G1000 / GFC 700 System Maintenance Manual

3.2 GCU 477 - MFD CONTROLLER ................................................................................................... 3-3 3.3 GMC 710 - AFCS CONTROLS ...................................................................................................... 3-3 3.4 GMA 1347D AUDIO P ANEL ........................................................................................................ 3-4 3.5 G1000 NORMAL M ODE ................................................................................................................ 3-5 3.6 REVERSIONARY M ODE ................................................................................................................ 3-6 3.7 CONFIGURATION M ODE OVERVIEW ............................................................................................ 3-7 3.8 G1000 / GFC 700 S OFTWARE I NFORMATION ............................................................................ 3-12 3.9 G1000 S OFTWARE /CONFIGURATION P ROCEDURE .................................................................... 3-19 3.10 GDC 74B AIR DATA COMPUTER S OFTWARE /CONFIGURATION ............................................ 3-24 3.11 GDC 7400 AIR DATA COMPUTER S OFTWARE /CONFIGURATION ........................................... 3-25 3.12 GTS 820/850 T RAFFIC S YSTEM CONFIGURATION ................................................................. 3-26 3.13 GTS T RAFFIC P ROCESSOR ..................................................................................................... 3-27 3.14 GTX 33/33D CONFIGURATION .............................................................................................. 3-28 3.15 GTX 3000 CONFIGURATION .................................................................................................. 3-29 3.16 GDL 59 W I -FI DATA L INK OPTION CONFIGURATION ........................................................... 3-30 3.17 GSR 56 S ATELLITE RECIEVER WITH GDL 59 W I -F I DATA L INK OPTION CONFIGURATION . 3-31 3.18 GSR 56 S ATELLITE RECIEVER S TAND- ALONE OPTION CONFIGURATION ............................ 3-32 3.19 GRS 77 AHRS S OFTWARE /CONFIGURATION ........................................................................ 3-33 3.20 GRS 7800 AHRS S OFTWARE /CONFIGURATION .................................................................... 3-34 3.21 GWX 68 S OFTWARE /CONFIGURATION .................................................................................. 3-35 3.22 GWX 70 S OFTWARE /CONFIGURATION .................................................................................. 3-36 3.23 GMU 44 S OFTWARE /CONFIGURATION .................................................................................. 3-37 3.24 TAWS-A S UPPORT CONFIGURATION .................................................................................... 3-38 3.25 TAWS-A VOICE NO CALLOUT OPTION CONFIGURATION ..................................................... 3-39 3.26 TAWS-A VOICE CALLOUT OPTION CONFIGURATION ........................................................... 3-40 3.27 ADF OPTION CONFIGURATION .............................................................................................. 3-41 3.28 DME OPTION CONFIGURATION ............................................................................................. 3-42 3.29 RAD ALT O PTION CONFIGURATION ..................................................................................... 3-43 3.30 NON-G ARMIN T RAFFIC S YSTEM OPTION CONFIGURATION .................................................. 3-46 3.31 L IGHTNING S YSTEM OPTION CONFIGURATION ..................................................................... 3-47 3.32 ESP S UPPORT ( WITH AOA) OPTION CONFIGURATION .......................................................... 3-50 3.33 ESP S UPPORT ( NO AOA) OPTION CONFIGURATION .............................................................. 3-51 3.34 POTS HANDSET CONFIGURATION ......................................................................................... 3-52 Page ii G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 3.35 GSM 85A S ERVO M OUNT CONFIGURATION .......................................................................... 3-53 3.36 GSM 86 SERVO M OUNT C ONFIGURATION ............................................................................ 3-54 3.37 VERIFICATION OF S ERVO M OUNT CONFIGURATION .............................................................. 3-55 3.38 F LITE CHARTS CONFIGURATION ............................................................................................. 3-56 3.39 OPTIONAL C HART VIEW E NABLE ........................................................................................... 3-56 3.40 S TANDARD TAWS-B E NABLE ............................................................................................... 3-57 3.41 OPTIONAL TAWS-A E NABLE ................................................................................................ 3-58 3.42 S UPPLEMENTAL DATABASE L OADING ................................................................................... 3-59 3.43 OPTIONAL SVS/P ATHWAYS E NABLE ..................................................................................... 3-60 3.44 OPTIONAL ESP E NABLE ......................................................................................................... 3-61 3.45 S EARCH AND RESCUE E NABLE .............................................................................................. 3-62 3.46 OPTIONAL G ARMIN TCAS I E NABLE (FROM GTS 825 TO GTS 855) .................................... 3-63 3.47 OPTIONAL G ARMIN TCAS II E NABLE (F ROM GTS 825 TO GTS 8000) ................................ 3-64 3.48 AIRCRAFT REGISTRATION NUMBER E NTRY .......................................................................... 3-65 3.49 V1 / V2 AIRSPEED OPTIONS ................................................................................................... 3-66 3.50 S PLASH S CREEN L OADING ..................................................................................................... 3-67 3.51 NAVIGATION DATABASE L OADING ....................................................................................... 3-68 3.52 CONFIGURATION OF NAVIGATION M AP FOR T RAFFIC S YSTEM ............................................. 