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Garmin G1000 NXi, System Maintenance Manual

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G1000 NXi System Maintenance Manual 

Page 155 

King Air 300 Series 

Revision 1 

190-00716-N1

 

Channel 

LRU 

Indicator  Status 

CHNL 2 

GEA2 

Green 

GIA2/GEA2 data path is functioning correctly. 

Red 

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 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. 

•

  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 GIA2/GEA2 interconnect wiring for faults. 

Amber 

GIA2GEA2 data path functionality is unknown.  Reload 
GIA2 configuration files. 

CHNL 4 

GFC 700 

Green 

GIA2/GFC 700 data path is functioning correctly. 

Red 

GIA2/GFC 700 data path is not functioning correctly. 

•

  Load GIA2 configuration files, GIA Gains file and GSA 

software and gains file (if 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. 

 

 

Summary of Contents for G1000 NXi

Page 1: ...190 00716 N1 2017 Revision 1 System Maintenance Manual King Air 300 Series Includes Instructions for Continued Airworthiness for STC SA01535WI D...

Page 2: ...rinted 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...

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

Page 4: ...Block Grounds 37 G1000NXi GFC700 Block Diagrams 37 GDU 1050A and GDU 1550 Displays 39 Softkeys 40 FMS Knob 40 GCU 477 MFD Controller 41 GMC 710 AFCS Controls 41 GMA 1347D Audio Panel 42 G1000 Normal M...

Page 5: ...Electrical Bonding Test 114 GSU 75B GRS 77 or GRS 7800 Earth Magnetic Field Updates 117 GSA 80 Greasing Procedure 117 Flaps in motion Discrete Input Check 118 GSM 86 Slip Clutch Torque Check Procedure...

Page 6: ...leshooting 212 Backshell Backplate Connectors 214 Mechanical Standby Attitude Indicator Troubleshooting 222 Mechanical Standby Airspeed Indicator Troubleshooting 222 Mechanical Standby Altimeter Troub...

Page 7: ...BF Goodrich PS 835 C or D Model Emergency Battery 248 MD 302 Standby Attitude Module SAM 248 Mechanical Standby Indicators 251 GIA Cooling Fans 253 GDU Cooling Fans 253 GTS 820 850 and GTS Processor...

Page 8: ...FliteCharts Functional Check 347 ChartView Functional Check 348 SafeTaxi Functional Check 349 DME Functional Check 350 ADF Functional Check 351 GRA 5500 Radar Altimeter Functional Check 351 Non Garmi...

Page 9: ...viii King Air 300 Series Revision 1 190 00716 N1 GPS Failure Test 378 GIA Failure Test 380 GEA Functional Check 381 Standby Instrument Electrical Power Checks 382 G1000 Backup Path Test 384 GFC 700 Gr...

Page 10: ...on Post G1000 STC 25 Figure 2 26 G1000 Component Power Sources 26 Figure 2 27 Pitot Static System with ADC s and AHRS s Installed 35 Figure 2 28 Pitot Static System with GDU 75B ADAHRS s Installed 36...

Page 11: ...or P15001 217 Figure 5 16 GRS 77 Backshell Connector P771 217 Figure 5 17 GRS 7800 Backshell Connector P78001 218 Figure 5 18 GSU 75B Connector View from Front P751 218 Figure 5 19 GDC 7400 Mating Co...

Page 12: ...1 Low Speed Awareness Band Symbolization 353 Figure 8 2 RVSM Critical Region 355 Figure 8 3 RVSM Critical Region modified 357 Figure 8 4 Dial Indicator 358 Figure 8 5 Static Port Measurement 358 Figur...

Page 13: ...dication Test Points 126 Table 4 13 Torque Indication Test Points 128 Table 4 14 Standby Battery Required Equipment 132 Table 5 1 SVS Troubleshooting 168 Table 5 2 SVS Related Alert Messages 168 Table...

Page 14: ...ed 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 Re...

Page 15: ...ading instructions for a complete system software load Section 4 Instructions for Continued Airworthiness Provides maintenance instructions for continued airworthiness of the G1000 system Section 5 Tr...

Page 16: ...Broadcast FS Flight StreamTM 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 Turbi...

Page 17: ...00629 52 Optional Equipment Install Tail Shelf King Air 300 B300 005 00629 54 Wire Harness Installation Nose King Air 300 B300 005 00629 55 Wire Harness Installation Cabin King Air 300 B300 005 00629...

Page 18: ...or the King Air 300 Series 190 00355 04 GDL 69 Series SiriusXM Satellite Radio Activation Instructions 190 00303 10 GRS77 GMU44 Installation Manual 190 00303 72 GSA8X GSM85 A Installation Manual 190 0...

Page 19: ...in 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 co...

Page 20: ...is processed within the servos and turned into aircraft flight control surface commands The autopilot cannot operate unless the flight director is engaged Manual Electric Trim When the autopilot is no...

Page 21: ...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 i...

Page 22: ...o the G1000 system without taking the data card out of the aircraft Figure 2 2 Flight Stream 510 GMA 1347D Audio Panel 2 The Garmin GMA 1347D Audio Panel integrates NAV COM digital audio intercom syst...

Page 23: ...ns regarding the controls are discussed in the G1000 Cockpit Reference Guide Figure 2 5 FMS Controller Transponder 2 The Garmin GTX 33 GTX 3000 GTX 345R or GTX 335R transponders communicate with the o...

Page 24: ...TCAS II operations with the GTS Processor The transponder units are mounted on the upper avionics equipment shelf in the tail section of the airplane Power is provided by the No 1 GTX from Triple Fed...

Page 25: ...1 s COM power supply COM 1 is provided by No 1 Triple Fed Bus GIA 2 s COM power supply COM 2 is provided by No 3 Triple Fed Bus Therefore both GIAs power up immediately with external or aircraft power...

Page 26: ...isplayed 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 No 1 Triple...

Page 27: ...o existing pitot static ports Refer to Figure 2 28 for a schematic of the aircraft s pitot static system and its connections to the G1000 STC installed equipment Each GSU 75B provides the following in...

Page 28: ...ves 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 por...

Page 29: ...sent using ARINC 429 digital interface to both GDU 1050As and GIA 63Ws The GRS interfaces with and provides power to the GMU 44 Magnetometer The GRS supplies attitude and heading information directly...

Page 30: ...69A 69A SXM provides the interface to the GWX 68 or GWX 70 weather radar and optional GDL59 Wi Fi datalink by acting as a communications hub between the MFD and GWX 68 GWX 70 and GDL 59 via HSDB The G...

Page 31: ...r or on the upper avionics equipment shelf in the tail section The GDL 59 is powered from the Right Gen Avionics bus Figure 2 15 GDL 59 Wi Fi Datalink GSR 56 Satellite Receiver optional The GSR 56 pro...

Page 32: ...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 820 850 traffic system is powered from the Right Gen Avionics...

Page 33: ...ervos to automatically control aircraft pitch pitch trim and roll 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 w...

Page 34: ...M 9100 Servo Gearbox The GSM 9100 is responsible for transferring the output torque of the GSA 9000 servo actuator to the mechanical flight control surface linkage Figure 2 22 GSA 9000 GSM 9100 GRA 55...

Page 35: ...by Indicators This STC has two options for standby primary flight indications The first option is a Mid Continent Instruments MD 302 Standby Attitude Module that provides attitude airspeed and altitud...

Page 36: ...ctric Attitude Indicator part number listed on General Arrangement drawing is used as the standby attitude indicator It is powered by No 3 Triple Fed Bus and the emergency standby battery Gyro power a...

Page 37: ...t Gen Avionics Bus is powered from the Right Generator Bus via the Avionics No 2 relay The Triple Fed Avionics Bus is powered from the Triple Fed bus via the Avionics No 3 relay All avionics relays ar...

Page 38: ...G1000 NXi System Maintenance Manual Page 25 King Air 300 Series Revision 1 190 00716 N1 Figure 2 25 300 Series Electrical Distribution Post G1000 STC...

Page 39: ...G1000 NXi System Maintenance Manual Page 26 King Air 300 Series Revision 1 190 00716 N1 Figure 2 26 G1000 Component Power Sources...

Page 40: ...190 00716 N0 Post Installation Checkout Procedure King Air 300 Series and 005 00629 22 Electrical Load Test Report G1000 integrated Avionics System Hawker Beechcraft Model 300 B300 King Air respective...

Page 41: ...0 011 03177 10 GDL 59 Wi Fi 1 0 572 A 011 01746 00 GTS Processor or GTS 820 Traffic Processor or GTS 850 Traffic Processor 1 2 5 A 011 02571 00 1 6 A 011 01446 00 1 6 A 011 01553 00 GRA 5500 Radio Alt...

Page 42: ...ut Secondary power input Secondary power input 0 45 A See Note GRS 7800 011 02278 00 GMU 44 011 00870 10 011 00870 20 0 38 A See Note GSU 75B 011 03094 40 GMU 44 011 00870 10 011 00870 20 GDC 7400 ADC...

Page 43: ...01020 10 GRS 77 GMU44 AHRS 1 or GRS7800 GMU44 AHRS 1 or GSU 75B GMU44 ADAHRS 1 11 0 3 A See Note GRS 77 011 00868 10 GMU 44 011 00870 10 011 00870 20 Primary power input 0 45 A See Note GRS 7800 011 0...

Page 44: ...20 GSA 80 Pitch Servo 1 1 61 A 011 00877 20 GSA 9000 Yaw Servo 1 1 80 A 011 02213 00 011 02213 10 GSA 80 Pitch Trim Servo 1 1 61 A 011 00877 21 MFD Cooling Fan 1 0 1 A 305468 00 Sandia P N or 013 0010...

