU button again and select Disable Flap Override from the pop up menu and press ENT on the GCU Verify the FLAP OVR annunciation on the PFDs has extinguished 11 With a GPS position acquired shield or disc
156. NFIRMATION ssssseeecceeeecaeseeeeeeeees 3 33 3 20 ESP SUPPORT WITH AOA OPTION CONFIGURATION ssssccccceccesssesecccceeceeeeseseeecceeeeaaeeeees 3 34 321 ESP SUPPORT NO AOA OPTION CONFIGURATION ssssseccccecceeesssecccceeceseesseecceeeesaeansees 3 35 3 22 GDL 59 WI FI DATA LINK OPTION CONFIGURATION c ssssseeccceeeeeeeeeseeecceeeeeaaaeeeeccceeeeaaas 3 36 3 23 GSR 56 SATELLITE RECIEVER OPTION CONFIGURATION ccccccnnnnnnnnnnnononncnnnnnnnnanonnnnnnnnnnnonanoos 3 37 3 24 POTS HANDSET CONFIGURATION rannan nA E E mane 3 38 3 25 GSM 85A SERVO MOUNT CONFIGURATION nic 3 38 3 26 GSM 86 SERVO MOUNT CONFIGURATION ccccsccceeeececeeceeeeccceeeeeeeeeeceeeceeececeeseseesseeeseeeeseeeas 3 39 3 27 VERIFICATION OF SERVO MOUNT CONFIGURATION 0scccccessseecceeeeesecccceeeeeeceeseeeeeeceseeeeees 3 40 3 28 PLITECHARTS CONFIGURATION id 3 41 3 29 CHARTY W ENABUE aptas laa 3 41 3 30 LAWS DB ENABLE R 3 42 3 31 LAW SAA ENADE A o os 3 43 3 32 SUPPLEMENTAL DATABASE LOADING la aere Sennen 3 44 3 33 DVS PATHWAYS ENABLE tai 3 45 3 34 ESP ENABLE ai ccoaenree ce nosoecioa nate taannabc a tate taaapel te dabane sa a a Aa 3 46 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 190 00915 01 Revision 6 3 35 AIRCRAFT REGISTRATION NUMBER ENTRY csscccssccesscccssccescceesccessccessceesccessccessscesseessees 3 47 3 36 SPLASH SCREEN LOADING srta ia 3 48 3 37 NAVIGATION DATABASE LOLDN Sd aii 3 49 3 3
157. NGE knob to the left and verify the pointer moves to the left Move the pointer up right and down and verify that the pointer moves accordingly E a Se E Press the RANGE knob to stop displaying the pointer 10 Press the left and right arrowheads of the SOFTKEY SELECT keys Verify softkeys highlighting on the MFD changes 11 Press the SEL key to select one of the softkeys 12 Press the gt key to display the DIRECT TO page 13 Use the keypad to type KIXD and verify KIXD is displayed on the MFD 14 Press the SPC key to add a space and then the BACK key to delete the space 15 Press the CLR key to clear the field 16 Type K34 and then press the ENTER key twice Verify that the flight path to K34 is displayed on the map 17 Press the FPL key to open the ACTIVE FLIGHT PLAN page Press the FPL key again to close it 18 Press the PROC key to open the PROCEDURES page Press the PROC key again to close it 19 Press the MENU key to open the MENU page Press the MENU key again to close it 20 Press the COMM keyuntil 1 is lit Verify the tuning box is present around the COMM 1 frequency on PFD1 21 Using GCU477 keypad enter in a frequency of 123 450 Verify COMM1 frequency changes as entered 22 Press the COMM keyuntil 2 is lit Verify the tuning box is present around the COMM 2 frequency on PFD1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 27 190 00915 01 Revision 6 23 Using GCU477 key
158. OECO Ra A dd 4 34 5 TROUBLESHOO TIN God 5 1 Sci GIO ALERTING SY STE Mt tdi 5 2 Sel SYSTEM ANNUNCIATION S erea NAN 5 4 5 3 20O B 200 SPECIFIC ATR Sarn A eRe A EN O OA Sr 5 25 So AWS TROUBLESHOOTING conien a a aa a aa I 5 26 5 5 SYNTHETIC VISION AND PATHWAYS TROUBLESHOOTING cccccsecccsscccscccescceesccessceuseceuscees 5 27 0 GEC JOC APCS TROUBLESHOOTING visgssiecedicts cite cietr acess A alemaudonaedet 5 30 5 7 BACKUP COMMUNICATIONS PATH CHECKS cortada 5 43 58 GDU OAK TROUBLE SHOOTIN Gn dd 5 44 DE CGODROASA TER DSi 5 46 5 10 LAOS TROUDE SHOOTIN eirinen as 5 54 5 11 GAC ACERT MESSAGE S curia ia 5 56 5 12 GEA TROUBLESHOO TN EEEE TE iia 5 63 5 13 GLA FROUBLESHOOLIN erren n O E ee 5 64 5 14 COE G9 AST ROUBLESHOO TNG N AN NNN 5 65 das GRS 77 6MU 44 TROUBLESHOO TNG tan a 5 67 5 16 GDC 748 TROUBLESHOOTING tai lolas 5 74 5 17 GWX 608 TROUBLESHOO LING ii taa 5 75 5 18 GMC TIOTROUBLE SHOOTIN Sat aio 5 76 5 19 GOW ATT TROUBLESHOOTING essere tales a i EENS 5 77 5 20 SOFTWARE CONFIGURATION TROUBLESHOOTING cscccccssccccsscccesscccesccceescceueceeueceesuecens 5 78 S2 BACKSHELL BACKPLATE CONNECTORS onena lic 5 80 5 22 STANDBY ATTITUDE INDICATOR TROUBLESHOOTING ccccccsssccsscccssccesccessseesccesscceseseues 5 85 5 23 STANDBY AIRSPEED INDICATOR TROUBLESHOOTING cccccscccsssccescccesccessccescceuscceesceeseseues 5 85 5 24 STANDBY ALTIMETER TROUBLESHOOTING ccccccscccsscccssccessccessccescceuscceessc
159. ONICS MASTER PWR and BATT switches to ON 2 Pull the MFD PFD1 PRI PFD1 SEC and PFD2 circuit breakers 3 Press and hold the ENT key on PFD2 co pilot while applying power using the PFD2 circuit breaker 4 Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner of PFD2 5 Press and hold the far right softkey on the MFD while applying power using the MFD circuit breaker Note that the ENT key on the GCU 477 MFD controller may be used after initial software loads 6 Release the softkey after INITIALIZING SYSTEM appears in the upper left corner of the MED 7 Press and hold the ENT key on PFD 1 pilot while applying power using the PFD1 PRI and PFD1 SEC circuit breakers 8 Release the ENT key after INITIALIZING SYSTEM appears in the upper left corner of PFD1 CAUTION The Configuration Mode contains certain pages and settings that are critical to aircraft operation and safety These pages are protected and cannot be modified unless the technician is properly authorized and equipped However most protected pages are viewable to allow system awareness for troubleshooting NOTE If the specific procedure requires an SD card to be in the top slot of the PFD MFD this card must be inserted prior to applying power to the PFD MFD Any time a card 1s inserted the power to the PFD MFD must be cycled NOTE For a complete description and breakdown of each Configuration Mode page re
160. OT USE SOLVENTS TO CLEAN THE OUTPUT GEAR 3 Using a brush or other applicator apply a thin coat of Aeroshell 33MS Lithitum complex based grease to the servo output gear Figure 6 1 Servo Gear 4 Carefully place the servo into the servo gearbox ensuring proper orientation and alignment 5 Fasten the servo to the servo gearbox using the existing hardware Follow the installation instructions provided in the respective servo installation drawing s listed in Table 1 2 6 Inspect the harness connectors and check that no pins are bent or otherwise damaged Connect the harness and secure it appropriately 7 Tfno further maintenance is required continue to Section 7 9 Page 6 6 Gl1000 GFC700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 12 GSM 85A 86 Servo Gearbox Removal 1 Remove the desired servo s per Section 6 11 2 For the Roll Pitch and Yaw Servos remove the servo bridle cables from the control cable clamps For the Pitch Trim Servo disconnect the servo cable at the forward turnbuckle and aft terminal 3 Use a socket or open wrench to loosen and remove the servo attachment bolts 4 Carefully remove the servo gearbox es 5 Remove the cable retention pins and ring or cover and then remove the servo cable from the capstan Reinstallation 1 Ensure cable retention pins are oriented correctly Follow the installation instructions provided in the respective servo installation drawing s
161. QOOOUOSOO Sl sas DIAL Figure 7 19 AUX TELEPHONE page Page 7 66 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 8 System Return to Service Procedure After reinstalling any G1000 LRU verify the correct LRU software part numbers and versions against the numbers listed on the General Arrangement drawing listed in Table 1 2 To check an LRU software part number and or version follow the procedure defined in Section 3 9 3 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 1 190 00915 01 Revision 6 8 1 Backup Path System Testing This final checkout tests various secondary communications paths to ensure that the paths function correctly Perform the following steps and verify the results of each test Before starting create a simple Direct To flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position Verify that the phase of flight displayed on the GPS CDI is ENR 8 1 1 GPS Failure Test Step DesiredResult Single GPS Failure Condition Ensure GPS satellites are acquired Place a shroud over the GPS antenna for GIA 1 to prevent signal reception Verify loss of signal on MFD AUX page 4 Check for desired results Remove shroud from the GIA 1 GPS antenna and allow system to re acquire satellites Place a shroud over the GPS antenna for GIA 2 to prevent signal reception Verify loss of signal on M
162. RP CODE CHNG Check the connector strap inputs to the unit MET STUCK SWTCH Check the MET switch inputs into the system MET STATUS DIF Check the MET switch inputs into the system Page 5 40 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 6 3 2 Downloading GIA and GSA Maintenance Logs If additional assistance is needed troubleshooting autopilot faults the Maintenance logs can be downloaded to an SD card as a text file txt and emailed to Garmin Aviation Product Support Please call Garmin Aviation Product Support before you send a Maintenance Log to notify them you are sending it to prevent a delay in response You may download multiple GIA and GSA Maintenance Logs to the same file however in your email to Garmin you must furnish the order in which they were downloaded i e GIA 1 then GIA2 then SRVO PTCH MON then SRVO PTCH CTL etc 1 Insert a FAT 32 formatted SD card into the top slot of the PFD before turning on the displays 2 Power up PFD1 PFD2 and MFD in the configuration mode 3 On the PFD1 in the System page group use the small FMS knob to scroll to the Diagnostics Terminal page 4 Press the LG2CRD softkey at the bottom of the PFD 1 Verify that the softkey text grays out This indicates the recording function is active and all text that is displayed in the OUTPUT window will be saved to the card 5 Enable the cursor by pressing the FMS knob select GIA1 in
163. RS 77 configuration module wiring for damage Check GRS 77 connector for bent pins v If no damage can be found replace GRS 77 configuration module v If problem persists replace the GRS 77 Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Ensure the four GRS 77 mounting screws are tight Finger tight is not sufficient a screwdriver must be used to verify Ensure mounting rack and airframe shelf are secure and all hardware and brackets are present CAUTION do not loosen the mounting rack Attitude appears unstable hardware to the airframe shelf or the aircraft will need to be re leveled and the PITCH ROLL OFFSET procedure performed Ensure GRS 77 connector is securely fastened and proper strain relief is provided Remove GRS 77 connector and verify there are no bent pins Replace the GRS 77 Contact Garmin for further troubleshooting if required G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 67 190 00915 01 Revision 6 5 15 2 GRS Alerts Failure Message Cause Solutions S MANIFEST GRS1 software mismatch Communication l halted The system has detected an Load correct software version See incorrect software version loaded Section 3 9 for the Software Load MANIFEST GRS2 software in the specified GRS 77 Procedure mismatch Communication halted AHRS1 SERVICE AHRS1 magnetic field model needs The A
164. S service Return unit for repair o Check wiring between GIA s and inoperative The specified GTX 33 is not GTX XPDR2 FAIL XPDR 2 is responding Page 5 64 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 14 GDL 69A Troubleshooting 5 14 1 GDL 69A Common Problems Symptom Recommended Action No XM audio is heard No XM weather information is displayed Ensure the following items are not preventing the audio panel from distributing XM audio reference applicable G1000 Pilot s Guide v Verify the XM volume is not muted on the AUX XM RADIO page on the MFD Verify the COM squelch is not open Verify the ICS squelch is not open Verify the marker beacon tones are not being received Verify the headphone if equipped volume is turned up Go to the AUX SYSTEM STATUS page on the MFD and ensure unit is online v If ared X is present verify the unit is receiving power at the rack connector Ensure there are no GDL alerts in the alert window If there is an Alert for software or configuration error or mismatch reload the file noted in the Alert Restart the PFD s and MFD in configuration mode and go to the GDL page v Verify unit is active v Verify the Signal number is 2 or 3 If it is 0 or 1 check the GDL 69 69A antenna and cabling for faults v Reseat the GDL 69 69A to verify the coax connector is fully seated If u
165. SYSTEM DESCRIPTION 2 1 Equipment Descriptions 2 1 1 GDU 1040A PFD 2 amp GDU 1500 MFD Two Garmin GDU 1040A displays and one GDU 1500 display are installed in the King Air instrument panel The GDU 1040A units 10 4 inch LCD displays with 1024x768 resolution are configured as PFD 1 and PFD 2 the GDU 1500 unit a 15 inch LCD display with 1024x768 resolution is configured as a MFD All displays provide control and display of nearly all functions of the G1000 integrated cockpit system The PFD displays are located on either side of the MFD with the stand by instruments located between the Pilot s PFD PFD 1 and the MFD GMA 1347D Audio Panels are located outboard of each PFD Additionally a GMC 710 AFCS Controller is located in the upper instrument panel above the MFD and a GCU 477 is installed in the pedestal The GCU 477 provides the control interface for the MFD The GDU 1500 communicates with the GDU 1040A units GDL 69A datalink GW X68 weather radar optional GDL59 wi fi datalink and optional GTS 8XX traffic through a high speed data bus HSDB Ethernet connection The GDU 1500 communicates with the GCU 477 via RS 232 digital interface The GDU 1040A units communicate with each other and the GIA 63W units through a high speed data bus HSDB Ethernet connection PFD receives primary electrical power from the new Essential Bus and secondary electrical power from Dual Fed Bus No 1 PFD 2 receives electrical power from Dual Fed Bus No
166. System Status System Upload 9 System Data Path Configuration 2 Time Configuration Diagnostics Terminal 10 System Setup 3 Lighting Configuration OEM Diagnostics 11 Manifest Configuration 4 System Audio System Configuration 12 Maintenance Log GDU Page Group 1 Serial Configuration 4 Diagnostics 7 Alert Configuration 2 CDU Status Page 5 Ethernet Test 8 Airframe Configuration 3 Key Test 6 Video Test 9 TAWS Configuration GIA Page Group 1 Serial Configuration 3 GIA I O Configuration 5 GIA Status Page 2 GIA RS 485 Configuration 4 GIA COM Setup 6 GIA CAN Configuration GEA Page Group 1 Engine Configuration 2 GEA Status Page 3 GEA Configuration GTX Page Group 1 Serial Configuration 2 Transponder Configuration GRS Page Group 1 Inputs Configuration 2 GRS GMU Calibration ADC Page Group 1 ADC Configuration 2 GDC Configuration GFC Page Group 1 GFC Configuration 2 GFC Status GMA Page Group 1 GMA Configuration GDL Page Group 1 GDL 69 Configuration 3 GDL 59 Configuration 5 GSR 56 Configuration 2 GDL 59 Status 4 GDL 59 Report Configuration RMT Page Group 1 Remote Controller Status GWX Page Group 1 GWX Configuration GTS Page Group 1 GTS Configuration OTHER Page Group 1 Stormscope CAL Page Group 1 Fuel Tank Calibration 2 Flaps amp Trim Calibration 3 HSCM Calibration Appears only if option is installed Page 3 10 G1000 GFC 700 System Maintenance Manual 200 B
167. THE SPLASH SCREEN NO WILL BE ASSUMED IN 30 SECONDS 8 Press the softkey labeled NO Note that the splash screen will need to be loaded after all software and configuration loading is completed 9 When complete the display starts in configuration mode displaying the System Status page Do not remove power 10 Remove the Loader Card from the display and insert 1t into the top card slot on another display 1f desired Repeat Steps 3 through 8 as needed IMPORTANT For the rest of the software configuration procedure do not operate the MFD or PFD 2 while loading software or configuration files unless specifically instructed to do so A failed or cancelled load may result G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 19 190 00915 01 Revision 6 3 9 2 G1000 System Software Upload The System Upload page allows a technician to load LRU software and system configuration files individually or in an automated sequence Depending on what maintenance is performed software and or configuration files may need to be reloaded to LRUs Follow the steps below as a guide to use the System Upload page The figures contained in the following sections represent software version 0985 04 and later Earlier software versions are similar IMPORTANT Do not allow power to be removed from the system when loading software Remove power only when instructed by the following procedure As a general rule all displays should
168. U Alerts If flying near large radio towers or other sources of possible electromagnetic interference the condition should correct itself as the aircraft leaves the area If problem persists run magnetic interference check in Section 5 15 4 to check for magnetic interference in the aircraft Failure Message Cause Solutions S MANIFEST GMU1 software mismatch Communication halted MANIFEST GMU2 software mismatch Communication halted HDG FAULT AHRS1 magnetometer fault has occurred HDG FAULT AHRS2 magnetometer fault has occurred The system has detected an incorrect software version loaded in the specified GMU 44 A fault has occurred in the specified magnetometer heading will be flagged invalid G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Load the correct software version See Section 3 9 for the Software Load Procedure Check GMU 44 GRS 77 interconnect for faults v Replace GMU 44 v If problem persists replace GRS 77 Page 5 69 Revision 6 5 15 4 Calibration Procedure E Magnetometer Interference Test A magnetometer interference test is available for troubleshooting and or verifying a magnetically clean installation of the GMU 44 This test exercises various devices on the aircraft that could potentially affect the magnetic field as measured by the GMU 44 NOTE This test is used to validate that no electronic device interfer
169. UP on the vane until the stall warning horn sounds Record the flaps extended Pot 2 TG value Return the force on the vane to 0 TG and remove the force applicator from the aircraft G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 13 Place the BATT master switch to the OFF position 14 Remove external power to the aircraft 15 Remove the breakout box from the aircraft 16 Reinstall the potentiometer access cover plate on the lift computer 7 24 2 Calibration of the C 05606 1 Lift Computer NOTE For calibration of the stall warning points reference King Air 200 Series Maintenance Manual listed in Table 1 2 section 27 31 00 The procedures listed here are provided to augment the King Air 200 Series Maintenance Manual and allow the installer to adjust the stall warning points Pots 0 1 and 2 and LAA output Pots 3 4 and 5 simultaneously to save setup time 1 Connect the SK100360 breakout box between the Safe Flight P N C 05606 1 lift computer and the mating aircraft harness see Figure 7 15 2 Make sure the stall warning heater system is turned OFF 3 Remove the potentiometer access cover plate from the lift computer 4 Simulate an in flight condition as follows Bypass the landing gear safety switch by connecting an electrical ground to TP7 of the breakout box This is best accomplished by placing a jumper between TP2 and TP7 of the breakout box CAUTION The anchor tab of the force ap
170. W POWER INV Check unit power MON SOL PWR ON FAIL Check unit power and AP Disconnect power Normal Mode Faults Page 5 38 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Control Processor The control processor contains the logs that are found in these processors 3 Pitch Servo 5 Roll Servo 7 Yaw 9 Pitch Trim Servo There are two main groupings of faults that can occur in the control processor The first grouping of faults can occur during the GSA unit pre flight test PFT If there is a fault during PFT the unit will not be able to transition to normal mode and the only way to clear this state would be to cycle unit power The second grouping of faults can occur during normal mode These faults generally cause a disconnect of power to the GSA and report that a fault has occurred to the GIA The Notes column indicates any actions that can be taken to troubleshoot the problem in the aircraft by the technician Any faults that are not listed here indicate an internal problem requiring replacement of the servo If the items in the Notes column check out ok replace the servo PFT Faults CONTROL PFT STEP NOTES INT COMM TEST FAIL This can sometimes be a result of a failure on the other board check faults on other processor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 39 190 00915 01 Revision 6 Normal Mode Faults ST
171. W s Reinstalled No software or configuration loading is required if the removed GIA is re installed in its original position GIA1 and GIA2 in their original racks This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the return to service checks in Section 8 Original GIA 63Ws Swapped for Troubleshooting No software loading is required if the originally installed GIA units are re installed in opposite positions GIAI and GIA2 in opposite unit racks However configuration loading is required See Section 3 9 and then continue to the GIA 63W Test Section 7 3 1 New Repaired or Exchange GIA 63W s Installed If a new repaired or exchange GIA 63 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GIA 63W Test Section 7 3 1 7 3 1 GIA 63W Test GPS Signal Acquisition UFOH POHI 1100 f y x100 To o i A gt f P n T J AEIR 4 i Pi i 15 AS lt gt 15 gt e A f TIHE in 7 P 4 w D F prop y ALTITUDE RPH 3 1111 ROUND APFFD 0 xinn sF TRACK T fi ao 80 A a maaana a TURB 100 C o TURB ur z RPH z RPM ATT 2 Ar 2 sA A FFL OM 4 PPH amp 020 028 20 020 020 020 028 624 122 135 Figure 7 3 AUX GPS STATUS Page MFD The GIA 63W units should normally acquire a GPS navi
172. WS were previously installed these must be reactivated See Sections 3 29 and 3 30 respectively If any other options were previously installed these must also be reactivated per Section 3 9 Then continue to the PFD MFD Test procedure G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 1 190 00915 01 Revision 6 7 1 1 PFD MFD Test 1 Allow displays to initialize for 1 minute Check that all COM NAV display fields are valid in the top corners of both PFDs Check that attitude heading altitude airspeed vertical speed and OAT fields are valid within 2 minutes of power up on both PFDs 4 Press the SENSOR softkey on each PFD and switch between ADC1 and ADC2 Verify that data from both GDC 74Bs is valid on both displays W N N Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2 Verify that data from both GRS 77s is valid on both displays 6 Check that the engine instrument fields are valid on the MFD 7 Push the red DISPLAY BACKUP button on the pilot side GMA 1347D Verify that the pilot side PFD and MFD displays enter reversion mode MFD should have valid altitude airspeed vertical speed COMM1 COMM2 NAV1 NAV2 and engine instruments 8 De activate pilot side reversion mode by pushing the DISPLAY BACKUP button Verify PFD 1 and MFD return to normal display modes 9 Repeat Step 1 using GMA2 Ensure that PFD 2 and MFD enter reversion mode and MFD displays valid altitude
173. _ the harness connector assembly as well as the integrity of the individual shields and their attachment PFD and MFD Fans Inspect fans for accumulation of dirt and other damage Remove excess dirt as Qty 3 required a Inspect the GDL 69A unit rack and connectors for corrosion or other defects Check GDL 69A the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment a Inspect the GMC 710 unit including face of the unit mount and connectors for GMC 710 corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Signal Conditioner a Inspect the signal conditioner unit mount and connectors for corrosion or other Qty 2 defects a Inspect the standby attitude indicator unit including face of unit and connector for Standby Attitude corrosion or other defects Check the integrity of the harness connector assembly in Indicator accordance with AC 43 13 1B Chapter 11 Section 8 Paragraphs 11 96 and 11 100 and the Cabin Wire Harness Routing drawing listed in Table 1 2 a Inspect the standby airspeed indicator unit including face of unit and connector for Standby Airspeed corrosion or other defects nogator b Visually inspect the plumbing and harness connector assembly and ensure it is secure an
174. ace if necessary If issue continues replace PFD1 master configuration PED 1 CONFIG PED 1 A configuration mismatch has module configuration error Config service OCCurred between the display and If problem persists replace the req d the Master Configuration Module display NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The PFD ee ne A G1000 System ID number will change to anew number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number configuration error Config service req d G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 47 190 00915 01 Revision 6 5 9 2 Database Alerts Failure Message Cause Solution S MFD1 DB ERR MFD1 aviation database error exists p Reload aviation database into PFD 1 DB ERR PFD 1 aviation Pe MFD or specified PFD has the display database enoras encountered an error in the l l Jeppesen aviation database Contact Garmin Technical PFD 2 DB ERR PFD 2 aviation Support for assistance MFD1 DB ERR MFD1 terrain database error exists The MFD has encountered an error in the terrain database Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard
175. age 3 23 Revision 6 3 10 TAWS A Support Configuration This section applies only to installations with the TAWS A option The procedures outlined in this section must be followed to load the necessary configuration files required to enable TAWS A gear and flap messages A TAWS A enable card is also required for this option see Section 3 31 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD 1 3 Rotate the small FMS knob to select FAWS A Support Press ENT key on PFD1 4 Verify the TAWS A Support is displayed in the Item window Press LOAD CONFIGURATION ID E168669 SYSTEM UPLOAD kins Ar LRU VERS CARD VERS CARD PART NUH SOFTHARE CONFIGURATION N A El Figure 3 21 TAWS A Support Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for ALERTS e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 11 TAWS A Voice No Callout Option Configuration This section applies only to in
176. ages 28 On the GMC 710 couple the Flight Director to the right side by pressing the XFR button The arrow that is illuminated indicates which side is coupled No flight director modes should be active at this time NOTE On power up the coupled side will default to the left side Each time power is reapplied couple back to the right side and continue test steps 29 Repeat step 1 thru 27 while coupled to right side 30 Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to OFF 31 Wait 1 minute before re applying power for further testing as required Page 7 60 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 26 GTS 8XX Traffic System Functional Check Perform the following tests to verify GTS 8XX operational and surveillance functions Use a ramp tester such as a TIC TR220 or equivalent to perform the tests To perform these tests the aircraft must be on the ground and the GTS 8XX must be in Ground Test mode On the MAP TRAFFIC MAP page of the MFD press the softkey sequence 3 4 4 3 The GND TEST softkey will appear Press the GND TEST softkey to activate Ground Test mode This simulates the GTS 8XX to be airborne at 50 000 feet with a magnetic heading of 0 degrees To exit the Ground Test mode press the GND TEST softkey again COTE SEC MAP TRAFFIC MAP __ STANDBY pa A NORMAL e STANDBY MAP Ogooo
177. ailed If problem persists replace master configuration module check config module harness for faults and replace if necessary GDL69 CONFIG GDL 69 configuration error Config service req d The G1000 has detected a GDL NOTE 69A configuration mismatch New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to anew number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number MANIFEST GDL software The system has detected an e Load correct software version mismatch Communication incorrect software version loaded See Section 3 9 for the halted in the GDL 69A Software Load Procedure Page 5 66 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 15 GRS 77 GMU 44 Troubleshooting 5 15 1 AHRS Common Problems Symptom Recommended Action Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin Ensure GPS has acquired at least four satellites has a 3D navigation solution and a DOP of less than 5 0 This is particularly important if this issue appears during ground operation only AHRS does not complete initialization Calibrate the GRS 77 Check G
178. ailure Message Cause Solutions S e Load GWX configuration files e Replace GWX e f problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE GWX CONFIG GWX configuration The G1000 has detected a New Terrain Obstacle cards error Configuration service GWX 68 configuration Jeppesen Aviation Database and required mismatch other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number e Check Ethernet connection The G1000 has detected a between the GWX and GDL69A failure in the GWX 68 for faults e Replace the GWX 68 GWX SERVICE Needs service The G1000 has detected a os SUS Return unit for repair failure in GWX 68 eplace The system has detected an e Load correct software version See MANIFEST GWX software incorrect software version Section 3 9 for the Software Load loaded in the GWX 68 Procedure GWX FAIL GWX is inoperative mismatch Communication halted G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 75 190 00915 01 Revision 6 5 18 GMC 710 Troubleshooting 5 18 1 GMC 710 Alerts and Problems Failure Message Cause Solutions S Loa
179. al GMA 1347D 2 o Replace original GMA 1347D 2 if box turns green CHNL 7 e ft i it 1347D 2 after swapping units Swap GIA2 and GIA1 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after swapping units Check the GIA1 GMA 1347D 2 interconnect wiring for faults Amber GIA1 GMA 1347D 2 data path functionality is unknown Reload GIA2 configuration files Page 5 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 GIA2 ARINC 429 GIA2 GDC 74 2 data path is not functioning correctly e Load GIA2 and GDC 74 2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 IN 5 GDC 74 2 o Replace original GIA2 if box turns green after swapping units e Check the GIA2 GDC 74 2 interconnect wiring for faults Replace GDC 74 2 if problem remains Amber GIA2 GDC 74 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GRS 77 2 data path is functioning correctly GIA2 GRS 77 2 data path is not functioning correctly e Load GIA2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after IN 6 GRS 77 2 swapping units Swap GRS2 and GRS no reconfiguration requi
180. al shields and their attachment G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 13 190 00915 01 Revision 6 Table 4 8 Rear Fuselage and Empennage Visual Inspection Procedure Litem __ Description Procedure _ Initials _ Witi Antenna Inspect the external wi fi antenna if installed for leading edge erosion and condition of base seals To gain access for the following Inspections refer to the servo installation drawings and the King Air 200 Series Maintenance Manual listed in Table 1 2 Inspect all exposed wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Tail Wire Harness Routing Tail Wiring Harness drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing Verify security of aft bulkhead connectors Using a flashlight inspect the servos servo gearboxes connectors support structure and control cables to ensure that no corrosion chaffing cracks or other defects exist If GSM 86 servo gearboxes are installed check that the retaining bolt for the slip clutch cartridge is not damaged or loose Have an assistant manually move the control surfaces and elevator trim wheel from stop to stop and visually observe the corresponding servo and control cabling Ensure there is no binding in the control cabling and that the capstan rotates freely GFC 700 Equ
181. alibration Criteria The following calibration procedures are provided for the GRS 77 and GMU 44 e Pitch Roll Offset Procedure Al PROVIDED IN SECTION 7 7 2 e Magnetometer Calibration Procedure B PROVIDED IN SECTION 7 7 4 e Engine Run Up Vibration Test Procedure D PROVIDED IN SECTION 7 7 5 e Magnetometer Interference Test Procedure E PROVIDED IN SECTION 5 15 4 When ready to perform the procedures shut the PFDs and MFD off by pulling the PFD and MFD circuit breakers Restart all displays in configuration mode Follow the steps given for each procedure on screen at the GRS GMU CALIBRATION page Note that the CALIBRATE command cannot be selected and activated until the installer acknowledges all required steps have been carried out by pressing the ENT key on each step Table 7 7 Required GRS GMU Calibrations Calibrations Required Procedure A1 Procedure B Procedure D wae GRS 77 GRS GMU Engine Run up ESO non Pitch Roll Magnetic Vibration Offset Calibration Test Either GMU 44 was removed and None Required reinstalled no change in serial number Continue to GRS GMU Test section GMU 44 was replaced with new unit New serial number GRS 77 AHRS was removed and or replaced The mounting tray was NOT None Required removed and the mounting tray bolts were Continue to GRS GMU Test section NOT loosened GRS 77 AHRS was removed and or replaced The mounting tray WAS removed and or mounting tray bolts WERE loosened X X
182. ance Manual 200 B200 Series King Air 190 00915 01 3 28 FliteCharts Configuration If ChartView has previously been enabled and is no longer desired follow the procedures outlined in this section to return the G1000 system to the basic FliteChart functions If ChartView has not been enabled the following procedure is not required Loading of the baseline configuration for the specific airframe 1s required for enabling FliteChart functions Reload the baseline configuration and all applicable options as described in Section 3 9 Reloading the baseline configuration disables all previously enabled options 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 7 16 FliteChart Functional Checks 3 29 ChartView Enable Follow this procedure to activate the ChartView option A ChartView Enable Card as specified in 005 00421 03 General Arrangement Drawing King Air 200 B200 will be required for this procedure NOTE 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 7 17 ChartView Functional Checks
183. ance Manual 200 B200 Series King Air Page 5 63 190 00915 01 Revision 6 5 13 GTX Troubleshooting 5 13 1 GTX Alerts Failure Message Cause Solutions S MANIFEST GTX1 software mismatch Communication a O E RIE halted e system has detected an incorrect software version loaded Reload software See Section 3 9 MANIFEST GTX2 software in the specified GTX 33 for the Software Load Procedure mismatch Communication halted XPDR1 CONFIG XPDR1 Perform a SET gt ACTV configuration error Config service configuration reset on the GTX req d Config page and verify the aircraft registration is present If error is still present reload config files from a loader card v If problem persists replace master configuration module check config module harness for faults and replace if The system has detected a Necessary configuration mismatch for the NOTE XPDR2 CONFIG XPDR2 specified GTX 33 configuration error Config service New Terrain Obstacle cards Jeppesen req d Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to anew number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number service Return unit for repair The G1000 has detected a failure Soares in the specified GTX 33 ASA
184. ard If an inequality between the LRU VERS and CARD VERS columns is detected the SOFTWARE and CONFIGURATION boxes will be pre selected checked for each LRU reporting a different software version than the one on the card The following softkeys provide an easy way to select files CHK ALL Selects all files both configuration and software CHK SW Selects all SW files only CHK CFG Selects all configuration files only CLR ALL Clears all selections LOAD Starts the software loading process NOTE When loading a new software image or re loading software to a particular LRU it may not be necessary to reload all software and configuration files The technician should be sure of the software requirements and load the appropriate files including any options If there is any doubt the CHK ALL softkey is recommended 5 After verifying that the desired software and configuration files are checked press the LOAD softkey The G1000 system automatically begins loading software and default configuration files to the selected LRUs in the proper order LRU VERS CARD VERS CARD PART NUM SOFTHARE CONFIGURATION N A MANIFEST N A AIRFRAME N A AIRFRAME PROP N A AIRFRAME ENGINE N A ALERTS N A N A N A N A T5 80bd 006 B0544 2V ud A A Y f f Y f Y A A Figure 3 19 Configuration Software Load Page 6 Press the LOAD softkey 7 Observe software loading progress and verify software load completes without errors as indicated
185. as follows 1 Make sure the dial indicator reads negative when the plunger is pressed and positive when the plunger is free 2 Place the gauging assembly on a flat surface gauge block or equivalent 3 Ensure the smaller needle is at approximately 1 4 Rotate the dial indicator to set the large needle at 0 as shown in Figure 7 10 DIAL INDICATOR AS a ie B ee ka ES 1 S ha O oe ore 40 Y ES e Lo 2 OSS ve MS Mee ff 2 SR 20 A a Z T ENF Figure 7 10 Dial Indicator The static port measurements are obtained at four locations on each static port as shown in Figure 7 12 These measurements are used to find an AVERAGE and ANGLE for each of the four static ports The AVERAGE is calculated by adding the four measurements and dividing the total by 4 The ANGLE is calculated by subtracting the minimum measurement from the maximum measurement The calculated AVERAGE and ANGLE for each static port must fall within the ranges shown in Figure 7 13 Perform the static port measurement as follows 1 Wipe the surface of static ports clean with isopropyl alcohol 2 Place the gauging assembly onto the static port surface as shown in Figure 7 11 DIAL INDICATOR Se GAGING ASSEMBLY ES w STATIC PORT FUSELAGE SKIN JH oN PE 7 Z Figure 7 11 Static Port Measurement G1000 GFC 700 Sys