3-69 3.53 CLEARING DEFAULT USER S ETTINGS .................................................................................... 3-69 4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS........................................................ 4-1 4.1 AIRWORTHINESS L IMITATIONS ................................................................................................... 4-1 4.2 S ERVICING I NFORMATION ........................................................................................................... 4-2 4.3 M AINTENANCE I NTERVALS ......................................................................................................... 4-5 4.4 VISUAL I NSPECTION .................................................................................................................. 4-12 4.5 E LECTRICAL BONDING T EST ..................................................................................................... 4-17 4.6 GRS 77 OR GRS 7800 E ARTH M AGNETIC F IELD UPDATES ...................................................... 4-20 4.7 GSA 80 GREASING P ROCEDURE ................................................................................................ 4-20 4.8 F LAPS- IN- MOTION DISCRETE I NPUT CHECK .............................................................................. 4-21 4.9 GSM 85A/GSM 86 S LIP CLUTCH T ORQUE CHECK P ROCEDURE .............................................. 4-22 4.10 G1000 REDUNDANT CONNECTION CHECK ............................................................................ 4-26 4.11 E NGINE DATA CHECK ............................................................................................................ 4-29 4.12 T RIM ANNUNCIATOR CHECK ................................................................................................. 4-32 4.13 G1000 MISCOMPARE CHECKS ............................................................................................... 4-33 4.14 NOSE AVIONICS COMPARTMENT F ANS OPERATIONAL CHECK ............................................. 4-35 4.15 I NSTRUMENT P ANEL F ANS OPERATIONAL CHECK ................................................................ 4-35 4.16 S TANDBY BATTERY PERIODIC CHECKS ................................................................................. 4-36 4.17 P OWER BUS CHECK ............................................................................................................... 4-39 4.18 E XTERIOR S KIN I NSPECTION AROUND ANTENNAS ................................................................ 4-40 5 TROUBLESHOOTING ................................................................................................................... 5-1 5.1 G1000 ALERTING S YSTEM .......................................................................................................... 5-2 5.2 S YSTEM ANNUNCIATIONS ........................................................................................................... 5-5 5.3 200/B200 S PECIFIC ALERTS ...................................................................................................... 5-28 5.4 TAWS T ROUBLESHOOTING ....................................................................................................... 5-29 5.5 S YNTHETIC VISION AND P ATHWAYS T ROUBLESHOOTING ........................................................ 5-30 5.6 GFC 700 AFCS T ROUBLESHOOTING ......................................................................................... 5-33 5.7 BACKUP COMMUNICATIONS P ATH CHECKS .............................................................................. 5-46 5.8 GDU 104X T ROUBLESHOOTING ................................................................................................ 5-47 5.9 GDU 104X ALERTS ................................................................................................................... 5-49 5.10 GIA 63 T ROUBLESHOOTING .................................................................................................. 5-57 5.11 GIA ALERT M ESSAGES .......................................................................................................... 5-59 5.12 GEA T ROUBLESHOOTING ...................................................................................................... 5-66 5.13 GTX T ROUBLESHOOTING ...................................................................................................... 5-67 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page iii 190-00915-01 Revision 9 5.14 GDL 69A T ROUBLESHOOTING .............................................................................................. 5-68 5.15 GRS 77 OR GRS 7800 AND GMU 44 T ROUBLESHOOTING .................................................... 5-70 5.16 GDC 74B/GDC 7400 T ROUBLESHOOTING ............................................................................ 5-76 5.17 GWX 68 OR GWX 70 T ROUBLESHOOTING ............................................................................ 5-77 5.18 GMC 710 T ROUBLESHOOTING .............................................................................................. 5-78 5.19 GCU 477 T ROUBLESHOOTING ............................................................................................... 5-79 5.20 S OFTWARE /C ONFIGURATION T ROUBLESHOOTING ................................................................ 5-80 5.21 BACKSHELL /BACKPLATE CONNECTORS ................................................................................ 5-82 5.22 S TANDBY ATTITUDE I NDICATOR T ROUBLESHOOTING .......................................................... 5-89 5.23 S TANDBY AIRSPEED I NDICATOR T ROUBLESHOOTING ........................................................... 5-89 5.24 S TANDBY ALTIMETER T ROUBLESHOOTING ........................................................................... 5-90 5.25 S AFE F LIGHT L IFT COMPUTER T ROUBLESHOOTING .............................................................. 5-90 5.26 GDL 59 T ROUBLESHOOTING ................................................................................................. 5-92 5.27 GSR 56 T ROUBLESHOOTING .................................................................................................. 5-93 5.28 GTS 820/850 T ROUBLESHOOTING ......................................................................................... 