Page 45: ...70 20 0 45 A Total GRS 7800 011 02278 00 GMU 44 011 00870 10 011 00870 20 0 38 A GSU 75B 011 03094 40 GMU 44 011 00870 10 011 00870 20 GDC 7400 ADC 2 1 0 230 A 011 02337 00 011 02337 01 GIA 63W NAV 2...

Page 46: ...Meggitt Sig Cond 2 1 0 032 A 85 292 4 Avionics Bus Triple Fed GTX 33 Transponder 1 or GTX 33D Transponder 1 or GTX 3000 Transponder 1 or GTX 335R 1 or GTX 345R 1 1 1 6 A 011 00779 30 1 6 A 011 00779 2...

Page 47: ...t Units Used Each Unit Amps DC Part Number Notes Standby Altimeter 1 See Note 3A43 22 35F 28 1 FU Thommen P N or Vibrator 0 030 A Lighting 0 096 A 0 157 A total 16650 1172 Aerosonic P N Standby Airspe...

Page 48: ...HEAD R H PITOT MAST L H PITOT MAST 1 AIR DATA COMPUTER 2 AIR DATA COMPUTER AFT PRESSURE BULKHEAD TOP BOTTOM R H STATIC PORTS L H STATIC PORTS ALTERNATE STATIC SELECTOR VALVE ALTERNATE STATIC PORT COPI...

Page 49: ...SURE BULKHEAD TOP BOTTOM R H STATIC PORTS L H STATIC PORTS ALTERNATE STATIC SELECTOR VALVE ALTERNATE STATIC PORT COPILOT PFD MFD PILOT PFD BOTTOM TOP DRAIN DRAIN OAT PROBE OAT PROBE DATA BUS Standby A...

Page 50: ...ine Airframe Unit GTX 345R 335R 33 33D 3000 Transponder 1 OAT Airspeed Altitude Vertical Speed Attitude Rate of Turn Slip Skid GMU 44 Magnetometer Heading GSA 80 Roll Servo Autopilot Calculations No 1...

Page 51: ...G1000 NXi System Maintenance Manual Page 38 King Air 300 Series Revision 1 190 00716 N1 Figure 2 30 G1000NXi GFC 700 Block Diagram with Separate ADC and AHRS...

Page 52: ...Air 300 Series Revision 1 190 00716 N1 GDU 1050A and GDU 1550 Displays Figure 2 31 and Figure 2 32 provide identification of the GDU 1050A PFD and GDU 1550 MFD controls Figure 2 31 GDU 1050A Control...

Page 53: ...ugh 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 dire...

Page 54: ...g figure Range pan knob Flight planning keys FMS Ctrl knob Alpha entry keys Numeric Entry keys Comm Nav Tranponder keys Figure 2 34 MFD Controls GCU 477 shown GMC 710 AFCS Controls The dedicated AFCS...

Page 55: ...controls Transceiver Audio Telephone Speaker Marker Beacon Signal Sensitivity Transceiver Audio Passenger Address Music Marker Beacon Mute Transmitters Digital Recording Playback Cabin Intercom Master...

Page 56: ...n GTX Mode S Transponders GDL 69A Datalink Unit GWX 68 or GWX 70 Weather Radar Unit GTS 820 850 or GTS Processor Traffic System GDL 59 GSR 56 Wi Fi Satellite Optional GRA 5500 Radar Altimeter Optional...

Page 57: ...anual 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 N...

Page 58: ...INITIALIZING SYSTEM appears in the upper left corner of the MFD 7 Press and hold the ENT key on PFD1 pilot while applying power using the PFD1 PRI circuit breaker 8 Release the ENT key after INITIALI...

Page 59: ...Set softkey Causes the LRUs current settings to be copied to the master configuration module as SET items CAUTION The ACTV SET softkey must be used with caution If an improperly configured unit is in...

Page 60: ...ubleshooting Figure 3 2 Loss of Communication Configuration Prompts When configuration settings are changed the technician receives on screen prompts and or confirmations such as those shown in Figure...

Page 61: ...figuration 6 Diagnostics 11 Airframe Configuration 2 CDU Status Page 7 Ethernet Test 12 TAWS Configuration 3 Key Test 8 Video Test 13 SurfaceWatch Configuration 4 FS 510 Test 9 Alert Configuration 14...

Page 62: ...RMT Page Group 1 Remote Controller Status GWX Page Group 1 GWX Configuration GTS Page Group 1 GTS Configuration GRA Page Group 1 GRA Configuration OTHER Page Group 1 Stormscope CAL Page Group 1 Fuel T...

Page 63: ...Arrangement drawing listed in Table 1 1 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 softw...

Page 64: ...e current file follow the procedures outlined below NOTE In order to create a King Air 300 Series system loader card the installer completing these procedures must be an authorized Garmin King Air Ser...

Page 65: ...ar to the one shown below will appear The numbers shown are for example only 5 Click on the Select Action button for software file 006 B2286 0 X _0A exe the X is the number from the General Arrangemen...

Page 66: ...d reader The loader card program will delete all files on the SD card before loading G1000 system software files on it if the card is not blank 8 Double click the exe file that was downloaded onto the...

Page 67: ...G1000 NXi System Maintenance Manual Page 54 King Air 300 Series Revision 1 190 00716 N1 10 Select the SD card reader drive and click Next 11 Follow the on screen prompts to continue...

Page 68: ...190 00716 N1 12 The program will make the SD loader card and prompt you when it s done 13 Once successfully completed the following window will display Click Finish to close the program The SD card c...

Page 69: ...ng software version part number and LRU status Software files are loaded to LRUs from the PFD1 System Upload page in configuration mode Configuration File Descriptions There are configuration files fo...

Page 70: ...figures to match master configuration module GMA 1347D Contains ACTIVE GMA settings Uses PFD internal configuration files for backup No 1 GIA 63W Contains ACTIVE settings Uses PFD internal configurati...

Page 71: ...a The GSU 75B ADAHRS air data configuration file is loaded directly to GSU 75B internal memory A copy of the file is stored in the GSU 75B configuration module The GSU also stores AHRS calibration dat...

Page 72: ...enter configuration mode and it is not needed to press and hold a softkey at power on G1000 Hardware Software Compatibility Check Before installing software the technician must first ensure that hardw...

Page 73: ...tional equipment i e GDC 7400 GRS 77 or 7800 AHRS or GSU 75 ADAHRS GTX 33 or GTX 3X5 transponder etc Section 3 5 1 helps find which units are installed without a physical inspection Third party avioni...

Page 74: ...t the unit part number is based on the unit s serial number reported on the MFD Aux System Status page in Normal mode or PFD1 System Status page in Config mode This table lists the units that have dif...

Page 75: ...0716 N1 For Garmin units that S N checking is not required but the technician needs to see if they are installed such as GSR 56 check for the presence of the unit in the LRU Information list If the un...

Page 76: ...sion 1 190 00716 N1 Determining Garmin Unit Ethernet Connections Place the displays in config mode and go to PFD1 SYSTEM DATA PATHS page Press the HSDB softkey at the bottom of the screen and the Ethe...

Page 77: ...stalled To check if the aircraft has ESP installed go to the MFD Aux System Setup page and press the Setup 2 softkey at the bottom of the screen If the Stability and Protection field is present the ai...

Page 78: ...GTX 33 Transponders With GTS Unit Installed King Air Dual GTX 3000 Transponders King Air Dual GTX 335R Transponders and No GTS Unit Installed King Air Dual GTX 335R Transponders With GTS Unit Install...

Page 79: ...ssible if installing TAWS A King Air TAWS A Support1 King Air TAWS A Voice No Callout Installation Option2 11 Non Garmin Options Multiple selections possible King Air ADF Option King Air DME Option Ki...

Page 80: ...oad 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 te...

Page 81: ...DO YOU WANT TO UPDATE SYSTEM FILES prompt appears press the YES softkey 7 After the new GDU software is loaded to PFD2 a DO YOU WANT TO UPDATE THE SPLASH SCREEN prompt may appear If it does press the...

Page 82: ...teps Do not operate or turn off MFD and or PFD2 while loading software and configuration files unless specifically instructed to do so A failed or cancelled load may result If an incorrect configurati...

Page 83: ...ons After the configuration files are loaded the units will update and remove the INV status and will load automatically 5 Press the CHK All softkey 6 Press the Load softkey Monitor the loading progre...

Page 84: ...ata checklist group and press the ENT key to select it 3 Press the CHK All softkey 4 In the PRODUCT window move the cyan selection box down with the large FMS knob to highlight the CARD COPY configura...

Page 85: ...ate the small FMS knob to highlight the item that was checked on the Configuration checklist in Section 3 6 in the 06 Garmin Transponders checklist group and press the ENT key to select it 3 Press the...

Page 86: ...TEM window rotate the small FMS knob to highlight the first item that was checked on the Configuration checklist in Section 3 6 in the 08 Radar checklist group and press the ENT key to select it 3 Pre...

Page 87: ...this section must be followed to load the necessary configuration files required to enable TAWS A gear and flap messages A TAWS A enablement card is also required for this option NOTE TAWS A Voice No...

Page 88: ...ndow move the cyan selection box down with the large FMS knob to highlight the CARD COPY configuration check box Press the ENT key to uncheck the configuration check box 4 Press the Load softkey 5 Mon...

Page 89: ...red by the installing agency from the Garmin or Jeppesen website The ChartView database is not present in a new display Insert the ChartView Enablement card in the top slot of PFD1 and power on PFD1 i...