186. ation gain cgn file PFT step 3 System initialization verify selected side This step is checking to make sure the PFD1 is online and sending the selected AFCS side data over HSDB to GIA1 If this step fails then make sure the PFD is powered up and there is an Ethernet connection from the PFD to the GIA PFT step 4 System initialization verify AHRS monitor This step is checking to make sure the AHRS monitor is valid and not reporting an AHRS failure NOTE AHRS monitor will be assumed valid if on the ground If this step fails then make sure the AHRS and ADC is powered up and sending valid attitude data to the G1000 Page 5 34 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 PFT step 5 System initialization verify servo PFT is complete This step is checking to make sure that all servos have completed their own PFT This does not check whether the servo PFT passed or failed It verifies that the servo PFT is no longer in progress PFT step 6 Verify cross GIA is initialized This step is checking to make sure the other GIA 1s also on step 6 of its PFT If this step fails try cycling power on GIA 1 GIA2 and all servos If PFT still fails at step 6 then you will need to go check the PFT status of the other GIA and see what step it is failing it should be prior to step 6 NOTE The PFT status is communicated between GIA1 and GIA2 using HSDB As a result both the PFD and MFD must
187. ation mismatch By pressing the SET gt ACTV softkey this copies the SET column to the LRU unit s configuration memory The settings then become the ACTIVE settings for the LRU being configured Configuration Mismatch Master Configuration Module LRU Memory Master Configuration Module LRU Memory OUTPUT ACTIVE SET gt ACTV Softkey li i Configuration Correct Master Configuration Module LRU Memory Master Configuration Module LRU Memory OUTPUT ACTIVE Figure 3 10 SET gt ACTV Diagram Page 3 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 When troubleshooting the system technicians can look for inequalities between SET and ACTIVE columns Certain problems can be resolved simply by pressing the SET gt ACTYV softkey which reloads settings to the specific LRU from the PFD Note that this can also be accomplished by reloading the configuration files for the LRU Section 7 describes this process for each LRU A blank active column as shown in Figure 3 11 represents loss of communication between the display and the particular unit See Section 5 for more details on troubleshooting CHANNEL INPUT OUTPUT SET ACTIVE SET ACTIVE CHNL 1 GDC74 1 GDC74 1 CHNL 2 GIA DEBUG GIA DEBUG CHNL 3 OFF OFF CHNL 4 OFF OFF CHNL 5 GTX 33 1 w TIS GTX 33 1 u TIS CHNL 6 GRS77 1 GRS77 1 CHNL 7 GMA1347 1 GMA1347 1 CHNL 8 OFF OFF Figure 3 11 Loss of Communication 3
188. be in the same mode configuration or normal unless instructed otherwise 1 Ensure loader card is inserted into top card slot of PFD1 On PFD1 select the System Upload page using the PFD1 small FMS knob 2 Activate the cursor and use the PFD1 small FMS knob to highlight the GROUP field Scroll small FMS knob to select the appropriate airframe and engine combination Press the PFD1 ENT key to select the configuration Figure 3 17 Airframe Options 3 Once an airframe type is selected the cursor moves to the ITEM window Rotate the PFD1 small FMS knob to activate the drop down menu Move the cursor to highlight the appropriate propeller configuration for the aircraft and press ENT on PFD 1 NOTE Not all propellers are available for selection with each airframe and engine configuration Only those props that are approved for installation on a particular airframe engine are available in the drop down selection window Figure 3 18 Propeller Options 4 Once the propeller type is selected the cursor moves to the PRODUCT windo Select the software and or configuration which 1s to be loaded for each G1000 LRU Page 3 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 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 C
189. be powered for this state to pass PFT step 7 Verify servo type This step 1s checking to make sure the Servos are the correct type torque and speed If this step fails make sure the Servo configuration on the GFC configuration page matches the Servos installed in the aircraft PFT step 8 Verify servo first certification data This step is checking to make sure the servos have the same certification gains loaded in them as the GIAs have If this step fails reload the certification gains in GIA1 GIA2 and all servos PFT step 9 Verify servo second certification data This step is checking to make sure the servos have the same certification gains loaded in them as the GIAs have If this step fails reload the certification gains in GIA1 GIA2 and all servos PFT step 10 Updating servo RTC This step is setting the system time in the servos to by the same time as the GIA system time This step should never fail PFT step 11 Verify servo PFT status This step is checking to make sure the servos have all passed their own PFT If this step fails please proceed to servo PFT explanation below G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 35 190 00915 01 Revision 6 PFT step 12 Verify AP disconnect enabled This step is checking to make sure GIA1 GIA2 and all servos have are connected to a 28 volt AP disconnect If this step fails make sure the AP disconnect input to GIA1 GIA2 and all ser
190. be present on the right isolation bus W109 Verify that the GDL69 FAIL alert message is NOT shown on the PFD Operation of the GDL 69A verifies continuity of the right isolation limiter F132 By observing the following annunciators power to each of the four buses will be verified L FUEL PRESS R FUEL PRESS L BL AIR FAIL and R BL AIR FAIL If any of the annunciators fail to illuminate the associated limiter F148 F149 F150 or F154 one of the four dual bus feeder diodes CR2 or dual bus circuit breakers RH NO 1 RH NO 2 RH NO 3 or RH NO 4 is open If failure of an annunciator is apparent reset or replace the faulty component and repeat the test Units on the No avionics bus SHOULD NOT operate Verify COM 2 is not powered by observing a red X is displayed in COM 2 tuning window If COM 2 is powered at least one of the dual bus feeder diodes 1s shorted Detection of the shorted diode diodes may be accomplished by opening the following dual bus feeder circuit breakers LH NO 1 LH NO 2 LH NO 3 or LH NO 4 After replacement of the shorted diode diodes the test should be repeated Remove all electrical power from the airplane Reinstall the left isolation limiter F131 Remove the right isolation limiter F132 Apply external power Turn BATT and AVIONICS MASTER switches to ON position Bus voltage SHOULD be present on the left isolation bus W108 Units on the No 1 avionics bus SHOULD operate Verify COM 2 is powered
191. blem does not follow the unit check GPS antenna and cabling The system has detected a failure G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 59 190 00915 01 Revision 6 Failure Message Cause Solution S LOI GPS integrity lost Crosscheck with other NAVS GPS NAV LOST Loss of GPS navigation Insufficient satellites GPS NAV LOST Loss of GPS navigation Position error GPS NAV LOST Loss of GPS navigation GPS fail Page 5 60 Revision 6 If the primary receiver is a WAAS sensor the alert indicates that GPS position data has timed out There is no GPS position fix available or the system is in dead reckoning mode The G1000 has detected an internal position warning has occurred The G1000 has detected a GPS engine failure Verify the area the aircraft was traveling through did not have loss of GPS coverage FAA NOTAMs may be issued for periods of outages or the US Coast Guard website http www navcen uscg gov gps gps notices default htm will have notices posted Using the MFD AUX GPS Status page verify the signal strength bars are not erratic If so this indicates outside interference is affecting the GPS receivers Find and remove the source of interference i e cell phones FBO datalink antennas etc If GPS receivers can not aquire a position lock troubleshoot per the Will not acquire satellites section G1000 GFC 700 System Maint
192. by observing a frequency is displayed in COM 2 tuning window Operation of COM2 will verify continuity of the left isolation limiter F131 By observing the following annunciators power to each of the four buses will be verified L FUEL PRESS R FUEL PRESS L BL AIR FAIL and R BL AIR FAIL If any of the annunciators fail to illuminate the associated limiter F145 F146 F147 or F153 one of the four dual bus feeder diodes CR1 or dual bus circuit breakers RH NO 1 RH NO 2 RH NO 3 or RH NO 4 is open If failure of an annunciator is apparent reset or replace the faulty component and repeat the test The GDL 69A SHOULD NOT operate Verify that the GDL69 FAIL alert message IS shown on the PFD If the GDL 69A DOES operate at least one of the dual bus feeder diodes CR2 is shorted Detection of the shorted diode diodes may be accomplished by opening the following dual bus feeder circuit breakers LH NO 1 LH NO 2 LH NO 3 or LH NO 4 After replacement of the shorted diode diodes the test should be repeated Remove all electrical power from the airplane Reinstall the right isolation limiter F132 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 35 190 00915 01 Revision 6 This page intentionally left blank Page 4 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 TROUBLESHOOTING This section provides instructions and guidance for G1000 syste
193. by resetting the PFD1 PRI PFD1 SEC PFD2 and MFD circuit breakers 11 The standby navigation databases in PFD1 PFD2 and MFD are now updated 12 On the AUX SYSTEM STATUS page press the MFD1 DB softkey Scroll through all of the databases contained in the MFD and confirm that the correct databases are loaded 13 Press the MFD1 DB softkey again to toggle to PFD1 DB Scroll through all of the databases contained in the PFD1 and confirm that the correct databases are loaded 14 Press the PFD1 DB softkey again to toggle to PFD2 DB Scroll through all of the databases contained in the PFD2 and confirm that the correct databases are loaded Page 3 50 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 38 Configuration of Navigation Map for Traffic System l With the MFD in normal mode use the GCU FMS knob to select the Navigation Map page then press GCU MENU key to display the PAGE MENU Turn the small right knob to select or verify selected Map Setup and press the ENT key and verify TRAFFIC is selected ON Verify the flashing cursor highlights the GROUP field Turn the GCU small FMS knob to select Traffic and press ENT on GCU If not already selected use the GCU FMS knob to make the following selections e TRAFFIC MODE ALL TRAFFIC e TRAFFIC SMBL 300NM e TRAFFIC LBL 300NM Return to the Map Page by pressing the GCU FMS knob or momentarily pressing and holding the
194. commended that the Phase 3 and Phase 4 electrical bonding checks contained in section 4 5 are conducted after the Phase 3 and 4 visual inspections while access to these zones 1s still open Table 4 3 Nose Section Visual Inspection Procedure A item Description Procedure Initials _ Gain access via the Radome for the following Inspection Inspect the GWX 68 unit mount and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Inspect wire harness for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Nose Wire Harness Routing drawing listed in Table 1 2 Table 4 4 Nose Avionics Compartment Visual Inspection Procedure A Hem Description Procedure _ Initials _ Gain access via the Nose Equipment Compartment access panel for the following Inspection a Inspect the GRS 77 units racks and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GRS 77 Qty 2 a Inspect the GIA 63W units racks and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to the harness connector as
195. completed after one minute from when the initialization started the PFT will fail After the system PFT has passed it will be performed again if a servo resets if the autopilot servo breaker is reset or the cross side GIA restarts it Generally the PFT failure fault is logged in the GIA Maintenance Log and not in the Servo Maintenance Logs unless the GIA log fault identifies a servo problem NOTE Thoroughly understanding the operation of the G1000 system in Configuration mode is recommended before starting this procedure The GFC Status page may be used to check the status of the servos and engage them to aid in troubleshooting To access the GIA and GSA Maintenance Logs perform the following steps 1 Start the G1000 in Configuration mode 2 Use the FMS knob on PFD1 to go to the Diagnostics Terminal page in the System group This page allows the technician to view maintenance logs associated with the GFC 700 3 Choose GIA 1 or GIA 2 in the LRU window 4 Inthe SERVO window choose NONE to view the GIA Maintenance Log or choose a servo to view their logs 5 Using the FMS knob choose VIEW MAINTENANCE LOG in the COMMAND window 6 Press the ENT key 7 When the Maintenance Log data starts to display in the OUTPUT window you may see More press any key to continue at the bottom of the OUTPUT window This informs you there 1s more data to display and the system has paused allowing you to view
196. correctly PFD1 GRS 77 1 data path is not functioning correctly e Verify GRS77 1 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GRS troubleshooting sections o Swap GRS1 and GRS2 no reconfiguration required to confirm if the problem is in the original GRSI Replace original GRS1 if box turns green after swapping units Load PFD 1 configuration file IN 1 GRS 77 1 Swap PFD1 and PFD2 to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays Swap GRS1I and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the PFD1 GRS 77 1 interconnect wiring for faults nee PFD1 GRS 77 1 data path functionally is unknown Reload PFD1 configuration file PFD1 GDC 74 1 data path is functioning correctly PFD1 GDC 74 1 data path is not functioning correctly e Verify GDC 74 1 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GDC troubleshooting sections Load PFD1 and GDC 74 1 configuration files IN2 GDC 74 1 Swap PFD1 and PFD2 to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays e Check the PFD1 GDC 74 1 interconnect wiring for faults Replace GDC 74 1 1f problem re
197. ct GIA GIA2 SERVICE GIA2 needs in the specified GIA p P service Return unit for repair Replace GIA with a WAAS unit Page 5 62 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 12 GEA Troubleshooting 5 12 1 GEA Alerts Failure Message Cause Solution S MANIFEST GEA1 software mismatch Communication l halted The system has detected an Load the correct software verion See incorrect software version loaded Section 3 9 for GEA 71 Software Load MANIFEST GEA2 software in the specified GEA 71 Procedure mismatch Communication halted GEA1 CONFIG GEA1 e Load GEA configuration files See configuration error Config service Section 3 9 for GEA 71 req d Configuration Procedure If problem persists replace master configuration module check config module harness for faults and replace if necessary NOTE New Terrain Obstacle cards The system has detected a Jeppesen Aviation Database and configuration mismatch in the other optional features i e TAWS GEA1 CONFIG GEA2 specified GEA 71 unlock card will need to be configuration error Config service replaced if the master configuration req d module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number G1000 GFC 700 System Mainten
198. cted annunciator on GMA flashes once per second during PA address 9 Repeat Step 8 using pilot hand mic 10 Initiate passenger address using copilot s headset boom mic by keying the copilot s PTT Verify the following e Clear PA audio can be heard over cabin speaker and CABIN ICS headsets e PA selected annunciator on GMA flashes once per second during PA address 11 Repeat Step 10 using copilot hand mic G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 3 190 00915 01 Revision 6 Transceiver Operational Check Perform a ramp test radio check by exercising the installed transceivers microphone microphone key and audio over the headphones and speaker Verify that communications are clear and PTT operation 1s correct for each pilot position 1 On the pilot s audio panel select the audio source corresponding to each installed avionics unit i e NAVI NAV2 COM1 COM2 ADF and DME and check for audio over the pilot s headset 2 Press the SPKR key on pilot s audio panel and verify that the selected audio is heard over the pilot s speaker 3 On the copilot s audio panel select the audio source corresponding to each installed avionics unit 1 e NAVI NAV2 COM1 COM2 ADF and DME and check for audio over the copilot s headset 4 Press the SPKR key on copilot s audio panel and verify that the selected audio is heard over the copilot s speaker Failsafe Operation Check GMA 1
199. ctions throughout the entire trim range during manual electric trim operation Ifthe trim wheel hesitates this may indicate that the pitch trim clutch is slipping and proper clutch setting or clutch cartridge and cable tension should be verified Refer to the King Air 200 Series Maintenance Manual and Pitch Trim Servo Install drawing listed in Table 1 2 for clutch settings and cable tensions If both clutch setting and cable tension are within tolerance check the aircraft pitch trim system for excessive friction Refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 8 2 4 Manual Electric Pitch Trim Speed Check 1 Run MANUAL ELECTRIC PITCH TRIM in one direction until it runs against the mechanical stop 2 Run the trim in the opposite direction and using a stop watch or equivalent device time the trim speed to the opposite mechanical stop Verify the elapsed time for full travel measures 13 3 seconds Page 8 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 8 2 5 Autopilot Operation Checks NOTE For aircraft with software version 0985 03 and the Electronic Stability and Protection ESP option an airspeed of 200 knots must be input using a pitot static test set 1 Engage the Autopilot by pressing the AP key on the AFCS mode controller Push the HDG knob to synchronize the heading bug to the current aircraft heading Select HDG mode by pressing the HDG key on the AFCS m
200. ctly e Verify GCU 477 is powered on o If GCU 477 will not power on remove unit and verify power and ground are present at the GCU connector If power or ground is not present troubleshoot aircraft wiring for faults CHNL 1 GCU 477 If power and ground are present replace GCU 477 e Load MFD1 and GCU 477 configuration files e Check the MFD1 GCU 477 interconnect wiring for faults e Replace GCU 477 Replace MFD if problem remains amber MFD1 GCU data path functionality is unknown Reload MFD1 Amber configuration file G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 9 190 00915 01 Revision 6 5 2 1 2 GIA RS 232 ARINC 429 CONFIG Page GIA1 RS 232 GIA1 GDC 74 1 data path is functioning correctly GIA1 GDC 74 1 data path is not functioning correctly e Load GIAI and GDC 74 1 configuration files e Swap GIA and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA 1 CHNL 1 GDC 74 1 o Replace original GIA 1 if box turns green after swapping units e Check the GIA1 GDC 74 1 interconnect wiring for faults Replace GDC 74 1 1f problem remains ee GIA1 GDC 74 1 data path functionality is unknown Reload GIA1 configuration files GRS 77 2 GIA1 GRS 77 2 output data path is not monitored A white N A box is normal GIA1 GTX 33 1 data path is functioning correctly GIA1 GTX 33 1 data path is not functioning correctly e Load GIAI and
201. cuit breaker panel and verify that NO DATA is removed after several seconds If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 31 190 00915 01 Revision 6 7 14 Stormscope Functional Check Reference Section 3 17 Stormscope WX 500 Configuration for configuring Stormscope This procedure assumes familiarity with the set up and operation of the WX PA portable analyzer kit 1 Apply power to the WX 500 and verify that no failed test messages appear If fault messages do appear refer to the WX 500 Installation Manual for troubleshooting 2 Following successful power up verify the following modes e Access to both 3600 and 1200 weather view modes e All available ranges can be displayed e Access to the cell mode and strike mode e Strike counter is displayed in all weather modes and ranges 3 Key COMI and COM2 several times on different frequencies representing the lower mid and upper portion of the VHF COM frequency band Verify keying of COM1 or COM2 does not cause strike data to appear on the MFD 4 Operate DME XPDR 1 XPDR 2 and 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 connection 1s tight If necessary use tape to secure the WX PA antenna Ensure the
202. d GMC configuration files Replace GMC If problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number The G1000 has detected a GMC 710 configuration mismatch GMC CNFG GMC Config error Config service req d Check wiring for faults ref Failed Path troubleshooting section 5 7 Replace the GMC 710 The G1000 has detected a GMC FAIL GMC is inoperative failure in the GMC 710 MANIFEST GMC software The system has detected an Load the correct software version incorrect software version See Section 3 9 for the Software loaded in the GMC 710 Load Procedure mismatch Communication halted Page 5 76 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 19 GCU 477 Troubleshooting 5 19 1 GCU 477 Alerts and Problems Failure Message Cause Solutions S Load GCU configuration files Replace GCU If problem persists replace master configuration module check config module wiring for faults and replace if necessary
203. d in good condition Standby Altimeter b Visually inspect the plumbing and harness connector assembly and ensure it is secure and in good condition a Inspect circuit breaker panel wiring and circuit breakers for chafing damage other defects and proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 the appropriate Circuit Breaker Panel Modification drawing listed in Table 1 2 and the Cabin Wire Harness Routing drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing Circuit Breaker Panels b Inspect edgelit overlay panels for damage or defect c Reinstall the circuit breaker edgelit overlays to the circuit breaker panels a Inspect that all required placards are installed Placards must be legible secure and Placards in good condition Refer to the Main Instrument Panel Installation drawing listed in Table 1 2 a Reinstall the MFD and PFDs as described in Section 6 a Inspect the standby altimeter indicator unit including face of the unit and connector for corrosion or other defects Page 4 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Table 4 7 Cabin Area Visual Inspection Procedure _ item __ Description Procedure _ Initials _ Inspect all external antennas for leading edge erosion and condition of base Antennas seals GPS WAAS top diversity transponder s
204. d off This unit is very delicate handle like eggs Refer to the 4200 Series Attitude Indicator Installation Manual listed in Table 1 2 for more handling instructions Removal 1 Remove MFD per Section 6 1 2 Disconnect the electrical connector of the standby attitude indicator 3 Use a 0 060 6 Spline wrench to remove the knob from the front of the standby attitude indicator 4 Use a Phillips screwdriver to remove the three attachment screws from the front of the standby attitude indicator 5 Remove the standby attitude indicator Reinstallation 1 Ensure the lighting control voltage switches on rear of unit are set for 28V 29 2 Reinstallation of the standby attitude indicator is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 3 If further maintenance is not required proceed to Section 8 6 28 Nose Avionics Bay Cooling Fans Removal 1 Gain access into the nose avionics equipment bay 2 Disconnect the cooling fan hoses from the cooling fan Take necessary precautions to prevent any foreign debris from entering the fan hoses during maintenance 3 Disconnect the electrical connector of the cooling fan 4 Use a Phillips screwdriver to remove the attachment screws from the cooling fan 5 Remove the cooling fan Reinstallation 1 Reinstallation of the avionics cooling fan is the reverse of the removal Reference the Elec
205. dg Value lt aircraft heading gt Inhibit Line Off Antenna Mount Bottom J3 3 4 Deactivate the cursor NOTE The DATA window is only updated once every five seconds G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 33 190 00915 01 Revision 6 3 20 ESP Support with AOA Option Configuration This section applies only to installations with the ESP option with AOA modes A new Safe Flight lift computer is used for this configuration The procedures outlined in this section must be followed to load the necessary configuration files required to enable ESP messages and functions An Enhanced AFCS unlock card is also required for this option see Section 3 34 l With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 Rotate the small FMS knob to highlight 200 B200 ESP Support with AoA For software version 0985 03 the option is labeled King Air 200 B200 Series ESP Support Press ENT key on PFD 1 Verify 200 B200 ESP Support with AoA or King Air 200 B200 Series ESP Support is displayed in the Item window Press LOAD CONFIGURATION ID D2C83E0 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A MANIFEST N A AL
206. dications l Verify the DATA indicators of the discrete inputs labeled FLAP EXTEND and FLAP RETRACT show an invalid condition 2 Extend the flaps down While the flaps are traveling down check that the DATA indicator of the discrete input labeled FLAP EXTEND changes to a valid condition 3 When the flap motion is completed verify the DATA indicators of the discrete inputs labeled FLAP EXTEND and FLAP RETRACT show an invalid condition 4 Retract the flaps up While the flaps are traveling up check that the DATA indicator of the discrete input labeled FLAP RETRACT changes to a valid condition 5 When the flap motion is completed verify the DATA indicators of the discrete inputs labeled FLAP EXTEND and FLAP RETRACT show an invalid condition 6 Repeat steps 1 through 5 for GIA2 7 The flap discrete input check is complete G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 19 190 00915 01 Revision 6 4 9 GSM 85A GSM 86 Slip Clutch Torque Check Procedure Perform the test per section 4 9 1 4 9 2 or 4 9 3 The following test procedures are the same for both the GSM 85A and the GSM 86 servo gearboxes 4 9 1 Automated Slip Clutch Test Procedure SW version 0985 04 and later l Verify the correct type of servo gearbox is configured for each servo per Section 3 27 2 With the MFD in Normal Mode press the red DISPLAY BACKUP button on the pilot s GMA aud
207. e Antenna System e Existing VHF COM 1 amp 2 Antennas e Newly installed GA 36 and GA 37 GPS WAAS Antennas e GMA 1347D 1 amp 2 e GEA 71 1 amp 2 e GDU 1040A 1 amp 2 e GSA 80 e GRS 77 1 amp 2 e Traffic System if installed The GIA 63W 1 interfaces to the following additional equipment e GDC 74B 1 e GTX 33 1 e DME 42 if installed The GIA 63W 2 interfaces to the following additional equipment e GDC 74B 2 e GTX 33 2 e ADF if installed e Stormscope if installed e Radio Altimeter if installed Figure 2 6 GIA unit Page 2 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 1 7 GEA 71 Engine Airframe Unit 2 The Garmin GEA 71 Engine Airframe Units provide engine airframe data to the G1000 system Data received from transducers sensors is processed and sent to GIA 63Ws via RS 485 digital interface and subsequently to the GDU 1500 MFD Engine parameters are normally displayed on the MFD In the event of MFD failure the engine parameters can be displayed on PFD 1 and or PFD 2 using display reversion The GEAs are located behind the instrument panel and is mounted in a vertical orientation Electrical power to GEA 1 is provided from Dual Fed Bus No 1 and to GEA 2 from Dual Fed Bus No 2 Both GEA units will power up immediately with external or aircraft power or battery operation NOTE On serial numbers BB 1484 1486 and subsequent the electrical s
208. e Flaps in motion discrete inputs to Discrete Input Check the G1000 to verify proper operation al Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 6 Revision 6 190 00915 01 Be ea Manual Removal amp Replacement GSA 80 Servos all Refer to Master Drawing List listed in Table 6 11 On Condition 1 2 for installation drawings Removal amp Replacement GSM 85A 86 Servo 10 On Conditi Gear Box all Refer to the servo install drawings listed in 6 n Condition Master Drawing List listed in Table 1 2 For installations with the GSM 86 servo gearbox verify that the pitch roll yaw and pitch trim GSM 86 slip clutch torque GSM 86 Servo Gear Box Slip Clutch Special 3 000 hrs Torque Check values are within acceptable limits GSM 85A Servo For installations with the GSM 85A servo Gear Box Slip gearbox verify that the pitch roll yaw Phase 2 amp 4 Clutch Torque and pitch trim GSM 85A slip clutch Check torque values are within acceptable limits Verify the integrity of the wiring interface WOW and Low between the landing gear safety switch a assembly and the No 1 and No 2 GIA heme Pase Artea inputs and the air ground status logic Special 10 000 cycles initial Inspect the exterior skin around Exterior skin antennas for cracks and loose and inspection around missing fasteners per Super King A
209. e connectors to ensure there are no bent or damaged pins Repair any damage 2 Insert the unit into the installation rack 3 Lock the unit into the rack by using the ratcheting latch mechanism 4 Reconnect the eight coax quick lock connectors and the three electrical connectors 5 Close access to the left forward avionics compartment 6 Configure the GTS 8XX per Section 3 17 and test per Section 7 26 6 31 GPA 65 PA LNA Unit Removal 1 Remove cabin interior to access FS 158 at WL 119 on the left side of the fuselage Reference the Antenna Install drawing listed in Table 1 2 for more details 2 Disconnect the eight coax quick lock connectors 3 Disconnect the electrical connector 4 Remove the four mounting screws that hold the unit to the installation brackets Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Reattach the unit to the mounting brackets reusing existing hardware 3 Connect the eight coax connectors Note the color coded bands which match the mating connectors on the unit 4 Reconnect the electrical connector pigtail 5 Ensure that all connectors coax and electrical are locked in place 6 Reinstall cabin interior G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 17 190 00915 01 Revision 6 7 No configuration is required for the GPA 65 Test the GTS 8XX per Section 7 26 6 32 GA 58 Traffic Antennas Removal 1
210. e electrical connector from the standby airspeed indicator 4 Use a Phillips screwdriver to remove the attachment screws from the front of the standby airspeed indicator 5 Remove the standby airspeed indicator Reinstallation 1 Reinstallation of the standby airspeed indicator is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 6 26 Standby Altimeter Removal 1 Remove MFD per Section 6 1 2 Disconnect pitot static plumbing from the back of the standby altimeter Take necessary precautions to prevent foreign object debris from entering the pitot static lines during maintenance 3 Disconnect the electrical connector from the standby altimeter 4 Use a Phillips screwdriver to remove the attachment screws from the front of the standby altimeter 5 Remove the standby altimeter Reinstallation 1 Reinstallation of the standby altimeter is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 15 190 00915 01 Revision 6 6 27 Standby Attitude Indicator Ensure the standby attitude indicator gyro 1s not spinning this may take 10 minutes or longer after the unit has been turne
211. e to the GMC 710 Test Section 7 11 1 New Repaired or Exchange GMC 710 Installed If a new repaired or exchange GMC 710 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GMC 710 Test Section 7 11 1 7 11 1 GMC 710 Test Perform a basic operational check on the GMC 710 The following knob wheel and key presses and rotations are to be performed on the GMC 710 1 Ensure the G1000 is operating in normal mode and the autopilot is operational 2 Press the FD key a few times verify the Flight Director display on PFD1 toggles on and off Leave the flight director displayed 3 Press the XFR key and verify the white illuminated arrowhead points in the opposite direction Verify the green arrow displayed at the top of PFD 1 also points in the same direction 4 Rotate the ALT SEL knob and verify the altitude bug displayed on PFD 1 altitude tape moves 5 Rotate the UP DN wheel and verify the flight director moves in the vertical direction 6 Press the HDG key and verify the white illumination appears next to the key Rotate the HDG knob and verify the heading bug displayed on PFD 1 compass card moves and the flight director follows 7 Press the HDG knob and verify the heading bug centers 8 Press the YD key and verify the white illumination appears next to the key 9 Press the VS key and verify the white illumination appears next to the key 10 Press
212. ecseesccesssceseseess 5 86 5 23 SAFE FLIGHT LIFT COMPUTER TROUBLESHOOTING cccccseccssccssccsccesccesccesccesccesscesscusseuecs 5 86 5 26 GDE 59 TROUBLES HOO LING cols 5 88 S2 GSROO TROUBLESHOOTING eair A r E E E E 5 89 5 28 GIS 8208530 TROUBLESHOOTING rt dt OREA 5 89 Page ii G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 EQUIPMENT REMOVAL amp INSTALLATION vesessccicccscssvasessccisncsscscucedsssedcossasocsessosedsessessveedesses 6 1 Cel E A E TEE RE 6 2 02 GMA IS4TDAUDIO PANE ni AA Id ees 6 2 6 3 GIA 63 W INTEGRATED AVIONICS UNITS a 6 3 O64 GEA TU ENGINE AR ERAME UN o taaan 6 3 OS GTA TRANS PONDE o Rda 6 4 6 6 GDC 74B AIR DATA COMPUTER oa 6 4 Gale STEPS OAT PROBE A tas 6 4 OS GRS L A A II A A O EP Ye NRE ET OR 6 5 69 GMUA4A MAGNETOMETER lt lt a 6 5 6 10 E aeren iE A EA EEE E A ERA 6 5 6 11 GSES E VO aa E EEE EEE NA E EEEE EAEE 6 6 6 12 GSM SSAB 5 ER VO UEARBO Xd aoe eae ee ATE ce ee 6 7 6 13 A paceataeasvadipogestatmarseadensmaceetieasbesimenaveadiancseda 6 7 6 14 MET Di A A A ES Pee ET ne 6 8 6 15 E A A tesaamen tase aeeana ee reaas a esesee aetna 6 8 6 16 CONFIGURATION MODULE REMOVAL amp REPLACEMENT cscccccssececsscccesscccesscccuscecueeceesuecs 6 9 6 17 GEA 71 BACKSHELL THERMOCOUPLE REMOVAL amp REPLACEMENT c ccscccssccssccsceesseeeees 6 11 6 18 GPS WAASINTENNA Sustrato irodlrtsa dridco 6 12 6 19 DIVERSITY TRANSPONDER ANTENNA vis a a a a 6
213. ection 27 31 00 3 Ifthe stall warning points for the new lift computer were set to match the lift computer that was removed adjustments to the new lift computer may not be necessary in flight If the stall warning points are adjusted in flight verify the LAA output per Section 7 24 2 4 Enable the STABILITY amp PROTECTION item via the MFD AUX SYSTEM SETUP 2 page Verify that the message ESP OFF is not present 7 25 ESP Functional Check NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection ESP feature 1 Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER PWR and BATT switches to ON Ensure G1000 system and components are powered and operating normally 2 Verify the DISPLAY BACKUP button on the audio panel is pushed in so that the GDUs will not operate in reversionary mode 3 Verify no AHRS ADC Autopilot PFD AFCS Mode Controller GCU alert messages or monitor flags HDG MISCOMP etc are present on PFD1 or PFD2 4 On initial power up verify that the MFD splash screen includes a graphic similar to the following GARMIN King Air with Electronic Stability and Protection ESP G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 57 190 00915 01 Revision 6 5 On the GMC 710 couple the Flight Director to the left side by pressing the XFR button The arrow that is illuminated indicates which
214. ection 7 2 1 New Repaired or Exchange GMA 1347D Installed If a new repaired or exchanged GMA 1347D 1s installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GMA 1347D Test Section 7 2 1 7 2 1 GMA 1347D Test Except for marker beacon operation an in aircraft checkout may be performed in the aircraft with known good microphone headset and speaker Intercom System ICS Check 1 Ensure that the MAN SQ key is off no light 2 Adjust GMA1 and GMA2 ICS volume to a comfortable level 3 Plug in a headset at each COCKPIT ICS position One at a time plug a headset into each left and right CABIN ICS jack location if installed one headset on right one headset on left 4 Verify the following e Two way communication between each CABIN ICS jack position e CABIN ICS position cannot hear the pilot and copilot e CABIN ICS positions cannot be heard by the pilot or copilot 5 OnGMAI select COMI MIC and AUDIO 6 Ensure INTR COM is deselected on GMA1 or GMA2 Verify an active green COM frequency is displayed on both PFDs 7 OnGMALl or 2 select PA and verify the PA select annunciator is illuminated on GMA1 and GMA2 Verify COM active frequency is displayed white 8 Initiate passenger address using pilot s headset boom mic by keying the pilot s PTT Verify the following e Clear PA audio can be heard over cabin speaker and CABIN ICS headsets e PA sele
215. ed PFD Software Loading procedure mismatch Communication Halted MANIFEST MFD1 software The system has detected an mismatch Communication incorrect software version loaded Halted in MFD Check master configuration module connector and wiring for damage inside the GDU connector backshell v Replace master configuration module wiring and pins If problem persists replace master configuration CNFG MODULE PFD 1 The PFD master configuration module configuration module is opera module has failed NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number Page 5 46 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Failure Message Cause Solution S Reload the display configuration files from SD Loader Card Reload system configuration files MFD1 CONFIG MFD1 by pressing the UPDT CFG configuration error Config service softkey on the Configuration req d Upload Page in the PFD1 System Page Group to load configuration files into the configuration module v If message persists check PFD1 config module wiring for faults and repl