5-93 5.29 GTS T RAFFIC P ROCESSOR T ROUBLESHOOTING .................................................................... 5-94 6 EQUIPMENT REMOVAL & INSTALLATION .......................................................................... 6-1 6.1 GDU 1040A/1500........................................................................................................................ 6-2 6.2 GMA 1347D AUDIO P ANEL ........................................................................................................ 6-2 6.3 GIA 63W I NTEGRATED AVIONICS UNITS .................................................................................... 6-3 6.4 GEA 71 E NGINE /AIRFRAME UNIT ............................................................................................... 6-3 6.5 GTX 33( ) OR GTX 3000 TRANSPONDER .................................................................................... 6-4 6.6 GDC 74B/GDC 7400 AIR DATA COMPUTER .............................................................................. 6-4 6.7 GTP 59 OAT P ROBE .................................................................................................................... 6-5 6.8 GRS 77 OR GRS 7800 AHRS ...................................................................................................... 6-5 6.9 GMU 44 M AGNETOMETER .......................................................................................................... 6-5 6.10 GDL 69A ................................................................................................................................. 6-7 6.11 GSA 80 S ERVOS ....................................................................................................................... 6-7 6.12 GSM 85A/86 S ERVO GEARBOX ............................................................................................... 6-8 6.13 GCU 477 .................................................................................................................................. 6-8 6.14 GMC 710 ................................................................................................................................. 6-8 6.15 GWX 68 OR GWX 70............................................................................................................... 6-9 6.16 CONFIGURATION M ODULES ................................................................................................... 6-10 6.17 GEA 71 BACKSHELL T HERMOCOUPLE REMOVAL & REPLACEMENT .................................... 6-13 6.18 GPS/WAAS ANTENNAS ........................................................................................................ 6-14 6.19 DIVERSITY T RANSPONDER ANTENNA.................................................................................... 6-14 6.20 I RIDIUM ANTENNA ................................................................................................................. 6-14 6.21 W I -F I ANTENNA ..................................................................................................................... 6-15 6.22 S IGNAL CONDITIONERS .......................................................................................................... 6-15 6.23 I NSTRUMENT P ANEL ANNUNCIATORS (P ROP S YNCH AND S TANDBY BATTERY) .................. 6-16 6.24 L-3 AVIONICS (BF GOODRICH) PS-835(C OR D M ODEL ) E MERGENCY BATTERY ................ 6-16 6.25 S TANDBY AIRSPEED I NDICATOR ............................................................................................ 6-16 6.26 S TANDBY ALTIMETER ............................................................................................................ 6-17 6.27 S TANDBY ATTITUDE I NDICATOR ........................................................................................... 6-18 6.28 GIA COOLING F ANS ............................................................................................................... 6-18 6.29 GDU COOLING F ANS ............................................................................................................. 6-20 6.30 GTS 820/850 T RAFFIC UNIT .................................................................................................. 6-20 6.31 GPA 65 PA/LNA UNIT .......................................................................................................... 6-20 6.32 GA 58 T RAFFIC ANTENNAS ................................................................................................... 6-21 6.33 GDL 59 W I -FI DATALINK ...................................................................................................... 6-21 6.34 GSR 56 S ATELLITE RECEIVER ............................................................................................... 6-22 6.35 GTS T RAFFIC P ROCESSOR ..................................................................................................... 6-22 6.36 GRA 5500 RADAR ALTIMETER .............................................................................................. 6-23 Page iv G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 7 G1000 EQUIPMENT CONFIGURATION & TESTING ............................................................. 7-1 7.1 GDU 1040/1500 MFD & PFD ..................................................................................................... 7-1 7.2 GMA 1347D AUDIO P ANEL ........................................................................................................ 7-3 7.3 GIA 63W I NTEGRATED AVIONICS UNIT ...................................................................................... 7-6 7.4 GEA 71 E NGINE /AIRFRAME UNIT ............................................................................................... 7-9 7.5 GTX 33( ) OR GTX 3000 TRANSPONDER .................................................................................. 7-12 7.6 GDC 74B OR GDC 7400 AIR DATA COMPUTER ....................................................................... 7-13 7.7 GRS AHRS / GMU 44 M AGNETOMETER .................................................................................. 7-18 7.8 GDL 69A XM DATA L INK ........................................................................................................ 7-26 7.9 GSA 80 S ERVOS ........................................................................................................................ 7-26 7.10 GCU 477 FMS CONTROLLER ................................................................................................ 