Page 90: ...the curser in the Group field Rotate the small FMS knob to highlight Enable_SurfaceWatch and press the ENT key to select it In the ITEM window rotate the small FMS knob to highlight SurfaceWatch Feat...

Page 91: ...lutter Suppression Enable and press the ENT key to select it Press the Load softkey Monitor load progress Verify software load completes without errors as indicated by the following Green PASS in the...

Page 92: ...all FMS knob to highlight Enable TAWS A and press the ENT key to select it Press the Load softkey Monitor load progress Verify software load completes without errors as indicated by the following Gree...

Page 93: ...Enable Enhanced AFCS and press the ENT key to select it Press the Load softkey Monitor load progress Verify software load completes without errors as indicated by the following Green PASS in the Confi...

Page 94: ...following Green PASS in the Configuration column for each item loaded Upload Complete COMPLETE in the summary box Press the ENT key to acknowledge the Upload Complete box Open PFD1 circuit breaker and...

Page 95: ...Monitor load progress Verify software load completes without errors as indicated by the following Green PASS in the Configuration column for each item loaded Upload Complete COMPLETE in the summary b...

Page 96: ...led by default in the baseline configuration 1 Insert the software loader card in the top slot of PFD1 power on PFD1 in configuration mode 2 Press the NO softkey number 11 softkey to acknowledge the f...

Page 97: ...the AIRCRAFT CONFIGURATION page on PFD1 2 Activate the cursor to select the AIRCRAFT REGISTRATION field and enter the aircraft s tail number 3 For non US N number aircraft registrations rotate the la...

Page 98: ...blank 9 Rotate the large FMS knob to select the VFR CODE field and enter the desired code that will become active when the VFR key on a PFD is pressed 10 Press the SET GTS softkey if present and ackno...

Page 99: ...knob to select Configuration Manager page 3 Press the softkey labelled CNFM CFG on PFD1 4 Press the ENT key on PFD1 to select OK when prompted to confirm configuration as expected configuration 5 Open...

Page 100: ...ettings select the YES softkey 10 When user settings have been cleared appears on the screen open PFD2 circuit breaker Database Loading Follow this procedure to load the databases Obtain the following...

Page 101: ...pear between the Standby and Active columns to show which databases will be transferred to Active use on the next power cycle Figure 3 12 MFD Aux Database Page DB Transfer When all database updates ar...

Page 102: ...al mode use the GCU FMS knob to select the Navigation Map page then press GCU MENU key to display the PAGE MENU 2 Turn the small right knob to select or verify selected Map Setup and press the ENT key...

Page 103: ...allation Manual Garmin P N 190 01277 00 GRA Software Download This section describes the GRA 5500 software loading process for airplanes that had previously installed the G1000 system and subsequently...

Page 104: ...erface between a personal computer USB A receptacle and the GRA 5500 USB B receptacle installed in the wiring harness PC Installation of the Installation Tool 1 Once downloaded launch the installation...

Page 105: ...tallation Tool will display a list of all valid software region files in the directory If no software region information is displayed in the list the selected directory does not contain valid software...

Page 106: ...ation with Section 8 2 Stormscope Functional Check 1 With PFD1 in configuration mode use the PFD1 large FMS knob to select OTHER and the Stormscope configuration page Figure 3 13 Stormscope Configurat...

Page 107: ...es made to any settings will NOT be saved until you select ACCEPT CHANGES in the menu prior to exiting the Configuration Mode MD 302 Configuration 1 Open STBY INSTR circuit breaker 2 Press and hold th...

Page 108: ...00 81 96 3 HALF WHITE 100 157 100 157 96 158 4 RAD BLUE 122 None 122 None 125 None 5 FULL BAR 259 None 259 None 263 None 16 Enter the range markings for the airframe model and propeller combination re...

Page 109: ...set to BLU and V1 and V2 values should be set to 000 g Continue in sequence through all rows to enter the color bands needed and select EXIT when done 17 In the CONFIGURE AIRCRAFT menu select VNE TAB...

Page 110: ...IXED POINTER 32 In the CONFIGURE DISPLAY menu select AIRSPEED MINIMUM 33 Select 40 KNOTS 34 In the CONFIGURE DISPLAY menu select DISPLAY ORIENTATION 35 Select VERTICAL RIGHT 36 In the CONFIGURE DISPLA...

Page 111: ...it 4 Close STBY INSTR circuit breaker 5 Release the control knob when the introduction screen appears 6 In the CONFIGURE MENU select CALIBRATE PRESSUES 7 Using the pitot static test set apply an altit...

Page 112: ......

Page 113: ...ation in this document should always be combined with sound aviation maintenance practices and a thorough knowledge of the system Use sound avionics maintenance practices when working around or on G10...

Page 114: ...ure A Calibration Calibrated VHF NAV COM ILS ramp tester or equivalent Calibrated transponder ramp tester or equivalent Calibrated pitot static ramp tester Outdoor line of site to GPS satellite signal...

Page 115: ...from the Garmin Dealer Resource Center at www garmin com and load with the GRA Retrofit Installation Tool part number 006 A0451 00 Download the software part number and versions listed in the General...

Page 116: ...he King Air 300 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...

Page 117: ...2 6 4 GTX 335R GTX 345R GTX 33 or GTX 3000 Transponder Qty 2 Removal Replacement 6 5 On Condition Special Inspection Perform GTX 335R GTX 345R GTX 33 or GTX 3000 test 7 5 4 24 Calendar Months GDC 740...

Page 118: ...s max G1000 Cooling Fan Fail Annunciation Check Verify the operation of the fan power and fan speed monitoring circuits for PFD1 fan MFD fan and PFD2 fan and fan fail messages 9 4 Nose Avionics Compar...

Page 119: ...installation drawings 6 12 On Condition GSM 86 and GSM 9100 Servo Gear Box Removal Replacement Refer to the servo install drawings listed in Master Drawing List listed in Table 1 1 6 13 On Condition...

Page 120: ...nding resistance check of G1000 equipment 4 5 3 Phase 3 Perform the Phase 4 electrical bonding resistance check of G1000 equipment 4 5 4 Phase 4 Lightning Strike to GTP 59 OAT Probe or Antenna Actual...

Page 121: ...of standby battery 4 16 2 12 Calendar Months Standby Battery Charge Check Verify the standby battery is being charged 4 16 1 220 hours max or 6 Calendar Months whichever comes first Standby Instrumen...

Page 122: ...r GWX 70 a Inspect the GWX 68 or GWX 70 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...

Page 123: ...are securely fastened Table 4 5 Pilot s Compartment Visual Inspection Procedure Item Description Procedure Initials Placards Inspect that all required placards are installed on the left and right con...

Page 124: ...and ensure it is secure and in good condition and routed to provide positive moisture drainage GEA 71 Engine Airframe Unit Qty 2 Inspect the GEA 71 unit rack and connectors for corrosion or other def...

Page 125: ...ess for the following Inspections remove floorboards in cabin at FS 185 00 and FS 246 750 Cabin Wiring Harness Inspect all exposed wire harness for chafing damage proper routing of wire bundles and se...

Page 126: ...n specifications g Ensure that each cable is correctly attached to the clamps h Follow recommended checks for checking main control cables following the instructions in Chapter 27 Flight Controls of t...

Page 127: ...eptable magnetic interference levels GIA Fans Verify the GIA cooling fan discrete out is correctly activating when the fan is not working by performing tests per Section 9 4 Electrical Bonding Test Th...

Page 128: ...sured voltage reading by the same percentage Example If the measured current is 1 2 amps 20 high from the desired 1 amp current and the measured voltage is 3 0 mV then the value recorded will be 3 mV...

Page 129: ...5 m is present Nose Section GWX 68 or GWX 70 body __________ m Nose Avionics Compartment GIA 1 top __________ m GIA 2 top __________ m GSU 75B GRS 77 or GRS 7800 1 metal base __________ m GSU 75B GRS...

Page 130: ...from Garmin every five years as long as the GSU 75B GRS 77 or GRS 7800 remain Garmin supported products The G1000 system alerts the operator that the magnetic field database is out of date by issuing...

Page 131: ...ETRACT 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...

Page 132: ...r INITIALIZING SYSTEM appears in the upper left corner of PFD1 Steps 1 through 3 put PFD1 in Configuration Mode and PFD2 MFD in normal mode 4 With the MFD in Normal Mode press the red DISPLAY BACKUP b...

Page 133: ...he aircraft control wheel If an abnormal disconnect of a servo occurs reset the AFCS SERVO circuit breaker and repeat the test 10 When test is completed verify the CLUTCH TEST PASS message is displaye...

Page 134: ...b 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 th...

Page 135: ...xternal power receptacle and turn on the ground power unit 2 Set the BAT EXT PWR and AVIONICS MASTER PWR switches to ON 3 With the G1000 system in normal mode pull the following circuit breakers on th...

Page 136: ...NC 429 IN6 GSU75 1 GRS77 1 or GRS7800 1 Ref Section 5 1 1 2 5 With GIA2 selected in the SELECT UNIT window verify the following indicators are green RS232 Channel 1 GDC72 2 or GDC74 2 RS232 Channel 6...

Page 137: ...n 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 ADC 1 data and GRS 1 data can be d...

Page 138: ...satellites and return to normal display modes 7 Open GIA1 primary and secondary CBs and GIA2 CB 8 Verify the following NAV 1 COM 1 NAV 2 and COM 2 flag invalid on both PFD 1 and PFD 2 GPS CDI flags D...