216. ed has failed See the GIA pre flight test steps for a description of the possible values for lt STEP gt on the failed GIA and corrective actions e AHRS MON invalid lt STATE gt The AHRS monitor has detected that the AHRS data is invalid The possible values for lt STATE gt are a Mon Prmtr Invalid The ARINC 429 data used by one of the monitors has not been received Attitude Prmtr Invalid The ARINC 429 pitch or roll angle has not been received a Exceeded Attitude Limits The pitch or roll angle has exceeded the engagement limits a e Cross Hdg Accel Fail Cross heading acceleration monitor failed e Vert Accel Fail Vertical acceleration monitor failed f Fltrd Cross Hdg Accel Fail Filtered cross heading acceleration monitor failed g Fltrd Vert Accel Fail Filtered vertical acceleration monitor failed h Roll Accel Fail Roll acceleration monitor has failed i Normal Accel Fail Normal acceleration has failed Troubleshoot the GRS 77 for the cause of the failure e Stuck switch invalidated parameter lt AXIS gt A MET switch in the specified axis is stuck Check the MET trim switches for proper operation G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 33 190 00915 01 Revision 6 e PRMTR lt PARAMETER gt MODE lt MODE gt Parameter lost The mode specified by lt MODE gt has been disengaged because the parameter specified by lt PARAMETER gt has become invalid The followi
217. eesssesssseessesssesseeeseeeens 7 42 Piotre 9 RVSM Critical Reina 7 44 ELLE 72 0 DA Indicator oncon yates ays saiascee eeakeaus ida A 7 45 Fie re 7 Wl Static Port Measurement scssi aiian e R 7 45 Figure 7 12 Static Port Measurement locations 000000000000000000000000000000000000000000000rrrrooorrrrrrerrrererrrrrrrerees 7 46 Figure 15 Static Port Measurement Lol iS A a 7 46 route 14 C0530006 LLC A A a 7 54 Fiare 115 Breakout BO ranean aT eae eee T O ee eee 7 55 Figure 7 16 Force Applicator Usage Instructions 0000000000000seseessessesseensssssssesssssssssssssssssssnsneees 7 56 Fisure 7 17 ES 8XX GND TESTS OIE A A a 7 61 Fiotre 7 15 GORD 6C Ono uration Pare dias 7 66 Fiure O AUX TELEPHONE Diao 7 66 Fisure 8 1 GDU Data Verification ARINC 49 ta Beas E ii 8 9 Figure 8 2 GIA Data Verification ARINC429 R9 232 ecooococoncncnnononoonnnonononoonnono nono nn ono non nono nono non nn nn nn nnnnnns 8 8 Figure 8 3 GIA Data Verification RS ds 8 11 Foue A aa a a a EA a a e ae 8 12 LIST OF TABLES TABLE cota didnt PAGE Table leal ETOD0S y Stem Software VEO o e a le O 1 1 Table 2 ANEQUITCA DO CUM Ii A AAA A A a 1 5 able ls RSterento Publica OA Si its 1 6 Table 32l SOMMWare VECA OI ene N A A ENT 3 23 Tabledi Whaintenance Mlevi St E ibid 4 4 Table 4 2 Discontinued Maintenance Intervals ocoooccnonocononocononocononocnnnaricnononononocononoccnnnncnonerononecoso 4 9 Table 4 3 Nose Section Visual Inspection PrO
218. em Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for GIA 2 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 30 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 17 GTS 8XX Traffic System Configuration Follow this procedure to enable the GTS 8XX traffic system function for the G1000 system if required NOTE The G1000 can only be configured for TIS or TAS TCAS but not both Performing this procedure will automatically disable the TIS function Coordinate this configuration with Section 7 26 GTS 8XX Traffic System Functional Check NOTE Configuration of the GTS 8XX TAS TCAS I will require the GTS system to be configured with the aircraft mode S address Coordinate this configuration with Section 3 35 Aircraft Registration Number Entry 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the System Upload page on PFD1 using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight GTS 8XX TAS TCAST Press ENT key on PFD1 4 Verify the GTS 8XX TAS TCAS1 is displayed in the Item
219. em to use the database when it becomes effective NOTE If the new database is not yet effective but it is desired to use the new database immediately select the YES softkey To eliminate database mismatch errors when selecting the YES softkey the database must also be loaded on PFD1 and PFD2 individually following the same process G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 49 190 00915 01 Revision 6 7 The system will synchronize and automatically update as necessary Monitor the synchronization process on the AUX SYSTEM STATUS page in the SYNC STATUS sub section within the DATABASE window This sub section is only present when a sync is occurring or has occurred on the current power cycle SYNC STATUS NAY STANDBY NAVIGATION INTERNAL REGION CYCLE EFFECT IVE EXPIRES STANDBY BOTTOM CARD REGION CYCLE EFFECTIVE EXPIRES Figure 3 46 Navigation Database Synchronization 8 Ifan error occurs during synchronization one of the following messages will be displayed followed by the affected GDU Err No Space SD card does not contain sufficient memory Timeout system timed out prior to the database transfer completing Err displayed for all other errors Note that a power cycle is required to restart synchronization when Err No Space or Err is shown 9 When the synchronization is complete the status is shown as Complete 10 Cycle power to PFD1 PFD2 and MED
220. emains stable during the entire test If the test still fails have maintenance checks performed on the GFC 700 system then repeat the test RVSM operations are prohibited until the autopilot is capable of maintaining altitude within 65 feet of the selected cruise altitude Altitude Airspeed Altitude Airspeed ft kt ft kt Table 7 9 In Flight Altitude Hold Performance Test Page 7 48 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 24 Safe Flight Lift Computer Ground Calibration NOTE This procedure is required only for aircraft with the optional Electronic Stability and Protection ESP feature with Angle of Attack AoA modes and the Safe Flight Lift Computer p n C 05606 1 Prior to removal of the lift computer it is recommended that Section 7 24 1 be accomplished to record the existing stall warning points for Pots 0 1 and 2 Original C 05606 1 Lift Computer Reinstalled No ground or flight calibration is required if the removed C 05606 1 Lift Computer is re installed and the potentiometers are not adjusted This does not include units that were returned for repair as their calibration will need to be completed at installation New Repaired or Exchange C 05606 1 Lift Computer Installed If a new repaired or exchange C 05606 1 Lift Computer is installed the ground and flight calibration will need to be accomplished See Section 7 24 2 for the ground calibration and Section
221. enance Manual 200 B200 Series King Air 190 00915 01 5 11 5 GIA Cooling Alerts Failure Message Cause Solution S GIA1 COOLING GIA1 GIA1 operating temperature is too z Aaa temperature too low low p GIA2 COOLING GIA2 GIA2 operating temperature is too EE TET temperature too low low p GIA1 COOLING GIA1 over GIA1 has exceeded its operating temperature temperature range GIA2 COOLING GIA2 over GIA2 has exceeded its operating temperature temperature range Check fan wiring and air tubing for proper operation if applicable Replace cooling fan if unable to determine if operating correctly Replace GIA1 If problem persists contact Garmin Aviation Product Support for assistance Check fan wiring and air tubing for proper operation if applicable Replace cooling fan if unable to determine if operating correctly Replace GIA2 If problem persists contact Garmin Aviation Product Support for assistance G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 61 190 00915 01 Revision 6 5 11 6 GIA Configuration Alerts Failure Message Cause Solution S MANIFEST GIA1 software The system has detected an mismatch Communication incorrect software version loaded Halted in GIA Load the correct software See Section 3 9 for the Software Loading MANIFEST GIA2 software The system has detected an procedure mismatch Communication incorrect software version l
222. equipped with the G1000 and GFC700 AFCS systems Modification of an aircraft by this Supplemental Type Certificate STC obligates the aircraft operator to include the maintenance information provided by this document in the operator s Aircraft Maintenance Manual and the operator s Aircraft Scheduled Maintenance Program Aircraft modified by this STC have been shown to qualify for operation in Reduced Vertical Separation Minimum RVSM airspace as a group aircraft in accordance with Title 14 of the Code of Federal Regulations 14 CFR Part 91 Appendix G Operations in Reduced Vertical Separation Minimum RVSM Airspace and Federal Aviation Administration FAA Document No 91 RVSM Change 2 dated 2 10 2004 Guidance Material On The Approval Of Operators Aircraft For RVSM Operations This qualification is based on analysis of the configuration and performance of the air data automatic altitude control altitude alerting and altitude reporting systems These systems must be maintained in accordance with the inspections and tests specified in this document and other current maintenance practices to guarantee continued compliance to RVSM specifications 1 1 2 Identifying an STC Configuration Table 1 1 lists the G1000 System Software Version numbers approved for this STC Table 1 1 G1000 System Software Version Aircraft Model oe eyo Notes Software Version 200 B200 Series King Air Updated GIA software superseded 200 B200 Series
223. er Verify FD is coupled to PFD1 as indicated by a left pointing arrow on the AFCS mode controller next to the XFR button Repeat step 9 while coupled to PFD1 Page 8 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 8 3 Maintenance Records After conducting required return to service procedures in accordance with the King Air 200 Series Maintenance Manual listed in Table 1 2 the aircraft may be returned to service Record the following information in appropriate aircraft maintenance logs e Part number of the G1000 software loader card used to perform software loading or software updates e Record part and serial numbers of any LRU which was replaced e Record any database updates which were performed during maintenance e Any other applicable information related to the maintenance work performed on the aircraft G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 15 190 00915 01 Revision 6 This page intentionally left blank Page 8 16 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01
224. er defects Check the integrity of the SHIELD BLOCK ground attachments to the GDC 74B Air Data harness connector assembly as well as the integrity of the individual shields and their Computer Qty 2 attachment Visually inspect the pitot static plumbing and ensure it is secure and in good condition GEA 71 Engine Inspect the GEA 71 unit rack and connectors for corrosion or other defects Check Airframe Unit Qty 2 the integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment GMA 1347D Qty 2 a Inspect the GMA 1347D unit including face of unit rack and connectors for corrosion or other defects Check the integrity of the SHIELD BLOCK ground attachments to Inspect all fwd bulkhead connectors for security of attachment Inspect all instrument panel wiring and coax for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 G1000 Wirin Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed in ES 9 Table 1 2 Pay particular attention to possible areas of chaffing Inspect all other exposed G1000 GFC wiring and coax for chafing damage proper G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page4 11 System Maintenance Manual 200 B200 Series King Air Page 4 11 190 00915 01 Revision 6 ltem __ Description Procedure _ Initials
225. er beacon annunciations appear at the upper left corner of the altitude indicator on the PFD Figure 7 2 Operate the MKR MUTE key on the 1 and 2 GMA 1347D and ensure that the audio signal is muted If no other service is to be performed continue to the return to service checks in Section 8 Page 7 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 2 2 Landing Gear Aural Alert Check This check should be conducted in conjunction with the Phase 2 and Phase 4 Landing Gear Retraction Warning Horn check in the existing King Air Maintenance Program NOTE This procedure is applicable only to aircraft equipped with a tone generator as part of the aircraft audio system Refer to the appropriate aircraft wiring diagrams to determine if a tone generator is installed This check can be accomplished in conjunction with the Weight on Wheels and Low Speed Awareness Band Test in Section 7 22 1 Conduct the Landing Gear Retraction Warning Horn check as stated in the King Air 200 Series Maintenance Manual listed in Table 1 2 2 Verify that the aural tone is played through the G1000 audio system and through both cockpit speakers 7 2 3 XM Audio Suppression Check This procedure is applicable only to aircraft that have XM radio subscriptions ooo aa ee i WARNING The following steps require movement of the landing gear Ensure aircraft is safe for the operation of the landing gear before proceed
226. ertainment Bus Figure 2 12 GDL 69A Datalink 2 1 13 GDL 59 Wi Fi Datalink optional The GDL 59 provides a POTS plain old telephone service phone interface and a high speed data link between the aircraft systems and ground computers while the aircraft is on the ground using the IEEE 802 11g Wi Fi protocol The GDL 59 also provides the interface to an optional GSR 56 satellite datalink which adds airborne low speed data link and voice communication capability The GDL 59 unit interfaces to the Garmin Integrated Flight Deck via the GDL69A using HSDB The GDL 59 1s located in the Figure 2 13 GDL 59 Wi Fi Datalink Page 2 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 1 14 GSR 56 Satellite Receiver optional The GSR 56 provides airborne low speed data link and voice communication capability to Garmin Integrated Flight Deck installations The GSR 56 contains a transceiver that operates on the Iridium Satellite network The GSR 56 interfaces directly to the GDL 59 via an RS 232 interface The GSR 56 is located in the aft cabin floor area just forward of the cabin door The GSR 56 is powered from the Avionics No 2 bus Figure 2 14 GSR 56 Satellite Receiver 2 1 15 GTS 8XX Traffic System optional The GTS 8XX 1s a traffic surveillance system that uses active interrogation of Mode S and Mode C transponders to provide traffic advisories to the pilot The GTS 820 is a TAS un
227. es with the operation of the GMU 44 magnetometer It is highly recommended that this test be performed after installation or maintenance of electrical components on the aircraft and or for troubleshooting the GMU 44 GRS GH CALIBRATION SELECT PROCEGUFE 7 GDRHUNTCAT ION STATUE AAG INERFEPEMLE TES a OFS a PHRETORETER BEFORE CAL 1B5A TI 0H a gt a 2 Prepa o detoled test sequence wih prec s stort od stop tines for eercism ol electron a 5 Ready to enter the 5577 A CALTAARATE CALIBRATION PROCEDUBE Begin tesi sequenca mael TEST OUNPLETE when finisher The col rotion siotus will then be displed ee SS Figure 5 7 Magnetometer Interference Test 1 Initiate the AHRS magnetometer interference test procedure by performing the following steps 2 On PFD1 enter Configuration Mode and go to GRS GMU Calibration page as shown in Figure 5 7 Page 5 70 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 This page is protected and requires a keystroke password to perform this test Press the following softkeys in sequence as counted from left to right on lower bezel of MFD e softkey 9 e softkey 10 e softkey 11 e softkey 12 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 NOTE The 3 item on the checklist instr
228. esource Center portion of the web site 4 7 GSA 80 Greasing Procedure The GSA 80 servo greasing procedure 1s required only when the GSA 80 is removed and reinstalled Refer to Section 6 11 for details Page 4 18 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 8 Flaps in motion Discrete Input Check To perform this check all G1000 and GFC 700 equipment must be installed and operational Start PFD1 in Configuration Mode and go to the GIA Page Group and select the GIA I O Configuration Page using the FMS knob Perform the following checks GIA 1 0 CONFIGURATION E SELECT GIA UNIT ME E SELECT INPUT OUTPUT CONFIGURATION CHANNEL DATA TYPE INVERTED ACTV DEBNCE ms INACTV DEBNCE ms DATA SET ACTIVE SET ACTIVE SET ACTIVE SET ACTIVE AUDIO INHIBIT 1 FALSE 300 300 OFF FALSE OFF FALSE AFCS GO AROUND FALSE PLT CTRL WHL FALSE AFCS DISCONNECT I FALSE NS LDG DN TRUE CPLT PIT TRM ARM FALSE PLT PIT TRM ARM FALSE OFF FALSE OFF FALSE GIA 1 FAN TRUE FLAPS 50 FALSE FLAPS 100 FALSE OFF FALSE FLAP EXTEND FALSE FLAP RETRACT FALSE FALSE SO YO YO YO YO YO YO YO YO O O O O O O od amp SO YO YO YO Y YO YO YO O O O O O O O O amp PLT PIT TF Gi PIN fl IF Ba BA Ba BA fl IF H Fl H Fl fH il fF HG Ba BA Ba BA L F L F L F Ba EA L F L F Ba BA MT HAGA HAGA HAGA HAGA Figure 4 1 GIA I O Page Invalid Valid Figure 4 2 Discrete Valid Invalid In
229. f no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 33 190 00915 01 Revision 6 7 15 TAWS Functional Check 7 15 1 Functional Check for TAWS B l 10 With the G1000 in Normal Mode use the GCU FMS knob to select the MAP group and TAWS page on the MFD Verify that the title at the top of the page reads MAP TAWS B NOTE If TAWS has not been enabled the title will read MAP TERRAIN PROXIMITY or MAP TERRAIN Refer to section 3 30 for TAWS Configuration for configuring TAWS Press the GCU MENU button and select Test TAWS System from the pop up menu Verify TAWS test annunciation is displayed on the MFD and both PFDs After the TAWS test has completed verify that TAWS System Test Okay is heard over the cockpit speaker if selected and the headsets Press the GCU MENU button again and select Inhibit TAWS from the pop up menu and press ENT on the GCU Verify TAWS INH is displayed on PFD 1 and PFD 2 Press the GCU MENU button again and select Enable TAWS from the pop up menu and press ENT on the GCU Verify the TAWS INH annunciation on the PFDs has extinguished With a GPS position acquired shield or disconnect the GPS antennas to remove the GPS signal Verify LOT shows on the MFD and the TAWS N A and LOT annunciations show on the
230. factory installations that would require these checks to remain Table 4 2 Discontinued Maintenance Intervals ll lem Description Procedure ll Manual Interval AC Inverter Operational Check Phase Inspections Phases 1 2 384 Phase 3 Dual Bus Feeder Inspection of Dual Bus Feeder Diodes 24 50 00 Diode superseded by 4 17 2 IMPORTANT For installed equipment not listed in this maintenance manual use the inspection procedures set forth in Chapter 05 of the King Air 200 Series Maintenance Manual or other appropriate maintenance manual as the requirements set forth by those manuals are still applicable The requirements set forth by this document take precedence over those set forth by the King Air 200 Series Maintenance Manual or other appropriate maintenance manual in cases where the requirements conflict G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 9 190 00915 01 Revision 6 4 4 Visual Inspection Perform a visual inspection in accordance with requirements in Table 4 1 Check for corrosion damage or other defects for each of the items listed in Table 4 3 through Table 4 8 Replace any damaged parts as required Inspection may require the temporary removal of a unit or units to gain access to connectors Follow guidance in Section 6 for equipment removal and replacement Refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 for instructions on removing any access panels NOTE It is re
231. fails to illuminate or illuminates incorrectly troubleshoot flap motor amp discrete input wiring refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 29 190 00915 01 Revision 6 5 6 GFC 700 AFCS Troubleshooting The GFC 700 is a digital Automatic Flight Control System AFCS which is integrated into various components of the G1000 This section touches upon key items to note while troubleshooting the GFC 700 Should a problem be encountered during the operation of the GFC 700 the pilot and technician should first evaluate the overall status and condition of the G1000 system at the AUX System Status page on MFD Any alert messages annunciations or other abnormal behaviors should be noted in an effort to pinpoint the fault The object is to locate the fault within a LRU or LRUs in efforts to replace the defective equipment The GFC 700 AFCS Annunciation field is located above the airspeed tape on the PFD as shown nav1 1 13 0 lt gt 118 98 TIXD PER GEN Navz 115 94 110 90 TIXD Figure 5 5 AFCS Annunciation Field Page 5 30 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 6 1 GFC Status Page The GFC Status page is presented in configuration mode and gives status information regarding the GFC 700 GFC STATUS SELECT GIA UNIT SELECT SERVO AXIS GIA 1 PITCH SERYO GIA STATUS
232. fer to the G1000 System Maintenance Manual listed in Table 1 3 3 7 1 SET gt ACTV Configuration Throughout the configuration mode pages there are SET and ACTIVE columns for input output settings and other parameters SET Refers to a setting or group of settings that reside in PFD Internal Memory and or the Master Configuration Module ACTIVE Refers to an active setting or parameter currently being used by the LRU LRUs store the active settings within internal memory G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 7 190 00915 01 Revision 6 Data can be manually copied from one column to the other and consequently from PFD memory to the LRU memory and vice versa by using the following two softkeys when available e SET gt ACTYV read Set to Active softkey Allows the installer to send the information in the SET column data stored in the master config module to the ACTV column data used by LRU e ACTV gt SET read Active to Set softkey Causes the LRUs current settings to be copied to the master configuration module as SET items CAUTION The ACTV gt SET softkey must be used with caution If an improperly configured unit is installed this softkey causes the wrong configuration to replace the correct aircraft configuration In the first example shown in Figure 3 10 the SET columns do not match the ACTIVE columns The inequality between SET and ACTIVE indicates a configur
233. ff The system has found the DB MISMATCH Aviation Jeppesen aviation database types in the PFDs and or MFD do not Load same type aviation database match i e different regions to all displays Americas International Atlantic etc database type mismatch Xtalk is off Page 5 48 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Failure Message Cause Solution S DB MISMATCH Airport Terrain The PFDs and or MFD have database version mismatch Xtalk different Airport Terrain database is off DB MISMATCH Terrain database version mismatch DB MISMATCH Obstacle database version mismatch DB MISMATCH Terrain database type mismatch 5 9 3 Cooling Alerts versions installed The PFDs and or MFD have different terrain database versions installed The PFDs and or MFD have different obstacle database versions installed The PFDs and or MFD have different terrain database types installed i e different regions Americas International Atlantic etc Confirm supplemental data card is inserted fully Reload the database or replace the supplemental datacard Failure Message Cause Solution MFD1 COOLING has poor cooling Reducing power usage PFD 1 COOLING has poor cooling Reducing power usage PFD 2 COOLING has poor cooling Reducing power usage G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air
234. figuration amp Testing Gives instructions for loading software configuring and testing of G1000 equipment Section 8 System Return to Service Procedure Specifies return to service procedures to be performed upon completion of maintenance of the G1000 system G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 3 190 00915 01 Revision 6 1 3 Definitions Abbreviations ADF Automatic Direction Finder ADTS Air Data Test Set AFCS Automatic Flight Control System AFM Airplane Flight Manual AFMS Airplane Flight Manual Supplement AHRS Attitude Heading Reference System CDU Control Display Unit CFR Code of Federal Regulations DME Distance Measuring Equipment EAU Engine Airframe Unit ESP Electronic Stability and Protection GPS Global Positioning System GPWS Ground Proximity Warning System HSDB High Speed Data Bus Ethernet IAU Integrated Avionics Unit ICS Inter Com System ITT Interstage Turbine Temperature LRU Line Replaceable Unit MFD Multi Function Display OAT Outside Air Temperature PFD Primary Flight Display RVSM Reduced Vertical Separation Minimum STBY Standby STBY ATT Standby Attitude Indicator STBY ALT Standby Altimeter STBY A S Standby Airspeed Indicator STC Supplemental Type Certificate TAWS Terrain Awareness amp Warning System WAAS Wide Area Augmentation System VHF Very High Frequency 1 3 1 Units of Measure Unless otherwise stated all unit
235. flag does not come into view on the PFD and verify that GPS 1 does not lose a 3 D navigation solution on the MFD Repeat steps 5 and 6 and re transmit while monitoring GPS 2 signal levels on the MFD Repeat steps 4 through 7 for each of the following frequencies e 121 175 MHz e 121 200 MHz e 131 250 MHz e 131 275 MHz e 131 300 MHz Repeat steps 4 through 8 for the No 2 COM transceiver GIA2 On the MFD select the AUX SYSTEM SETUP page Under the COM CONFIG field change the COM channel spacing from 25 kHz to 8 33 kHz Go back to the AUX GPS STATUS page Select 121 185 MHz on the No 1 COM transceiver Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels During the transmit period verify that the GPS INTEG flag does not come into view on the PFD and verify that GPS 1 does not lose a 3 D navigation solution on the MFD Repeat steps 14 and 15 and re transmit while monitoring GPS 2 signal levels on the MFD Repeat steps 14 through 16 for each of the following frequencies e 121 190 MHz e 130 285 MHz e 131 290 Mhz Repeat steps 14 through 17 for the No 2 COM transceiver GIA2 On the MFD select the AUX SYSTEM SETUP page and change the COM channel spacing back to 25 kHz Continue to the VOR LOC GS Test G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 7 190 00915 01 Revision 6 VOR LOC GS Test Check the VOR ILS and Glideslope functions with
236. for basic operation The integrated transponder altitude reporting system must be verified in accordance with Title 14 of the Code of Federal Regulations 14 CFR 91 411 and 91 413 every 24 calendar months or any time the transponder is removed This test requires the use of a Mode S ramp generator Specific instructions for operating the ramp tester are contained in the applicable operator s manual Refer to 14 CFR Part 43 Appendices E and F for testing criteria Note that for GTX 33D units the aircraft must be put on jacks to simulate an in air condition in order to test the Mode S diversity transmission channel isolation If no other service 1s to be performed continue to the return to service checks in Section 7 6 GDC 74B Air Data Computer Original GDC 74B is Reinstalled No software or configuration loading is required if the removed GDC 74B is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to GDC 74B Test Section 7 6 1 Original GDC 74B Installed in Opposite Locations for Troubleshooting No software loading is required if the original GDC 1 and GDC 2 are installed in opposite locations Continue to GDC 74B Test Section 7 6 1 New Repaired or Exchange GDC 74B is Installed If a new repaired or exchange GDC 74B is installed the correct software and configuration files must be loaded to the unit See
237. formed in order to guarantee that the AHRS mounting is sufficiently rigid and insensitive to vibration This procedure must be performed for both GRS 77 units installed in the aircraft Calibration Procedures Al and B Sections 7 7 2 and 7 7 4 respectively are not required prior to this procedure GRS GMU CALIBRATION SELECT PROCEDURE COMMUNICATION STATUS ENGINE RUN UP TEST m AIR DATA m MAGNETOMETER 41 Ensure the aircraft is in a location where it can safely increase the engine to full throttle w 2 Ensure the aircraft is stationary CALIBRATE Figure 7 6 Engine Run Up Test Page 1 Press the FMS small knob to highlight GRS 77 1 The FMS small knob can now be turned to select either GRS 77 1 or GRS 77 2 for calibration Press the ENT key after selecting the desired GRS 77 unit to calibrate The SELECT PROCEDURE field is not blinking 2 Initiate the AHRS engine run up vibration test procedure by performing the following steps a Select the ENGINE RUN UP TEST procedure and press the ENT key b Follow the checklist items displayed on the PFD 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 3 The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over a period of 2 4 minutes 4 When the operator has completed the engine run up and the engine 1s back to an idle setting pre
238. from the unit ground stud If replacing with a new unit disconnect the ground strap from the removed unit and retain the ground strap and associated hardware for reinstallation on the new unit Reinstallation 1 Reinstallation of the Signal Conditioners is the reverse of the removal Note that the p n 85 292 2 and 85 292 4 units are interchangeable Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 Proceed to Section 7 4 1 for testing 6 23 Instrument Panel Annunciators Prop Synch and Standby Battery Removal 1 Remove MFD from the instrument panel as per Section 6 1 2 Using a M22885 108T8234 extraction tool disconnect connector from the back of the switch 3 Pull the pushbutton cap fully out of the switch body and allow the cap to rotate 90 where it is held by the retaining element 4 While holding the retaining sleeve back side of the instrument panel loosen the two screws inside the switch body until the switch is free to come out 5 Remove the mounting sleeve and switch from the instrument panel Reinstallation 1 Reinstallation of the Prop Synch and Standby Battery switches is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 Press and hold the cockpit annunciator Press To Test switch located to the left of the annunciator panel and verify the following e For the Standby Battery
239. from the PFD via the TMR REF softkey 6 After each configuration setting change press the ENT key to configure the transponders 7 Press the ENT key on PFD1 to acknowledge prompt 8 After completing transponder configuration deactivate the cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 47 190 00915 01 Revision 6 3 36 Splash Screen Loading When all software and configuration has been loaded the splash screens must be loaded to all display units PFD1 PFD2 and MFD 1 If not applied apply power to the G1000 system 2 Remove power from PFD1 PFD2 and MFD by opening the PFD1 PRI SEC PFD2 and MFD circuit breakers Insert the software loader card in the upper slot of PFD2 Apply power to PFD2 When prompted to update system files press the NO softkey When prompted to update splash screen files press the YES softkey Remove the loader card from PFD2 and insert 1t into the upper slot ofthe MFD Apply power to the MFD and repeat steps 5 and 6 ES EN A ae Remove the loader card from the MFD and insert it into the upper slot of PFD1 10 Apply power to PFD1 and repeat steps 5 and 6 11 Cycle power to the MFD and splash screen will be present NOTE Any time software and or configuration is loaded to the system the splash screens will need to be reloaded to all three display units Page 3 48 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190
240. fter moving aircraft away from metal objects to determine if metal objects were the source of the interference Allow up to five minutes for the heading to reinitialize GRS 77 Perform a Magnetometer Interference Test to check amp for interference from onboard electrical system components e g NAV lights Pay particular attention to any new electrical devices that have been installed since the aircraft was new Correct any discrepancies that do not allow this test to pass before continuing HDG FAIL Ensure GRS 77 and GMU 44 connectors are secure Check the wiring and any inline connectors between the GRS and GMU for faults Recalibrate the GMU 44 Load configuration files to the PFD1 PFD2 GIA1 and GIA2 v If problem persists replace the GMU 44 v If problem persists replace the GRS 77 If this message persists longer than five minutes perform AHRS calibration procedures as described in Section 7 7 3 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 21 190 00915 01 Revision 6 Associated Invalid Data Field LRU s If software was loaded to a new GDU display be sure that the user settings for the replaced display were cleared Clear user settings by pressing the Engine Airframe Sensors All CLR key on the replaced display while applying Invalid power to it Acknowledge the on screen prompt by pressing the ENT key or the right most softkey Check for GEA related Alert messages on
241. g Air Page 5 17 System Maintenance Manual 200 B200 Series King Air Page 5 17 190 00915 01 Revision 6 5 2 2 System Failure Troubleshooting The following table provides basic troubleshooting guidance for LRU failures Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 as needed to verify interconnects Associated Low Speed Awareness Band permanently displayed With aircraft weight on wheels and the G1000 in Configuration Mode check that the RH GEAR ON GROUND Discrete In indication for GIA2 on GIA I O CONFIGURATION page is illuminated With aircraft weight on wheels and the G1000 in Configuration Mode check that the LH GEAR ON GROUND Discrete In indication for GIA1 on GIA I O CONFIGURATION page is illuminated If both indications are illuminated Green switch GIA1 and GIA2 to verify location of problem v If problem is resolved replace defective unit v If indication is not illuminated check for wiring faults between the GIAs and aircraft squat switch system TAS OKT Low Speed Awareness Band permanently inhibited With aircraft weight on wheels and the G1000 in Configuration Mode check that the RH GEAR ON GROUND Discrete In indication for GIA2 on GIA I O CONFIGURATION page is illuminated With aircraft weight on wheels and the G1000 in Configuration Mode check that the LH GEAR ON GROUND Discrete In indication for GIA1 on GIA I O CONFIGURATION page is illuminated If both
242. g for all ranges and bearings indicated press 2ND then MENU ENTER to return to the main menu Select Circular Pattern mode on the WX PA mode menu and press MENU ENTER Select bottom mount antenna configuration on the WX PA keyboard A key NOTE The MFD should be set at 100 NM or next highest available range on the 360 degree weather screen and in strike mode Use the 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 Observe the MFD to ensure the proper positioning of the test strikes Verify the strikes are within 10 degrees of the 30 degree azimuth increment and within 12 NM of 60 NM When complete set WX PA for 55 NM set the MFD for 50 NM or the next highest available range and repeat test On the MFD verify the sensor plots points just outside of 25 NM and the strikes are within 10 degrees of the 30 degree azimuth and within 5 NM of 27 5 NM Repeat above setting the MFD for 25 NM or the next highest available range and the WX PA for 15 NM On the MFD verify the positioning of test strikes are within 10 degrees of azimuth and within 2 NM of 7 5 NM Restart the G1000 in configuration mode by opening the PFD and MED circuit breakers While holding the ENT keys on the PFDs and MFD restore power by closing the PFDs and MFD circuit breakers Select the OTHER page group on the MFD The STORMSCOPE page is shown by default I
243. g load cell calibration return the servo to Garmin DRIVE SERVO Allows the technician to enter a desired RPM at which to manually drive the selected servo Direction of rotation 1s controlled by the polarity of the RPM or After the speed is entered the technician may use the ENG CLCH and DRV SRVO softkeys to drive the servo NOTE Be especially certain that the flight controls are clear and safe to operate before manually driving the servo G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 31 190 00915 01 Revision 6 SERVO DATA Shows real time reported data including servo voltage speed motor current load cell torque and clutch solenoid status A green box indicates the servo clutch is engaged SLIP CLUTCH TEST RESULTS This window is used during the automatic slip clutch torque measurement check 5 6 2 GIA Fault Log Descriptions The section was created to help determine why the GFC 700 has failed the Pre Flight Test indicated by the red PFT annunciation 1t defines the PFT sequence for the servos and the GFC 700 system and then provides troubleshooting information to help resolve failures There are 16 steps to the GFC 700 PFT The PFT is performed by both GIA s at startup and needs to pass on both GIA s before the autopilot can be engaged The PFT is only started if the AHRS has aligned the GIA s and servos are configured and the certification gains are valid If the PFT has not
244. gation solution within 5 to 10 minutes of startup provided the aircraft is outside or indoors with a GPS repeater Select the GPS STATUS page on the MFD 4th page in AUX group Two softkeys on the bottom of the display allow the user to toggle between GPS 1 and GPS 2 Verify that both receivers show 3D DIFF NAV on the MFD Continue to the VHF COM Interference test NOTE It may be necessary to temporarily disable or move away from GPS repeaters while testing as repeaters may adversely affect GPS receiver performance Page 7 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 VHF COM Interference Test This test must be conducted outside Use of a GPS repeater inside a hangar may result in a failed test This procedure assumes that the system 1s currently set to 25 kHz COM channel spacing Once the signal acquisition test has been completed successfully perform the following steps l 2 Fe SA E a 10 11 12 13 14 15 16 7 18 19 On the MFD monitor GPS signal strength bars on the AUX GPS STATUS page On the PFD ensure that the CDI is set to GPS If it is not press the CDP softkey until GPS ENR is displayed Verify that the GPS INTEG flag is out of view Select 121 150 MHz on the No 1 COM transceiver Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels During the transmit period verify that the GPS INTEG