7-27 7.11 GMC 710 AFCS CONTROLLER .............................................................................................. 7-29 7.12 GWX 68 OR GWX 70 W EATHER RADAR .............................................................................. 7-30 7.13 NON-G ARMIN T RAFFIC S YSTEM F UNCTIONAL CHECK .......................................................... 7-31 7.14 S TORMSCOPE F UNCTIONAL CHECK ....................................................................................... 7-32 7.15 TAWS F UNCTIONAL CHECK .................................................................................................. 7-34 7.16 F LITE CHARTS F UNCTIONAL CHECK ...................................................................................... 7-37 7.17 CHART VIEW F UNCTIONAL CHECK ........................................................................................ 7-38 7.18 S AFE T AXI F UNCTIONAL CHECK ............................................................................................ 7-39 7.19 DME F UNCTIONAL CHECK .................................................................................................... 7-40 7.20 ADF F UNCTIONAL CHECK ..................................................................................................... 7-41 7.21 GRA 5500 RADAR ALTIMETER F UNCTIONAL CHECK ........................................................... 7-41 7.22 NON-G ARMIN RADAR ALTIMETER CHECK (OPTIONAL ) ....................................................... 7-41 7.23 W EIGHT ON W HEELS AND L OW S PEED AWARENESS BAND CHECK ...................................... 7-42 7.24 RVSM CHECKS ...................................................................................................................... 7-43 7.25 S AFE F LIGHT L IFT COMPUTER GROUND CALIBRATION ........................................................ 7-49 7.26 ESP F UNCTIONAL CHECK ...................................................................................................... 7-57 7.27 GTS T RAFFIC S YSTEM F UNCTIONAL CHECK ......................................................................... 7-61 7.28 ACTIVATION OF GARMIN CONNEXT ...................................................................................... 7-63 7.29 GDL 59 W I -FI DATA L INK F UNCTIONAL CHECK .................................................................. 7-65 7.30 GSR 56 S ATELLITE RECEIVER F UNCTIONAL CHECK ............................................................. 7-66 7.31 S EARCH AND RESCUE F UNCTIONAL CHECK .......................................................................... 7-67 8 SYSTEM RETURN TO SERVICE PROCEDURE ...................................................................... 8-1 8.1 BACKUP P ATH S YSTEM T ESTING ................................................................................................. 8-1 8.2 GFC 700 GROUND CHECKOUT .................................................................................................... 8-9 8.3 M AINTENANCE RECORDS .......................................................................................................... 8-14 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page v 190-00915-01 Revision 9 LIST OF ILLUSTRATIONS FIGURE PAGE Figure 2-1, Display Units ........................................................................................................................... 2-2 Figure 2-2, Audio Panel ............................................................................................................................. 2-3 Figure 2-3, AFCS Controller ..................................................................................................................... 2-3 Figure 2-4, FMS Controller ....................................................................................................................... 2-4 Figure 2-5, Transponder............................................................................................................................. 2-4 Figure 2-6, GIA unit .................................................................................................................................. 2-5 Figure 2-7, GEA unit ................................................................................................................................. 2-6 Figure 2-8, Air Data Computer .................................................................................................................. 2-7 Figure 2-9, OAT probe .............................................................................................................................. 2-7 Figure 2-10, AHRS .................................................................................................................................... 2-8 Figure 2-11, Magnetometer ....................................................................................................................... 2-8 Figure 2-12, GDL 69A Datalink ................................................................................................................ 2-9 Figure 2-13, GDL 59 Wi-Fi Datalink ........................................................................................................ 2-9 Figure 2-14, GSR 56 Satellite Receiver ................................................................................................... 2-10 Figure 2-15, GTS 820/850 Traffic System .............................................................................................. 2-10 Figure 2-16, GTS Traffic Processor ......................................................................................................... 2-11 Figure 2-17, Weather Radar ..................................................................................................................... 2-11 Figure 2-18, Servo ................................................................................................................................... 2-11 Figure 2-19, GRA 5500 Radar Altimeter................................................................................................. 2-12 Figure 2-20, 200/B200 Electrical Distribution (Post G1000 STC) .......................................................... 2-16 Figure 2-21, G1000 Component Power Sources...................................................................................... 