Page 139: ...leads from the left hand engine thermocouple junction block mounted to the gas generator case 2 Connect the DC Power Supply or ITT Tester or equivalent across the Alumel Green 10 and Chromel White 8 l...

Page 140: ...e GIA 2 circuit breaker 8 Turn off the G1000 system and remove external power from aircraft 9 Reconnect all thermocouple wires to the junction blocks and torque nuts per Beechcraft King Air 300 Series...

Page 141: ...autopilot is not engaged and the AFCS 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...

Page 142: ...im wheel and repeat the test step 20 Use the pitch trim switch or the pitch trim wheel to trim full down 21 Hold the elevator in the neutral position control wheel at the mid point position between fu...

Page 143: ...AFCS mode controller press the ALT HDG and AP buttons and verify autopilot engages 6 Slowly increase the altitude to simulate an altitude miscompare of greater than 200 ft Verify PFD 2 altitude does...

Page 144: ...itude and verify that attitude display on PFD1 displays current aircraft attitude 18 Repeat Steps 13 through 17 for AHRS 2 ADAHRS 2 For this test PFD 1 attitude should not change and PFD 2 attitude sh...

Page 145: ...Table 1 1 With the PS 835 battery installed in the aircraft connect 28VDC ground power to the aircraft Turn the ground power and aircraft power on then verify all four Battery Voltage LEDs are lit to...

Page 146: ...G1000 NXi System Maintenance Manual Page 133 King Air 300 Series Revision 1 190 00716 N1 Figure 4 5 Standby Battery...

Page 147: ...h 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 B Discharge Te...

Page 148: ...CEPTABLE DISCHARGE CURVE the unit is considered satisfactory 10 If unit discharge plot is satisfactory and no other failures were revealed perform the Charging Procedure within 2 hours of completion o...

Page 149: ...tor is extinguished 5 Pull GIA 2 circuit breaker Verify RUD BOOST OFF annunciator illuminates 6 Reset GIA 1 and GIA 2 circuit breakers Verify RUD BOOST OFF annunciator extinguishes 7 Pull the AFCS SER...

Page 150: ...D or GTX 3000 transponder is installed Transponder Antenna Upper 2 if Garmin GTX 33D or GTX 3000 transponder is installed Iridium Antenna if Garmin GSR 56 satellite receiver is installed Wi Fi Antenna...

Page 151: ...aced the technician must follow the procedures given in Sections 6 7 and 9 to ensure proper operation of the system Troubleshoot the G1000 system by first identifying then isolating the specific failu...

Page 152: ...eck 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 System Annunciations If dat...

Page 153: ...wn to be good The applicable data paths can be verified by viewing the following configuration mode pages GDU RS 232 ARINC 429 CONFIG Page PFD 1 RS 232 Channel LRU Indicator Status CHNL 2 GMC 710 Gree...

Page 154: ...er 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 PFD1 GRS...

Page 155: ...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 GMC 710 Load PFD2 and GMC 71...

Page 156: ...r 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...

Page 157: ...77 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 If po...

Page 158: ...1 if problem remains Amber GIA1 GDC 1 data path functionality is unknown Reload GIA1 configuration files CHNL 2 GRS 77 or GRS 7800 or GRS 79 2 output only White N A GIA1 GRS or GSU 2 output data path...

Page 159: ...Check the GIA1 GRS or GSU 1 interconnect wiring for faults Amber GIA1 GRS or GSU 1 data path functionality is unknown Reload GIA1 configuration files CHNL 7 GMA 1347 1 Green GIA1 GMA 1347D 1 data pat...

Page 160: ...the problem is in the original GRS2 o Replace original GRS2 if box turns green after swapping units Check the GIA1 GRS or GSU 2 interconnect wiring for faults Amber GIA1 GRS or GSU 2 data path functi...

Page 161: ...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 Swap GRS1 and GRS2 no reconfigurati...

Page 162: ...mber GIA2 GDC 2 data path functionality is unknown Reload GIA2 configuration files CHNL 2 GRS 77 or GRS 7800 or GRS 79 1 output only White N A GIA2 GRS or GSU 1 output data path is not monitored A whi...

Page 163: ...Check the GIA2 GRS or GSU 2 interconnect wiring for faults Amber GIA2 GRS or GSU 2 data path functionality is unknown Reload GIA2 configuration files CHNL 7 GMA 1347D 2 Green GIA2 GMA 1347D 2 data pa...

Page 164: ...m if the problem is in the original GRS1 o Replace original GRS1 if box turns green after swapping units Check the GIA2 GRS or GSU 1 interconnect wiring for faults Amber GIA2 GRS or GSU 1 data path fu...

Page 165: ...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 swapping units Swap GRS2 and...

Page 166: ...al GEA1 if box turns green after swapping units Check the GIA1 GEA1 interconnect wiring for faults Amber GIA1 GEA1 data path functionality is unknown Reload GIA1 configuration files CHNL 2 GEA2 Green...

Page 167: ...U Indicator Status CHNL 1 GEA1 Green GIA2 GEA1 data path is functioning correctly Red GIA2 GEA1 data path is not functioning correctly Verify GEA1 is powered on using the GEA Status page Load GIA2 and...

Page 168: ...g 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 GIA...

Page 169: ...If problem is resolved replace faulty unit If indication is not illuminated check for wiring faults between the GIAs and aircraft squat switch system Low Speed Awareness Band permanently inhibited GDU...

Page 170: ...If problem follows the GIA replace the GIA If problem persists replace the PFD1 or PFD2 XPDR FAIL GTX 335R GTX 345R GTX 33 or GTX 3000 Check GTX 335R 345R 33 33D 3000 configuration settings for GIA1...

Page 171: ...ware to the airframe shelf or the aircraft will need to be re leveled and the PITCH ROLL OFFSET procedure performed Ensure GPS has acquired at least four satellites has a 3D navigation solution and a...

Page 172: ...harger 2 The resistance between the base of each static discharger and the surface to which it is attached 3 The resistance between the elevators rudder and the airplane structure Ensure that a cell p...

Page 173: ...e or configuration errors by reloading software or configuration as noted Verify GEA internal power supply configuration and calibration status in configuration mode The internal power supply configur...

Page 174: ...ple cable Replace GEA 71 Torque Check torque transmitter GEA wiring Check power input to torque transmitter Replace torque transmitter Replace GEA 71 Prop RPM Check prop tachometer Signal Conditioner...

Page 175: ...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...

Page 176: ...n 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 flashes between white letters on...

Page 177: ...arning alert GPWS mode 1 or 2 Excessive Descent Rate Or Excessive Closure Rate Don t Sink voice or Too Low Terrain voice TAWS Caution alert GPWS mode 3 altitude loss after takeoff or go around Glide S...

Page 178: ...ical speed and climbing or descending through the threat s flight path Increase Climb Increase Climb voice TCAS II Resolution Advisory Climb at the rate depicted by the solid green bar on the vertical...

Page 179: ...closed Check cooling fan wiring Refer to G1000 GFC 700 Wiring Diagram listed in Table 1 1 Replace cooling fan Refer to Sections 6 29 and 6 30 AVN 2 FAN FAIL Avionics cooling fan 2 is inoperative PFD 1...

Page 180: ...ase or GDU SW mismatch has not occurred If a mismatch has occurred load correct database software files or replace the terrain card TAWS system is currently being tested N A Test will be conducted up...

Page 181: ...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 Verify that the G1000 AHRS and heading data are valid on the PFD Ver...

Page 182: ...lem 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 aler...

Page 183: ...page for additional GFC 700 system information Review the fault and assert logs for the GIAs and servos see Section 5 8 2 Isolate the fault to an LRU Replace this LRU and confirm the resolution of the...

Page 184: ...e King Air 300 Series Maintenance Manual Check aircraft control cables for proper tension per the King Air 300 Series Maintenance Manual AP DISC Problems For intermittent nuisance disconnects with no...

Page 185: ...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...

Page 186: ...here 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 t...

Page 187: ...e the gains are not compatible with the GIA software Reload the gain files to correct PFT FAIL Timeout STEP Pre flight test has failed because the specified step has not passed in the allotted time Se...

Page 188: ...stuck The specified mode has been disengaged due to a stuck pitch MET switch Check the MET trim switches for proper identification GIA Pre Flight Test Steps PFT step 0 System initialization verify GFC...

Page 189: ...GIA is initialized This step is checking to make sure the other GIA is also on step 6 of its PFT If this step fails try cycling power on GIA1 GIA2 and all servos If PFT still fails at step 6 then you...

Page 190: ...ct switch down on the yoke PFT step 13 Verify servo validity This step is 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 m...

Page 191: ...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 dur...

Page 192: ...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 pow...

Page 193: ...ct 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 em...

Page 194: ...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...

Page 195: ...700 backup data path Data Path Failures Failure Message Cause Solutions FAILED PATH A data path has failed A communications data path status is not being received by the G1000 Determine which data pat...

Page 196: ...inserted with the label facing to the right do not attempt to remove Return the unit to an authorized repair facility for service A button knob joystick does not appear to function Go to the GDU TEST...

Page 197: ...mismatch Communication Halted The system has detected an incorrect software version loaded in MFD CNFG MODULE PFD 1 configuration module is inoperative The PFD master configuration module has failed C...

Page 198: ...tion module If message persists check PFD1 config module wiring for faults and replace if necessary If issue continues replace PFD1 master configuration module If problem persists replace the display...

Page 199: ...base error exists The specified PFD has encountered an error in the terrain database PFD 2 DB ERR PFD 2 terrain database error exists MFD1 DB ERR MFD1 obstacle database error exists The MFD has encoun...