245. ge repeatedly in the case of intermittent failures The box next to each channel indicates the current status of the channel per the below e Red X data path is known to be failed e Amber question mark data path status is unknown e Green checkmark Y data path is known to be good Page 5 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 The applicable data paths can be verified by viewing the following configuration mode pages 5 2 1 1 GDU RS 232 ARINC 429 CONFIG Page PFD 1 RS 232 PFD1 GMC 710 data path is functioning correctly PFD1 GMC 710 data path is not functioning correctly e Verify GMC710 is powered on o IfGMC 710 will not power on remove unit and verify power and ground are present at the GMC connector If power or ground is not present troubleshoot aircraft wiring for faults If power and ground are present replace CHNL2 GMC 710 GMC 710 Load PFD1 and GMC 710 configuration files Swap PFD land PFD2 to confirm if the problem is in the original PFD1 o Replace original PFD1 if box turns green after swapping displays e Check the PFD1 GMC 710 interconnect wiring for faults Replace GMC 710 if problem remains Anbei PFD1 GMC 710 data path functionality is unknown Reload PFD1 configuration file G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 5 190 00915 01 Revision 6 PFD 1 ARINC 429 PFD1 GRS 77 1 data path is functioning
246. goes blank PFD1 and MFD remain in normal display formats The following illuminate on PFD1 HDG NO COMP illuminates on PFD1 ROLL NO COMP illuminates on PFD1 PIT NO COMP illuminates on PFD1 IAS NO COMP illuminates on PFD1 ALT NO COMP illuminates on PFD1 GMA2 Fail GMA2 is inoperative XPDR2 Fail XPDR2 is Inoperative For a PFD1 failure condition the following shall occur PFD1 goes blank PFD2 and MFD remain in normal display formats The following illuminate on PFD2 HDG NO COMP illuminates on PFD2 ROLL NO COMP illuminates on PFD2 PIT NO COMP illuminates on PFD2 IAS NO COMP illuminates on PFD2 ALT NO COMP illuminates on PFD2 GMA1 Fail GMA1 is inoperative XPDR1 Fail XPDR1 is Inoperative G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 8 1 4 G1000 Cooling Fan Fail Annunciation Check Do the following to verify the cooling fans and annunciations are functioning properly Step oC Desired Result Cooling Fan Failure Conditions For the cooling fan failure conditions verify that the 1 Ensure the G1000 is in normal mode and following alert messages are displayed verify that there are no fan related alert e AVN FAN 1 FAIL Avionics cooling fan 1 is messages displayed in the PFD1 or PFD2 inoperative Alerts Window Pull the following cooling fan circuit AVN FAN 2 FAIL Avionics cooling fan 2 is breakers inoperative a PFD GIA FANS LEFT PFD 1 FAN FAIL
247. gure both GEA s to their new locations to confirm if the problem is in the original GEAL o Replace original GEA 1 1f box turns green after swapping units Check the GIA2 GEA 1 interconnect wiring for faults Amber GIA2 GEAL1 data path functionality is unknown Reload GIA2 Amber configuration files GIA2 GEA2 data path is functioning correctly GIA2 GEA2 data path is not functioning correctly Verify GEA2 is powered on using the GEA Status page Load GIA2 and GEA2 configuration files Swap GIA2 and GIA 1 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after CHNL 2 GEA2 swapping units Swap GEA2 and GEA reconfigure both GEA s to their new locations to confirm if the problem is in the original GEA2 o Replace original GEA2 1f box turns green after swapping units Check the GIA2 GEA2 interconnect wiring for faults Amber GIA2GEA2 data path functionality is unknown Reload GIA2 Amber configuration files GIA2 GFC 700 data path is functioning correctly GIA2 GFC 700 data path is not functioning correctly e Load GIA2 configuration files GIA Gains file and GSA CHNL 4 GFC 700 software and gains file 1f LRU and Card versions are different Reference GFC section for further troubleshooting Amber GIA2 GFC 700 data path functionality is unknown Reload GIA2 configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series Kin
248. he ENG CLCH softkey on the PFD With the clutch engaged take hold of the aircraft controls and manually overcome the clutch Move the control surface to be tested from stop to stop a minimum of two times each direction Position the control surface in the neutral position full forward position if the PITCH SERVO is selected Press the DIS CLCH softkey IMPORTANT If the test must be stopped firmly grasp the aircraft control being moved and press the red AP DISC switch on the aircraft control stick If an abnormal disconnect of a servo occurs reset AFCS SERVO circuit breaker and repeat the step Manually select 2 50 rpm for the Drive Servo and press ENT Press the ENG CLCH softkey 10 Press the DRV SRVO softkey 11 Allow the selected servo to drive the control surface to either the NOSE DOWN stop Pitch and Pitch Trim or the LEFT stop Roll and Yaw G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 21 190 00915 01 Revision 6 12 13 14 15 16 17 18 19 20 Allow the servo to continue driving against the control stop for at least 50 seconds Observe the TORQUE values displayed in the Servo Data field and record the maximum and minimum values in Table 4 10 or in the appropriate aircraft maintenance records Manually select 0 00 rpm for the Drive Servo and press ENT Allow the servo to stop Manually select 2 50 for the Drive Servo and press ENT Allow the selected servo to drive
249. he forward cabin lower fuselage at F S 185 The pitch yaw and pitch trim servos are located in the tail Power to the servos is received from the avionics No 2 bus All servos mount to a Garmin GSM 85A or GSM 86 Servo Gearbox The GSM 85A 86 is responsible for transferring the output torque of the GSA 80 servo actuators to the mechanical flight control surface linkage The GSM 85A has a slip clutch that can be adjusted to a desired torque value The GSM 86 has a clutch cartridge that cannot be adjusted to a different torque value Figure 2 17 Servo 2 1 18 Garmin G36 and 37 GPS WAAS Antennas This installation uses one G36 GPS WAAS antenna and a G37 GPS WAAS XM antenna The antennas are located in the upper forward cabin at F S 152 2 1 19 Signal Conditioner 2 Each GEA 71 receives signals from its on side engine turbine speed sensor propeller speed sensor and fuel flow sensors via a Meggitt Vibro Meter Signal Conditioner This unit converts the signals from the engine sensors to a signal usable by the GEA 71 These units are installed behind the instrument panel Electrical power to the No 1 Engine Signal Conditioner is provided from Dual Fed Bus No 1 and to the No 2 Engine Signal Conditioner from Dual Fed Bus No 2 Both signal conditioners will power up immediately with external or aircraft power or battery operation NOTE On serial numbers BB 1484 1486 and subsequent the electrical system includes the L ENG INSTR and RENG
250. hes are operating correctly by performing the following l 10 11 Actuate both sections of the PITCH TRIM NOSE UP NOSE DN switch to activate Manual Electric Pitch Trim MEPT Verify the trim clutch engages and the trim wheel drives in the requested direction Check operation in both the up and down direction Press the AP YD DISC TRIM INTRPT switch and hold while actuating the manual electric trim switch Verify trim does not run and the trim wheel rotates freely when moved manually Release the AP YD DISC TRIM INTRPT button and PITCH TRIM switch Engage the autopilot by pressing the AP key on AFCS mode controller Press and hold the left section of the manual electric trim switch Verify the Autopilot disengages normally with an aural alert and the trim wheel rotates freely when moved manually Engage the autopilot again by pressing the AP key on the AFCS mode controller Verify the pitch and roll clutches engage and resist movement of the control wheel Press and hold the CWS switch and verify the control wheel moves freely when moved manually Verify the green AP at the top of PFD1 and PFD2 is replaced by a white CWS Release 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 wheel moves freely when moved manually Verify the green AP at the top of PFD1 and PFD2 is rep
251. hose aircraft equipped with an ADF 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to select ADF Option Press ENT key on PFD 1 4 Verify the ADF Option is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ES N A f GMA COPIL N A mi Figure 3 24 ADF Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for GIA2 GMA PIL and GMA COPIL e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 27 190 00915 01 Revision 6 3 14 DME Option Configuration This section loads the necessary configuration files for those aircraft equipped with a DME 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT
252. ibed in the following steps 1 Connect to an available network reference Section 7 28 for details 2 Using the large FMS knob select the AUX page group on the MFD Using the small FMS knob select the AUX REPORT STATUS page 3 Press the MENU key on the GCU to display the PAGE MENU window 4 With the Register With GFDS option highlighted press the ENT key on the GCU to display the GARMIN FLIGHT DATA SERVICE REGISTRATION window 5 Using the keypad on the GCU enter the access code provided by Garmin Product Support during the initial activation of the system in the NEW REGISTRATION ACCESS CODE field and press the ENT key on the GCU NOTE The replacement GDL 59 unit must be registered again even if the MFD already shows REGISTERED in the STATUS window 6 With the REGISTER field highlighted press the ENT key on the GCU 7 Verify that the STATUS field indicates REGISTERED and that the data displayed in the CURRENT REGISTRATION field matches the aircraft information Page 7 64 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 28 GDL 59 Wi Fi Data Link Functional Check This check verifies GDL 59 Wi Fi Data Link interface is configured and is functional This check requires an operating and available wireless network to be within range of the aircraft NOTE This check only verifies the data output from the G1000 equipment Any equipment wiring added that is not part of the i
253. ing Jack aircraft to allow operation of landing gear reference King Air 200 Series Maintenance Manual Chapter 7 00 00 Ensure both left and right throttles are at IDLE position While monitoring pilot and copilot XM audio retract landing gear to the full up and locked position and verify the following e landing gear warning horn is active e XM audio is muted in the pilot and co pilot stations Increase both left and right throttles forward of IDLE position towards takeoff position and verify the following e landing gear warning horn is not active e XM audio can be heard For aircraft not equipped with a tone generator deselect mute softkey or adjust XM volume to restore XM audio Extend landing gear to the full down and locked position and return both throttles to idle position Remove aircraft from jacks Ensure STALL WARN circuit breaker is closed While monitoring pilot and copilot XM audio press the STALL WARN TEST switch and verify the following e Stall warning tone is active e XM audio is muted in the pilot and co pilot stations Release the STALL WARN TEST switch and verify the following e Stall warning tone is not active e XM audio can be heard For aircraft not equipped with a tone generator deselect mute softkey or adjust XM volume to restore XM audio G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 5 190 00915 01 Revision 6 7 3 GIA 63W Integrated Avionics Unit Original GIA 63
254. ing Air 190 00915 01 3 5 G1000 Normal Mode To start the G1000 system in Normal Mode 1 With a ground power unit connected to the external power receptacle set the BAT switch to ON The following G1000 equipment is powered PFD displays amp MFD display GRS 77 AHRS Units GDC 74B Air Data Computers GIA 63W Integrated Avionics Units GEA 71 Engine Airframe Units GCU 477 FMS Control Unit GMC 710 Autopilot Control Unit 2 Set the AVIONICS MASTER switch to ON The following G1000 equipment is powered GTX 33 Mode S Transponders GMA 1347D Digital Audio Panels GDL 69A Datalink Unit GSA Servos GWX 68 Weather Radar Unit The G1000 system is now powered in the normal mode In the normal operating mode data fields that are invalid have large red X s through them A valid field does not display a red X Allow the displays to initialize for approximately one minute The GDC 74Bs requires a longer initialization period than do the other LRUs During normal operation this causes the airspeed altitude vertical speed and OAT fields to be invalid during the first 40 60 seconds of PFD power up The PFDs and MFD will function as specified in the G1000 200 B200 Series Cockpit Reference Guide when the system has been correctly installed and configured G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 5 190 00915 01 Revision 6 3 6 Reversionary Mode Reversionary mode allows for display of
255. ing power If a circuit breaker is tripped determine source of short before resetting breaker Ensure circuit breakers have not failed and power wire connections are secure Swap PFD1 and PFD2 v If problem follows unit replace the display Please note the position it failed in PFD1 2 v If problem does not follow unit troubleshoot aircraft wiring for fault DO NOT insert a screwdriver of any length into the card slot DO NOT pry against the overlay DO NOT force the SD Card out Use a small screwdriver in the groove on the side of the exposed end of the card to help pull out the card Push the card in further to release the card locking mechanism Check SD Card for having more than one label Two or more labels on the card will cause sticking Y Remove all but one label Ensure the SD card is from Toshiba or SanDisk Use of other SD Cards is not recommended If card was inserted with the label facing to the right do not attempt to remove Return the unit to Garmin for repair Go to the GDU TEST page in configuration mode and verify button Knob or joystick operates correctly by observing a change in color from red to green in the button knob joystick icon when the button knob joystick is pressed If a button is stuck the button icon will be green without pressing the button as soon as you turn to the GDU TEST page v If problem is verified replace GDU Page 5 44 G1000 GFC 700 System Maintenance Manual
256. io panel to place the MED in reversion mode 3 With PFD1 in Configuration Mode go to the GFC Page Group and select the GFC STATUS page using the FMS knobs GFC STATUS SELECT GIA UNIT SELECT SERVO AXIS GIA 1 PITCH SERVI GIA STATUS AP DISCONNECT MONITOR BOARD STATUS SERVO PROGRAM 1 AP DISCONNECT PFT HIGH RES LOAD CELL CAL m HIGH RNG LOAD CELL CAL SLIP CLUTCH TEST RESULTS NOSE DOWN in lb inib CLUTCH ENGAGE STATUS TEST SVO TEST ALL ENG CLCH DRY SRVO RST GAIN Figure 4 3 GFC Status Page IMPORTANT It is highly recommended that the following test be performed at temperatures between 50 F and 120 F Use the FMS knob to select the desired servo Pitch Roll Yaw or Pitch Trim Verify that the PFT status field shows PASSED Verify that the aircraft control surface to be checked 1s free to travel throughout its range of motion a a ee Press the TEST SVO softkey on the PFD Follow prompts to begin the test IMPORTANT If the test must be stopped firmly grasp the aircraft control being moved and press the red AP DISC switch on the aircraft control wheel If an abnormal disconnect of a servo occurs reset the AFCS SERVO circuit breaker and repeat the test 8 When test is completed verify the CLUTCH TEST PASS message is displayed on the MFD 9 Repeat steps 4 through 8 for each servo axis Pitch Roll Yaw and Pitch Trim 10 Ifthe CLUTCH TEST FAIL message is displayed on the
257. ion When the G1000 Alerting System issues an alert the ALERTS softkey is used as a flashing annunciation to accompany the alert During the alert the ALERTS softkey label changes to ADVISORY as shown in Figure 5 3 Pressing the ADVISORY softkey annunciation acknowledges the presence of the alert and displays the advisory message in the Alert Window ADVISORY Figure 5 3 ADVISORY Softkey Annunciation System Failure Annunciations Typically a large red X appears in windows when a failure is detected in the LRU providing the information to the window Page 5 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Aural amp Audio Alerts The G1000 system is capable of issuing audio and aural voice alerts for various situations The following alerts are utilized by the G1000 Caution Terrain Caution Terrain voice and TAWS Caution alert Reduced required terrain clearance Terrain Ahead Terrain Ahead voice Or Imminent impact with terrain Terrain Terrain Pull Up Pull Up voice and TAWS Warning alert Reduced required terrain clearance Terrain Ahead Pull Up Terrain Ahead Pull Up voice Or Imminent impact with terrain Terrain Terrain voice TAWS Caution alert GPWS mode 2 Excessive Closure Rate o a TAWS Caution alert GPWS mode 4A B C Flight into terrain Too Low Terrain voice fakeco on hishspesd z ms TAWS Caution alert GPWS mode 4A B
258. ions as described in Section 3 9 Reloading the baseline configuration disables all previously enabled options 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight ESP Support no AOA Press ENT key on PFD1 4 Verify ESP Support no AOA is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD CO LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ALERTS N A GIA 1 N A GIA 2 N A Figure 3 33 ESP Support Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME ALERTS GIA 1 and GIA2 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 35 190 00915 01 Revision 6 3 22 GDL 59 Wi Fi Data Link Option Configuration Follow this procedure to enable the optional GDL 59 Wi Fi data link function Note that if the GDL 59 option is reloaded for any reason the GSR 56 option must also be reloaded per Section 3 23 l With
259. ipment Check the servo control cables in accordance with AC 43 13 1B Chapter 7 Section 8 Paragraph 7 149 to ensure no fraying corrosion or other damage exists If the condition of the cable is questionable replace it with a new one Check the tension on the control cables Refer to the respective servo installation drawing listed in Table 1 2 for cable tension specifications Ensure that each cable is correctly attached to the clamps Follow recommended checks for checking main control cables following the instructions in Chapter 27 Flight Controls of the King Air 200 Series Maintenance Manual listed in Table 1 2 Reinstall the access panels if no other maintenance is to be performed The GMU 44 units are mounted in the tailcone To gain access remove tailcone Refer to King Air 200 Series Maintenance Manual listed in Table 1 2 for removal instructions For each GMU 44 do the following Remove the three Phillips screws holding the GMU access plate to the mounting bracket Be sure to use a non magnetic screwdriver to avoid harming the GMU Carefully remove the assembly taking care not to damage unit or wiring and inspect the GMU 44 and mounting plate GMU 44 Qty 2 Inspect the mounting hardware and GMU 44 for corrosion or other damage Inspect all exposed GMU wiring and ensure no chaffing wear or other damage exists in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Tail Wire Harness Rou
260. ir 200 antennas Series Maintenance Manual section 53 10 00 chart 201 1 000 cycles repeat G1000 Accessories Configuration Module Replacement Qty 7 Removal amp Replacement GEA 71 Backshell Thermocouple Qty 2 Removal amp Replacement GTP 59 OAT Probe Removal amp Replacement 6 7 On Condition Qty 2 Removal 8 Replacement PFD MFD and GIA ee Cooling Fans Qty 5 Refer to Master Drawing List listed in Table N A 1 2 for installation drawings G1000 Lightning Protection Perform the Phase 3 electrical bonding Test Perform the Phase 4 electrical bonding resistance check of G1000 equipment a Phase 4 Lightning Strike to pect the antenna probe and surrounding T or Antenna installation per Table 4 9 4 4 On Condition Actual or Suspected Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 7 190 00915 01 Revision 6 Be ia Manual Engine Airframe Sensors ITT Thermocouple Cable Qty 2 Oil Pressure Sensor Qty 2 Oil Temperature Sensor Qty 2 Removal amp Replacement Torque Transmitter Refer to King Air 200 Series Maintenance Qty 2 Manual listed in Table 1 2 N A On Condition Fuel Flow Transmitter Qty 2 Prop Tachometer Qty 2 Engine Speed Tachometer Qty 2 signal conditioner Qty 2 6 22 Removal amp Replacement On Condition Annunciator Switch 6 23 Prop S
261. irm if the problem is in the original GIA1 o Replace original GIA1 if box turns green after swapping units GRS 77 1 Swap GRSI and GRS2 no reconfiguration required ref GRS Configuration and Testing sections to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the GIA1 GRS 77 1 interconnect wiring for faults bas GIA1 GRS 77 1 data path functionality is unknown Reload GIA 1 configuration files Page 5 12 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 GIA2 RS 232 GIA2 GDC 74 2 data path is functioning correctly GIA2 GDC 74 2 data path is not functioning correctly e Load GIA2 and GDC 74 2 configuration files e Swap GIA2 and GIA1 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA 1 CHNL 1 GDC 74B 2 o Replace original GIA2 if box turns green after swapping units Check the GIA1 GDC 74 2 interconnect wiring for faults Replace GDC 74 2 if problem remains Amber GIA2 GDC 74B 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GRS 77 1 output data path is not monitored A white N A box is normal GIA2 GTX 33 2 data path 1s functioning correctly GIA2 GTX 33 2 data path is not functioning correctly e Load GIA2 and GTX 33 2 configuration files e Swap GIA2 and GIA1 reconfigure both GIA s to their new locatio
262. is complete When this is done the TEST COMPLETE field stops blinking 9 PFD informs the operator if the installation has passed or failed the magnetometer interference test If the test passes no further action is required for this test If the test fails the installation should be considered unreliable until the source of magnetic interference is identified and remedied When the magnetometer interference test fails record the three magnetometer maximum deviation values and their corresponding timestamps Any maximum deviation value greater than 2 5 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 NOTE Three common reasons for a failed magnetometer interference test are 1 rudder bellcrank or other structure has become magnetized 2 new equipment is installed in close proximity to the GMU 44 magnetometer and 3 an existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair 10 Press the ENT key on the PFD to conclude this procedure G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 73 190 00915 01 Revision 6 5 16 GDC 74B Troubleshooting 5 16 1 Air Data Common Problems Symptom Recommended Action e Perform a pitot static check per Sectio
263. is to be performed continue to the return to service checks in Section 8 Page 7 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 16 FliteCharts Functional Check Reference Section 3 20 FliteCharts Configuration for configuring FliteCharts NOTE This test is not required if ChartView is enabled 1 With the G1000 in Normal Mode use the GCU FMS knob to select AUX System Status page then select MFD1 DB softkey 2 Use the small FMS knob to scroll to CHART 3 Verify FliteCharts is displayed in blue text adjacent to CHART 4 Verify the FliteCharts database cycle number is displayed in blue text and the FliteCharts database 1s current 5 Deactivate the cursor and use the GCU large FMS knob to select the Navigation Map Page then press the SHW CHRT softkey 6 Verify the airport chart is displayed and the following softkeys are displayed some softkeys may be grayed out e CHRT OPT e CHRT e INFO 1 e DP e STAR e APR e WX e NOTAM e GO BACK 7 Press the CHRT OPT softkey and verify the following softkeys are displayed some softkeys may be grayed out e ALL e HEADER e PLAN e PROFILE e MINIMUMS e FIT WDTH e FULL SCN e BACK If no other service 1s to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 37 190 00915 01 Revision 6 7 17 ChartView Functional
264. it the GTS 850 is a TCAS I unit The installation includes a top directional antenna GA 58 paired with a GPA 65 power amplifier low noise amplifier PA LNA unit and a bottom unamplified GA 58 antenna The GTS 8XX is located in the nose avionics bay on the top left shelf The GPA 65 is located in the left sidewall area just in front of the most forward cabin window The GTS 8XX traffic system is powered from the Avionics No 2 bus Figure 2 15 GTS 8XX Traffic System 2 1 16 GWX 68 Weather Radar The GWX 68 Airborne Weather Radar provides weather radar data output to the GDU 1500 MFD The GWX 68 is mounted forward of the forward bulkhead at F S 30 Power to the GWX 68 is received from the avionics No 1 bus Data received from the GWX 68 is routed through the GDL 69A data link unit to the MED via high speed data bus Ethernet Figure 2 16 Weather Radar G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 9 190 00915 01 Revision 6 2 1 17 GSA 80 Servos and GSM 85A 86 Servo Gearboxes 4 The Garmin GFC 700 AFCS uses GSA 80 high torque servos to automatically control aircraft pitch roll yaw damper turn coordination and pitch trim The pitch trim variant of the GSA 80 is a high speed servo actuator The GSA 80 contains a motor control and monitor circuit board as well as a solenoid and a brushless DC motor The GSA 80 servo receives serial RS 485 data packets from the GIA 63Ws The roll servo is located in t
265. its connections to the G1000 STC installed equipment IMPORTANT Aircraft modified by this STC are eligible to be approved for RVSM operation RVSM critical maintenance instructions contained in this document must be followed in order to guarantee performance within RVSM specifications Figure 2 8 Air Data Computer 2 1 9 OAT Probe 2 The Garmin GTP 59 OAT Probes provide the GDC 74B with air temperature data The OAT probes are mounted to the bottom of the fuselage at F S 113 5 Figure 2 9 OAT probe Page 2 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 1 10 GRS 77 Attitude amp Heading Reference System 2 The Garmin GRS 77 AHRS units provide attitude and heading information to the G1000 system The units mounted in the nose equipment bay contain advanced tilt sensors accelerometers and rate sensors The unit interfaces with the GDC 74B and GMU44 Magnetometer and utilizes GPS signals from the GIA 63Ws Actual attitude and heading information is sent using ARINC 429 digital interface to both GDU 1040As and GIA 63Ws The GRS 77 interfaces with and provides power to the GMU 44 Magnetometer The GRS 77 supplies attitude and heading information directly to the PFDs MFD and GIAs GRS receives primary electrical power from the Essential Bus and a secondary power supply from the Dual Fed No 1 Bus GRS 2 receives electrical power from Dual Fed No 2 bus Figure 2 10 AHRS
266. k GTX 33 33D configuration settings for GIA1 and GIA2 Check GTX 33D GIA1 interconnect AREA Check GTX 33D GIA2 interconnect A GTX 33 Perform a SET gt ACTV configuration reset on the GTX XPDR2FAIL Config page for each GTX and verify the aircraft o registration is present Replace GTX 33 33D Y If problem persists replace GIA TAS FAIL AIRSPEED FAIL ALTITUDE FAIL Inspect GDC 74B pitot static plumbing integrity VERT SPEED FAIL p p p g ony Inspect pitot static ports and associated equipment for faults For TAS failure also check GTP 59 probe Check GDC 74B configuration settings for the PFDs MFD GIA1 and GIA2 v If PFDs MFD and GIA configuration settings are correct replace the GDC configuration module v If problem persists replace the GDC 74B e Check OAT probe wiring and connectors for faults e Check GDC config module wiring for damage replace If any is found Es e Replace GDC config module e Replace GDC 74B with a known good unit v If problem persists replace the GTP 59 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 19 190 00915 01 Revision 6 GDC 74B Associated Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring State in the cabin e Cycle GRS 77 power to restart initialization e Ensure GRS 77 connecter is secure and proper wire harness strain relief is provided e Ensure the GRS 77 is fastened down
267. knobs to set VOR1 and VOR2 course pointers to aircraft heading CDI Synchronization must be set to OFF on the AUX SYSTEM SETUP 1 page on the MFD Verify full scale deflection of VOR1 and VOR2 CDI by varying the selected course at least 10 left and right Reset course pointers to aircraft heading Engage the autopilot and press the NAV key on the AFCS mode controller Using the CRS1 knob alter course by 10 to the right Verify the flight director and aircraft controls respond by flying to the VOR course Repeat to the left Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller Verify FD is coupled right as indicated by a right pointing arrow on the AFCS mode controller next to the XFR button Repeat step 5 using CRS2 knob while coupled to PFD2 Set CRS1 and CRS2 course pointers to aircraft heading Simulate a Localizer Glideslope signal Tune this signal on NAV 1 and NAV 2 receiver Set the PFD1 HSI to LOCI and PFD2 HSI to LOC2 by pressing CDI soft key until LOC1 and LOC2 is selected Use the test equipment to center the deviation bars localizer and glideslope on PFD1 and PFD2 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 glideslope signals using the test equipment Verify that the Flight Director and flight controls respond appropriately Couple FD to PFD1 by pressing the XFR button on the AFCS mode controll
268. kout Box Ensure that 28 VDC is not present If the flap information is incorrect troubleshoot in accordance with King Air 200 Series Maintenance Manual procedure 27 31 00 Using the force applicator slowly apply a negative Tip Gram TG force forward UP on the vane until the stall warning horn sounds Record the flaps retracted Pot 0 TG value Return the force on the vane to 0 TG 11 Approach Flaps Pot 1 measurement a b C d Run the flaps to the APPROACH position Install voltmeter leads between TP5 H1 and TP2 Lo TP6 Hi and TP2 Lo of the SK100360 Breakout Box Ensure that 28 VDC is ONLY present between TP5 and TP2 If the flap information is incorrect troubleshoot in accordance with King Air 200 Series Maintenance Manual procedure 27 31 00 Using the force applicator slowly apply a negative TG force forward UP on vane until the stall warning horn sounds Record the approach flaps Pot 1 TG value Return the force on the vane to 0 TG 12 Flaps Extended Pot 2 measurement Page 7 50 Revision 6 a b Run the flaps to the FULL DOWN position Install voltmeter leads between TP5 H1 and TP2 Lo TP6 Hi and TP2 Lo of the SK100360 Breakout Box Ensure that 28 VDC is ONLY present between TP6 and TP2 If the flap information is incorrect troubleshoot in accordance with King Air 200 Series Maintenance Manual procedure 27 31 00 Using the force applicator slowly apply a negative TG force forward
269. laced NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features i e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number 1 The entire G1000 system must be re configured Insert the correct G1000 software loader card into PFD 1 2 Start the G1000 in configuration mode Go to the System Upload Page on PFD 1 3 See Section 3 9 for instructions on how to use the System Upload page Check all configuration files and reload them 4 After reloading configuration files examine the G1000 installation for any installed configuration options Options are listed in Section 3 9 Load optional files as necessary 5 Continue to Section 8 and conduct the return to service checkout Page 6 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 6 17 GEA 71 Backshell Thermocouple Removal amp Replacement The GEA 71 has a K Type thermocouple Item 1 shown below installed in 1ts backshell in addition to the configuration module The thermocouple is used in conjunction with the configuration module temperature sensor to compensate for temperature probe errors resulting from the dissimilar metals at the pin contacts Figure
270. laced by a white CWS Release the CWS switch and press the AP YD DISC TRIM INTRPT switch on the pilots control wheel Verify the autopilot disengages with a flashing amber AP annunciation on PFD1 and PFD2 accompanied by an aural alert Verify that the control wheel is free in pitch and roll axes Engage the autopilot again by pressing the AP key on the AFCS mode controller Open AFCS SERVOS circuit breaker Verify the autopilot disconnects and the abnormal disconnect is provided consisting of a continuous aural alert and a flashing red white AP annunciation Verify no AFCS annunciations e g AFCS PFT Mistrim remain on PFD1 or PFD2 Press the AP YD DISC TRIM INTRPT switch to cancel the abnormal alert Close the AFCS SERVOS circuit breaker to restore power to the system and wait for completion of the pre flight test sequence Engage the autopilot again by pressing the AP key on the AFCS mode controller Ensure the autopilot is coupled to GIA 1 by verifying the arrowhead next to the XFR key on the AFCS mode controller is pointing to the pilot s side If the arrowhead points to the copilot s side press the XFR key Open GIA 1 primary and secondary circuit breakers Verify the autopilot disconnects with a continuous aural alert and a flashing red white AP annunciation Press the AP YD DISC TRIM INTRPT switch to cancel the alert and annunciation Close the GIA1 primary and secondary circuit breakers and
271. layed on PFD 1 and PFD2 11 Use the pitot static test set to simulate an airspeed of 95 kts for ADC1 and 85 kts for ADC2 Verify the autopilot does not disconnect and amber comparator window text IAS MISCOMP is displayed on PFD 1 and PFD2 12 Reduce ADC1 and ADC2 airspeeds to 0 kts 13 Slowly rotate AHRS1 along the lateral pitch axis to a pitch attitude of greater than 5 degrees verify the following e AHRS2 pitch attitude does not change e Anamber PIT MISCOMP is annunciated on PFD1 and PFD2 e Autopilot disconnects at approximately 5 deg AHRS1 AHRS2 miscompare e The autopilot disconnect audio alert two hi low tones sounds e A red flashing AP annunciator on PFD1 and PFD2 e Flight director command bars remain in view with autopilot in HDG and ALT mode 14 Replace AHRS1 to normal attitude and verify that attitude display on PFD1 displays current aircraft attitude 15 Use the AFCS mode controller to re engage autopilot 16 Slowly rotate AHRS1 along the longitudinal roll axis to a roll attitude of greater than 5 degrees verify the following e AHRS2 roll attitude does not change e Anamber ROL MISCOMP is annunciated on PFD1 and PFD2 e Autopilot disconnects at approximately 5 deg AHRS1 AHRS2 miscompare e The autopilot disconnect audio alert two hi low tones sounds e A red flashing AP annunciator on PFD1 and PFD2 e Flight director command bars remain in view with autopilot in HDG and ALT mode G1000 GFC 700 S
272. librated VHF NAV COMI ILS ramp tester or equivalent Calibrated transponder ramp tester or equivalent Calibrated pitot static ramp tester Outdoor line of site to GPS satellite signals or GPS indoor repeater Headset microphone Ground Power Unit Capable of supplying 28 Vdc Calibrated Flight Control Cable Tension Meter or equivalent GSM 85A Servo Gearbox Slip Clutch Adjustment Tool Garmin P N T10 00110 01 and a 2 Amp 24 V DC Power Supply Calibrated torque wrench capable of measuring 0 70 1m lbs Standard sockets amp wrenches 3 8 9 16 and 13 16 Calibrated digital thermometer suitable for measuring ambient temperature Laptop with RS232 emulation software M22885 108T8234 extraction tool An 0 060 6 Spline wrench WX PA portable analyzer kit If Stormscope is installed Lift Computer Breakout Box P N SK100360 or equivalent af ESP with AOA option is installed Lift Transducer Force Applicator Kit Safe Flight P N 1952 1 3 5 if ESP with AOAoption is installed Gauging Equipment Tool SPF 4 AIM BCH GE The gauging equipment tool is used for the static port inspection for RVSM compliant aircraft only This tool is available from Hawker Beechcraft Any alternate tool authorized in the King Air 200 Series Maintenance Manual for RVSM static port measurements may be substituted for this tool Refer to Chapter 34 10 00 of the King Air 200 Series Maintenance Manual for more details G1000 GFC 700 Syste
273. lide Path Pull the PFD1 PRI and PFD1 SEC circuit breakers and re power PFD1 in normal operating mode NOTE The following steps require the movement of the flaps and landing gear This portion of the check can be accomplished in conjunction with the Landing Gear Aural Alert and XM Audio Suppression Test in Section 7 2 2 Place the airplane on jacks Ref King Air 200 Series Maintenance Manual Chapter 7 00 00 with the wheels clear of the ground Ensure all equipment and personnel are clear of the flaps and landing gear Place the flaps and landing gear in the full down positions Using an air data test set connected to the pilot side pitot static system set an airspeed of at least 190 kts as displayed on PFD1 After an alert advisory appears press the softkey directly below the flashing ADVISORY Verify the TAWS FLAP FAULT Flaps detected in the LDG position and TAWS GEAR FAULT Landing Gear detected in the DOWN position messages are present Press the ALERTS softkey to close the alerts window Place the flaps and landing gear in the full up positions Press the ALERTS softkey again to open the alerts window Verify the TAWS FLAP FAULT Flaps detected in the LDG position and TAWS GEAR FAULT Landing Gear detected in the DOWN position messages not present Return air data test set to GROUND Place the landing gear in the down position and remove the aircraft from the jacks If no other service