2-17 Figure 2-22, Pitot/Static System (Post G1000 STC)................................................................................ 2-18 Figure 2-23, G1000/GFC 700 Block Diagram......................................................................................... 2-19 Figure 3-1, GDU 1040A Control Interface ................................................................................................ 3-1 Figure 3-2, GDU 1500 Control Interface ................................................................................................... 3-2 Figure 3-3, G1000 Softkeys ....................................................................................................................... 3-2 Figure 3-4, MFD Controls (GCU 477 shown) ........................................................................................... 3-3 Figure 3-5, AFCS Controls (GMC 710 shown) ......................................................................................... 3-3 Figure 3-6, GMA 1347D Controls ............................................................................................................. 3-4 Figure 3-7, Normal Mode .......................................................................................................................... 3-5 Figure 3-8, Automatic Reversion with MFD failure ................................................................................. 3-6 Figure 3-9, Manual Reversion with pilot PFD failure .............................................................................. 3-6 Figure 3-10, SET>ACTV Diagram........................................................................................................... 3-8 Figure 3-11, Loss of Communication ....................................................................................................... 3-9 Figure 3-12, Configuration Status............................................................................................................. 3-9 Figure 3-13, Data Transmission Indicators ............................................................................................... 3-9 Figure 3-14, G1000 LRU Configuration File Storage ............................................................................ 3-17 Figure 3-15, GRS/GDC Configuration Settings Storage ........................................................................ 3-18 Figure 3-16, Software/Configuration Overview ..................................................................................... 3-19 Figure 3-17, Airframe Options ................................................................................................................ 3-21 Figure 3-18, Propeller Options ................................................................................................................ 3-21 Figure 3-19, Configuration/Software Load Page .................................................................................... 3-22 Figure 3-21, Stormscope Configuration.................................................................................................. 3-48 Figure 3-22, Servo Mount Configuration Verification ............................................................................ 3-55 Figure 3-23, Supplemental Database Synchronization ............................................................................ 3-59 Figure 3-24, Aircraft Registration ............................................................................................................ 3-65 Figure 3-25, Navigation Database Synchronization ................................................................................ 3-68 Figure 4-1, GIA I/O Page........................................................................................................................ 4-21 Figure 4-2, Discrete Valid/Invalid Indications ........................................................................................ 4-21 Figure 4-3, GFC Status Page................................................................................................................... 4-22 Figure 4-4, GFC Status Page................................................................................................................... 4-23 Page vi G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 Figure 4-5, Ambient Temperature Conversion Chart .............................................................................. 4-30 Figure 4-6, Standby Battery ..................................................................................................................... 4-36 Figure 4-7, Power Supply Connection .................................................................................................... 4-38 Figure 4-8, Exterior Skin Inspection Around Antennas.......................................................................... 4-41 Figure 5-1, AUX – System Status Page .................................................................................................... 5-1 Figure 5-2, Alerts & Annunciations .......................................................................................................... 5-2 Figure 5-3, ADVISORY Softkey Annunciation ....................................................................................... 5-2 Figure 5-4, System Annunciations ............................................................................................................ 5-5 Figure 5-5, AFCS Annunciation Field .................................................................................................... 5-33 Figure 5-6, GFC Status Page ................................................................................................................... 5-34 Figure 5-7, Magnetometer Interference Test .......................................................................................... 5-73 Figure 5-8, GIA 63W Backplate Connectors .......................................................................................... 5-82 Figure 5-9, GEA 71 Backplate Connectors ............................................................................................ 5-83 Figure 5-10, GMA 1347D Backplate Connectors................................................................................... 5-83 Figure 5-11, GTX 33/33D Backplate Connectors................................................................................... 