Page 200: ...OOLING has poor cooling Reducing power usage PFD 1 has exceeded its operating temperature range Check cooling fan and wiring for proper operation if applicable Replace cooling fan if unable to determi...

Page 201: ...ined a key is stuck on the PFD 2 Miscellaneous Alerts Failure Message Cause Solution XTALK ERROR A flight display cross talk error has occurred A communication error has occurred between the MFD and o...

Page 202: ...G1000 has determined the specified PFD needs service Ensure the PFD connector is fully seated and locked Return unit to an Authorized Repair Facility for service PFD 2 SERVICE needs service Return un...

Page 203: ...ources of noise are eliminated Buttons Do Not Work Some buttons are disabled in the GMA CONFIGURATION page by default This is to remove potential sources of audio noise for inputs that are not used If...

Page 204: ...ted The system has detected an incorrect software version loaded in the specified GMA 1347D Load the correct unit software See Section 3 8 for the Software Loading procedure MANIFEST GMA2 software mis...

Page 205: ...d GIA2 to verify location of problem If problem follows unit replace GIA If problem persists replace GMA1 with a known good unit If problem persists reinstall original GMA1 and replace GMA2 NAV Sympto...

Page 206: ...orized Repair Facility for service COM2 SERVICE COM2 needs service Return unit for repair The system has determined COM2 needs service Replace GIA2 Return unit to an Authorized Repair Facility for ser...

Page 207: ...al remote transfer switch is stuck in the enabled or pressed state Press the COM2 external remote transfer switch again to cycle its operation Check COM2 external remote transfer switch and wiring Swi...

Page 208: ...ransfer switch again to cycle its operation Check NAV1 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...

Page 209: ...antenna and cabling 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...

Page 210: ...no GPS position fix available or the system is in dead reckoning mode GPS NAV LOST Loss of GPS navigation Position error The G1000 has detected an internal position warning has occurred GPS NAV LOST L...

Page 211: ...IAs are not properly configured after being swapped replaced this message appears Load the configuration files for that GIA See Section 7 3 3 8for GIA 63 Configuration Loading procedure If problem per...

Page 212: ...tected a configuration mismatch in the specified GEA 71 Load GEA configuration files See Section 7 4 for GEA 71 Configuration Procedure If problem persists replace master configuration module check co...

Page 213: ...tion 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 databases will no longer work as they will remain loc...

Page 214: ...e GDL 69A 69A SXM antenna and cabling for faults Reseat the 69A 69A SXM to verify the coax connector is fully seated If unit is not active contact SiriusXM Customer service to have a refresh signal se...

Page 215: ...r the Configuration Procedure If problem persists replace master configuration module check config module harness for faults and replace if necessary NOTE New Terrain Obstacle cards Jeppesen Aviation...

Page 216: ...blem persists replace the GSU75B GRS 77 or GRS 7800 Attitude appears unstable Ensure that a cell phone or a device using cell phone technology is not turned on even in a monitoring state in the cabin...

Page 217: ...a monitoring state in the cabin Check GPS status for GIA 1 and 2 on MFD Aux GPS Status page If one or both GPS receivers cannot acquire a position lock see GPS troubleshooting section Troubleshoot GIA...

Page 218: ...than 6 degrees Perform Calibration Procedure A1 GSU 75B GRS 77 or GRS 7800 Pitch Roll Offset Calibration reference Section 7 10 1 GMU Alerts Failure Message Cause Solutions MANIFEST GMU1 software mism...

Page 219: ...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 Figure 5 7 Magnetometer Interfere...

Page 220: ...g lights on 0 50 Landing lights off 1 00 Taxi lights on 1 20 Taxi lights off 1 40 Strobes on 1 50 Strobes off 2 00 Recognition lights on 2 10 Recognition lights off 2 20 Beacon on 2 30 Beacon off 2 40...

Page 221: ...appropriate installation manual for the GSU 75B 190 01639 00 GRS 77 190 00303 10 and GRS 7800 190 01091 00 for acceptable magnetic interference limits Compare the corresponding timestamps with the pr...

Page 222: ...onfiguration mismatch Load GWX configuration files Replace GWX If problem persists replace master configuration module check config module wiring for faults and replace if necessary NOTE New Terrain O...

Page 223: ...onal 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 mod...

Page 224: ...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...

Page 225: ...RU is reporting data on the Aux 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...

Page 226: ...t be powered on PFD 1 and MFD must have correct software Load Software Configuration files to GIA 63Ws SW Loader Card must be inserted in top slot of PFD 1 G1000 system must be powered on PFD and MFD...

Page 227: ...29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 2...

Page 228: ...1 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 P13471 P13472 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 1718 19 20 21 22 2324 25 26 2728 29 30 3132 33 34 3536 3738 39 4...

Page 229: ...000 NXi System Maintenance Manual Page 216 King Air 300 Series Revision 1 190 00716 N1 P3301 Figure 5 12 GTX 3000 Connectors P3301 and P3302 Figure 5 13 GTX 335R 345R Looking at Front of Connector P32...

Page 230: ...Manual Page 217 King Air 300 Series Revision 1 190 00716 N1 Figure 5 14 GTX 345R Only Looking at Front of Connector P3252 Figure 5 15 GDU 1050A 1550 Backshell Connector P10401 or P15001 Figure 5 16 GR...

Page 231: ...King Air 300 Series Revision 1 190 00716 N1 Figure 5 17 GRS 7800 Backshell Connector P78001 Figure 5 18 GSU 75B Connector View from Front P751 Figure 5 19 GDC 7400 Mating Connector P74001 Figure 5 20...

Page 232: ...ision 1 190 00716 N1 Figure 5 21 GCU 477 Backshell Connector P4751 Figure 5 22 GMC 710 Backshell Connector P7101 Figure 5 23 GWX 68 Backshell Connector P681 Figure 5 24 GWX 70 Backshell Connector P751...

Page 233: ...Air 300 Series Revision 1 190 00716 N1 Figure 5 26 GTS 820 850 Mating Connector P8003 Rear View Figure 5 27 GTS Processor Connector P8001 Figure 5 28 GPA 65 Mating Connector P651 Rear View Figure 5 2...

Page 234: ...9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75...

Page 235: ...nstructions Contact the manufacturer to find a qualified service facility Mechanical Standby Airspeed Indicator Troubleshooting Symptom Recommended Action Airspeed Indicator lighting is inoperative or...

Page 236: ...er or contact the manufacturer for further troubleshooting See Section 6 28 2 for removal instructions MD 302 Standby Indicator Troubleshooting Symptom Recommended Action Standby indicator is inoperat...

Page 237: ...y Iridium signal Ensure the Iridium antenna has an unobstructed view of satellite constellation Check the Iridium antenna cable and connectors Verify antenna ground plane is adequate No audio output C...

Page 238: ...cility for service Whisper Shout Fault Internal Fault Return unit to an authorized Repair Facility for service Transmit Power Fault Internal voltages are out of tolerance Check power connections to th...

Page 239: ...sed Verify that the GTS Traffic Processor is configured correctly for the desired display Traffic Display erroneously indicates TA at own ship position Check the mutual suppression line to ensure it i...

Page 240: ...Cal Fault Check antenna installation and all cable connections and retry self test Ensure that self test occurs in area free of buildings and large objects that can reflect signals Download the asser...

Page 241: ...ntenance of electrical components near the GMU 44 magnetometers either tail or horizontal stabilizer locations perform the Calibration Procedure E Magnetometer Interference Test reference Section 5 an...

Page 242: ...the corresponding holes 4 Seat the display in the panel cutout Do not use excessive force while inserting the display 5 Once seated rotate all four GDU 1050A or six GDU 1550 turn fasteners clockwise...

Page 243: ...le screw to 10 14 in lbs 5 Configure and test the GIA 63W s according to Section 7 3 GEA 71 Engine Airframe Unit Removal 1 Gain access by removing the appropriate GDU 1050A display unit see Section 6...

Page 244: ...the rack 4 Lock the handle to the GTX 33 body using the Philips screw Torque the handle screw to 10 14 in lbs 5 If the unit is installed under the cabin floor reinstall the remote equipment shelf or t...

Page 245: ...32 hex drive tool into the access hole in the front of the unit 6 Push on the left side of the unit and turn hex drive tool clockwise until it stops Do not apply more than 8 in lbs of torque on the he...

Page 246: ...the GRS 77 on the mounting plate ensuring the orientation is correct 3 Use a 2 Phillips screwdriver to torque the GRS 77 mounting screws to the rack to 22 25 in lbs 4 Connect the connector to the GRS...

Page 247: ...the unit back until the feet are fully engaged with the remote rack 3 Push down and turn each retention screw clockwise Torque each retention screw to 15 20 in lbs 4 Connect the pitot and static lines...

Page 248: ...e guard to the unit and retain the wire guard and grommet from the pigtail harness Reinstallation 1 Visually inspect the connectors to ensure there are no bent or damaged pins Repair any damage 2 Rein...

Page 249: ...e Philips screw Torque the handle screw to 10 14 in lbs 5 Configure and test the GDL 69A 69A SXM according to Section 7 11 GSA 80 and GSA 9000 Servo Motors Removal 1 Gain access to the desired servo s...

Page 250: ...fully place the servo into the servo gearbox ensuring proper orientation and alignment 4 Fasten the servo to the servo gearbox using the existing hardware Follow the installation instructions provided...

Page 251: ...einstall the servo s per Section 6 12 GCU 477 Removal 1 Use a 3 32 hex drive tool to turn each of the four locking sockets turn counterclockwise until they reach their stops 2 Disconnect backshell ass...