274. listed in Table 1 2 2 Ifno other maintenance is to be performed reinstall the servo s per Section 6 11 6 13 GCU 477 Removal 1 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn counterclockwise until they reach their stops 2 Disconnect backshell assembly from unit Reinstallation 1 Inspect connector s for damaged pins 2 Connect backshell assembly to unit 3 Hold unit flush with the pedestal ensuring locking stud alignment marks are in the vertical position 4 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn clockwise This may require applying a small amount of forward pressure to engage the 1 4 turn sockets 5 Configure and test the GCU 477 according to Section 7 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 7 190 00915 01 Revision 6 6 14 GMC 710 Removal 1 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn counterclockwise until they reach their stops 2 Disconnect backshell assembly from unit Reinstallation 1 Inspect connector s for damaged pins 2 Connect backshell assembly to unit 3 Hold unit flush with the mounting bracket ensuring locking stud alignment marks are in the vertical position 4 Use a 3 32 hex drive tool to turn each of the four locking sockets 1 4 turn clockwise This may require applying a small amount of forward pressure to engage the 4
275. ll down wiring input to the GIAs Refer position to G1000 GFC 700 Wiring Diagram listed in Table 1 2 WOW Invalid Ensure that the GIA1 PRI and SEC and GIA2 circuit breakers are closed Check weight on wheels switch inputs to GIA1 and GIA2 Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 WOW Fault Ensure that the GIA1 PRI and SEC and GIA2 circuit breakers are closed Check weight on wheels switch inputs to GIA1 and GIA2 Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 2 AVN 1 FAN FAIL Avionics cooling fan 1 is inoperative AVN 2 FAN FAIL Avionics cooling fan 2 is Ensure that the PFD GIA FAN LEFT and RIGHT and inoperative MFD FAN circuit breakers are closed PFD 1 FAN FAIL PFD 1 cooling fan is Check cooling fan wiring Refer to G1000 GFC 700 inoperative Wiring Diagram listed in Table 1 2 PFD 2 FAN FAIL PFD 2 cooling fan is Replace cooling fan Refer to Sections 6 28 and 6 29 inoperative MFD FAN FAIL MFD cooling fan is inoperative FAN FAIL MFD MFD FAN FAIL MFD cooling fan is inoperative fan is inoperative ESP FAIL ESP is inoperative Troubleshoot the GFC 700 AFCS Refer to Section 5 5 gt e Check that the MFD AUX SYSTEM SETUP 2 page Bet ee a een shows Stability amp Protection status is ENABLED e Ensure GIA units are operational and GPS satellites have been acquired e Ensure STALL WARN circuit breaker is closed ESP DEGRADE ESP
276. ll of the databases contained in the MFD and confirm that the correct databases are loaded 12 Press the MFD1 DB softkey again to toggle to PFD1 DB Scroll through all of the databases contained in the PFD1 and confirm that the correct databases are loaded 13 Press the PFD1 DB softkey again to toggle to PFD2 DB Scroll through all of the databases contained in the PFD2 and confirm that the correct databases are loaded Page 3 44 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 33 SVS Pathways Enable Follow this procedure to enable the Synthetic Vision option An SVS Pathways Enable Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE The Garmin Synthetic Vision and Pathways feature requires 9 arc second high resolution terrain databases to function Each G1000 display must be equipped with the Terrain Obstacle SafeTaxi database card installed in the lower slot NOTE When the SVS Pathways option is enabled for the first time the G1000 writes its unique system ID to the physical card and locks the files to this unique ID This prevents the SVS Pathways unlock card from ever being used to activate the SVS Pathway feature in other G1000 systems The unlock card is tied to the specific aircraft in which it was used for the first time This card MUST be kept with the aircraft for situations where SVS Pathways must be re activated 1 With
277. llation to provide power to the new Standby Instrument Bus and the new Essential bus Dual fed Buses The electrical distribution uses four individual dual fed buses referred through this document as Dual Fed No 1 Bus Dual Fed No 2 Bus Dual Fed No 3 Bus and Dual Fed No 4 Bus Each of these dual fed buses are powered from the Left and the Right Generator buses Avionics Buses The No 1 Avionics bus is powered from the Left Generator Bus via the Avionics No 1 relay The No 2 Avionics bus is powered from the Right Generator Bus via the Avionics No 2 relay Both Avionics relays are controlled using the Avionics Master Switch Left and Right Engine Instrument Buses On serial numbers BB 1484 1486 and subsequent the electrical system includes the L ENG INSTR and R ENG INSTR buses This STC relocates these two buses such that they are powered from Dual Fed Bus No 1 and No 2 respectively Prior to these serial numbers these two buses are not installed and engine instruments are powered directly from the dual fed buses Figure 2 1 shows the system with these buses installed and relocated Essential Bus The Essential bus is a new bus added by this STC It is powered from Dual Fed No 1 bus and the Isolation bus Standby Instrument Bus The Standby Instrument bus is a new bus added by this STC It is powered by the Isolation bus and provides one source of power to the standby attitude indicator and standby altimeter vibrator Entertainment
278. locity 360 kts Initiate the intruder scenario and observe the following e Traffic should be acquired at approximately 10 NM at 90 degree bearing and co altitude Observe intruder closes on own aircraft at a rate of 0 1 NM sec Verify that only a single target is displayed in the expected quadrant e The intruder should transition from Other Traffic displayed as an open diamond with 00 displayed above to proximate traffic displayed as a filled white diamond with 00 displayed above to a Traffic Advisory TA alarm yellow filled circle with 00 displayed above Page 7 62 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 NOTE The aural TA annunciations are muted if the gear is extended and the Radio Altimeter indicates below 400 feet 7 27 Activation of Garmin Flight Data Services In order to activate the optional GDL 59 wi fi datalink and optional GSR 56 satellite receiver for Garmin Flight Data Services contact Garmin Product Support at one of the following numbers M F 7 00 a m to 7 00 p m Central Standard Time Central USA e 1 866 739 5687 toll free in USA e 1 913 440 1135 worldwide Have the following information ready prior to calling e If activating services for a GDL 59 only installation o Aircraft tail number serial number manufacturer and model o Gl1000 system ID number e If activating services for a GDL 59 and GSR 56 installation o Aircraft tail number
279. lush no external doublers If any damage is found the area must be repaired Locations of existing protruding head rivets in frames and skin laps are acceptable 2 The paint including stripes must be uniform and smooth Remove any paint blisters or flaking and sand smooth Any decals or placards must be flush with no peeling edges 3 The static ports must be free from any corrosion elongation of holes deformation or obstructions If any damage is found replace the static port 4 The oxygen servicing door on the right hand side must close approximately flush with the fuselage skin and be free from damage or deformation The ELT access hole cover on the right hand side must be in place E u 7 ES 3 e pa A 2 INCHES B E SS a O AFT f CORNER MARKING TYPICAL 2 USE CONTRASTING COLOR r i 1 12 INCHES g gt STATIC PORTS ELT ACCESS HOLE e gh o RH SIDE ONLY LE a no iN i 7 i 12 INCHES 10 INCHES 14 INCHES L i AFT Figure 7 9 RVSM Critical Region Page 7 44 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 23 3 RVSM Static Port Height Inspection The Gauging Assembly p n SPF 4 Al M BCH GE is available from Hawker Beechcraft Any alternate tool authorized in the King Air 200 Series Maintenance Manual for RVSM static port measurements may be substituted for this tool Initialize the tool
280. m Maintenance Manual 200 B200 Series King Air Page 4 3 190 00915 01 Revision 6 4 3 Maintenance Intervals Table 4 1 shows systems and items installed by this STC which must undergo tests or checks at specific intervals If the interval is shown to be in flight time as well as calendar months the first interval reached should be used as the limit The inspection time tables used for this STC are aligned with the existing maintenance 200 hr phase inspection program used in the current King Air 200 Series Maintenance Manual A complete inspection cycle for the King Air 200 B200 is 800 hours or 24 calendar months divided into the following four phases Inspection Phase 1 To be performed at 200 hours and every 800 hours thereafter Inspection Phase 2 To be performed at 400 hours and every 800 hours thereafter Inspection Phase 3 To be performed at 600 hours and every 800 hours thereafter Inspection Phase 4 To be performed at 800 hours and every 800 hours thereafter Those inspections that are based on flight time calendar elapsed time or cycles shall have specific intervals stated in Table 4 1 IMPORTANT As allowed in the King Air 200 Series Maintenance Manual a tolerance of 20 hours for all phase inspections Special Inspection Items Calendar limited inspections have a tolerance of 12 days per 12 calendar months The intention of Garmin is to align this maintenance program as best possible with the existing King Air 200 B
281. m does not follow unit check G S1 antenna and cabling e Switch GIA1 and GIA2 to verify location of problem The system has detected a failure in G S1 receiver G S1 FAIL G S1 is inoperative v If problem follows the unit The system has detected a failure 4 replace GIA G S2 FAIL G S2 is inoperative in G S2 receiver Y If problem does not follow unit check G S2 antenna and cabling 5 11 4 GPS Alerts NOTE Before troubleshooting ensure that no cell phones or devices using cell phone technology are turned on even in a monitoring state in the cabin Failure Message Cause Solution S MANIFEST GPS1 software The system has detected an mismatch Communication incorrect software version loaded halted in GIA1 Load the correct GPS software See Section 3 9 for the Software Loading MANIFEST GPS2 software The system has detected an procedure mismatch Communication incorrect software version loaded halted in GIA2 GPS1 SERVICE GPS1 needs The system has detected a failure service Return unit for repair in GPS1 receiver Replace GIA GPS2 SERVICE GPS2 needs The system has detected a failure service Return unit for repair in GPS2 receiver E e The system has detected a failure Switch GIA1 and GIA2 to verify GPS1 FAIL GPS1 is inoperative m GPSi receiver dealer oi problemi v If problem follows the unit replace GIA GPS2 FAIL GPS2 is inoperative M PSD receiver Y if pro
282. m troubleshooting as installed in the King Air 200 B200 IMPORTANT Sections 6 7 and 8 provide detailed instructions on equipment removal replacement configuration and return to service testing Anytime a G1000 component or LRU is removed swapped or replaced the technician must follow the procedures given in Sections 6 7 and 8 to ensure proper operation of the system Troubleshoot the G1000 system by first identifying then isolating the specific failure to the responsible LRU There are several indications that the G1000 presents to the pilot or technician showing overall system condition A course of action should be determined based on the information presented on the display This section shows possible scenarios likely to be encountered during normal operation and gives troubleshooting guidance to the technician to resolve problems TN as DIK TRK ETE E A Ey gt LRU INFO AIRFRAME 177 17 STATUS SERIAL NUMBER VERSION ALRFRAHE C2 x100 V2 x100 gt SYS SOFTHARE VERSTON CRU PARI NUMBER N PAE Meee SYSTEM ID TORQUE ai ffs TORQUE A i CHECKLIST Lo x100 ye x100 15 a gt N EN DATABASE fn LA EN BASEMAP E 5 E ee E 5 eal ost REGION Lo x100 Lo x100 3 VERSION 5 E A E SAFETAXI 20 TURB 100 20 TURB 100 REGION VERSION CYCLE Eaa E fran EFFECTIVE F LOW F z LOW EXPTRES 2100 AVIATION p 150 a 150 REGION L50 OIL L 50 OIL F PSI 200 f PSI 200 nooooos8 LRU ARFRM DBASE ANN TEST RA TEST
283. mains as PFD1 GDC 74 1 data path functionality is unknown Reload PFD1 configuration file Page 5 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 PFD 2 RS 232 PFD2 GMC 710 data path is functioning correctly PFD2 GMC 710 data path is not functioning correctly e Verify GMC 710 is powered on o IfGMC 710 will not power on remove unit and verify power and ground are present at the GMC connector If power or ground is not present troubleshoot aircraft wiring for faults If power and ground are present replace CHNL 2 GMC 710 GMC 710 e Load PFD2 and GMC 710 configuration files e Swap PFD2 and PFD1 to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays e Check the PFD2 GMC 710 interconnect wiring for faults Replace GMC 710 if problem remains Amber PFD2 GMC 710 data path functionality is unknown Reload PFD2 configuration file G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 7 190 00915 01 Revision 6 PFD 2 ARINC 429 PFD2 GRS 77 2 data path is functioning correctly PFD2 GRS 77 2 data path 1s not functioning correctly e Verify GRS77 2 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GRS troubleshooting sections o Swap GRSI and GRS2 no reconfiguration required to confirm if the problem is in the o
284. may cause damage to occur to the connectors unit and or unit rack If heavy resistance is felt during installation stop Remove the GDL 56 and identify the source of resistance 3 Lock the unit into the rack by using the ratcheting latch mechanism 4 Reinstall the cabin center floor panel 5 Ifnew unit is installed register with Garmin Flight Data Services per Section 7 27 6 No configuration is required for the GSR 56 Test the GSR 56 according to Section 7 29 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 19 190 00915 01 Revision 6 This page intentionally left blank Page 6 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 G1000 Equipment Configuration amp Testing This section provides procedures to be followed after a piece of G1000 equipment is replaced At the beginning of each LRU section instructions are given to guide the technician for various removal replacement scenarios These instructions define necessary procedures to be followed for situations where original equipment was reinstalled as well as for situations where new equipment new serial number is installed CAUTION Remove Supplemental Database Cards from the lower slot of all displays before loading software into any unit Not removing the cards may corrupt them Replacing corrupted database cards are not covered under warranty Garmin recommends the use of SanDisk or Toshiba bra
285. mbient temperature 3 Verify that the OAT measurement shown on PFD1 and PFD2 in degrees Celsius indicate within 2 C of the ambient temperature as measured by the calibrated thermometer If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 17 190 00915 01 Revision 6 7 7 GRS 77 AHRS GMU 44 Magnetometer Original GRS 77 is Reinstalled If the original GRS 77 is reinstalled then no software loading 1s required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process If the GRS rack was not removed or loosened continue to the GRS GMU Test Section 7 7 6 If the GRS rack was removed or loosened continue to the GRS GMU Calibration Procedures Section 7 7 1 Original GRS 77 is Installed in Opposite Location for Troubleshooting If the original GRS 1 and GRS 2 are installed in opposite locations GRS 1 and GRS 2 in opposite unit racks no software loading is required If the GRS rack s was not removed or loosened continue to the GRS GMU Test Section 7 7 6 If the GRS rack s was removed or loosened continue to the GRS GMU Calibration Procedures Section TLT New Repaired or Exchange GRS 77 is Installed If a new repaired or exchange GRS 77 is installed then software must be loaded Continue to Section 3 9 for softwa
286. ment these cards are generically referred to as enable cards In some cases the actual label on the physical card may say unlock If uncertain the technician should verify the card part number prior to use Ensure that the ESP Support Configuration has been loaded per Section 3 20 or 3 21 1 With the Enhanced AFCS Unlock card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight Enhanced AFCS and press ENT key on PFD 1 3 Rotate the small FMS knob to select Enable Enhanced AFCS Press ENT key on PFD1 4 Verify Enable Enhanced AFCS is displayed in the Item window Press LOAD CONFIGURATION ID 63FE738C SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A mA N A AY Figure 3 44 ESP Enable 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for GIA1 and GIA2 e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the Enhanced AFCS Unlock Card from PFD1 Page 3 46 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 35 Aircraft Regis
287. n 7 4 1 to check for correct operation of the sensors and GEA 71 after any part has been replaced Refer to G1000 GFC 700 Wiring Diagram and King Air 200 Series Maintenance Manual listed in Table 1 2 as needed Possible Solutions for applicable engine system Check thermocouple cable ITT Replace thermocouple cable Replace GEA 71 at Check torque transmitter GEA wiring A Check power input to torque transmitter TORQUE 157 Torque FT LB Replace torque transmitter a Replace GEA 71 Check prop tachometer Signal Conditioner wiring Check Signal Conditioner GEA wiring Prop RPM Check power input to Signal Conditioner Replace prop tachometer sensor Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 Check engine speed tachometer Signal Conditioner wiring Check Signal Conditioner GEA wiring Turbine RPM Check pow input to Signal Conditioner Replace engine speed tachometer sensor Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 Check Signal Conditioner unit wiring Check power input to Signal Conditioner Fuel Flow Replace fuel flow transmitter Replace Signal Conditioner Refer to Section 6 22 Replace GEA 71 Check oil pressure sensor GEA wiring Oil Pressure Replace oil pressure sensor Replace GEA 71 Check oil temperature sensor GEA wiring Invalid Field Oil Temperature Replace oil temperature sensor Replace GEA 71 G1000 GFC 700 System Mainte
288. n 7 6 of this manual Determine which instrument is outside limits and replace The GDC may be field adjusted per Garmin Service Advisory 0720 Note Both units may individually be in spec but show a difference in altitude Do not return the GDC to Garmin for service if not outside limits Note The GDC 74B software for the 200 B200 contains error correction at 19 000 feet and above The standby altimeter does not contain any correction GDC Config file does not load e Replace GDC config module v If problem persists replace GDC config module wire harness 5 16 2 GDC 74B Alerts Failure Message Cause Solutions S MANIFEST GDC1 software mismatch Communication halted The system has detected an e Load correct software version See Section 3 9 for the Software Altitude is different than standby altimeter incorrect software version loaded MANIFEST a GDC2 software in the specified GDC 74B Load Procedure mismatch Communication halted Page 5 74 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 17 GWX 68 Troubleshooting 5 17 1 GWX 68 Alerts and Problems WARNING Before energizing the equipment be sure microwave radiation safety precautions including both fuel and personnel safety considerations have been observed These include clearing all personnel to an area beyond the maximum permissible exposure level MPEL boundary The MPEL for the GWX 68 is 11 feet F
289. n Checks Perform engine indicating systems checks for the following left and right engine indications Reference King Air 200 Series Maintenance Manual Chapter 77 00 00 Engine Indicating Maintenance Practices O ITT e NI O N2 e Torque 7 4 3 GEA Fuel Flow Indication Functional Check The special tools and equipment listed in Table 7 1 are provided for reference only and are not specifically required Any product conforming to the specification listed may be used It 1s the responsibility of the technician or mechanic to determine the applicable specification prior to testing Table 7 1 Fuel Flow Indication Special Equipment ame Requirement Signal Generator 0 10Vdc 0 1k Hz The following steps are required to be completed on both engines as necessary l Remove the engine cowling Ref King Air 200 Series Maintenance Manual Chapter 71 10 00 to gain access to the engine MTS fuel flow transmitter connector P6 2 Disconnect the P6 connector from the fuel flow transmitter 3 Connect the Decade Box set to a resistance of 1000 Q to pins C and D of the P6 connector 4 Connect the Signal Generator to pins A and B of the P6 connector 5 Apply external power to aircraft 6 Set the BATT and AVIONICS MASTER PWR switches to ON 7 Inject a 25 mV P P signal with the signal generator and simulate the frequencies specified in the table below 8 Observe MFD in normal mode and verify fuel flow indications ma
290. n PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight Configuration Files and press ENT key on PFD1 3 Rotate the small FMS knob to highlight Enable TAWS Press ENT key on PFD1 4 Verify Enable TAWS is displayed in the Item window Press LOAD CONFIGURATION ID 63FE738C SYSTEM UPLOAD LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A of Figure 3 40 TAWS B Enable 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 De activate the cursor 8 Power down the system and remove the TAWS B Enable Card from PFD1 Page 3 42 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 31 TAWS A Enable Follow this procedure to enable the TAWS Class A function A TAWS A Enable Card as specified on General Arrangement Drawing 005 00421 03 will be required for this procedure NOTE Ensure that the TAWS A Support Configuration has been loaded per Section 3 10 Ensure that the RAD ALT Option Configuration has been loaded per Section 3 15 1 With the TAWS A Enable card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1
291. n for service Execution Fault Internal Fault Return to Garmin for service Electrical Fault Internal Fault Return to Garmin for service Whisper Shout Fault Internal Fault Return to Garmin for service Transmit Power Fault Internal voltages are out of tolerance Check power connections to the GPA 65 to verify that they are not connected to ground or each other Ensure that power and ground connections to the GPA 65 are G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 89 190 00915 01 Revision 6 ll Problem Cause Solution _____ connected in their proper place Verify input voltage and if it continues return to Garmin for service 1030 MHz Fault Internal Fault Return to Garmin for service 1090 MHz Fault Internal Fault Return to Garmin for service PA LNA Fault Antenna connections or internal fault Ensure all antenna connections are correct otherwise return to Garmin for service Receiver Fault Antenna connections or internal fault Ensure all antenna connections are correct otherwise return to Garmin for service Transmitter Fault Antenna connections or internal fault Ensure all antenna connections are correct otherwise return to Garmin for service Baro Altitude Fault Baro Altimeter is not powered on or Verify that the baro altimeter has improper wiring power and is properly wired Improper configuration settings Verify the configuration correct Temperature Fault Fan is not operating Poor ventilation at the
292. n now be turned to select either GRS 77 1 or GRS 77 2 for calibration Press the ENT key after selecting the desired GRS 77 unit to calibrate The SELECT PROCEDURE field is not blinking 8 Using the FMS small knob select MAGNETOMETER Press the ENT button 9 Use the cursor to highlight the BEFORE CALIBRATION window 10 Follow the checklist items displayed on the PFD 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 11 The PFD display advises the operator when to turn the aircraft when to stop and when to turn again Page 7 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 12 Upon instruction to turn taxi the aircraft in a right turn After approximately 25 to 30 of turn from the last heading the PFD display advises 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 the approximate 30 turn Instead of using the PFD instruction to turn as a real time indication of when to turn simply judge the 30 59 turn increments of the aircraft by using the compass rose radials Dwelling
293. nance Manual 200 B200 Series King Air Page 5 23 190 00915 01 Revision 6 5 2 4 ADF DME Failure A DME or ADF failure is represented by the following red X s Refer to G1000 GFC 700 Wiring Diagram and King Air 200 Series Maintenance Manual listed in Table 1 2 as needed Invalid Field Ensure that GIA 63 2 is properly functioning Reload the ADF option configurations Check for proper operation of the ADF receiver Ensure that the receiver is receiving power Check ADF GIA2 interconnect For other failures of the ADF system refer to King Air 200 Series Maintenance Manual listed in Table 1 2 Ensure that GIA 63 1 is properly functioning Reload the DME option configurations Check for proper operation of the DME receiver Ensure that the receiver is receiving power Check DME GIA1 interconnect For other failures of the DME system refer to the King Air 200 Series Maintenance Manual listed in Table 1 2 Page 5 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 9 3 200 B200 Specific Alerts The following alerts are configured specifically for the King Air 200 B200 installation ANNUNCIATION ADVISORY Alerts Message Advisory Solution S TAWS GEAR FAULT Landing Gear detected in Check the gear down wiring input to the GIAs Refer to the DOWN position G1000 GFC 700 Wiring Diagram listed in Table 1 2 TAWS FLAP FAULT Flaps detected in the LDG Check the flap fu
294. nctional Check The maximum map ranges for enhanced detail are configurable by the flight crew When zoomed in close enough to show the airport detail the map reveals runways with numbers taxiways with identifying letters numbers and airport landmarks including ramps buildings control towers and other prominent features Resolution is greater at lower map ranges When the aircraft location is within the screen boundary including within SafeTaxi ranges an airplane symbol is shown on any of the navigation map views for enhanced position awareness Any map page that displays the navigation view can also show the SafeTaxi airport layout within the maximum configured range The following is a list of pages where the SafeTaxi feature can be seen e Navigation Map Page e Inset map e Weather Datalink Page e Airport Information Page e Intersection Information Page e NDB Information Page e VOR Information Page e User Waypoint Information Page e Trip Planning Page e Nearest Pages 1 Use the FMS knob on the GCU to select the AUX System Status page and select DBASE softkey Use the small FMS knob to scroll to CHART category and verify FliteCharts is displayed in blue text adjacent to CHART 2 Verify the FliteCharts database REGION CYCLE number EFFECTIVE EXPIRES and DISABLES dates of the subscription appear in blue text 3 Use the FMS knob on the GCU to select MAP Navigation Map page
295. nd GIA2 to identify whether the unit or connectors wiring is at fault Both GIAs must be configured when swapped see Section 3 9 v If problem follows the unit replace GIA1 v If problem persists continue to troubleshoot remote transfer switch amp wiring Press the COM2 external remote transfer switch again to cycle its operation Check COM2 external remote transfer switch and wiring Switch GIA1 and GIA2 to identify whether the unit or connectors wiring is at fault Both GIAs must be configured when swapped see Section 3 9 v If problem follows the unit replace GIA2 v If problem persists continue to troubleshoot remote transfer switch amp wiring Check fan wiring and air tubing for proper operation if applicable Replace cooling fan if unable to determine if operating correctly Replace GIA If problem persists contact Garmin Aviation Product Support for assistance Page 5 57 Revision 6 5 11 2 NAV Alerts Failure Message Cause Solution NAV1 SERVICE NAV1 needs The system has detected a failure Replace GIA service Return unit for repair in NAV1 receiver p i NAV2 SERVICE NAV2 needs The system has detected a failure e Replace GIA2 service Return unit for repair in NAV2 receiver p i Press the NAV1 external remote transfer switch again to cycle its operation Check NAV1 remote transfer switch and wiring Switch GIA1 and GIA2 to identify whether the unit or connectors wi
296. nd SD cards to load G1000 software and configuration files If another brand of card is used and software loading problems occur replace the card with a SanDisk or Toshiba brand card and reattempt the software load WARNING Connect a ground power unit to the aircraft for software loading Do not rely on only the aircraft batteries to prevent loss of power during the software loading process DO NOT ALLOW POWER TO BE REMOVED FROM THE SYSTEM WHEN LOADING SOFTWARE Remove power only when told to do so by the following procedure As a general rule all displays should be in the same mode configuration or normal unless instructed differently 7 1 GDU 1040 1500 MFD amp PFD Original Display Reinstalled If the removed display s are re installed in their original positions no software or configuration loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the PFD MFD Test procedure Original PFD Displays Installed in Opposite Locations for Troubleshooting If the PFD 1 and PFD 2 are installed in opposite positions no software or configuration loading is required Continue to the PFD MFD Test procedure New Repair or Exchange Display s Installed If a new repaired or exchange GDU 1040A or GDU 1500 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 If ChartView or TA
297. ne to 0 TG and reposition the force applicator to apply a downward force on the vane Calculate the Pot 4 TG force by adding 14 TG to the Pot 1 TG force Example If the Pot 1 force is 9 TG add 14 TG and the Pot 4 force is 5 TG e f g h Install voltmeter leads between TP18 Lo and TP19 H1 of the SK100360 Breakout Box Apply the calculated Pot 4 TG force to the vane with the force gram applicator Adjust the Pot 4 on the lift computer until the voltage output from TP18 Lo and TP19 Hi reads 2 2 0 2 VDC on the voltmeter Return the force on the force applicator to 0 TG 11 Flaps Extended calibration Page 7 52 Revision 6 a b Run the flaps to the FULL DOWN position Using the force applicator deflect the transducer vane forward UP to the Pot 2 TG force measured in step 12 in Section 7 24 1 If the stall warning horn is already ON turn the Pot 2 CCW until the horn is OFF and then slowly turn the Pot 2 CW until the horn is ON again Press down on the vane until the horn is OFF and slowly release the vane If the horn is not ON when the vane is released turn the Pot 2 until the horn is ON Reduce the force on the vane to 0 TG and reposition the force applicator to apply a downward force on the vane Calculate the Pot 5 TG force by adding 17 TG to the Pot 2 setting G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Example If the Pot 2 fo
298. nfirm if the problem is in the original GIA 1 o Replace original GIA 1 if box turns green after swapping CHNL 2 GEA2 units Swap GEA2 and GEA1 reconfigure both GEA s to their new locations to confirm if the problem is in the original GEA2 o Replace original GEA2 if box turns green after swapping units Check the GIA1 GEA2 interconnect wiring for faults Amber SIANGEA2 data path functionality is unknown Reload GIA 1 Amber l configuration files Green Green GIA1 GFC 700 data path is functioning correctly GIA1 GFC 700 data path is not functioning correctly e Load GIA1 configuration files GIA Gains file and GSA software CHNL 4 GFC 700 and gains file if LRU and Card versions are different Reference GFC section for further troubleshooting Amber GIANGRC 700 data path functionality is unknown Reload GIA1 Amber configuration files Page 5 16 Page 5 16 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 GIA2 RS 485 GIA2 GEA1 data path is functioning correctly GIA2 GEA1 data path is not functioning correctly Verify GEA 1 is powered on using the GEA Status page Load GIA2 and GEA configuration files Swap GIA2 and GIA1 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA2 o Replace original GIA2 if box turns green after CHNL 1 GEA swapping units Swap GEA and GEA2 reconfi
299. ng is a list of some of the possible values for lt PARAMETER gt a AD TDM Comm Valid The specified mode has been disengaged because communication with the servos via the Time Division Multiplexer protocol has been lost b AP Pitch MET not stuck The specified mode has been disengaged due to a stuck pitch MET switch Check the MET trim switches for proper identification 5 6 3 GIA Pre Flight Test Steps PFT step 0 System initialization verify GFC powered This step is checking to make sure the GFC is powered up It checks to make sure the GIA AP disconnect input is connected to 28 volts and makes sure the Servos are up and communicating If this step fails make sure the GIA is connected to AP disconnect by using the GFC configuration page Also make sure all configured Servos are communicating by checking for Servo product data in configuration mode PFT step 1 System initialization verify GIA audio is valid This step is checking to make sure that the GIA audio region has been loaded and configured If this step fails load GIA audio region and audio configuration PFT step 2 System initialization verify required servos are configured This step is checking to make sure the current Servo configuration matches the Servo configuration specified in the certification gain file If this step fails then make sure the Servo configuration on the GFC configuration page matches the Servo configuration specified in the configur
300. nit is not active contact XM Customer service to have a refresh signal sent to your unit You will need to provide them the Audio Radio ID and Data Radio ID number for XM weather numbers Also verify with XM that the correct Weather package Aviator Lite or Aviator is on the account and that no traffic service has been activated against that Radio ID The unit must be on for approximately one hour after the request for the refresh has been sent to receive the signal y Alternatively you may also go to XM s website and enter the radio ID s to have a refresh signal sent If there is still problems receiving weather products after performing the above step call XM and have the account deactivated and a new account activated to clear out any corrupt account information Verify there is a good ground connection through the aircraft between the MFD and the GDL69 69A unit Reference the Aircraft Maintenance Manual for instructions on how to check bonding and ground points If problem persists replace the GDL 69 69A G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 65 190 00915 01 Revision 6 5 14 2 GDL 69A Alerts Failure Message Cause Solutions S Replace GDL 69A The G1000 has detected a failure see GDL 69A antenna and in the GDL 69A cabling Check the GDL 69A and MFD interconnect Reload configuration file See Section 3 9 for the Configuration Procedure GDL 69 FAIL GDL 69 has f
301. nless otherwise specified 8 2 1 Pre Flight Test 1 If selected ON select the BATT and AVIONICS MASTER PWR switches and ground power unit to OFF After 30 seconds select the ground power unit and BATT and AVIONICS MASTER PWR switches to ON Verify the GFC 700 begins an automatic pre flight test after AHRS and ADC parameters become valid 2 Verify that a white PFT annunciation is displayed on PFD1 and PFD2 as shown in Figure 8 4 AA ii an 113 88 118 98 WET ors Orr TR li hi2 115 98 118 98 11 00 123 898 135 325 corn 1600 ref 2 Mil 208 aT BY LOL ddr FFE LETS Gl POR LUEI TAAYREF ol ALERTS Figure 8 4 Pre Flight Test NOTE A momentarily red annunciation displayed before PFT starts is acceptable 3 Upon successful completion of the test an aural alert will sound and the annunciation will clear The aural alert is generated by either GIA 63W 1 or GIA 63W 2 alternately with each system power up Thus the PFT sequence must be run twice to verify both GIA units are providing the correct aural alert NOTE If the PFT annunciation turns red the test has failed Return to Section 5 for troubleshooting 4 Repeat Steps 3 to test the PFT aural alert for the other GIA 63W Continue to Section 8 2 2 Page 8 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 8 2 2 AFCS Switch Checks Verify that the AFCS system buttons and switc
302. nnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnos 7 10 Taole 122 3 FIELEN Let le OMS a iio ainia 7 10 Table 7 3 Oil Pressure Indication Special Equipment oooooooonooooonnnnnnnnnnnnnnnnnnnnnnnnononnnnnonnnnnnnnnnnnnnnnnnnnnnnnnos 7 11 Table 94 011 Pressure Test POINTS sust ritlctaodia 7 11 Table els A Data ym Leda ida 7 15 Table 72 Venice des 7 17 Table 7 3 Required GRS GMU Calibrations sssr innne a seetann E E E a 7 19 Table 7 4 RVSM IRGGUIFE AI li 7 43 Table 7 5 In Flight Altitude Hold Performance TeSt ooooccccccncnncnnnnnnnnononnnononnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnnoss 7 48 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page vil 190 00915 01 Revision 6 This page intentionally left blank Page viii G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 1 INTRODUCTION 1 1 Content Scope Purpose This document provides Instructions for Continued Airworthiness ICA for the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control System AFCS as installed in the Hawker Beechcraft Model 200 B200 series King Air under STC SA01535WI D This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23 1529 and Appendix G Information in this document is required to maintain the continued airworthiness of the G1000 and GFC700 1 1 1 Applicability This document applies to all Model 200 B200 series King Air aircraft