5-83 Figure 5-12, GTX 3000 Connectors (P3301 and P3302) ......................................................................... 5-84 Figure 5-13, GDU 1040A/1500 Backshell Connector (P10401 or P15001)........................................... 5-84 Figure 5-14, GRS 77 Backshell Connector (P771) ................................................................................. 5-84 Figure 5-15, GRS 7800 Backshell Connector (P78001) .......................................................................... 5-84 Figure 5-16, GDC 74B Backshell Connector (P74B1) ........................................................................... 5-85 Figure 5-17, GDC 7400 Mating Connector (P74001) ............................................................................ 5-85 Figure 5-18, GDL 69A Backplate Connector (P69A1) .......................................................................... 5-85 Figure 5-19, GCU 477 Backshell Connector (P4751) ............................................................................ 5-85 Figure 5-20, GMC 710 Backshell Connector (P7101)............................................................................ 5-85 Figure 5-21, GWX 68 Backshell Connector (P681) ............................................................................... 5-86 Figure 5-22 GWX 70 Backshell Connector (P751) ................................................................................ 5-86 Figure 5-23, GTS 820/850 Mating Connectors (P8001 and P8002) ....................................................... 5-86 Figure 5-24, GTS 820/850 Mating Connector (P8003) .......................................................................... 5-86 Figure 5-25 GTS Processor Connector (P8001) ..................................................................................... 5-86 Figure 5-26, GPA 65 Mating Connector (P651) ..................................................................................... 5-87 Figure 5-27, Signal Conditioner (1PVIB1 and 2PVIB1) ........................................................................ 5-87 Figure 5-28, GDL 59 Mating Connector (1P591)................................................................................... 5-87 Figure 5-29, GSR 56 Mating Connector (1P561) .................................................................................... 5-87 Figure 5-30, GRA 5500 Connector (P55001) ......................................................................................... 5-88 Figure 6-1, Servo Gear ............................................................................................................................... 6-7 Figure 6-2, Configuration Module Installation ....................................................................................... 6-10 Figure 6-3, GRS 7800 Configuration Module Installation ...................................................................... 6-11 Figure 6-4, GEA Backshell Thermocouple............................................................................................. 6-13 Figure 6-5, GIA Cooling Fan Installation ................................................................................................ 6-19 Figure 6-6, GIA Cooling Fan Inlet Duct Installation ............................................................................... 6-19 Figure 7-1, G1000 Normal Mode Check .................................................................................................. 7-2 Figure 7-2, Marker Beacon Symbology .................................................................................................... 7-4 Figure 7-3, AUX – GPS STATUS Page (MFD) ....................................................................................... 7-6 Figure 7-4, Normal Engine Instrument Markings (MFD) ........................................................................ 7-9 Figure 7-5, Aircraft Registration.............................................................................................................. 7-12 Figure 7-6, Engine Run-Up Test Page ..................................................................................................... 7-24 Figure 7-7, Normal Mode AHRS Check ................................................................................................ 7-25 Figure 7-8, Low Speed Awareness Band Symbolization........................................................................ 7-42 Figure 7-9, RVSM Critical Region .......................................................................................................... 7-44 Figure 7-10, Dial Indicator ...................................................................................................................... 7-45 Figure 7-11, Static Port Measurement ..................................................................................................... 7-45 Figure 7-12, Static Port Measurement locations ...................................................................................... 7-46 Figure 7-13, Static Port Measurement Log .............................................................................................. 7-46 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page vii 190-00915-01 Revision 9 Figure 7-14, C-05606-1 Lift Computer.................................................................................................... 7-54 Figure 7-15, Breakout Box ...................................................................................................................... 7-55 Figure 7-16, Force Applicator Usage Instructions ................................................................................... 7-56 Figure 7-17, GTS 820/850 or GTS Processor GND TEST softkey ......................................................... 7-61 Figure 7-18, GSR56 Configuration Page ................................................................................................. 7-66 Figure 7-19, AUX-TELEPHONE page ................................................................................................... 7-66 Figure 8-1, GDU Data Verification (ARINC 429) .................................................................................... 8-6 Figure 8-2, GIA Data Verification (ARINC429/RS-232).......................................................................... 