Page 252: ...tion 7 15 Configuration Modules Configuration Module Removal Replacement Configuration modules Reference Figure 6 3 and Table 6 1 Item 1 shown below are located in the following LRU harness connector...

Page 253: ...2 2 Spacer Config Module 1 213 00043 00 3 Cable 4 Conductor Harness 1 325 00122 00 4 Pins 22 AWG HD 5 336 00021 00 Removal 1 Disconnect connector from LRU 2 Remove 2 screws 8 from cover 7 and remove c...

Page 254: ...nector 1 011 02582 00 Garmin 5 Socket Contact 4 M39029 56 348 Best Source Removal 1 Disconnect connector 1 from LRU 2 Remove 2 screws 3 washers ring terminals and configuration module 4 from strain re...

Page 255: ...02179 00 2 Cable 4 Conductor Harness 1 325 00122 00 3 Pins 22 AWG HD 4 336 00021 00 4 Pan Head Screw 1 211 60232 07 Removal 1 Disconnect connector from LRU 2 Remove two screws from cover 3 Remove one...

Page 256: ...ble 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 Go to the Configuration Upload Page on PFD 1 3 Press the UPDT CFG...

Page 257: ...e dissimilar metals at the pin contacts Figure 6 6 GEA Backshell Thermocouple Table 6 4 Thermocouple Kit 011 00981 00 Item Description Qty Needed Garmin Part Number 1 3 Thermocouple K type 1 925 L0000...

Page 258: ...in Table 1 1 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...

Page 259: ...e Antenna Install drawing listed in Table 1 1 4 Reinstall the aft cabin ceiling panel 5 Proceed to Section 8 17 for testing of the GSR 56 Wi Fi Antenna Removal 1 Gain access to the antenna coaxial cab...

Page 260: ...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...

Page 261: ...ds illuminate and reflect EMERG FREQ in white and 121 5 in white 3 Release cockpit annunciator Press To Test switch 4 If further maintenance is not required proceed to Section 9 L 3 Avionics BF Goodri...

Page 262: ...a nut driver to remove the four hex head attachment screws from the front of the indicator 5 Remove the indicator Reinstallation 1 Reinstall the electronic standby indicator referencing the Main Inst...

Page 263: ...nd 5 5 Remove the Configuration Module PC Board Assembly BACKSHELL COVER 9017274 CFG MODULE ASSY 9017184 1 SPRING part of 9016479 BACKSHELL 9017218 SLIDE LOCK part of 9016479 SCREW 4 40 part of 901647...

Page 264: ...with the holes of the PC board and the backshell 6 Using a Phillips screwdriver re install the two counter sunk screws and secure the cover 7 Configure MD 302 unit per Section 3 19 8 Test MFD per Sec...

Page 265: ...dicator Ensure the standby attitude indicator gyro is not spinning this may take 10 minutes or longer after the unit has been turned off This unit is very delicate handle like eggs Refer to the 4300 S...

Page 266: ...emove the cooling fan Reinstallation 1 Reinstallation of the avionics cooling fan is the reverse of the removal Reference the Electrical Equipment Install Nose Bay drawing listed in Table 1 1 for more...

Page 267: ...the rack by using the ratcheting latch mechanism 4 Reconnect the eight coax QMA or TNC connectors and the three electrical connectors 5 Close access to the left forward avionics compartment 6 Configur...

Page 268: ...or panel at the main entry door Remove the remote equipment shelf or detach the two rack mount angles from the shelf Retain all mounting hardware b If the unit is installed in the tail open the tailco...

Page 269: ...ack This 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...

Page 270: ...a RS 422 connection to GIA2 configure and test the GRA 5500 according to Section 7 16 For non integrated installations using Arinc 429 connections configure and test per Section 3 17 GSD 41 Data Conc...

Page 271: ...EMOVED FROM THE SYSTEM WHEN LOADING SOFTWARE Remove power only when told to do so by the following procedure Power loss during a software upgrade may cause a LRU to become corrupted and unresponsive r...

Page 272: ...or system alerts are present troubleshoot as necessary using Section 5 or re load the system using the legacy method in Section 3 8 16 If there are no red Xs or system alerts continue to Section 7 1 7...

Page 273: ...replaced all databases will have to be reloaded 1 Open the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Remove SD cards from top and bottom slots of PFD2 MFD and PFD1 if present 3 Apply power...

Page 274: ...on both displays 6 Check that the engine instrument fields are valid on the MFD Figure 7 1 G1000 Normal Mode Check 7 Push the red DISPLAY BACKUP button on the pilot side GMA 1347D Verify that the pilo...

Page 275: ...must be loaded to the unit See Section 7 2 1 LRU Replacement Procedure GMA 1 or GMA 2 1 Open the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Apply power to the G1000 system by connecting ext...

Page 276: ...was replaced 9 Highlight the software box and press the ENT key 10 Highlight the Configuration box and press the ENT key 11 Press Load softkey 12 Monitor load progress Verify software load completes w...

Page 277: ...placement and aircraft equipped with a DME only 1 Scroll the curser to the ITEM window highlight King Air DME Option and press the ENT key on PFD1 2 Press the CLR ALL softkey 3 Scroll the curser to GM...

Page 278: ...the PA select annunciator is illuminated on GMA1 and GMA2 Verify COM1 active frequency is displayed white 8 Initiate passenger address using pilot s headset boom mic by keying the pilot s PTT Verify t...

Page 279: ...inue 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 positi...

Page 280: ...udio system and through both cockpit speakers SiriusXM Audio Suppression Check This procedure is applicable only to aircraft that have Sirius XM radio subscriptions WARNING The following steps require...

Page 281: ...eaker is closed 8 While monitoring pilot and copilot Sirius XM audio press the STALL WARN TEST switch and verify the following Stall warning tone is active XM audio is muted in the pilot and co pilot...

Page 282: ...aded to the unit See Section 7 3 1 LRU Replacement Procedure GIA1 or GIA2 1 Open the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Apply power to the G1000 system by connecting external power t...

Page 283: ...light 01 Baseline and press ENT key on PFD1 6 Rotate the small FMS knob to display the drop down menu Rotate the large FMS knob to highlight King Air 200 300 Series Baseline Load Press ENT key on PFD1...

Page 284: ...without errors as indicated by the following Green PASS in the Configuration and Software columns for each item loaded Upload Complete COMPLETE in the summary box 8 Acknowledge the prompt by pushing...

Page 285: ...figuration box whichever was replaced Press the ENT to check the box 7 Press Load softkey 8 Monitor load progress Verify software load completes without errors as indicated by the following Green PASS...

Page 286: ...uipped with a Garmin GRA 5500 radar altimeter only 1 Scroll the curser to the Group window and select 08 Radar 2 Press the ENT key 3 In the ITEM window highlight King Air GRA 5500 Radar Altimeter and...

Page 287: ...loaded Upload Complete COMPLETE in the summary box 6 Acknowledge the prompt by pushing the ENT key 11 Non Garmin Options For GIA 2 replacement and aircraft equipped with a non Garmin radar altimeter...

Page 288: ...in the summary box 5 Acknowledge the prompt by pushing the ENT key Non Garmin Options For GIA 2 replacement and aircraft equipped with a lightning detection system only 1 Scroll the curser to the ITE...

Page 289: ...nd Software columns for each item loaded Upload Complete COMPLETE in the summary box 11 Acknowledge the prompt by pushing the ENT key Configuration Manager Update 1 With the system still in configurat...

Page 290: ...NR is displayed 3 Verify that the GPS INTEG flag is out of view 4 Select 121 150 MHz on the No 1 COM transceiver 5 Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels 6 D...

Page 291: ...ected Rotate CRS1 and CRS2 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 4 Verify full scale deflectio...

Page 292: ...ight 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 o...

Page 293: ...ion 7 4 1 LRU Replacement Procedure GEA1 or GEA2 1 Open the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Apply power to the G1000 system by connecting external power to the aircraft to energiz...

Page 294: ...chever was replaced 9 Highlight the software box and press the ENT key to check the box 10 Highlight the Configuration box and press the ENT key to check the box 11 Press Load softkey 12 Monitor load...

Page 295: ...ad progress Verify software load completes without errors as indicated by the following Green PASS in the Configuration and Software columns for each item loaded Upload Complete COMPLETE in the summar...

Page 296: ...l values and markings with no red Xs or erratic indications Reference Figure 7 3 for normal engine instrument markings figure may not reflect actual aircraft installation If individual engine readings...

Page 297: ...ng connections 3 Apply external power to aircraft and start the G1000 system in normal mode 4 If the test input shows an incorrect ITT gauge reading outside the Indication tolerance in Table 7 1 perfo...

Page 298: ...ack to conduct the continuity test from the terminal block to the GEA 2 unit ITT input pins b If the ITT Wire Harness Continuity Check passes replace GEA 2 5 If the test input shows a correct ITT read...

Page 299: ...y external power to aircraft and start the G1000 system in normal mode 3 Inject a DC voltage into GEA 1 by connecting the DC power source to the left engine firewall connector pins J102 C HI and J102...

Page 300: ...cuit wiring for faults b Replace GEA 2 6 If no other EIS gauge tests are needed reconnect and safety the J103 connector and reinstall the engine cowling s Test Point VDC Torque Indication 0 000 0 020...

Page 301: ...ignal into the No 2 TACH GEN Adapter by connecting the Signal Generator to the left engine firewall connector pins J105 J and J105 K 4 Allow five seconds for the input signal to stabilize after change...