303. ns to confirm if the problem is in the original GIA 1 CHNL 2 GRS 77 1 output only White N A CHNL 5 GTX 33ES 2 w TIS o Replace original GIA2 if box turns green after swapping units Check the GIA2 GTX 33 2 interconnect wiring for faults Replace GTX 33 2 if problem remains Ambar GIA2 GTX 33 2 data path functionality is unknown Reload GIA2 configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 13 190 00915 01 Revision 6 GIA2 RS 232 continued GIA2 GRS 77 2 data path is functioning correctly GIA2 GRS 77 2 data path is not functioning correctly e Load GIA2 configuration files e Swap GIA2 and GIAI reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA 1 o Replace original GIA2 1f box turns green after CHNL6 GRS77 2 Swappie Umit Swap GRS2 and GRS1 no reconfiguration required to confirm if the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units Check the GIA2 GRS 77 2 interconnect wiring for faults Amber GIA2 GRS 77 2 data path functionality is unknown Reload GIA2 configuration files GIA2 GMA 1347D 2 data path is functioning correctly GIA2 GMA 1347D 2 data path is not functioning correctly e Load GIA2 and GMA 1347D 2 configuration files e Swap GMA 1347D 2 and GMA 1347D 1 reconfigure both GMA s to their new locations to confirm if the problem is in the origin
304. nstallation data will need separate testing and verification not covered as part of this document 1 Start the G1000 System in Normal Mode 2 Using the large FMS knob select the AUX page group on the MFD Using the small FMS knob select the AUX REPORT STATUS page 3 Press the WI FI softkey on the MFD to select the AUX WI FI SETUP page 4 Press the AVAIL softkey on the MFD to display the available WI FI networks 5 Press the FMS knob on the GCU to activate the cursor and rotate the small FMS knob to highlight the desired network in the AVAILABLE NETWORKS field 6 Press the CONNECT softkey on the MFD to connect to the network Skip to step 12 if the selected network is a non secure network 7 Ifthe selected network is a secure network enter the passcode in the ENTER PASSPHRASE field in the WPA SECURITY SETTINGS pop up window 8 Press the ENT key on the GCU to accept the passcode then press the ENT key on the GCU again 9 When the SAVE SETTINGS pop up window is displayed press the ENT key on the GCU keypad to select SAVE CONNECTION 10 Enter the appropriate airport identifier in the SELECT AN AIRPORT TO ASSOCIATE WITH THE CONNECTION field then press the ENT key on the GCU to accept the identifier 11 With the CONNECT button highlighted press the ENT key on the GCU to connect to the network 12 Press the ENT key on the GCU if the verification window Are you sure you want to connect is displayed 13 Verify that
305. nstalled on the aircraft that require the GIA config to be updated e Cycle power on the system and allow it to restart in normal mode Place the aircraft outside and allow 15 30 minutes for the GPS to acquire a position and download a new almanac v If clearing nonvolatile memory is unsuccessful and the GPS still can not acquire a position replace the GIA v If problem does not follow unit check GPS antenna and cabling G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 55 190 00915 01 Revision 6 5 11 GIA Alert Messages 5 11 1 COM Alerts Failure Message Cause Solutions COM1 SERVICE COM1 needs The system has determined e Replace GIA1 according to service Return unit for repair COM1 needs service instructions in Section 6 COM2 SERVICE COM2 needs The system has determined Replace GIA2 according to service Return unit for repair COM2 needs service instructions in Section 6 Press the push to talk switch s again to cycle its operation Check push to talk switch s and wiring Check GIA1 GMA 1347D 1 interconnect COM1 PTT COM1 push to talk The COM1 external push to talk Switch GIA1 and GIA2 to identify key is stuck PTT switch is stuck in the whether the unit or connectors wiring enabled or pressed state is at fault Both GIAs must be configured when swapped see Section 3 9 v If problem follows the unit replace GIA1 v If problem persists replace defective GMA 1347D
306. nted to ambient pressure conditions ground Pitot leak rate is not to exceed 1 knot in 1 minute b For the static leak check set the air data test set to 30 000 feet and an indicated airspeed of 120 knots Static leak rate is not to exceed 300 feet in 1 minute 2 Connect the pitot static tester to the aircraft left and right pitot and static ports Note that the standby altimeter and airspeed indicator are connected to the copilot side pitot and static lines 3 Verify that the PFD1 altimeter baro setting is set to 29 92 in Hg 1013 25 mb 4 Start PFD1 in configuration mode and navigate to the GRS page The values for altitude and airspeed are shown on the AHRS AIR DATA INPUT table as B ALT and IAS for both AIR DATA 1 and AIR DATA 2 5 Simulate the altitudes and airspeeds for each condition shown in Table 7 5 Wait for ADTS to report that target values have been achieved 6 On Table 7 5 record the altitude B ALT displayed on PFD1 for AIR DATA 1 and AIR DATA 2 for each condition 7 On Table 7 5 record the airspeed IAS displayed on PFD1 for AIR DATA 1 and AIR DATA 2 for each condition 8 Verify that the indicated altitudes and airspeeds are within allowable tolerances 9 File the results with the aircraft maintenance records If either the pilot or copilot air data system does not meet the tolerances specified have maintenance checks performed on the air data system or the pitot static system Page 7 14 G1000 GFC 70
307. ntrol oda Fourco Normal MO A ETE E E aia Figure 3 8 Automatic Reversion with MFD fallure ooonooocooooooocnncnnnnccnnnnnnnnnnnanononnnnoos Figure 3 9 Manual Reversion with pilot PFD failure oooocccncccnccnnnnnnnnnnnonannnnnoos Figure 3 10 SE AG Vs Diari ica Rietre 5 11 Cosso Communication cia Hisute 5212 Conticuration Stas ooo Figure 3 13 Data Transmission INdICAatoTS occccccccnnnonononononooononnnnnnnnnncnnnnnnnnanononnnnnos Figure 3 14 G1000 LRU Configuration File Storage ooonnnnnnnnnnnnnnnnnnnnnnnananannrrrnrrnoo nono Figure 3 15 GRS GDC Configuration Settings Storage cccccccessessessssssssseeseeeens Figure 3 16 Software Configuration Overview ccccccnnnnnooooooooonnnnnnnnnnnncnnnnnnnnnnananononnnnnos Figure 344 1 ATA Opos a Fistire 3 18 Propeller Opt ONS A eons oat a Figure 3 19 Configuration Software Load Page ccccccnnococoooooonnnnnnnnncnnnonanananannonononoos Fieiro 5220 Syste U ea a a Figure 3 21 TAWS A Support Configuration 0000ccccccccsseessesssesssssssssseseeseeeeens Figure 3 22 TAWS A Voice No Callout ConfiguratiOO ooooooooooocnnnnnocnccnononananananannnnnnoss Figure 3 23 TAWS A Voice Callout ConfIguratiON ccccooooooononononononnnnncnnnnnnnnnanan ono nnnnnos Figure 3224 ADE COnmtmeurai OI smc da E dead EEE igure 3225 DME C Omi Our al OU is ati idci ns Figure 3 20 RADALT C Oni CUT AtO il Figure 3 27 Non Garmin Traffic System Configuration
308. o J ALT MODE Figure 7 17 GTS 8XX GND TEST softkey 7 26 1 Antenna Verification The following test assures the antennas and coaxial cables are properly connected The GTS 8XX must be in Ground Test mode 1 On the MAP TRAFFIC MAP page of the MFD press the OPERATE softkey A self test of the antenna circuit is initialized If the MFD displays FAILURE at the upper left corner of the traffic display area it will be necessary to recheck the coaxial connections If MFD displays OPERATE without indicating a fault proceed to the next step of antenna verification 2 Ensure that the transmitter or receiver RX TX that you are testing is significantly closer to the ramp tester than another operating RX TX or erroneous and inaccurate results may occur All four quadrants 0 90 180 and 270 degrees will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the MAP TRAFFIC MAP page of the MFD G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 61 190 00915 01 Revision 6 Set up a stationary intruder by selecting the following on the ramp tester Intruder type ATCRBS Intruder Start Distance 2 nm Intruder Start Altitude 50 000 ft Vertical Speed 0 fpm Velocity 0 kts on some ramp testers a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario Position ramp tester at 0 degrees Initiate the
309. o GEA OP dO rai iii 4 19 Figure 4 2 Discrete Valid Invalid Indications cccccccnnononononononnnononnnnnncnnnnnnanonnnn ono nnonnnnnnnnnnnncnnnnnnnnnnnns 4 19 Figure 4 9 GFE Salas Dar da 4 20 Pte dd Go cl ed 2AM PISE oen a eee eee ne ee DC A na eee ee mes See me 4 21 Proteo de Stand DY Bate O eee eee eee es 4 31 Freire 4 60 Power Supply COMNEC OM li a 4 33 Figure Sal AUX System Slats Da A iaa 5 1 Pisure 5 2 AKES AUN AON S aid ea bieaantaeeend 5 2 Figure 5 3 ADVISORY Softkey Annunci ON 5 2 Figure 0 4 SyS Enr Annne a OS a Aaa 5 4 Figure 5 5 AFCS Annuneciation Field al 5 30 Feur o GFC Stalls Pane od 5 31 Figure 3 gt Mashelometer mterterence TES a A a 5 70 Figure 5 3 5 GIA 63 W Backplate Connect usario 5 80 Figure 3 9 GEA TL Backplate CONMECLOTS ai AA Il 5 81 Figure 5 10 GMA 134 7D Backplate Comet odas 5 81 Figure 3 11 GLX 33 33D Backplate COME A A a 5 81 Figure 5 12 GDU 1040A 1500 Backshell Connector P10401 or P1500Ol oooocnnnncccccananananananananonnn nono 5 82 Figure 5 13 GRS 77 Backshell Connector P771 cccccccceseeeeeeeeeeeseeeeeeeeeeseeeeseseeeseeeeseeeeeeeeeeegs 5 82 Figure 5 14 GDC 74B Backshell Connector P74B1 ooooonnnnnnninininonanannnonoonononnnonnorr nono ono nono nono non ono nnnnnnos 5 82 Figure 5 15 GDL69A Backplate Connector P69A Vi ie nee 5 82 Piour 5 16 GCU 477 Backshell Connector P4751 A eee ee 5 83 Figure 5 17 GMC 710 Backshell Connector PIO tn 5 83 Figure 5 18 GWX 68
310. o PFD 1 top slot G1000 must be powered on PFD 1 and MFD must have correct software and configuration settings GIA 63WSs must have correct software GIA 63Ws must be successfully configured with GIA1 and GIA2 configuration files Data path from GIA1 to each LRU must be operational Page 5 79 Revision 6 Backshell Backplate Connectors 9 21 The following figures depict the backplate connectors as viewed with the LRU removed oc E 2 S O a gt 5 Z a Z O O O E O lt x O O z Ww O _ 2 Z a Lu z O E O To SL O Oo lt x lt q oc Y z O o Lu O E LL z Z gt S 7 O mua lt oc LLI Y Z lt COM BOARD CONNECTOR P601 MAIN DISCRETE CONNECTOR P604 IO CONNECTOR 1 P605 I O CONNECTOR 2 P606 See ee Eee EEC ES SESE ESS CSCS ACACIA OD AAA REX KAKI RADA AREA TEC CC CCC CECE O E O rt Z Z O O lt zZ Z m F Z lt 9 VOR ILS CONNECTOR P602 am O _ Q LL lt lt O QO lt lt lt LL F Z lt gt lt lt Figure 5 8 GIA 63W Backplate Connectors G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 80 190 00915 01 Revision 6 16 17 18 19 20 9 10411 12 13 14 15 7 3 4 5 2 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 0000000000000000009090 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 9000000000000000000 21 22 23 24 25 26 27 28 29 30 31
311. oaded Halted in GlA2 GIA1 CONFIG GIA1 audio config error Config service req d The GIA s audio configuration files ee Rel nfiguration files are incorrect or missing eload audio configuration files GIA2 CONFIG GIA2 audio config error Config service req d Load the configuration files for that GIA See Section 3 9 for G A 63 Configuration Loading procedure GIA1 CONFIG GIA1 configuration error Config service If problem persists replace req d master configuration module check config module harness for faults and replace if necessary The system has detected a GIA NOTE configuration mismatch If GIAs New Terrain Obstacle cards are not properly configured after Jeppesen Aviation Database and being swapped replaced this other optional features i e TAWS Me ASA unlock card will need to be replaced if the master configuration GIA2 CONFIG GIA2 module is changed The G1000 configuration error Config service System ID number will change to a req d new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number HW MISMATCH GIA hardware mismatch GIA1 communication halted The G1000 has detected a non HW MISMATCH GIA hardware WAAS GIA 63 mismatch GlA2 communication halted GIA1 SERVICE GIA1 needs service Return unit for repair The G1000 has detected a failure g Replace suspe
312. ode controller Verify the command bars are level and the control wheel 1s stationary There may be some roll motion in the yoke if the aircraft not perfectly level 2 Turn the HDG knob to the left and right and check that the command bars move in the correct direction and the control wheel follows the command bars 3 Push and hold the CWS button and pull the control wheel to the center of the pitch control range Release the CWS button Verify the autopilot clutches re engage and hold the wheel stationary 4 Holding the control wheel lightly rotate the NOSE UP DN wheel on the AFCS mode controller two clicks UP to increase the pitch reference Verify the command bars move up degree and the control wheel begins moving aft In some aircraft the down spring may require manual assistance to get aft control stick movement 5 While holding the control wheel firmly press and hold the CWS button to re synchronize the pitch reference Re center the control wheel to wings level and mid range elevator travel Release the CWS button and check that servo clutches re engage before releasing the control wheel 6 Rotate the NOSE UP DN wheel on the AFCS mode controller two clicks DOWN to decrease the pitch reference Verify the command bars move down degree and the control wheel begins moving forward Hold the controls and press CWS to re center the command bars and stop control wheel movement 7 With the Autopilot still engaged and the CWS button
313. oftware Update This wizard will guide you through the process of updating the software in your 67000 integrated cockpit Airframe King Air B200 B 300 Version of card Version 098504 lt being created Please enter your SO card in the card programmer and then click Nest to proceed SS Enter SD card Cancel Click next once card is inserted G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 13 190 00915 01 Revision 6 8 Ensure the card and correct drive letter is used and click next G1000 Software Update DoR 2 GARMIN Choose the appropriate dive below and click Nest IF your drive is not listed plug it in and click Find Drive Storage Card Reader Select the drive letter used by our storage card reader Find Dire Select drive Back Cancel 9 A window will pop up onto the screen to indicate file progress Transferring Data Copying E aud rgn Copy of files to selected drive Page 3 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 10 Once successfully completed the following message window will pop up Click Finish to finalize SD card G1000 Software Update The update was successfully transterred to your card To complete the software update insert this card into your GIO00 system 3 8 3 Software Files Software files are defined by part number and ver
314. oid switch to on and move the direction switch to the clockwise or counter clockwise position Allow the clutch to rotate at least one revolution in each direction note the capstan itself is fixed 6 Observe the torque reading for at least two full revolutions in each direction Ensure the minimum and maximum torque readings are within the tolerance specified 7 Ifthe minimum and maximum torque values are within the specified range in Table 4 11 the GSM slip clutch is acceptable Reinstall the GSM 85A or GSM 86 servo gearbox per Section 6 12 8 Ifthe minimum and maximum torque values are not within the specified range in Table 4 11 the GSM 86 slip clutch cartridge must be replaced or the GSM 85A must be adjusted 9 For GSM 85A only If adjustment is required remove cotter pin and adjust the nut on the capstan as needed to obtain the torque value listed in Table 4 11 as shown on the torque wrench Position the nut to align with holes in the capstan shaft and install a new cotter pin 10 When finished remove the fixture cable and then remove the servo gearbox from the fixture 11 Install the GSM 85A or GSM 86 servo gearbox per Section 6 12 Table 4 11 GSM 85A GSM 86 Slip Clutch Torque Settings GSM 85A 65 8 in lbs 32 5 1n lbs 90 10 in lbs 135 13 in lbs GSM 86 66 19 in lbs 32 9 1n lbs 90 27 in lbs 135 40 in lbs Valid with continuous travel servo gearbox only G1000 GFC 700 System Maintenance Manual 2
315. ols on the GMC 710 allow crew control interface with the various GFC 700 autopilot flight director functions GMC 710 controls are discussed in detail in the G1000 King Air 200 B200 Series Cockpit Reference Guide The GMC 710 is powered by Dual Fed Bus No 1 Figure 2 3 AFCS Controller Page 2 2 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 2 1 4 GCU 477 FMS Control Unit The GCU 477 functions as the primary control interface to the GDU 1500 MFD The GCU 477 provides alphanumeric softkey and flight planning function keys used to interface with the G1000 the MFD does not possess any knobs or controls other than softkeys The GCU 477 is powered by the Essential Bus The GCU 477 also provides the crew with the added functionality of tuning their receivers via the GCU as well as the PFD Detailed instructions regarding the controls are discussed in the G1000 Cockpit Reference Guide Figure 2 4 FMS Controller 2 1 5 GTX 33 Extended Squitter Transponder 2 The Garmin GTX 33 transponders communicates with the on side GIA 63W through RS 232 digital interface This STC installation allows for installation of two GTX 33 non diversity transponders two GTX 33D Diversity transponders or one of each type The units are mounted under the floor in the cabin just aft of fuselage station 246 750 Power is provided by the No 1 GTX 33 from the Essential Bus The No 2 GTX 33 is powered from
316. omplished by placing a jumper between TP 2 and TP 7 of the breakout box G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 49 190 00915 01 Revision 6 CAUTION The anchor tab of the force applicator can be bent if the knob that applies tension to the transducer mounting plate is over tightened Use care when installing the force applicator to prevent damage to the anchor tab Refer to the data supplied with the force applicator 6 Install the 1952 3 gauge 2 to 15 gram scale in the force applicator see Figure 7 16 onto the left wing in accordance with the manufacturer s instructions Refer to the data supplied with the force applicator The force arm must be positioned so that the applied force is within 1 32 inch of the transducer vane tip Forces applied forward or up will be classified as minus values Forces applied aft or down will be classified as plus values Make sure that the vane is free to move with the force applicator 7 Apply external power to the aircraft 8 Place the BATT master switch to the ON position 9 Verify the STALL WARN circuit breaker on the copilot circuit breaker panel 1s set WARNING Make sure that all personnel are clear of the flap area before proceeding with these procedures 10 Flaps retracted Pot 0 measurement a b d Run the flaps to the full UP position Install voltmeter leads between TP5 Hi and TP2 Lo TP6 Hi and TP2 Lo on the SK 100360 Brea
317. only if TAWS A voice callouts 400 300 200 100 have been disabled and are now desired TAWS A voice callouts are the default configuration Follow the procedures outlined in this section to load the necessary configuration files to enable TAWS A voice callouts 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to select TAWS A Voice Callout Installation Option Press ENT key on PFD1 4 Verify the TAWS A Voice Callout Installation Option is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A ES Figure 3 23 TAWS A Voice Callout Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME e Upload Complete COMPLETE in the summary box 6 Select ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor Page 3 26 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 3 13 ADF Option Configuration This section loads the necessary configuration files for t
318. onnect the GPS antennas to remove the GPS signal Verify LOT shows on the MFD and the TAWS N A and LOT annunciations show on the PFDs 12 Reconnect or remove the shield from the GPS antennas and verify the MFD LOT indication and PFD TAWS N A and LOT annunciations are removed once the GPS satellites are acquired 13 Pull the RADIO ALTM circuit breaker Verify GPWS FAIL is displayed on PFD1 and PFD2 14 Reset the RADIO ALTM circuit breaker Verify GPWS FAIL annunciations are removed 15 Pull PFD1 PRI and PFD1 SEC circuit breakers Re power PFD1 in configuration mode and use the PFD1 FMS knob to select the Audio Alert Configuration page G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 35 190 00915 01 Revision 6 16 ee 18 19 20 2i 22 2 24 25 26 2T 28 Ensure cockpit speaker is selected ON Use the PFD1 FMS knob to highlight each of the following messages then select PLAY Verify each of the following audio messages are played e Too Low Terrain e Terrain Ahead 2X e Too Low Flaps e Terrain Ahead Pull Up 2X e Too Low Gear e Obstacle Ahead 2X e Sink Rate e Obstacle Ahead Pull Up 2X e Pull Up e Five Hundred e Don t Sink e Four Hundred e Caution Terrain 2X e Three Hundred e Terrain 2X Pull Up 2X e Two Hundred e Terrain 2X One Hundred e Caution Obstacle 2X Glide Slope e Obstacle 2X Pull Up 2X e G
319. oss talk error has occurred DATA LOST Pilot stored data lost Recheck settings Page 5 50 Revision 6 A communication error has occurred between the MFD and or PFDs Pilot stored data has been lost Go to the GDU TEST page in configuration mode and verify key is stuck if key is stuck the corresponding indicator will be green Exercise suspected stuck key and reset GDU TEST page to see if indicator remains green without pressing the key v If problem persists replace the display Ensure a database error has not occurred identified in the ALERTS window on the PFD v Ifa database error has occurred correct error before proceeding Check display Ethernet interconnect wiring Replace PFD1 with a known good unit to verify location of problem v If problem persists reinstall original PFD1 and replace PFD2 v If problem persists reinstall PFD2 and replace MFD If the CLR key was held during a power cycle disregard message Cycle power to PFD1 v Ensure CLR key is not stuck on the GDU TEST page v If problem persists replace PFD1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Failure Message Cause Solution S MFD1 SERVICE needs service Return unit for repair PFD 1 SERVICE needs service Return unit for repair PFD 2 SERVICE needs service Return unit for repair PFD 1 VOLTAGE PFD 1 has low voltage Reducing power
320. owing procedure verifies the type of servo gearbox that is configured for each servo 1 With PFD1 in configuration mode use the large FMS knob on PFD1 to select the GDU page then select AIRFRAME CONFIGURATION using the small FMS knob 2 Activate cursor and rotate the large FMS knob to scroll to the last entries in the AIRFRAME field 3 Verify the correct type of GSM servo gearbox GSM 85A or GSM 86 is installed for each servo AIRCRAFT ENGINE ENGINE TYPE NUM ENGINES AIRFRAME CONFIGURATION TURBOPROP NUM CYLINDERS OVERSPEED WARNING RPM MIN TACH TIMER RPM TACH TIMER 1 1 RPM GAUGE Min Value E Value 1 Value 2 Value 3 Value 4 Max Torque 005 0 5 5 9540 4 3 99500e 02 1 49208e 03 3 02415e 13 3 2918e 13 4 06 745e 13 3 52512e 13 2700 AIRSPEEDS green green barber_pole GUBFt B kt 4000fFpm ALT TAPE RANGE TAS TAPE RANGE VS TAPE RANGE LEFT TANK USEABLE 1825 2LB RIGHT TANK USEABLE 1825 2LB CNTR TANK USEABLE GLB TYPE Jet A King Air 206 Series AIRFRAME R ENG S N PITCH ROLL GSM 85A YAW GSM 85A PITCH TRIM GSM 85A Figure 3 38 Servo Mount Configuration Verification 4 Deactivate cursor NAVIGATION CENTER OFFSET VERTICAL 1 FT If any of the servo gearboxes shown do not match the actual installation on the aircraft reload the correct servo gearbox configuration per section 3 25 or 3 26 as applicable Page 3 40 Revision 6 G1000 GFC 700 System Mainten
321. own menu Highlight King Air Options and press ENT key on PFD1 3 Rotate the small FMS knob to highlight King Air 200 B200 GSM 86 Servo Mounts Press ENT key on PFD 1 4 Verify King Air 200 B200 GSM 86 Servo Mounts is displayed in the Item window 5 Deselect any servos that have GSM 85A servo gearboxes installed by scrolling to the servo and pressing ENT key on PFD1 6 When all of the servos that have GSM 86 servo gearboxes are selected press LOAD CONFIGURATION ID D2C83E0 SYSTEM UPLOAD GROUP LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A PITCH TRIM SERVO N A ROLL SERVO N A YAW SERVO N A Figure 3 37 GSM 86 Servo Mount Configuration 7 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for PITCH SERVO PITCH TRIM SERVO ROLL SERVO and or YAW SERVO as selected e Upload Complete COMPLETE in the summary box 8 Press ENT key on PFD1 to acknowledge upload complete 9 Deactivate cursor 10 Verify the servo mount configuration per section 3 27 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 39 190 00915 01 Revision 6 3 27 Verification of Servo Mount Configuration For software versions 0985 04 and later the section 4 9 1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured The foll
322. pad enter in a frequency of 123 450 Verify COMM2 frequency changes as entered 24 Press the NAV key until 1 is lit Verify the tuning box is present around the NAV 1 frequency on PFD1 25 Using GCU477 keypad enter in a frequency of 108 00 Verify NAV1 frequency changes as entered 26 Press the NAV key until 2 is lit Verify the tuning box is present around the NAV 2 frequency on PFD1 27 Using GCU477 keypad enter in a frequency of 108 00 Verify NAV1 frequency changes as entered 28 Press the XPDR key until the light to the left of the button is lit Verify a flashing box appears in the XPDR 1 code window 29 Using GCU477 keypad enter in a code of 1234 Verify XPDR1 shows a code of 1234 in the window 30 Press the XPDR key until the light to the right of the button is lit Verify a flashing box appears in the XPDR 2 code window 31 Using GCU477 keypad enter in a code of 1234 Verify XPDR2 shows a code of 1234 in the window If no other service is to be performed continue to the return to service checks in Section 8 Page 7 28 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 11 GMC 710 AFCS Controller Original GMC 710 Reinstalled No software or configuration loading is required if the removed GMC 710 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continu
323. plays the CALIBRATION SUCCESSFUL SITE IS CLEAN message upon completion of the Magnetometer Calibration Procedure in each clockwise and counter clockwise direction then the candidate site is sufficiently free of magnetic disturbances and is acceptable for performing the Magnetometer Calibration Procedure It is important to obtain successful result in both the clockwise and counter clockwise directions to ensure that the magnetometer sweeps over a large enough area at the candidate site If the PFD displays either the MAG FIELD AT SITE NOT UNIFORM or MAG FIELD AT SITE DIFFERS FROM IGRF MODEL message upon completion of the Magnetometer Calibration Procedure in either of the two directions then the site contains magnetic disturbances that are too large G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 21 190 00915 01 Revision 6 7 7 4 Procedure B GRS 77 GMU 44 Magnetic Calibration NOTE Procedure A 1 Section 7 7 2 must first be successfully accomplished before performing Procedure B only for situations where the GRS 77 was replaced with a new unit Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free of environmental magnetic disturbances Attempting to carry out this maneuver on a typical ramp area may not yield a successful calibration The accuracy of the AHRS cannot be guaranteed if this calibration is not performed on a magnetically clean compass
324. plicator can be bent if the knob that applies tension to the transducer mounting plate is over tightened Use care when installing the force applicator to prevent damage to the anchor tab Refer to the data supplied with the force applicator 5 Install the appropriate gauge 1952 1 gauge 0 5 to 3 gram scale or the 1952 3 gauge 2 to 15 gram scale in the force applicator see Figure 7 16 onto the left wing in accordance with the manufacturer s instructions Refer to the data supplied with the force applicator The force arm must be positioned so that the applied force 1s within 1 32 inch of the transducer vane tip Forces applied forward or up will be classified as minus values Forces applied aft or down will be classified as plus values Make sure that the vane is free to move with the force applicator 6 Apply external power to the aircraft 7 Place the BATT master switch to the ON position 8 Verify the STALL WARN circuit breaker on the copilot circuit breaker panel is set WARNING Make sure that all personnel are clear of the flap area before proceeding with these procedures 9 Flaps retracted calibration a Run the flaps to the FULL UP position G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 51 190 00915 01 Revision 6 b Using the force applicator deflect the transducer vane forward UP to the Pot 0 TG force measured in step 10 in Section 7 24 1 If the stall warning horn is already ON
325. ption must be loaded per Section 3 21 prior to loading the POTS handset configuration 1 2 3 4 5 6 3 25 Power up the PFD1 in configuration mode On the PFD1 select GDL page group using the large FMS knob Using the small FMS knob select the GDL 59 Configuration page Activate the cursor Use the large FMS knob to select POTS CONNECTED in the PHONE SETTINGS field Use the small FMS knob to select YES and press the ENT key After GDL 59 is configured press the ENT key GSM 85A Servo Mount Configuration For software versions 0985 04 and later the section 4 9 1 slip clutch torque check procedure requires the correct type of GSM servo gearbox to be configured It is not required to load this configuration if GSM 86 servo gearboxes are installed for all servos default configuration l 8 9 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD1 Rotate the small FMS knob to highlight King Air 200 B200 GSM 85A Servo Mounts Press ENT key on PFD1 Verify King Air 200 B200 GSM 85A Servo Mounts is displayed in the Item window Deselect any servos that have GSM 86 servo gearboxes installed by scrolling to the servo and pressing ENT key on PFD1 When all of the servos that have
326. r from configuration module 1 4 Remove configuration module Installation 1 Inspect connector for damaged pins 4 2 Place configuration module 1 in position 3 Insert connector into configuration module 1 4 Assembly of the connector is the reverse of disassembly 5 Continue to Section 6 16 1 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 9 190 00915 01 Revision 6 6 16 1 Configuration Module Checkout Ifa GRS 77 AHRS Configuration Module is replaced All three GRS 77 GMU 44 calibration procedures must be performed Proceed to Section 7 7 3 Ifa GDC 74B Configuration Module is replaced Configuration settings must be reloaded to the GDC 74B per Section 3 9 then proceed to Section 7 6 1 Ifa GEA 71 Configuration Module is replaced Proceed to Section 7 4 1 If only the Master Configuration Module is replaced NOTE New Terrain Obstacle cards Jeppesen Aviation Database and other optional features 1 e TAWS unlock card will need to be replaced if the master configuration module is changed The G1000 System ID number will change to a new number when installing a new master config module The old Terrain and other cards will no longer work as they will remain locked to the old System ID number 1 Start the G1000 system in configuration mode 2 Goto the Configuration Upload Page on PFD 1 3 Press the UPDT CFG softkey and press ENT lf both PFD 1 and Master Configuration Module are rep
327. r visual inspection of the zone to minimize access requirements 4 5 2 Test Equipment A milli ohm meter and Kelvin probes are recommended for this test However a standard voltmeter power supply with adjustable current limit and ammeter may be substituted The following procedure is written using the voltmeter power supply and ammeter All test equipment must have valid calibration records 4 5 3 Phase 3 Electrical Bonding Procedure 1 Connect the positive lead of the power supply to the engine compartment grounding bracket battery negative connection to the airframe Connect touch the positive lead of the voltmeter to the same point NOTE Ensure that the voltmeter and power supply probes do not touch so as not to induce contact resistance 2 Touch negative lead of power supply to each of the test points listed while performing Step 3 At each point configure the power supply to produce 1 amp before measuring voltage Use an ammeter to ensure current is within 1 amp 100 milli amp at each point 3 Set the voltmeter to measure milli volts and null the reading Measure the voltage from the engine grounding bracket step 1 to each of the following points and record the voltage Perform Step 2 at each point to ensure that 1 amp 100 milli amp is present before measuring G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 15 190 00915 01 Revision 6 Pilot Compartment e Top metal case of PFD 1 milli
328. ramp test equipment Operate the equipment according to the test equipment manufacturer s instructions Adjust the RF signal to a level adequate to perform the test Select the appropriate HSI source by using the CDI softkey NOTE The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned GFC 700 VOR LOC GS Test 1 Ensure FD is coupled to PFD1 as indicated by a left pointing arrow next to the AFCS mode controller XFR button 2 Simulate a VOR signal on a radial equivalent to the aircraft heading Tune the NAV 1 and NAV 2 receivers to the simulation frequency 3 Set the HSI on PFD1 to VORI by pressing the CDI soft key until VOR1 is selected Set the HSI on PFD2 to VOR2 by pressing the CDI soft key until VOR2 is selected Rotate CRS1 and CRS2 knobs to set VORI and VOR2 course pointers to aircraft heading CDI Synchronization must be set to OFF on the AUX SYSTEM SETUP 1 page on the MFD 4 Verify full scale deflection of VOR1 and VOR2 CDI by varying CRS1 and CRS2 selected course at least 10 left and right Reset course pointers to aircraft heading 5 Engage the autopilot and press the NAV key on the AFCS mode controller Using the CRS1 knob alter course by 10 to the right Verify the flight director and aircraft controls respond by flying to the VOR course Repeat to the left 6 Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller Verify FD is coupled right as indicated by a right
329. ration files for backup GMA 1347D Contains ACTIVE GMA settings Uses PFD internal configuration files for backup No 2 GEA 71 Contains ACTIVE settings Uses PFD internal configuration files for backup settings U for backu GWX 68 Contains ACTIVE ses PFD internal configuration files p G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 The GRS 77 and GDC 74B configuration modules function differently than the rest of the system The GDC 74B s configuration file 1s loaded directly to GDC internal memory A copy of the file is stored in the GDC configuration module The GRS 77 configuration module does not store any configuration settings Instead 1t stores calibration data recorded during installation calibration procedures GRS 77 Config Module located in GRS backshell connector Stores a copy of AHRS magnetometer calibration values that are recorded upon completion of post installation calibration procedures GRS 77 AHRS The GRS stores calibration data internally The GRS 77 also stores factory calibration data internally Should internal memory or the configuration module fail AHRS output data flags invalid GRS Internal Memory Contains internal sensor calibration data that is not installation specific Data is stored from factory calibrations
330. rator noise and absence of flag STBY attitude STBY Altimeter STBY Airspeed indicators are illuminated full bright Amber ON is annunciated full bright on the STANDBY BATTERY switch White STANDBY BATTERY legend on the standby battery switch is illuminated full bright 6 Activate aircraft power by selecting the Verify the following on position of the BATTERY switch e ON annunciation should extinguish on the STANDBY BATTERY switch ARM should be fully illuminated green on the STANDBY BATTERY switch The STBY attitude STBY altimeter and STBY airspeed instrument lighting reverts to the aircraft settings The STBY attitude motor and STBY altimeter vibrator remain active White STANDBY BATTERY legend on the standby battery switch remains illuminated Deselect the STANDBY BATTERY Verify the following switch Pop NETE e ARM annunciation extinguishes on the STANDBY BATTERY switch STBY attitude motor and STBY altimeter vibrator remain active White STANDBY BATTERY legend on the standby battery switch remains illuminated Remove aircraft power by selecting the Verify the following battery switch to OFF position e The STBY Attitude motor is deactivated the sound of the motor may be present as the gyro spools down The STBY altimeter vibrator is deactivated The STBY attitude STBY altimeter STBY airspeed and magnetic compass are no longer illuminated e White STAND
331. rce is 10 TG add 17 TG and the Pot 5 force is 7 TG e Install voltmeter leads between TP18 Lo and TP19 Hi of the SK 100360 Breakout Box f Apply the calculated Pot 5 TG force to the vane with the force applicator g Adjust the Pot 5 on the lift computer until the voltage output from TP18 Lo and TP19 Hi reads 2 2 0 2 VDC on the voltmeter h Return the force on the force applicator to 0 TG 12 Place the BATT master switch in the OFF position and remove the external power from the airplane 13 Remove the force applicator from the left wing 14 Remove the breakout box and reconnect the lift computer 15 Install the potentiometer access cover on the lift computer 16 Close all panels opened to access the lift computer G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 53 190 00915 01 Revision 6 STALL WARNING AND LAA ADJUSTMENT POTS SHOWN WITH COVER OFF FOR CLARITY s ta MS SAFE FLIGHT LIFT COMPUTER P N C 05606 1 NOT TO SCALE Figure 7 14 C 05606 1 Lift Computer Page 7 54 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 BUD MINI BOX ds PN CU 3O06A TP 1TP 2TP 37TP 4 3 CABLES TP 7 Thad TEA TRE CN 600090 99988 208 LIFT COMPUTER PLUG AMP 205840 3 LL TEST POINT JACKS RED EXCEPT TEST POINT 2 E 26 WHICH ARE BLACK H SMITH TEST RECEPTACLE 1508 SYSTEM WIRING H
332. re deleted during the repair testing process Continue to the return to service checks in Section 8 Original GEA 71 Installed in Opposite Locations for Troubleshooting No software loading 1s required if the original GEA units are installed in opposite locations GEA 1 and GEA 2 in opposite unit racks Continue to the GEA 71 Test Section 7 4 1 New Repaired or Exchange GEA 71 Installed If a new repaired or exchange GEA 71 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GEA 71 Test Section 7 4 1 7 4 1 GEA 71 Test On the MFD normal mode check the indication for each of the sensor or monitor inputs with the aircraft engines off In general verify all engine and system instruments show valid static normal values and markings with no red Xs or erratic indications Reference Figure 7 4 for normal engine instrument markings figure may not reflect actual aircraft installation If necessary reference Sections 7 4 2 7 4 3 and 7 4 4 for additional tests to verify instrument readings 3 3 TORQUE aa TORQUE 5 FT LB FT LB TURB 100 4 TURB 100 3 Z RPM Z RPM PSI 200 PSI 200 Figure 7 4 Normal Engine Instrument Markings MFD If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 9 190 00915 01 Revision 6 7 4 2 GEA Engine Indicatio
333. re loading then proceed as follows If the GRS rack s was not removed or loosened continue to the GRS GMU Test Section 7 7 6 If the GRS rack s was removed or loosened continue to the GRS GMU Calibration Procedures Section TAA New GRS 77 Configuration Module is Installed If the GRS 77 configuration module is replaced no software loading is required Continue to the GRS GMU Calibration Procedures Section 7 7 1 Original GMU 44 is Reinstalled If the original GMU 44 is reinstalled then no software loading is required This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GRS GMU Test Section 7 7 6 Original GMU 44 is Installed in Opposite Location for Troubleshooting If the original GMU 1 and GMU 2 are installed in opposite locations GMU 1 and GMU 2 in opposite unit racks no software loading is required However performing the Magnetometer Calibration Procedure is required Continue to the GRS GMU Test Section 7 7 6 New Repaired or Exchange GMU 44 is Installed If a new repaired or exchange GMU 44 1s installed then software must be loaded Continue to Section 3 9 for software loading then continue to the GRS GMU Calibration Procedures Section 7 7 1 Page 7 18 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 7 1 GRS GMU Calibration Procedures GRS GMU Rec
334. re that the correct 9 Arc Second databases were used 5 5 1 General Troubleshooting G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 27 190 00915 01 Revision 6 The following annunciations may appear in the AFCS Annunciation field Table 5 3 AFCS Annunciation Troubleshooting Confirm AFCS Servos circuit breaker IN Ensure that the G1000 system is in proper working order Check specifically for proper operation of the GIA 63 Integrated Avionics Units GRS 77 AHRS Units GDC 74B Air Data Computers All GSA 80 Servos Check that no red X s are present on the MFD and PFD displays Check that no related alert messages are present on the AFCS System PFD displays press the ALERTS softkey Failure Go to the AUX SYSTEM STATUS page on the MFD and verify that all LRUs have a green check see Section 5 In Configuration mode review the GFC 700 equipment status software and certification gains Reload software configuration and certification gains to the GIAs and GSA 80 servos Check the GFC Status page for additional GFC 700 system information Review the fault and assert logs for the GIAs and servos see Section 5 6 2 Isolate the fault to an LRU Replace this LRU and confirm the resolution of the annunciation Check the AUX SYSTEM STATUS page to see if the PTCH Pitch Axis Failure servo is online green check Pitch Ti Axis Check that the affected servo is receiving power
335. red to confirm if the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units Check the GIA2 GRS 77 2 interconnect wiring for faults Arbor GIA2 GRS 77 2 data path functionality is unknown Reload GIA2 configuration files G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 15 190 00915 01 Revision 6 9 2 1 3 GIA CAN RS 485 CONFIGURATION Page GIAI RS 485 Green Green GIAI GEAI data path is functioning correctly GIA1 GEA1 data path is not functioning correctly e Verify GEA is powered on using the GEA Status page e Load GIA and GEA configuration files e Swap GIA and GIA2 reconfigure both GIA s to their new locations to confirm if the problem is in the original GIA 1 o Replace original GIA 1 1f box turns green after swapping CHNL 1 GEA1 units Swap GEA and GEA2 reconfigure both GEA s to their new locations to confirm if the problem is in the original GEA 1 o Replace original GEA1 1f box turns green after swapping units Check the GIA1 GEA interconnect wiring for faults A amor SIANGEAL data path functionality is unknown Reload GIA 1 Amber configuration files Green Green GIAI GEA2 data path is functioning correctly GIA1 GEA2 data path is not functioning correctly e Verify GEA2 is powered on using the GEA Status page e Load GIAI and GEA2 configuration files e Swap GIA and GIA2 reconfigure both GIA s to their new locations to co
336. rent supplemental databases into the lower slot of the MED 5 Close PFD1 PFD2 and MED circuit breakers 6 The system will synchronize the data to the PFDs as necessary FliteCharts and ChartView are located only on the MFD and do not require synchronization Monitor the synchronization process on the AUX SYSTEM STATUS page in the SYNC STATUS sub section within the DATABASE window This sub section is only present when a sync is occurring or has occurred on the current power cycle SYNC STATUS SAFETAXI OBSTACLE NAVIGATION INTERNAL REGION CYCLE EFFECTIVE EXPIRES NAY STANDBY BOTTOM CARD REGION CYCLE EFFECTIVE Figure 3 42 Supplemental Database Synchronization 7 Ifan error occurs during synchronization one of the following messages will be displayed followed by the affected GDU Err No Space SD card does not contain sufficient memory Timeout system timed out prior to the database transfer completing Canceled an active synchronization has been cancelled due to the SYNC DBS softkey being unpressed Err displayed for all other errors Note that a power cycle is required to restart synchronization when Err No Space or Err is shown 8 When the synchronization is complete the status is shown as Complete 9 Cycle power to PFD1 PFD2 and MFD 10 The supplemental databases in PFD1 PFD2 and MFD are now updated 11 On the AUX SYSTEM STATUS page press the MFD1 DB softkey Scroll through a
337. returns to normal navigation mode GPS CDI restored LOI annunciation removed amp GPS data magenta G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 8 1 2 GIA Failure Test Step SSI Desired Result GIA 1 Failure Condition For a GIA 1 failure condition the following shall occur NAV 1 and COMM1 tuning fields on PFD1 and PFD2 are invalid red X L R engine data remains valid 1 Ensure GPS satellites are acquired Open GIA1 primary and secondary CBs 2 3 Verify desired results 4 Close GIA1 primary and secondary CBs Allow system to re acquire satellites and return to normal display modes GMA1 Is Inoperative XPDR1 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 AHRS and ADC data remain valid on PFD1 and PFD2 GIA 2 Failure Condition For a GIA 2 failure condition the following shall Open GIA 2 CB ria Verify desired results e NAV2 and COMM2 tuning fields on PFD1 and PFD2 are invalid red X Close GIA 2 CB Allow system to re UR ine d l lid acquire satellites and return to normal engine data remains valia display modes XPDR2 is Inoperative GMAZ2 Is Inoperative AHRS2 is using backup GPS source AHRS1 not receiving backup GPS Information An amber BOTH ON GP 1 is displayed on PFD1 and PFD2 AHRS and ADC data remain valid on PFD1 and PFD2 Dual GIA
338. riginal GRS1 Replace original GRS1 1f box turns green after swapping units Load PFD2 configuration file IN 1 GRS 77 2 E Swap PFD2 and PFD1 to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays Swap GRS1 and GRS2 no reconfiguration required to confirm if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the PFD2 GRS 77 2 interconnect wiring for faults ee PFD2 GRS 77 2 data path functionality is unknown Reload PFD2 configuration file PFD2 GDC 74 2 data path is functioning correctly PFD2 GDC 74 2 data path is not functioning correctly e Verify GDC 74 2 status is OK using the System Status page on the MFD If it is not correct condition before proceeding reference GDC troubleshooting sections Load PFD2 and GDC 74 2 configuration files IN 2 GDC 74 2 Swap PFD2 and PFD1 to confirm if the problem is in the original PFD2 o Replace original PFD2 if box turns green after swapping displays e Check the PFD2 GDC 74 2 interconnect wiring for faults Replace GDC 74 2 if problem remains abet PFD2 GDC 74 2 data path functionality is unknown Reload PFD2 configuration file Page 5 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 MFD1 RS 232 MFD1 GCU 477 data path is functioning correctly MFD1 GCU 477 data path is not functioning corre
339. ring from GSR 56 toGDL 59 No audio output Verify subscription with Garmin Flight Data Services reference Section 7 27 Verify signal quality is adequate Unable to make a phone call Verify communication between GSR 56 and the display control device Verify subscription with Garmin Flight Data Services reference Section 7 27 5 28 GTS 820 850 Troubleshooting gt Problem Cause Solution Unit does not power up Data Improper wiring circuit breaker open Ensure power is properly wired to the failed message GTS 8XX and the TRFC circuit breaker is closed correctly for the desired display Traffic Display erroneously Suppression bus I O fault Check the mutual suppression line to indicates TA at own ship position ensure it is connected to the correct pins at the GTS 8XX as well as the installed transponder Ensure there are no fractures in the wire and that the suppression line is functioning roperl property No Audio alerts Improper wiring Volume not set correctly Ensure the audio is properly wired from the GTS 8XX and volume is not set too low Calibration Fault Factory calibration invalid If the unit fails to go into operate mode then return to Garmin for service Configuration Fault Both internal and external configuration Verify the configuration checks failed Verify wiring to the configuration module and replace if necessary FPGA Fault Internal Fault Return to Garmin for service ROM Fault Internal Fault Return to Garmi
340. ring is at fault Both GIAs must be configured when swapped see Section 3 9 The NAV1 external remote transfer switch is stuck in the enabled or pressed state NAV1 RMT XFR NAV1 remote transfer key is stuck v If problem follows unit replace GIA1 v If problem persists continue to troubleshoot remote transfer switch amp wiring Press the NAV2 external remote transfer switch again to cycle its operation Check NAV2 remote transfer switch and wiring Switch GIA1 and GIA2 to identify whether the unit or connectors wiring is at fault Both GIAs must be configured when swapped see Section 3 9 The NAV2 external remote transfer switch is stuck in the enabled or pressed state NAV2 RMT XFR NAV2 remote transfer key is stuck v If problem follows unit replace GIA1 v If problem persists continue to troubleshoot remote transfer switch amp wiring Page 5 58 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 11 3 Glideslope Alerts Failure Message Cause Soluti n G S1 SERVICE G S1 needs The system has detected a failure e Replace GIA1 service Return unit for repair in G S1 receiver p i G S2 SERVICE G S2 needs The system has detected a failure e Replace GIA2 service Return unit for repair in G S2 receiver p l e Switch GIA1 and GIA2 to verify location of problem v If problem follows the unit replace GIA v If proble
341. ropriate servo installation drawing listed in Table 1 2 If no other service is to be performed continue to the return to service checks in Section 8 Page 7 26 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 10 GCU 477 FMS Controller Original GCU 477 Reinstalled No software or configuration loading is required if the removed GCU 477 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GCU 477 Test Section 7 10 1 New Repaired or Exchange GCU 477 Installed If a new repaired or exchange GCU 477 1s installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GCU 477 Test Section 7 10 1 7 10 1 GCU 477 Test Perform the following key and knob presses and knob rotations on the GCU 477 and verify the actions on the MFD l Rotate the large FMS knob and verify that the page groups change 2 Rotate the small FMS knob and verify that the pages change within the page groups 3 Use the large FMS knob to display the MAP page group and the small FMS knob to display the NAVIGATION MAP page Rotate the RANGE knob to the right and verify the map display zooms out Rotate the RANGE knob to the left and verify the map display zooms in Press the RANGE knob to get the pointer on the map display Move the RA
342. rose If the compass rose condition is not known it is recommended that the technician follow the guidance in Section 7 7 3 1 Start the aircraft engine following the procedures referenced in the appropriate King Air AFM or AFMS as shown in the General Arrangement drawing listed in Table 1 2 2 After aircraft engine startup taxi the aircraft to a properly calibrated compass rose 3 At the compass rose align the aircraft to a heading of magnetic north 5 CAUTION Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free of environmental magnetic disturbances Attempting to carry out this maneuver on a typical ramp area may not yield a successful calibration The accuracy of the AHRS cannot be guaranteed if this calibration is not performed on a magnetically clean compass rose or equivalent NOTE This procedure provides instructions for calibrating both GRS 77 magnetometers separately It is acceptable to calibrate both GRS 77 magnetometers simultaneously by putting both PFD 1 and PFD 2 in configuration mode and following the procedure below using PFD 1 to calibrate GRS 1 and PFD 2 to calibrate GRS 2 4 Restart the PFD and MFD in configuration mode Go to the GRS Page Group on the PFD 6 Select the GRS GMU Calibration page and enter the following softkey password e 9 e 10 eo 11 e 12 far right softkey 7 Press the FMS small knob to highlight GRS 77 1 The FMS small knob ca
343. s or other defects exist If GSM 86 servo gearbox is installed check that the retaining bolt for the slip clutch cartridge is not damaged or loose Have an assistant manually move the aileron control surfaces from stop to stop and visually observe the servo and control cabling chain Ensure there is no binding in the control cabling or chain and that the capstan sprocket rotates freely GFC 700 Equipment Check the servo control cables in accordance with AC 43 13 1B Chapter 7 Section 8 Paragraph 7 149 to ensure no fraying corrosion or other damage exists If the condition of any cable is questionable replace it with a new one Check the tension on the control cables Refer to the Roll Servo Install drawing listed in Table 1 2 for cable tension specifications Ensure that each cable is correctly attached to the clamps Follow recommended checks for checking main control cables following the instructions in Chapter 27 Flight Controls of the King Air 200 Series Maintenance Manual Reinstall the access panels if no other maintenance is to be performed To gain access for the following inspection remove the left cabin sidewall panel at FS 158 Inspect the GPA 65 PA LNA unit if installed brackets and connectors for GPA 65 a corrosion or other defects Check the integrity of the shield block ground GTS 8XX traffic option only attachments to the harness connector assembly as well as the integrity of the individu
344. s King Air Page 4 27 190 00915 01 Revision 6 14 Hold the control yoke in the forward position and center the pitch trim wheel 15 Engage the autopilot maintain the control yoke in the forward position and keep the pitch trim wheel from rotating for approximately five seconds 16 Quickly release the trim wheel and verify that the red PTRM annunciator is displayed on both PFD 1 and PFD 2 17 Disengage the autopilot and use the pitch trim switch or the pitch trim wheel to trim full down 18 Hold the control yoke in the full forward position 19 Engage the autopilot apply firm aft pressure on the control yoke for approximately 10 seconds allowing the pitch trim wheel to move freely Verify that the amber ELE annunciator is displayed on both PFD 1 and PFD 2 20 Disengage the autopilot and use the pitch trim switch or the pitch trim wheel to trim full up 21 Move the control yoke to the full aft position and hold 22 Press the Go Around button on the throttle and engage the autopilot Apply firm forward pressure on the control yoke for approximately 10 seconds allowing the pitch trim wheel to move freely Verify that the amber ELE annunciator is displayed on both PFD 1 and PFD 2 23 Disengage the autopilot NOTE If the ELE annunciation appears during any of the following steps reset the trim wheel and repeat the test step 24 Use the pitch trim switch or the pitch trim wheel to trim full down 25 Hold the elevator
345. s listed in Table 1 2 Then continue to the GDL 69A Test Section 7 8 1 7 8 1 GDL 69A Test If an XM Satellite Radio subscription has already been activated for the GDL 69A then power up the G1000 and go to the AUX XM INFORMATION page and verify that the GDL 69A is working properly Refer to the Cockpit Reference Guide listed in Table 1 2 for details on XM Radio weather and music operation If the GDL 69A is replaced new unit the owner must re activate the subscription using the new GDL 69A s Radio ID number s Refer to the GDL 69A 69A XM Satellite Radio Activation Instructions listed in Table 1 3 for details on the activation process As a final operations check make sure there are no MANIFEST errors shown on the PFD for the GDL 69A If no other service 1s to be performed continue to the return to service checks in Section 8 7 9 GSA 80 Servos Original Servo s Reinstalled No software loading is required if the removed servo s is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the return to service checks in Section 8 New Repaired or Exchange Servo s Installed If a new repaired or exchange servo 1s installed the correct software files and certification gains must be loaded to the unit See Section 3 9 and then continue to the return to service checks in Section 8 NOTE Refer to the app
346. s of measure are English units Page 1 4 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 1 4 Publications The following documents are required by this maintenance manual to perform maintenance It is the responsibility of the owner operator to ensure latest versions of these documents are used during operation servicing or maintenance of the airplane Table 1 2 Required Documents Part Number 005 00421 00 Master Drawing List Garmin G1000 GFC 700 in Hawker Beechcraft Model 200 B200 Series King Air GWX 68 Radar Install King Air 200 B200 005 00421 39 Magnetometer Install King Air 200 B200 005 00421 40 OAT Sensor Install King Air 200 B200 005 00421 46 Yaw Servo Install wGSM 86 King Air 200 B200 005 00421 48 Pitch Trim Servo Install w GSM 86 King Air 200 B200 005 00421 38 Pitch Trim Servo Install w GSM 85A King Air 200 B200 005 00421 47 Pitch Servo Install w GSM 86 King Air 200 B200 005 00421 58 Glareshield Lighting Modification King Air 200 B200 Hawker Beechcraft Document __ Other Documents 85 292 1 1033 Signal Conditioner Installation Manual Meggitt Vibro Meter 9016182 Mid Continent Instruments Installation Manual and Operating Instructions 4200 Series Attitude Indicator TP 336 L 3 Avionics Systems Emergency Power Supply Installation Manual PS 835 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 1 5 190 00915 01 Revision 6
347. s ok replace MFD G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Page 5 51 Revision 6 5 9 6 GMA Common Problems Symptom Failure Recommended Action Message Noise in Audio Most often the cause of the noise is external to the GMA Try the following to locate the source of the noise before replacing the GMA Buttons Do Not Work COM Bleedover e Speaker Cuts Out Try a different pair of headsets Noise cancelling headsets may pick up and or generate more noise than standard headsets from their own circuitry Check for noise with the engine turned off v Ifthe noise is present only when the engine is running check the generator and or ignition system as possible sources of noise see applicable airframe specific maintenance manual Check for noise as all electrical equipment is turned on and off strobes other radios etc v Ifthe noise is identified from one electrical system or component refer to the applicable airframe specific maintenance manual Ensure the NAV COM squelch is not open Ensure the ADF and DME audio is not active Ensure the marker beacon audio is not active Ensure the ICS squelch is not open v Master squelch level can be adjusted on the GMA CONFIGURATION page for higher noise environments Replace unit only after all possible external sources of noise are eliminated Some buttons are disabled in the GMA CONFIGURATION page by default This is
348. s on PFD1 and PFD2 then press the DME softkey Verify the DME window is displayed next to the PFD1 and PFD2 HSI On PFD1 and PFD2 press the BACK softkey then select DME softkeys Verify the DME TUNING screen 1s displayed On PFD1 and PFD2 use the large FMS knob to select the NAV1 NAV2 and HOLD modes in the DME field Verify that the NAV1 NAV2 and HOLD modes can be selected by turning the small FMS knob Set NAV1 and NAV2 frequencies to 108 00 and 117 00 respectively On PFD1 and PFD2 select the DME NAV1 mode Verify that the DME window display is set to the NAVI frequency of 108 00 On PFD1 and PFD2 select the DME NAV2 mode by pressing the ENT softkey Verify that the DME window display is set to the NAV2 frequency of 117 00 On PFD1 and PFD2 select the DME HOLD mode by using the FMS knob Verify that the last selected NAV frequency of 117 00 remains the same when the NAV2 frequency is changed Deselect DME HOLD On the NAV Test Set set up a DME test and note the nav frequency Tune NAV 1 to the test set frequency and set PFD1 and PFD2 DME MODE to NAV1 Set NAV 2 to a frequency other than the test set frequency Verify that the DME distance on PFD1 and PFD2 match the test set Select or verify selected DME and SPKR buttons on GMA1 and GMA2 audio panels to select the DME audio and select speaker to ON Verify that the DME audio can be heard over the cockpit speakers On PFD1 and PFD2 set the DME mode to NAV2 and verify that
349. sembly as well as the integrity of the individual shields and their attachment GIA 63W Qty 2 a Inspect the standby battery rack and connectors for corrosion or other defaults Standby Battery b Inspect the standby battery fuses and associated bracket for corrosion or other defects GIA Avionics Fan Inspect remote avionics fans and hoses for dirt accumulation and other damage Qty 2 Remove excess dirt as required a Inspect the GTS 8XX unit if installed rack and connectors for corrosion or other GTS 8XX Traffic defects Check the re of the aa block ground attachments to the harness option connector assembly as well as the integrity of the individual shields and their attachment cae and Inspect the LMD rack modules and terminations for corrosion or other defects NN a Inspect bulkhead connectors for security of attachment corrosion or other defects b Inspect wire and coax for chafing damage proper routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Nose Wire Harness Routing drawing listed in Table 1 2 Nose Wiring harness Pay particular attention to possible areas of chaffing such as the middle shelf feed through hole wheel well protrusion etc c Inspect Ground blocks for security of attachment corrosion or other defects d Ensure all connectors are securely fastened Page 4 10 G1000 GFC 700 System Maintenance Manual 200
350. shown in the following image G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page8 7 190 00915 01 Revision 6 SELECT UNIT GIA RS 232 CHANNEL CHNL 1 CHNL 2 CHNL 3 CHNL 4 CHNL 5 CHNL 6 CHNL 7 CHNL 8 DATA Bae S E MENOS ARINC 4239 CHANNEL IN 1 IN 2 IN 3 IN 4 IN 5 IN 6 IN 7 IN 8 DATA MARA Y MENE INPUT SET GDC 74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 1 OFF SPEED SET Low Low Low Low Low High Low Low Low Low Low Common RS 232 ARINC 429 CONFIG ACTIVE GDC 74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 1 OFF ACTIVE Low Low Low Low Low High Low Low Low Low Low Common OUTPUT SET GDC 74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 1 OFF DATA SET OFF OFF OFF OFF GDC74 1 GRS77 1 OFF OFF OFF OFF OFF ACTIVE GDC 74 1 GIA DEBUG OFF OFF GTX 33 1 w TIS GRS77 1 GMA1347 1 OFF ACTIVE OFF OFF OFF OFF GDC74 1 GRS77 1 OFF OFF OFF OFF OFF ERAS E RNP Figure 8 2 GIA Data Verification ARINC429 RS 232 15 Activate the cursor and select GIA2 in the SELECT UNIT field and then press the ENT key 16 Repeat Steps 13 and 14 Page 8 8 Revision 6 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 17 On PFD1 go to the CAN RS 485 CONFIGURATION page in the GIA Page Group 18
351. sion number on the General Arrangement drawing See Table 1 2 for the correct General Arrangement drawing part numbers Each G1000 GFC 700 LRU reports the software version it currently contains to the user in two places e Normal System Mode The AUX SYSTEM STATUS page lists each LRU and the reported software version e Configuration Mode The SYSTEM STATUS page SYSTEM page group reports more detailed LRU information including software version part number and LRU status Software files are loaded to LRUs from the SYSTEM UPLOAD page in configuration mode See Section 3 9 2 3 8 4 Configuration File Descriptions There are configuration files for baseline settings and various options Configuration files contain preset selections for input output channels aircraft specific settings and LRU specific settings IMPORTANT Certain software and configuration files are REQUIRED to be re loaded during maintenance that involves removal and replacement of G1000 equipment Refer to Section 7 for re configuration requirements for each G1000 LRU Pay special attention to the configuration of options for the G1000 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 15 190 00915 01 Revision 6 3 8 5 Configuration File Storage The G1000 system is designed to store all configuration settings in various places so that the configuration is retained in the aircraft during maintenance of units During system configura
352. ss the ENT key to indicate that the process is complete When this is done the TEST COMPLETE field stops blinking 5 The PFD 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 associated numeric values are displayed on the PFD Page 7 24 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 NOTE Should a failure occur the technician may perform the Engine Run up test up to 3 times successively before corrective action must be taken If the test does not pass after three attempts then the installation should not be considered reliable until the source of the vibration problem is identified and remedied In the event of repeated failure of the engine run up test 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 Vibration motion of GRS77 and or GMU44 caused by neighboring equipment and or supports b Mounting screws and other hardware for GRS77 and or GMU44 not firmly attached c GRS77 connector not firmly attached to unit d Cabling leading to GRS77 or GMU44 not firmly secured to supporting structure e An engine propeller that is significantly out of balance 6 Press the ENT key on the PFD to conclude this procedure 7 Repeats steps 1 through 6 for GRS 77 2 and proceed
353. stall PFD1 as described in Section 6 1 4 Repeat Steps through 3 for the MFD and PFD2 5 The Instrument Panel Fans Operational Check is complete Page 4 30 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 16 Standby Battery Periodic Checks 4 16 1 Charge Check Refer to the PS 835 Emergency Power Supply Installation Manual listed in Table 1 2 With the PS 835 battery installed in the aircraft and aircraft power applied verify all four Battery Voltage LEDs are lit to indicate the battery 1s being charged see Figure 4 5 With the PS 835 battery installed in the aircraft and no aircraft power applied press TEST SWITCH Figure 4 5 Item 4 into TEST position for 5 seconds The PS 835 indicates that it is adequately charged when the VOLTAGE LEVEL 24Vdc LED Figure 4 5 Item 2 illuminates momentarily AND the 20Vdc LED Figure 4 5 Item 6 remains lit during the test If the VOLTAGE LEVEL 24Vdc LED does not at least momentarily illuminate while the 20Vdc LED is illuminated perform the Section 4 16 3 Cell Isolation Test because the battery is incapable of providing adequate power Table 4 12 Standby Battery Required Equipment DVM Figure 4 5 Standby Battery G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 31 190 00915 01 Revision 6 4 16 2 Capacity Test NOTE The PS 835 Emergency Power Supply must have completed a full charge prior to any discharge
354. stall antenna using retained mounting screws 2 Connect the antenna coaxial cable 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Reinstall the aft cabin ceiling panel 5 Proceed to Section 7 29 for testing of the GSR 56 6 21 Wi Fi Antenna Removal 1 Gain access to the antenna coaxial cable connector by opening the tail access door behind the aft pressure bulkhead Refer to the Antenna Install drawing listed in Table 1 2 2 Disconnect the antenna coaxial cable 3 Remove the antenna mounting screws 4 Remove antenna Reinstallation 1 Install antenna using retained mounting screws 2 Connect the antenna coaxial cable 3 Fillet seal around antenna Refer to the Antenna Install drawing listed in Table 1 2 4 Secure the tail access door 5 Proceed to Section 7 28 for testing of the GDL 59 6 22 Signal Conditioners Removal 1 For Signal Conditioner No 1 remove PFD1 from the instrument panel as per Section 6 1 For Signal Conditioner No 2 remove PFD2 from the instrument panel as per Section 6 1 2 Remove 3 top screws from Signal Conditioner rack 3 Slide mounting tray out from rack and disconnect the unit connector If needed remove MFD as per Section 6 1 to access the Signal Conditioner connector 4 Remove the four mounting bolts and remove the Signal Conditioner unit 190 00915 01 Revision 6 5 If planning to reinstall the same unit it is not necessary to disconnect the ground strap
355. stallations with the TAWS A option If TAWS A voice callouts 400 300 200 100 are not desired follow the procedures outlined in this section to load the necessary configuration files to disable TAWS A voice callouts 1 With the loader card in the top slot of PFD1 and PFD1 in configuration mode select the SYSTEM UPLOAD page using the small FMS knob on PFD1 2 Activate cursor and rotate the small FMS knob to display drop down menu Highlight King Air Options and press ENT key on PFD 1 3 Rotate the small FMS knob to select TAWS A No Voice Callout Installation Option Press ENT key on PFD1 4 Verify the TAWS A No Voice Callout Installation Option is displayed in the Item window Press LOAD CONFIGURATION ID 3571B604 SYSTEM UPLOAD Kmart LRU VERS CARD VERS CARD PART NUM SOFTWARE CONFIGURATION N A x Figure 3 22 TAWS A Voice No Callout Configuration 5 Monitor load progress Verify software load completes without errors as indicated by the following e Green PASS in Configuration column for AIRFRAME e Upload Complete COMPLETE in the summary box 6 Press ENT key on PFD1 to acknowledge upload complete 7 Deactivate cursor G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 3 25 190 00915 01 Revision 6 3 12 TAWS A Voice Callout Option Configuration This section applies only to installations with the TAWS A option This step is necessary
356. start the G1000 in normal mode C PFD and MFD Ethernet connection check includes ARINC connection check between ADC1 and MFD and between GRSI and MFD and the DISPLAY BACKUP button check On the right hand circuit breaker panel open the MFD circuit breaker Verify NAV 1 COM 1 NAV 2 and COM 2 remain valid on both PFD 1 and PFD 2 Close the MFD circuit breaker and wait for MFD to initialize Open the PFD 2 circuit breaker Press the DISPLAY BACK UP button on the Pilot s GMA 1347D audio panel Verify NAV 2 and COM 2 are each replaced by a red X and NAV 1 and COM 1 remain valid on both the MFD and PFD 1 7 Press the DISPLAY BACK UP button on the Pilot s GMA 1347D audio panel to return to normal mode Sy ae yee A A 8 Close the PFD 2 circuit breaker and wait for PFD 2 to initialize 9 Open the PFD 1 PRI and PFD 1 SEC circuit breakers 10 Press the DISPLAY BACK UP button on the Co pilot s GMA 1347D audio panel 11 Verify NAV 1 and COM 1 are each replaced by a red X and NAV 2 and COM 2 remain valid on both the MFD and PFD 2 12 Verify ADC1 data and GRS data can be displayed on the MFD 13 Press the DISPLAY BACK UP button on the Co pilot s GMA 1347D audio panel to return to normal mode 14 Close the PFD 1 PRI and PFD 1 SEC circuit breakers and wait for PFD 1 to initialize G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 4 25 190 00915 01 Revision 6 D Engine data availability to
357. sted in Table 1 2 Inspect that all required placards are installed on the left and right control wheels Placards Placards must be legible secure and in good condition Refer to the Control Wheel Modification drawing listed in Table 1 2 Table 4 6 Instrument Panel G1000 Equipment Visual Inspection Procedure tem Description Procedure Initials Gain access to behind the instrument panel by removing the PFDs and MFD see below Gain access to circuit breaker panels by removing the screws which fasten the edgelit overlays to the panels Inspect the PFDs and MFD for any visual damage to the display screens or bezels including buttons and control knobs Remove the MFD and PFDs as described in Section 6 GDU 1040A PFD Inspect the mounting surface copper bonding fingers and connector for corrosion Qty 2 amp GDU 1500 heavy oxidation or other damage Check the integrity of the SHIELD BLOCK ground MFD attachments to the harness connector assembly as well as the integrity of the individual shields and their attachment Do not reinstall GDUs at this time GDU cutouts provide access for visual inspections below routing of wire bundles and security of attachment in accordance with AC 43 13 1B Chapter 11 Section 8 Paragraph 11 96 and the Cabin Wire Harness Routing drawing listed i in Table 1 2 Pay particular attention to possible areas of chaffing Visually inspect each GDC 74B unit mount and connector for corrosion or oth
358. step is completed or confirmed 9 When the CALIBRATE field is blinking press the ENT button to begin the procedure 10 After several seconds a new checklist appears in the lower half of the PFD Press the ENT key as each step is confirmed When the CONFIRM AIRCRAFT IS LEVEL field is blinking press the ENT key to continue Page 7 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 11 The result of the pitch roll offset compensation is displayed on the PFD If successful the AHRS records the required pitch and roll offsets informs the operator of a successful conclusion and returns to normal operation 12 Press the ENT key on the PFD to conclude this procedure for GRS 77 1 13 Repeat steps 1 through 6 for GRS 77 2 NOTE The Magnetometer Calibration Procedure that follows in Section 7 7 4 Calibration Procedure B must be carried out at a site that is determined to be free of magnetic disturbances If it is unsure whether the site is clean the technician should verify that the site is clean by following the guidance provided in Section 7 7 3 The technician may skip Section 7 7 3 if the site condition is acceptable 7 7 3 Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure Optional NOTE Typically a compass rose is an acceptable location to perform the magnetometer calibration procedure However because not all compass roses are
359. t Drawing and to Section 5 20 1 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 System Maintenance Manual 200 B200 Series King Air 190 00915 01 5 20 1 System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation Desired Operation Load Software to MFD or PFD Displays Load AIRFRAME SYSTEM MFD1 PFD 1 PFD 2 and MANIFEST configuration files to MED and PFDs Load Software Configuration files to GIA 63Ws Load Software Configuration files to GMA 1347D GDC 74B GEA 71 GRS 77 software only GMU 44 software only GTX 33 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air 190 00915 01 Criteria for Success SW Loader Card must be inserted in top slot for each display to be loaded CLR 8 ENT keys must be held during power up of display Power on only one display at a time during software loading SW Loader Card must be inserted in top slot of PFD 1 PFD 1 and MFD must be powered on PFD 1 and MFD must have correct software SW Loader Card must be inserted in top slot of PFD 1 G1000 system must be powered on PFD and MFD must have correct software PFD 1 and MFD must be successfully configured with AIRFRAME SYSTEM MANIFEST MFD1 PFD 1 and PFD 2 configuration files SW Loader Card must be inserted int
360. t useful for troubleshooting The following is a listing of possible faults that could be reported in a GSA fault log Faults can occur in either the monitor board processor or the control board processor both of which are contained in the GSA unit Monitor Processor The monitor processor contains the logs that are found in these processors 2 Pitch Servo 4 Roll Servo 6 Yaw 8 Pitch Trim Servo There are two main groupings of faults that can occur in the monitor processor The first grouping of faults can occur during the GSA unit pre flight test PFT If there is a fault during PFT the unit will not be able to transition to normal mode and the only way to clear this state would be to cycle unit power The second grouping of faults can occur during normal mode These faults generally cause a disconnect of power to the GSA and report that a fault has occurred to the GIA The Notes column indicates any actions that can be taken to troubleshoot the problem in the aircraft by the technician Any faults that are not listed here indicate an internal problem requiring replacement of the servo If the items in the Notes column check out ok replace the servo G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 37 190 00915 01 Revision 6 PFT Faults MONITOR PFT STEP NOTES A A This can sometimes be a result of a failure on the other internal servo db board check faults on the other processor UNS