Page 302: ...Indication tolerance in Table 7 4 perform the following a Check gauge circuit wiring for faults b Replace the Signal Conditioner c Replace GEA 1 8 If no other EIS gauge tests are needed reconnect and...

Page 303: ...to the left engine firewall connector pins J104 Y HI and J104 Z LO 5 If the test input shows a correct gauge reading within the Indication tolerance in Table 7 5 troubleshoot the fuel flow sensor per...

Page 304: ...tional Check Required test equipment Name Requirement Calibrated DC Power Source 0 10 VDC If the left engine gauge needs to be tested perform the following Disconnect the J104 firewall connector Apply...

Page 305: ...e GEA 2 Turn off the G1000 system and remove external power from the aircraft If no other EIS gauge tests are needed reconnect and safety the J105 connector and reinstall the engine cowling s Test Poi...

Page 306: ...t the G1000 system in normal mode 3 Inject a resistance into GEA 2 by connecting the Decade box to the left engine firewall connector pins J105 W and J105 X 4 If the test input shows a correct gauge r...

Page 307: ...circuit breakers 2 Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses 3 Turn on Avionics electrical busses 4 Power on...

Page 308: ...mns for each item loaded Upload Complete COMPLETE in the summary box 13 Acknowledge the prompt by pushing the ENT key 14 Deactivate the curser 15 Scroll to the Configuration Manager page 16 Press the...

Page 309: ...ified 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 ram...

Page 310: ...uration module has been replaced LRU Replacement Procedure GSU1 or GSU2 1 Open the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Apply power to the G1000 system by connecting external power to...

Page 311: ...Magnetometer Press ENT key on PFD1 7 Press the CLR ALL softkey 8 Use the large FMS knob to scroll to GSU 1 or GSU 2 whichever was replaced 9 Highlight the software box and press the ENT key to check t...

Page 312: ...ded to the unit LRU Replacement Procedure GDC 1 or GDC 2 1 Open the MFD PFD 1 PRI PFD 1 SEC and PFD 2 circuit breakers 2 Apply power to the G1000 system by connecting external power to the aircraft to...

Page 313: ...indicated by the following Green PASS in the Configuration and Software columns for each item loaded Upload Complete COMPLETE in the summary box 13 Acknowledge the prompt by pushing the ENT key 14 De...

Page 314: ...he 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 conf...

Page 315: ...0 0 20 20 2 2 0 99 0 20 20 2 2 0 132 0 20 20 2 2 0 198 0 20 20 2 2 1000 50 1000 20 20 2 2 2000 50 2000 25 25 2 2 4000 80 4000 25 25 2 2 8000 80 8000 30 30 2 2 8000 260 8000 30 30 2 2 10000 120 10000 3...

Page 316: ...7 34961 87 87 2 2 35000 156 34953 87 87 2 2 35000 164 34946 87 87 2 2 35000 171 34939 87 87 2 2 Aircraft S N _____________________ Date __________________ Operator __________________ ADTS Make _______...

Page 317: ...e 7 9 Table 7 9 Vertical Speed Table Vertical Speed feet minute Allowed tolerance feet minute 2000 100 1000 50 500 45 200 45 0 N A No VS Display 200 45 500 45 1000 50 2000 100 OAT Probe Check 1 Ensure...

Page 318: ...w Repaired or Exchange GRS is Installed If a new repaired or exchange GRS is installed then software must be loaded New GRS Configuration Module is Installed If the GRS configuration module is replace...

Page 319: ...FMS knob to highlight 04 AHRS Air Data and press ENT key on PFD1 8 Rotate the small FMS knob to display the drop down menu Rotate the large FMS knob to highlight the installed GRS Press ENT key on PFD...

Page 320: ...connecting external power to the aircraft to energize the aircraft and avionics electrical busses 3 Turn on Avionics electrical busses 4 Power on PFD2 MFD and PFD1 in configuration mode 5 Using the PF...

Page 321: ...ate the curser 15 Scroll to the Configuration Manager page 16 Press the CNFM CFG softkey 17 Select ok when prompted to Confirm configuration as expected configuration 18 Power cycle the system Verify...

Page 322: ...S GMU Test Section GRS AHRS or GSU ADAHRS was removed and or replaced The mounting tray WAS removed and or mounting tray bolts WERE loosened X X X GRS AHRS or GSU ADAHRS Configuration Module was repla...

Page 323: ...yed on the PFD and press the ENT key as each 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...

Page 324: ...ometer 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...

Page 325: ...curacy of the AHRS ADAHRS cannot be guaranteed if this calibration is not performed on a magnetically clean compass rose or equivalent If the compass rose condition is not known it is recommended that...

Page 326: ...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 con...

Page 327: ...n mode 2 Use the FMS small knob to highlight GRS 1 for calibration and press the ENT key The SELECT PROCEDURE field is not blinking 3 Initiate the AHRS engine run up vibration test procedure by perfor...

Page 328: ...nce The following are potential causes for failure of the engine run up test a Vibration motion of GSU GRS and or GMU44 caused by neighboring equipment and or supports b Mounting screws and other hard...

Page 329: ...i System Maintenance Manual Page 316 King Air 300 Series Revision 1 190 00716 N1 Figure 7 8 Normal Mode AHRS Check If no other service is to be performed continue to the return to service checks in Se...

Page 330: ...l busses 4 Power on PFD2 MFD and PFD1 in configuration mode 5 Using the PFD1 scroll to the LRU replacement page 6 Activate the curser and select GDL69 in the LRU dropdown box 7 Press the CHK All softk...

Page 331: ...13 Press the CNFM CFG softkey 14 Select ok when prompted to Confirm configuration as expected configuration 15 Power cycle the system Verify there are no red Xs or system alerts 16 If red Xs or system...

Page 332: ...ectrical busses 3 Turn on Avionics electrical busses 4 Power on PFD2 MFD and PFD1 in configuration mode 5 Using the PFD1 scroll to the LRU replacement page 6 Activate the curser and select the install...

Page 333: ...oll to highlight the installed servo 9 Highlight the software box and press the ENT key to check the box 10 Scroll to highlight the installed servo cert line 11 Highlight the software box and press th...

Page 334: ...1 in configuration mode 5 Using the PFD1 scroll to the LRU replacement page 6 Activate the curser and select the installed servo CTL in the LRU dropdown box 7 Press the Load softkey 8 Press ENT to ack...

Page 335: ...uration as expected configuration 18 Power cycle the system Verify there are no red Xs or system alerts 19 If red Xs or system alerts are present troubleshoot as necessary using Section 5 20 If there...

Page 336: ...1 frequency on PFD1 21 Using GCU477 keypad enter in a frequency of 123 450 Verify COM1 frequency changes as entered 22 Press the COM key until 2 is lit Verify the tuning box is present around the COM...

Page 337: ...Activate the curser and select GMC1 in the LRU dropdown box 7 Press the Load softkey 8 Press ENT to acknowledge the process was complete 9 Deactivate the curser 10 Scroll to the Configuration Manager...

Page 338: ...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...

Page 339: ...ion mode 3 Select NO when Do you want to update system files is displayed on the screen of PFD1 4 Select the SYSTEM UPLOAD page using the small FMS knob on PFD1 5 Activate cursor and rotate the small...

Page 340: ...omplete 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 softkey to activate or...

Page 341: ...n Avionics electrical busses 4 Power on PFD2 MFD and PFD1 in configuration mode 5 Using the PFD1 scroll to the LRU replacement page 6 Activate the curser and select GRA in the LRU dropdown box 7 Press...

Page 342: ...14 Select ok when prompted to Confirm configuration as expected configuration 15 Power cycle the system Verify there are no red Xs or system alerts 16 If red Xs or system alerts are present troublesh...

Page 343: ...5 Using the PFD1 scroll to the LRU replacement page 6 Activate the curser and select GTS in the LRU dropdown box 7 Press the CHK All softkey 8 Press the Load softkey 9 Press ENT to acknowledge the pr...

Page 344: ...he following a Press the OPERATE softkey for TAS TCAS I or press TA ONLY softkey for TCAS II A self test of the antenna circuit is initialized If the MFD displays FAILURE at the upper left corner of t...

Page 345: ...coax cables System Test The following test provides a scenario that will converge and intercept the GTS to assure proper operational and surveillance functions NOTE Prior to simulating the in air con...

Page 346: ...d circle with 03 displayed above For GTS 8000 TCAS II installations the following applies The simulated intruder should transition from a Traffic Advisory displayed as a solid yellow circle with 03 di...

Page 347: ...Using the PFD1 scroll to the LRU replacement page 6 Activate the curser and select GDL 59 in the LRU dropdown box 7 Press the CHK All softkey 8 Press the Load softkey 9 Press ENT to acknowledge the pr...

Page 348: ...system alerts continue to Section 7 18 3 Activation of Garmin Connext In order to activate the optional GDL 59 and optional GSR 56 for Garmin Connext contact Garmin Product Support at one of the foll...

Page 349: ...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 s...

Page 350: ...les is displayed on the screen of PFD1 4 Select the SYSTEM UPLOAD page using the small FMS knob on PFD1 5 Activate cursor and rotate the small FMS knob to display the drop down menu Rotate the small F...

Page 351: ...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 is unique for each G1000 system 3 Press the LRU softkey to...

Page 352: ...D 1 in the LRU dropdown box 7 Press the CHK All softkey 8 Press the Load softkey 9 Press ENT to acknowledge the process was complete 10 Deactivate the curser 11 Scroll to the Configuration Manager pag...

Page 353: ...on and Software columns for each item loaded Upload Complete COMPLETE in the summary box 10 Press ENT key on PFD1 to acknowledge upload complete 11 Deactivate cursor 12 Scroll to the Configuration Man...

Page 354: ...and verify that TAS OPERATING is displayed in the upper left corner of the traffic map 4 Press the TAS STBY softkey and verify that TAS STANDBY is displayed in the upper left corner of the traffic map...

Page 355: ...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 th...

Page 356: ...R to start the test Verify the WX 500 plots discharge points at approximately 60 NM 22 Observe the MFD to ensure the proper positioning of the test strikes Verify the strikes are within 10 degrees of...

Page 357: ...isplayed 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 With...

Page 358: ...n 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 fro...

Page 359: ...ear Aural Alert and Sirius XM Audio Suppression Test in Section 7 2 4 18 Place the airplane on jacks Ref King Air 300 Series Maintenance Manual Chapter 7 00 00 with the wheels clear of the ground 19 E...

Page 360: ...oftkey 3 Use the small FMS knob to scroll to CHART 4 Verify FliteCharts is displayed in blue text adjacent to CHART 5 Verify the FliteCharts database cycle number is displayed in blue text and the Fli...

Page 361: ...t MFD1 DB softkey 3 Use the small FMS knob to scroll to CHART 4 Verify ChartView is displayed in blue text adjacent to CHART 5 Verify the ChartView database cycle number is displayed in blue text and...

Page 362: ...tion Page User Waypoint Information Page Trip Planning Page Nearest Pages 1 Use the FMS knob on the GCU to select the Aux System Status page and select MFD1 DB softkey Use the small FMS knob to scroll...

Page 363: ...encies to 108 00 and 117 00 respectively 5 On PFD1 and PFD2 select the DME NAV1 mode Verify that the DME window display is set to the NAV1 frequency of 108 00 6 On PFD1 and PFD2 select the DME NAV2 mo...

Page 364: ...his check verifies that the G1000 radar altimeter interface is operates correctly 1 Navigate to the Aux System Status page on the MFD 2 Press the RA Test softkey and verify that the RA TEST annunciati...

Page 365: ...all aircraft and avionics systems to complete their initialization and begin operating normally 3 Verify there are no WOW INVALID or WOW FAULT messages Refer to Section 5 2 to troubleshoot messages 4...

Page 366: ...l antennas probes fairings or radomes along the sides of the airplane that may impact the air data system or aircraft performance may also invalidate the RVSM certification for this aircraft RVSM Requ...

Page 367: ...UDIO GIA2 AUDIO GPS WAAS ENGINE GPS2 CERTIFICATION GAINS GFC CERT GIA 2 3 GDU 1050A PFD 1 SYSTEM PFD1 FPGA PFD1 FPGA 4 GDU 1050A PFD 2 SYSTEM PFD2 FPGA PFD2 FPGA 5 GDU 1550 MFD SYSTEM MFD1 FPGA MFD FP...

Page 368: ...s 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...

Page 369: ...n AFT STATIC PORTS OXYGEN SERVICING DOOR RH SIDE ONLY AFT COVER PLATE EXTERNAL DOUBLER These items are installed by SNC drawing number 01211012 B300 Aft ASE Provisions Installation For these aircraft...

Page 370: ...from Beechcraft Any alternate tool authorized in the King Air 300 Series Maintenance Manual for RVSM static port measurements may be substituted for this tool Initialize the tool as follows 1 Make sur...

Page 371: ...GLE for each static port must fall within the ranges shown in Figure 8 7 Perform the static port measurement as follows 1 Wipe the surface of static ports clean with isopropyl alcohol 2 Place the gaug...

Page 372: ...D measurements Record the ANGLE in the measurement log Figure 8 7 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...

Page 373: ...2 Record the data from the primary cockpit displays as specified by Table 8 2 every 5 minutes for a minimum flight segment of 30 minutes in length The maximum altitude deviation shown on the display...

Page 374: ...pilot PFD AFCS Mode Controller GCU alert messages or monitor flags amber HDG etc are present on PFD1 or PFD2 4 On initial power up verify that the MFD splash screen includes a graphic similar to the f...

Page 375: ...hat the status is DISABLED 15 Verify on PFD 1 and PFD 2 the ESP Roll Indices are not displayed at 45 on the roll indicator on the Attitude Display 16 Verify on PFD 1 and PFD 2 that there is an ESP OFF...

Page 376: ...us is ENABLED 26 Verify on PFD 1 and PFD 2 that there are no ESP FAIL or ESP OFF alert messages 27 On the GMC 710 couple the Flight Director to the right side by pressing the XFR button The arrow that...

Page 377: ...adar altimeter must read over 2000 feet to play the aural alerts To make the radar altimeter read over 2000 feet disconnect the receive coaxial cable or cover the receive antenna from the radar altime...

Page 378: ...p tester Intruder type ATCRBS Intruder Start Distance 2 nm Intruder Start Altitude 500 feet above field elevation Vertical Speed 0 fpm Velocity 0 kts on some ramp testers a velocity greater than 0 kts...

Page 379: ...n ramp tester at 90 degrees i e off the right wing 5 Select the following on the ramp tester Intruder type ATCRBS Intruder Start Distance 10 nm Intruder Start Altitude 300 ft above PFD1 displayed alti...

Page 380: ...numbers M F 7 00 a m to 7 00 p m USA Central Standard Time 1 866 739 5687 toll free in USA 1 913 440 1135 worldwide Have the following information ready prior to calling If activating services for a...

Page 381: ...bed in the following steps 1 Connect to an available network reference Section 8 16 for details 2 Using the large FMS knob select the Aux page group on the MFD Using the small FMS knob select the Map...

Page 382: ...ip to step 11 if the selected network is a non secure network 6 If the selected network is a secure network enter the pass code in the Enter Passphrase field in the WPA Security Settings pop up window...

Page 383: ...f 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...

Page 384: ...rch and Rescue Menu turn the large and small FMS knobs to enter the starting waypoint 6 Press ENT key to complete the selection and move to the next option PATTERN type 7 Use the FMS knob to move to t...

Page 385: ...perating correctly Display Test Apply aircraft power On the MFD power up screen in the upper right corner find the King Air B300 Series System XXXX XX number This number is the G1000 System Software L...

Page 386: ...ormal operation this causes the airspeed altitude vertical speed and OAT fields to be invalid during the first 40 60 seconds of PFD power up After two minutes verify no Red X s are present on both PFD...

Page 387: ...G1000 NXi System Maintenance Manual Page 374 King Air 300 Series Revision 1 190 00716 N1 Without SVS enabled With SVS enabled Figure 9 3 PFD Normal Operation...

Page 388: ...alert messages If any MANIFEST errors appear the correct software to the related LRU must be loaded before proceeding Display Failure Test Step Desired Result MFD Failure Condition 1 Open MFD CB 2 Ver...

Page 389: ...A white ROL box adjacent to the roll scale o A white PIT box adjacent to the pitch ladder o A white IAS box in the airspeed tape o A white ALT box in the altitude tape GMA1 Fail GMA1 is inoperative X...

Page 390: ...fan related alert messages displayed in the PFD1 or PFD2 Alerts Window 2 Pull the following cooling fan circuit breakers a PFD GIA FANS LEFT b PFD GIA FANS RIGHT c MFD FAN For the cooling fan failure...

Page 391: ...on 1 Ensure GPS satellites are acquired 2 Place a shroud over the GPS antenna for GIA 1 to prevent signal reception Verify loss of signal on MFD Aux GPS Status page 3 Check for desired results 4 Remov...

Page 392: ...shall occur GPS CDI flags LOI on both PFDs 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...

Page 393: ...red results 3 Close GIA 2 CB Allow system to re acquire satellites and return to normal display modes For a GIA 2 failure condition the following shall occur NAV 2 and COM 2 tuning fields on PFD 1 and...

Page 394: ...ruments are displayed and indicate valid readings Reference figure below for normal EIS Display On GMA1 select DISPLAY BACKUP button Observe MFD in reversion mode and verify all engine instruments are...

Page 395: ...sure the STBY INSTR knob is turned to full bright Verify the STANDBY BATTERY annunciator switch is not illuminated Select depress the STANDBY BATTERY switch Verify the following For airplanes with MD...

Page 396: ...witch Verify the following ARM annunciation extinguishes on the STANDBY BATTERY switch White STANDBY BATTERY legend on the standby battery switch remains illuminated For airplanes with MD 302 standby...

Page 397: ...ollow an Autopilot disconnect should be accompanied by an aural alert two second tone unless otherwise specified Pre Flight Test 1 Turn off the AVIONICS MASTER PWR EXT PWR and BATT switches and ground...

Page 398: ...T switch on the pilots control wheel Verify the autopilot disengages with a flashing amber AP annunciation on PFD 1 and PFD 2 accompanied by an aural alert Verify that the control wheel is free in pit...

Page 399: ...is removed allowing manual checks of the slip clutch settings 1 Engage the Autopilot by pressing the AP key on the AFCS mode controller 2 Manually overpower the autopilot clutches in pitch roll and ya...

Page 400: ...he pitch reference Verify the command bars move up 1 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 W...

Page 401: ...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...

Page 402: ...een performed and maintained with the aircraft permanent records Record the following information Part number of the G1000 software loader card used to perform software loading or software updates Rec...

Page 403: ...011 00870 20 39Z GSU 75B 011 03094 40 4E4 GTX 33 LEGACY 011 00779 30 891 GTX 33D OPTIONAL 011 00779 21 848 GTX 3000 OPTIONAL 011 01997 00 20S GTX 335R OPTIONAL 011 03301 00 3EF GTX 345R OPTIONAL 011 0...

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