361. tandby battery This unit is connected to the right hand static system 2 1 22 Standby Attitude Indicator The Mid Continent Model 4200 11 Electric Attitude Indicator is used as the standby attitude indicator It is connected to the new Standby Instrument Bus and the emergency standby battery Gyro power and internal lighting of this unit is powered from Dual Fed No 1 Bus and the emergency standby battery 2 1 23 L 3 PS 835 C or D Model Emergency Standby Battery In the event of loss of all normal electrical power the battery is designed to provide 24 Vdc nominal emergency power source for the following items e standby attitude indicator operation and internal lighting e standby altimeter vibrator and internal lighting e standby airspeed indicator lighting only e pilot side glareshield lighting The aircraft power buss provides a trickle charge to the PS 835 under normal conditions This battery is installed in the nose avionics bay It is controlled using the standby battery switch indicator on the instrument panel 2 1 24 Safe Flight Lift Computer For the optional Electronic Stability and Protection ESP feature with Angle Of Attack modes a new Safe Flight lift computer part number C 05606 1 that is a direct replacement for the existing lift computer is installed to provide an additional Low Airspeed Awareness LAA output to support the Angle of Attack modes of Electronic Stability and Protection The lift computer is loca
362. tch those values listed in Table 7 2 Table 7 2 Fuel Flow Test Points Test Point Hz Indication PPH TO 0 Page 7 10 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 7 4 4 GEA Oil Pressure Indication Functional Check The special tools and equipment listed in Table 7 3 are provided for reference only and are not specifically required Any product conforming to the specification listed may be used It is the responsibility of the technician or mechanic to determine the applicable specification prior to testing Table 7 3 Oil Pressure Indication Special Equipment Signal Generator 0 10Vdc 0 1k Hz The following steps are required to be completed on both engines as necessary 1 Remove the engine cowling Ref King Air 200 Series Maintenance Manual Chapter 71 10 00 to gain access to the engine Oil Pressure Transmitter connector P12 2 Disconnect the P12 connector from the Oil Pressure Transmitter 3 Connect the Signal Generator to pins A and B of the P12 connector 4 Apply external power to aircraft 5 Set the BATT and AVIONICS MASTER PWR switches to ON 6 Inject a DC signal with the signal generator to the values specified in the table below 7 Observe MFD in normal mode and verify Oil Pressure indications match those values listed in Table 7 4 Table 7 4 Oil Pressure Test Points Test Point VDC Indication PSI a 0 50 G1000 GFC 700 System Maintenance Manual 200
363. ted in the same location as the original lift computer under the forward cabin floor Note this unit is not used for the ESP no AOA option 2 2 G1000 Optional Interfaces Optional equipment interfaces include L 3 WX 500 Stormscope traffic systems radio altimeter ADF systems and DME systems The G1000 also provides a general purpose ARINC bus for use with third party entertainment and cabin equipment Refer to wiring diagram listed in Table 1 2 for specific interface information G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 11 190 00915 01 Revision 6 2 3 Electrical Power Distribution This airplane uses a multi bus system as detailed below and in Figure 2 18 This Figure shows the system post installation of this STC Although this STC made several bussing changes to the distribution system the core electrical generation and distribution system remains unchanged from the basic airplane design Figure 2 19 shows the power sources for all equipment used by this STC Each bus used or modified by this installation is described below Left and Right Generator Buses The left and right generator buses receive power from their respective left and right generators The left and right generator buses also support all four dual fed buses and No 1 and No 2 avionics buses respectively Isolation Bus The Isolation bus is fed by two generator buses and the battery bus The Isolation bus 1s used in this insta
364. tem Maintenance Manual 200 B200 Series King Air Page 7 45 190 00915 01 Revision 6 NOTE The dial indicator shows 0 100 inch when completely flush Therefore subtract the readings from 0 100 inch to determine the actual static port height This should be completed before making any calculations 3 For each static port measure the static port height at the A B C and D locations as shown in Figure 7 12 Record the measurements in the measurement log Figure 7 13 4 Calculate the AVERAGE for each static port using the measurements by adding the four measurements and dividing the total by 4 Record the AVERAGE in the measurement log Figure 7 13 5 Ensure the AVERAGE for each static port is within tolerance 0 045 to 0 085 inch If it is not remove and reinstall the static ports as necessary to meet the tolerance 6 Calculate the ANGLE for each static port by subtracting the smallest of the A B C or D measurements from the largest of the A B C or D measurements Record the ANGLE in the measurement log Figure 7 13 7 Ensure the ANGLE for each static port is within tolerance 0 000 to 0 026 inch If it is not remove and reinstall the static ports as necessary to meet the tolerance Figure 7 12 Static Port Measurement locations AVERAGE ANGLE A B C D 4 Largest Smallest Aircraft s n Figure 7 13 Static Port Measurement Log Page 7 46 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision
365. testing This test is performed with the battery removed from the aircraft Press and hold TEST SWITCH Figure 4 5 Item 4 and observe the OUTPUT VOLTAGE MONITOR LED s 1 Ifthe 24VDC OUTPUT VOLTAGE MONITOR LED comes on proceed with Discharge Test procedure 2 If OUTPUT VOLTAGE MONITOR LED s do not come on check fuses at bracket next to battery and replace if blown Perform Cell Isolation Test if no fuses are blown Discharge Test Load Resistor 1 Prepare for test by first constructing an X Y graph similar to the one shown below If possible use pre printed graph paper to create a record of the discharge period along the X axis and voltage readings along the Y axis Volts Volts NOTE E THESE ARE TYPICAL CURVES AND MAY VARY DUE PSEA 4 E TO TEMPERATURE TEST EQUIPMENT ETC TYPICAL OUTPUT USING INTERNAL PS HEATER 7 4 OHMS AS LOAD y TYPICAL OUTPUT USING 5 7 OHM 41 LOAD PIN Au L TO 12 GND REFERENCE MINIMUM A ACCEPTABLE DISCHARGE CURVE 0 5 10 15 20 25 30 35 40 45 Time minutes PS 835B D amp F 25 TYPICAL OUTPUT USING INTERNAL 24 a HEATER 7 4 OHMS AS LOAD TYPICAL OUTPUT USING _ 7 OHM 1 LOAD PIN 11 TO 12 GND REFERENCE 23 22 MINIMUM dl ACCEPTABLE 7 DISCHARGE CURVE 2 20 0 10 20 30 40 50 60 70 BO 90 Time minutes 2 Position all INDIVIDUAL CELL DIP SWITCHES Figure 4 5 Item 5 to the ON position If the
366. the Avionics Bus No 1 Each GTX 33 transponder interfaces with a transponder antenna mounted to the bottom of the fuselage Each GTX33D diversity transponder interfaces to a transponder antenna mounted to the top of the fuselage So A J A AI 001 8 Figure 2 5 Transponder G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 3 190 00915 01 Revision 6 2 1 6 GIA 63W Integrated Avionics Unit 2 Two Garmin GIA 63W Integrated Avionics Units IAUs contain the VHF COM NAV receivers WAAS GPS receiver Flight Director and system integration microprocessors The GIAs also serve as a communication interface to all other G1000 LRUs in the system Each GIA 63W communicates directly with the on side GDU 1040A display using a HSDB Ethernet connection Both GIAs are located remotely in the nose equipment bay GIA 1 receives primary electrical power from the Essential Bus and a secondary electrical power supply from Dual Fed Bus No 1 GIA 2 receives electrical power from Dual Fed Bus No 2 The GIA 1 s COMM power supply COMM 1 is provided by the Essential Bus GIA 2 s COMM power supply COMM 2 is provided by Avionics Bus No 1 Therefore both GIAs power up immediately with external or aircraft power or battery operation with the exception of COMM 2 operation which will become active after selection of Avionics Master on Both GIA 63Ws interface to the following equipment e Existing VOR LOC Glideslop
367. the FLC key and verify the white illumination appears next to the key If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 29 190 00915 01 Revision 6 7 12 GWX 68 Weather Radar Original GWX 68 Reinstalled No software or configuration loading is required if the removed GWX 68 is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GWX 68 Test Section 7 12 1 New Repaired or Exchange GWX 68 Installed If a new repaired or exchange GWX 68 is installed the correct software and configuration files must be loaded to the unit See Section 3 9 and then continue to the GWX 68 Test Section 7 12 1 7 12 1 GWX 68 Test Operation of the GWX 68 Weather Radar is accomplished using the MFD GCU 477 Refer to G1000 200 B200 King Air Cockpit Reference Guide listed in Table 1 2 for basic operation NOTE Before energizing the equipment be sure microwave radiation safety precautions including both fuel and personnel safety considerations have been observed These include clearing all personnel to an area beyond the maximum permissible exposure level MPEL boundary The MPEL for the GWX 68 is 11 feet 1 On the GCU turn the large FMS knob to select the Map Page Group then turn the small FMS knob to select the
368. the PFD Correct any Alerts concerning software or gt configuration errors by reloading software or cas f ron 153 configuration as noted 10 TORQU FT LB x100 15 a aa Verify GEA internal power supply configuration and calibration status in configuration mode v The internal power supply configuration and GEA 71 calibration boxes should be green If they are amp red replace the GEA 71 GIA 63W i Verify internal external and reference voltages listed in the Main Analog and I O A Analog boxes are not dashed out does not include Aircraft Power 1 and 2 v If any voltages are dashed out replace the GEA Ensure the GEA is online green checkmark on the AUX SYSTEM STATUS page If GEA is not online verify unit is receiving power at the rack connector Check the GIA GEA interconnects for faults Reload configuration files to both GIA s and the GEA If problem persists replace the GEA 71 Page 5 22 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 2 3 Engine Airframe Instrument Failures The following table provides guidance for troubleshooting individual engine airframe sensor failures Be sure to also follow previous guidance given for the GEA 71 The technician should troubleshoot to isolate the fault by checking sensor to GEA wiring replacing the suspect sensor and finally by replacing the GEA 71 Replace one part at a time Refer to Sectio
369. the procedure defined in Section 3 9 3 If a faulty LRU 1s not reporting its software version and part number check aircraft maintenance logs for last software version loaded and verify against the General Arrangement drawing The Software Manifest page may also be used to check part numbers and versions The General Arrangement drawing allows alternate part number units to be installed with certain hardware software combination restrictions Refer to the applicable Garmin Equipment Software List contained in the General Arrangement drawing for details G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 1 190 00915 01 Revision 6 6 1 GDU 1040A 1500 Removal 1 Using a 3 32 hex tool rotate all four 4 turn fasteners counter clockwise until they reach their Stops 2 Carefully remove the display from the panel 3 While supporting the display disconnect the connector Reinstallation 1 Visually inspect the connector and pins for signs of damage Repair any damage While supporting the display connect the connector to the rear of the unit 2 Carefully insert the display into the panel cutout ensuring that all 4 4 turn fasteners align with the corresponding holes 3 Seat the display in the panel cutout Do not use excessive force while inserting the display 4 Once seated rotate all four 4 turn fasteners clockwise to lock the display to the panel 5 Configure and test the MFD and or PF
370. tightly in it s mounting rack and that the mounting rack is not loose CAUTION do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need ATTITUDE FAIL to be re leveled and the PITCH ROLL OFFSET procedure performed e Ensure GPS has acquired at least four satellites has a 3D navigation solution and a DOP of less than 5 0 GRS 77 This is particularly important for an ATTITUDE FAIL that appears during ground operation only e Perform an Engine Run Up Test to check if engine vibration is causing the GRS 77 to go offline e Load configuration files to the PFD MFD GIA1 and GIA2 e Calibrate the GRS 77 Pitch Roll Offset and Magnetometer Calibration e Replace GRS 77 v If problem persists replace GRS 77 configuration module Y Contact Garmin Aviation Product Support if condition continues after replacing the GRS 77 and config module for additional assistance Page 5 20 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Associated LRU s Invalid Data Field Ensure metal objects tool boxes power carts etc are not interfering with the magnetometer and aircraft is not in hangar near other buildings parked over metal drainage culverts or on hard surfaces that may contain steel reinforcements Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring State in the cabin Cycle power a
371. ting drawing listed in Table 1 2 Pay particular attention to possible areas of chaffing Reinstall the GMU 44 A post lightning strike inspection must be done for a suspected or actual lightning strike to antennas or the OAT probes Inspect antenna probe and surrounding GTP 59 OAT Probe installation to ensure that there is no structural damage around the areas where lightning may have attached If there is visible sign of damage to the probe or antenna then it should be replaced per section 6 Refer to the Hawker Beechcraft Structural Inspection and Repair Manual listed in Table 1 2 for any aircraft structural repairs or Antenna Page 4 14 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 5 Electrical Bonding Test The following bonding tests are provided for G1000 equipped 200 B200 King Air aircraft as a requirement beyond what is given in the aircraft maintenance manual The electrical bonding checks are split into two tests Phase 3 Electrical Bonding Test and Phase 4 Electrical bonding test This places the bonding test requirement for each G1000 LRU in the same phase as the visual inspection of that zone to minimize access requirements 4 5 1 Requirements All G1000 equipment must be installed Gain access for the procedure listed below in Section 4 5 3 as required and in accordance with the King Air 200 Series Maintenance Manual It 1s recommended that these tests are conducted afte
372. tion each file is sent directly to the applicable LRU where it is stored in local LRU memory except GRS 77 amp GDC 74B Each file is also stored in the PFD internal memory The applicable PFD also sends a copy of all configuration files to the Master Configuration module located in the connector backshell see Section 6 16 Ifthe PFD is replaced the configuration module retains all configuration files in the aircraft NOTE The GRS 77 AHRS and GMU 44 Magnetometer do not have a configuration file However these LRUs do store calibration data acquired during the post installation checkout which are characteristic to the specific installation While performing maintenance on these units re calibration may be required See Section 7 7 1 for more information on re calibration criteria G1000 Master Configuration Module located in PFD backshell connector Master configuration module contains identical backup configuration files of PFD configuration memory PFD cross checks these backup files against files contained with PFD memory PFD self configures to match master configuration module J No 1 GDU 1040A PFD Contains ACTIVE PFD settings Represents SET column for all LRUs Stores all configuration files in internal memory Uses master configuration module for backup GMA 1347D Contains ACTIVE GMA settings Uses PFD internal configuration files for backup
373. tion is shown In case of PFT failure see Section 5 6 3 for additional PFT diagnostics Table 5 4 AFCS General Troubleshooting Condition Check each servo gearbox slip clutch per Section 4 9 Verify the clutches are not excessively loose and are within limits Poor AP Performance torque limits se l Check aircraft controls for proper balancing and adjustment Limited AP Authority per the King Air 200 Series Maintenance Manual Check aircraft control cables for proper tension per the King Air 200 Series Maintenance Manual For intermittent nuisance disconnects with no AFCS of PFT alert check A P disconnect switch and wiring for intermittent faults If an AFCS or PFT alert is displayed at the time of the disconnect troubleshoot per Section 5 5 AP DISC Problems Check the GIA AFCS Fault Logs according to Section 5 6 2 If a Mon Prmir Invalid message is received check for valid true airspeed A faulty GTP 59 OAT probe may cause TAS to become invalid which will flag the Mon Prmtr Invalid message Contact Garmin Product Support for assistance Check pitch trim servo status Loss of Manual Electric Trim Check MET switch discrete inputs to both GIAs by going to the GIA I O Configuration page and selecting DISCRETE IN inputs Check flap in motion discrete inputs to both GIAs for proper operation by going to the GIA I O Configuration page and selected DISCRETE IN inputs See Section 4 8 AutoTrim Inoperative If DATA indicator
374. to Section 7 7 6 7 6 GRS GMU Test The aircraft can now be taxied back and the engine can be shut down for final testing Restart the 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 within 1 minute of power up as shown in Figure 7 7 provided both GPS receivers have a valid position if GPS is unavailable AHRS initialization may take as long as 2 minutes SEC ots 799 ere 279 122 5886 125 500 com 127 258 26 675 com navi 109 10 118 98 nava 113 88 110 30 RECS Figure 7 7 Normal Mode AHRS Check If no other service is to be performed continue to the return to service checks in Section 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 7 25 190 00915 01 Revision 6 7 8 GDL 69A XM Data Link Original GDL 69A is Reinstalled No software or configuration loading is required if the removed GDL 69A is re installed This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process Continue to the GDL 69A Test Section 7 8 1 New Repaired or Exchange GDL 69A is Installed If a new repaired or exchange GDL 69A 1s installed the correct software and configuration files must be loaded to the unit then the XM Satellite Radio subscription must be reactivated See Section 3 9 and the XM Activation Instruction
375. to the instrument e If input electrical power is not adequate troubleshoot the wiring harness If input power is appropriate the unit must be removed and serviced by a qualified service facility See Section 6 27 for removal instructions Contact the manufacturer to find a qualified service facility The unit must be removed and serviced by a qualified service facility See Section 6 27 for removal instructions Contact the manufacturer to find a qualified service facility 5 23 Standby Airspeed Indicator Troubleshooting Symptom Recommended Action Airspeed Indicator lighting is inoperative or malfunctioning Airspeed displayed is incorrect Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Remove standby airspeed indicator per Section 6 25 and inspect the electrical connector Check that electrical power is being appropriately supplied to the instrument e If the input electrical power is not adequate troubleshoot the wiring harness If the input electrical power is appropriate replace the standby airspeed indicator or contact the manufacturer for further troubleshooting Using a pitot static ramp tester check airspeed displayed on standby altimeter against airspeed display from ADC2 e Ifthe airspeeds are the same inspect the pitot static ports and associated equipment for faults If the airspeeds are different replace the standby altimeter or contact the manufacturer for further tro
376. tration Number Entry 1 Ifnot applied apply power to the G1000 system 2 With PFD1 in configuration mode select the GTX page group then select the TRANSPONDER CONFIGURATION page 3 The ADDRESS TYPE default is US TAIL To enter a non US Mode S registration number set the ADDRESS TYPE field to HEX ID 4 Activate the cursor and highlight the MODE S ADDRESS field Use the small large FMS knobs to enter the US aircraft registration number or other Mode S registration number TRANSPONDER CONFIGURATION XPDR 1 ACTIVE XPDR 2 ACTIVE VFR CODE 1200 1200 AIRCRAFT WEIGHT lt 15 500 LBS lt 15 500 LBS MAX AIRSPEED lt 300 KTS lt 300 KTS ADDRESS TYPE US TAIL US TAIL MODE S ADDRESS N N FLIGHT ID TYPE SAME AS TAIL SAME AS TAIL FLIGHT ID N N ENHANCED SURVEIL ENABLED ENABLED ADS B TRANSMIT PFD CONFIG PFD CONFIG AIRCRAFT WIDTH lt 23 MT lt 23 MT AIRCRAFT LENGTH lt 15 MT lt 15 MT SURVEIL INTEGRITY lt 1x1 5 ERR HR FLT lt 1x10 5 ERR HR FLT Figure 3 45 Aircraft Registration 5 For US registered aircraft the FLIGHT ID TYPE field should be set to SAME AS TAIL For other aircraft the FLIGHT ID TYPE field should be set to CONFIG ENTRY or PFD ENTRY NOTE The CONFIG ENTRY setting requires the Aircraft Registration ID number to be entered once in the FLIGHT ID field The PFD ENTRY setting allows the pilot to enter the Aircraft Registration ID number
377. trical Equipment Install Nose Bay drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 6 29 GDU Cooling Fans Removal 1 Remove the display associated with the cooling fan per Section 6 1 2 Disconnect the electrical connector of the cooling fan 3 Use a Phillips screwdriver to remove the attachment screws from the cooling fan 4 Remove the cooling fan Page 6 16 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 Reinstallation A Reinstallation of the Sandia GDU cooling fan is the reverse of the removal Reference the Main Instrument Panel Installation drawing listed in Table 1 2 for more details 2 If further maintenance is not required proceed to Section 8 6 30 GTS 8XX Traffic Unit CAUTION After any maintenance or modification is made to the GTS 8XX TAS TCAS cables such as replacing a connector or entire cable be sure to adhere to all of the specifications and limitations such as minimum and maximum cable attenuation attenuation balance between cables phase matching etc Removal 1 Gain access to the left forward avionics compartment in the nose of the aircraft 2 Disconnect the eight coax quick lock connectors 3 Disconnect the three electrical connectors 4 Unlock the unit from the rack by loosening the ratcheting latch mechanism 5 Remove the unit from the rack Reinstallation 1 Visually inspect th
378. ubleshooting See Section 6 25 for removal instructions G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 85 190 00915 01 Revision 6 5 24 Standby Altimeter Troubleshooting Symptom Recommended Action Perform the Standby Instrument Electrical Power Checks in Section 8 1 5 Altimeter lighting is inoperative or Remove standby altimeter per Section 6 26 and inspect the electrical malfunctioning connector Check that electrical power is being appropriately supplied to the instrument e If the input electrical power is not adequate troubleshoot the wiring Altimeter Vibrator is inoperative or harness malfunctioning or fail flag is displayed e lfthe input electrical power is appropriate replace the standby altimeter or contact the manufacturer for further troubleshooting Using a pitot static ramp tester check altitude displayed on standby altimeter Note that PFD2 has error correction above 19 000 ft and will E De not be the same as the non corrected standby altimeter o ee nCOUige Inspect the pitot static ports and associated equipment for faults Replace the standby altimeter or contact the manufacturer for further troubleshooting See Section 6 26 for removal instructions 5 25 Safe Flight Lift Computer Troubleshooting Symptom Recommended Action Stall Warning System is not Troubleshoot in accordance with the King Air 200 Series Maintenance working properly or is invalid Manual listed
379. ucts the operator to prepare a detailed test sequence with precise start and stop times for exercising all electronic devices The list of relevant electronic devices are given in Table 5 5 Begin test with flaps retracted flight controls in a neutral position all lights selected OFF Elapsed Time since Start of Test Action min secs esteis G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 5 71 190 00915 01 Revision 6 Table 5 5 Magnetometer Interference Test Sequence min secs esteis 6 When the CALIBRATE field is blinking press the ENT key to begin the procedure and have a stopwatch ready to begin recording the elapsed time Page 5 72 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 NOTE It is important that the time equals zero moment corresponds with the moment the PFD first displays the blinking TEST COMPLETE Message CALIBRATION PROCEDURE Begin test sequence Select TEST COMPLETE vhen finished The calibration status will then be displayed TEST COMPLETE 7 The operator 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 8 When the operator has completed the actions specified in the test sequence press the ENTER button to indicate that the process
380. uf log txt file from the SD card using the WordPad program Verify that all of the fault logs were downloaded by checking for the End of Fault Log message at the end of the GIA data and that the last servo log entry has the current date 15 Insert the fault log as an attachment to an email and include the LRU order how the data was downloaded and send to Garmin Aviation Product Support at avionics Garmin com Page 5 42 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 7 Backup Communications Path Checks 5 1 Overview The G1000 system architecture is designed with redundant communication ports for several LRUs so that critical information can continue to be displayed in the event of an equipment or wiring failure Of most importance is flight attitude heading and air data information The GRS 77 and GDC 74B each have four separate ARINC 429 data lines which are all capable of sending data to the displays The GEA 71 GTX 33 D and GMA 1347D each have two redundant serial communication paths for the same purpose See Figure 2 21 for a basic G1000 block diagram depicting this architecture Several other diagrams are shown later in this section for illustrative purposes When troubleshooting refer to the G1000 GFC 700 Wiring Diagram listed in Table 1 2 NOTE Refer to Section 8 1 6 for procedures on checking the status of each configured G1000 GFC 700 backup data path 5 7 2 Data Path
381. val 1 Gain access by removing the right side GDU 1040A display unit see Section 6 1 2 Unlock the GDL 69A handle by loosening the Phillips screw on the handle 3 Pull the handle upward to unlock the GDL 69A Gently remove the unit from the rack Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Gently insert the GDL 69A into its rack The handle should engage the dogleg track 3 Press down on the GDL 69A handle to lock the unit into the rack 4 Lock the handle to the GDL 69A body using the Philips screw G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 6 5 190 00915 01 Revision 6 5 Configure and test the GDL 69A according to Section 7 8 6 11 GSA 80 Servos Removal 1 Gain access to the desired servo s 2 Disconnect the servo harness connector 3 Use a socket or open wrench to loosen and remove the servo attachment bolts The Pitch Trim servo bracket will need to be removed to access all the Pitch Trim servo attachment bolts 4 Carefully remove the servo and place a protective cover on the output gear 5 Place a protective cover over the GSM 85A 86 servo gearbox Reinstallation 1 Inspect the servo output gear for abnormal wear 2 Using a lint free cloth remove excess grease build up from the servo output gear see Figure 6 1 IMPORTANT It is not necessary to remove all of the grease from the output gear only the excess grease DO N
382. vos is connected and registering 28 volts Make sure the AP disconnect switch has been installed in the aircraft Make sure no one is holding the AP disconnect switch down on the yoke PFT step 13 Verify servo validity This step 1s checking to make sure all the Servos are up and communicating with valid data to the GIA in TDM mode If this step fails then make sure all Servos are turned on and communicating by checking for green boxes on the GFC configuration page PFT step 14 Verify cross GIA PFT is completed This step is checking to make sure the other GIA 1s also on step 14 of its PFT If this step fails try cycling power on GIA1 GIA2 and all servos If PFT still fails at step 14 then you will need to go check the PFT status of the other GIA and see what step it is failing NOTE The PFT status is communicated between GIA1 and GIA2 using HSDB As a result both the PFD and MFD must be powered for this state to pass PFT step 15 PFT completed The PFT has successfully completed PFT step 16 PFT failed The PFT has failed Page 5 36 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 5 6 3 1 Servo Faults and Troubleshooting Whenever a servo fault occurs a status message is logged to the corresponding servo control or monitor maintenance log This information is also accompanied by a time and date stamp An RTC DATE entry is made every time a servo is powered on it is normally no
383. wait for completion of the pre flight test sequence Press the XFR key on the AFCS mode controller and engage the autopilot by pressing the AP key on the 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 and PFD2 Press the GO AROUND button on the left throttle Verify TO is annunciated on PFD1 and PFD2 for both PITCH and ROLL modes and the command bars should be at 8 degrees nose up and wings level Press the Flight Director FD key on the AFCS mode controller to deactivate the GA mode Press the AP key to engage the autopilot Press the CWS button for a minimum of 5 seconds and release verifying there is no residual force on the control stick for the pitch axis G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 8 11 190 00915 01 Revision 6 IZ 13 14 ES Disengage the autopilot by pressing the AP YD DISC TRIM INTRPT switch on the co pilot s control wheel Engage VS mode by pressing the VS key on the AFCS mode controller Verify PFD1 and PFD2 display VS in green and indicates a pitch reference of 0 FPM Press the FLC key on the AFCS mode controller and verify that FLC is annunciated on PFD1 and PFD2 in green with a reference of 100 KTS Press the ALT key on the AFCS mode controller and verify that the ALT annunciation is displayed in green on
384. well maintained even an existing compass rose should be regularly evaluated using the method described here to determine if it 1s free of magnetic disturbances If evaluation of an existing compass rose indicates that magnetic disturbances are present then an alternative location must be found to perform the Magnetometer Calibration Procedure A G1000 equipped airplane that has completed the pitch roll offset compensation procedure Procedure A 1 Section 7 7 2 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 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 7 7 4 of this document with the exception of the direction of turns around the site NOTE Although Section 7 7 4 indicates that the Magnetometer Calibration Procedure should be performed by making a series of clockwise turns around the site the procedure can also be performed by making counter clockwise turns for the purpose of evaluating the site for magnetic disturbances If the PFD dis
385. will verify the availability of the feeders to the essential bus and the No 1 and No 2 dual feed buses 1 Apply external power Turn BATT and AVIONICS MASTER switches to ON position Verify all circuit breakers are closed Observe PFD1 PFD2 and MFD displays and verify all displays are powered and in normal format Verify the absence of red Xs or alert messages Select or verify selected on side sensors for PFD1 and PFD2 Open the ESS BUS PRI circuit breaker Verify the MFD remains powered Open the ESS BUS SEC circuit breaker Verify the MFD 1s not powered Close the ESS BUS PRI circuit breaker Verify the MFD powers up Close the ESS BUS SEC circuit breaker Open the No 1 dual bus feeder circuit breakers RH NO 1 LH NO 1 Verify PFD1 FAN FAIL and GIAI FAN FAIL alert messages are shown on the PFD If the messages are not shown check the dual bus feeder circuit breakers RH NO 1 LH NO 1 and the diode CR1002 between No 1 dual feed bus and the essential bus After replacement of the faulty component the test should be repeated 7 Close No 1 dual bus feeder circuit breaker RH No 1 Verify PFD1 FAN FAIL and GIA1 FAN FAIL alert messages are not shown on the PFD If messages illuminates check dual bus feeder circuit breaker RH No 1 associated limiter and diode 8 Open No 1 dual bus feeder circuit breaker RH No 1 9 Close No 1 dual bus feeder circuit breaker LH No 1 Verify PFD1 FAN FAIL and GIA1 FAN FAIL alert messages are not shown on
386. ync l Other Equipment Removal amp Replacement On Condition Standby Airspeed Si A Indicator tatic pressure system test according to 14 CFR 91 411 and Part 43 Appendix E 24 Calendar Months Removal 8 Replacement On Condition Standby Altimeter Test according to 14 CFR 91 411 and Standby Attitude Removal 8 Replacement On Condition L 3 PS 835 C or D Removal amp Removal amp Replacement On Condition Condition Standby Battery Capacity test of standby battery 4 E E 2 12 12 Calendar Months 12 Calendar Months Standby Battery Verify the standby battery is being Phase 1 2 3 amp 4or Charge Check charged 6 Calendar Months Verify STBY ATT 8 STBY ALT vibrator operate and STBY ATT STBY ALT amp Standby Instrument STBY A S illumination function on either a Power aircraft power or standby battery power Phase 1 2 3 8 4 ecks standby compass checked during existing maintenance Annunciator Switch les Standby Battery Removal amp Replacement On Condition Denotes Airworthiness Limitation Maintenance Requirement See Section 4 1 Page 4 8 G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Revision 6 190 00915 01 4 3 1 Discontinued Maintenance Table 4 2 shows a list of inspections and tests that are listed in the King Air 200 Series Maintenance Manual but may be no longer required post incorporation of this STC It is the responsibility of the installer to ensure that there are no post
387. ystem Maintenance Manual 200 B200 Series King Air Page 4 29 190 00915 01 Revision 6 17 Replace AHRS1 to normal attitude and verify that attitude display on PFD1 displays current aircraft attitude 18 Repeat Steps 13 through 17 for AHRS2 19 The G1000 Miscompare checks are complete 4 14 Nose Avionics Compartment Fans Operational Check This procedure will verify that airflow is present from the ported avionics cooling fans to the 1 and 2 GIA units The fan speed monitoring circuits and annunciations are checked by the G1000 Cooling Fan Fail Annunciation Check in Section 8 1 4 and a Visual Inspection of the fan and its hoses is accomplished in Section 4 4 This check requires the G1000 to be powered on 1 Gain access to the nose avionics compartment 2 Disconnect cooling fan hose from the pilot side GIA and verify airflow is present 3 Reconnect the cooling fan hose to the GIA 4 Repeat Steps 2 through 3 for the copilot side GIA 5 The Nose Avionics Compartment Fans Operational Check is complete 4 15 Instrument Panel Fans Operational Check This procedure will verify that airflow is present from the PFD1 MFD and PFD2 cooling fans The fan speed monitoring circuits and annunciations are checked by the G1000 Cooling Fan Fail Annunciation Check in Section 8 1 4 This check requires the G1000 to be powered on 1 Remove PFD1 as described in Section 6 1 2 Identify the PFD1 cooling fan and verify airflow is present 3 Rein
388. ystem includes the L ENG INSTR and R ENG INSTR buses which after this STC are powered from Dual Fed Bus No 1 and No 2 respectively On these aircraft GEA 1 receives power from Dual Fed Bus No via the L ENG INSTR bus and GEA 2 receives power from Dual Fed Bus No 2 via the R ENG INSTR bus Each GEA interfaces to the following sensors for its onside engine e Oil Pressure Sensor e Oil Temperature Sensor e Fuel Flow Sensor via onside Signal Conditioner e Turbine Speed Sensor via onside Signal Conditioner e Propeller Speed Sensor via onside Signal Conditioner e Torque Sensor e Interstage Turbine Temperature ITT Sensor Figure 2 7 GEA unit G1000 GFC 700 System Maintenance Manual 200 B200 Series King Air Page 2 5 190 00915 01 Revision 6 2 1 8 GDC 74B Digital Air Data Computer 2 The Garmin GDC 74B computers compile information from the pitot static system and various outside air temperature OAT and awareness sensors and provide digital air data computations to the G1000 system The GDC 74B communicates with the GIA 63W GDU 1040A and GRS 77 using ARINC 429 digital interface The unit is mounted behind the instrument panel GDC 1 receives primary electrical power from the Essential Bus and a secondary power supply from Dual Fed Bus No 1 GDC 2 receives power from Dual Fed Bus No 2 GDC 1 and GDC 2 connect to existing pitot static ports Refer to Figure 2 20 for a schematic of the aircraft s pitot static system and

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