8-7 Figure 8-3, GIA Data Verification (RS-485) ............................................................................................. 8-8 Figure 8-4, Pre-Flight Test ........................................................................................................................ 8-9 LIST OF TABLES TABLE ................................................................................................................................................ PAGE Table 1-1, G1000 System Software Version ............................................................................................ 1-1 Table 1-2, Required Documents ............................................................................................................... 1-5 Table 1-3, Reference Publications ............................................................................................................ 1-6 Table 4-1, Maintenance Intervals.............................................................................................................. 4-5 Table 4-2, Discontinued Maintenance Intervals ..................................................................................... 4-11 Table 4-3, Nose Section Visual Inspection Procedure ............................................................................ 4-12 Table 4-4, Nose Avionics Compartment Visual Inspection Procedure .................................................. 4-12 Table 4-5, Pilot’s Compartment Visual Inspection Procedure................................................................ 4-13 Table 4-6, Instrument Panel G1000 Equipment Visual Inspection Procedure ....................................... 4-13 Table 4-7, Cabin Area Visual Inspection Procedure ............................................................................... 4-15 Table 4-8, Rear Fuselage and Empennage Visual Inspection Procedure ................................................ 4-16 Table 4-9, Lightning Strike Inspection Procedure ................................................................................... 4-17 Table 4-10, Measured Torque ................................................................................................................. 4-24 Table 4-11, GSM 85A/GSM 86 Slip Clutch Torque Settings ................................................................ 4-25 Table 4-12, Engine Data Check Test Equipment ..................................................................................... 4-29 Table 4-13, Oil Pressure Indication Test Points....................................................................................... 4-29 Table 4-14, ITT Indication Test Points .................................................................................................... 4-30 Table 4-15, Torque Indication Test Points............................................................................................... 4-31 Table 4-16, Standby Battery Required Equipment .................................................................................. 4-36 Table 5-1, SVS Troubleshooting ............................................................................................................. 5-30 Table 5-2, SVS-Related Alert Messages................................................................................................. 5-30 Table 5-3, AFCS Annunciation Troubleshooting ................................................................................... 5-31 Table 5-4, AFCS General Troubleshooting ............................................................................................ 5-32 Table 5-5, Magnetometer Interference Test Sequence ........................................................................... 5-74 Table 6-1, Configuration Module Kit – 011-00979-00 ........................................................................... 6-10 Table 6-2, GRS 7800 Configuration Module Parts.................................................................................. 6-11 Table 6-3, Thermocouple Kit (011-00981-00) ....................................................................................... 6-13 Table 7-1, Fuel Flow Indication Test Equipment .................................................................................... 7-10 Table 7-2, Fuel Flow Test Points ............................................................................................................. 7-10 Table 7-3, Oil Pressure Indication Test Equipment ................................................................................. 7-11 Table 7-4, Oil Pressure Test Points.......................................................................................................... 7-11 Table 7-5, Air Data System Test ............................................................................................................. 7-15 Table 7-6, Vertical Speed Table ............................................................................................................. 7-17 Table 7-7, Required GRS/GMU Calibrations ......................................................................................... 7-19 Table 7-8, RVSM Required Avionics ...................................................................................................... 7-43 Table 7-9, In-Flight Altitude Hold Performance Test .............................................................................. 7-48 Page viii G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 This page intentionally left blank. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 1-1 190-00915-01 Revision 9 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 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 G1000 System Software Version Notes 200/B200 Series King Air 0985.01 superseded Updated GIA software 200/B200 Series 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 200/B200 Series King Air 0985.06 Updated GDU and GRS software 200/B200 Series King Air 0985.07 Updates and adds various G1000 LRU hardware and 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. Page 1-2 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 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 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 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 1-3 190-00915-01 Revision 9 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 & 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 Configuration & 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. Page 1-4 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 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 & Warning System WAAS: Wide Area Augmentation System VHF: Very High Frequency 1.3.1 Units of Measure Unless otherwise stated, all units of measure are English units. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 1-5 190-00915-01 Revision 9 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 Garmin Document 005-00421-00 Master Drawing List, Garmin G1000/GFC 700 in Hawker Beechcraft Model 200/B200 Series King Air 005-W0025-00 Wiring Diagram, G1000/GFC 700 King Air 200/B200 005-00421-03 General Arrangement, G1000/GFC700 AFCS King Air 200/B200 Series 005-00421-32 GWX Radar Install, King Air 200/B200 005-00421-33 Antenna Install, King Air 200/B200 005-00421-30 Main Instrument Panel Installation, King Air 200/B200 005-00421-34 Electrical Equipment Install, Nose Bay, King Air 200/B200 005-00421-35 Roll Servo Install, w/GSM 85A King Air 200/B200 005-00421-36 Yaw Servo Install, w/GSM 85A King Air 200/B200 005-00421-37 Pitch Servo Install, w/GSM 85A King Air 200/B200 005-00421-38 Pitch Trim Servo Install, w/GSM 85A King Air 200/B200 005-00421-39 Magnetometer Install, King Air 200/B200 005-00421-40 OAT Sensor Install, King Air 200/B200 005-00421-41 Transponder Install, King Air 200/B200 005-00421-42 Datalink Install, King Air 200/B200 005-00421-45 Roll Servo Install, w/GSM 86 King Air 200/B200 005-00421-46 Yaw Servo Install, w/GSM 86 King Air 200/B200 005-00421-47 Pitch Servo Install, w/GSM 86 King Air 200/B200 005-00421-48 Pitch Trim Servo Install, w/GSM 86 King Air 200/B200 005-00421-51 Wire Harness Installation, Nose, King Air 200/B200 005-00421-52 Wire Harness Installation, Cabin, King Air 200/B200 005-00421-53 Wire Harness Installation, Tail, King Air 200/B200 005-00421-54 Control Wheel Modification, King Air 200/B200 005-00421-55 Overhead Control Panel Modification, King Air 200/B200 005-00421-31 Pedestal Re-Configuration, King Air 200/B200 005-00421-56 Circuit Breaker Panel Modification, King Air 200/B200 005-00421-58 Glareshield Lighting Modification, King Air 200/B200 005-00421-A9 Optional Equipment Install, Tail Shelf, King Air 200/B200 Hawker Beechcraft Document 101-590010-39 Beech Super King Air 200 and 200T Wiring Diagram Manual 101-590010-133 Super King Air Wiring Diagram Manual 101-590010-161 Super King Air Wiring Diagram Manual 101-590010-19 Super King Air 200 Series Maintenance Manual 101-590010-453 Super King Air 200 Series Airworthiness Limitations Manual 101-590097-13 King Air Series Component Maintenance Manual 98-39006 Structural Inspection and Repair Manual 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 Page 1-6 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 The following publications are recommended to be on hand during the performance of maintenance activities. Table 1-3, Reference Publications Part Number Garmin Document 190-00915-02 Airplane Flight Manual Supplement, G1000, Hawker Beechcraft 200, 200C, B200, B200C King Air 190-00929-01 G1000 Cockpit Reference Guide for the Beechcraft 200/B200 190-00355-04 GDL 69 Series XM Satellite Radio Activation Instructions 190-00907-00 G1000/G1000H System Maintenance Manual (Standard Piston/Turboprop/Helicopter) 190-00303-72 GSA8X/GSM85(A) Installation Manual 190-00303-83 GSM 86 Servo Gear Box Installation Manual 190-00313-63 GMU 44 Installation Location Magnetic Interference Survey Procedure 190-00313-12 Circular Connector (and Configuration Module) Installation 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 Revision 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. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-1 190-00915-01 Revision 9 2 SYSTEM DESCRIPTION 2.1 Equipment Descriptions 2.1.1 GFC 700 Operation The GFC 700 is a fail-passive digital flight control system composed of multiple G1000 LRUs and servos. The following functions are provided by the GFC 700 in this installation: • Flight Director • Autopilot • Pitch Trim • Yaw Damper • Electronic Stability and Protection (optional) Flight Director: The Flight Directors operate within the GIA 63Ws and use data from the G1000 system, including air, attitude and flight data, to calculate commands for display to the pilot and for the Autopilot. Flight director command bars and mode annunciations are sent to the PFDs through a high-speed Ethernet connection for display to the pilot and copilot. The flight directors operate independently of the autopilot and allow the pilot to hand-fly the command bars, if desired. The GMC 710 allows the pilot to switch the active director between flight director #1 (GIA1) and flight director #2 (GIA2). Autopilot: The autopilot operates within one high-speed GSA 80 servo (pitch trim) and three GSA 80 servos (pitch, roll and yaw). Flight director data is processed within the servos and turned into aircraft flight control surface commands. The autopilot cannot operate unless the flight director is engaged. Manual Electric Trim: When the autopilot is not engaged, the pitch trim servo may be used to provide a Manual Electric Pitch Trim (MEPT) function. This allows the pilot or co-pilot to adjust pitch trim from the PITCH TRIM switch on the control wheel in lieu of using the elevator trim wheel. Trim speeds are scheduled to provide easier control over a wide speed or configuration range. The PITCH TRIM switch is split into two halves. The left half arms MEPT. The right half controls direction. Both halves must be actuated at the same time to command the pitch trim servo to operate. If only one half of the PITCH TRIM switch is actuated for more than 3 seconds, a red PTRM message will appear on the PFDs. Yaw Damper: The yaw damper reduces Dutch roll tendencies and coordinates turns. It can operate independently of the autopilot and may be used during normal hand-flight maneuvers. Electronic Stability and Protection: Electronic Stability and Protection (ESP) is an optional function that is intended to assist the pilot in maintaining the airplane in a safe flight condition within the aircraft flight envelope. This envelope is defined by pitch, roll, and airspeed. This feature is only active when in flight and the autopilot is off. There are two versions of the ESP option available: ESP with Angle of Attack (AOA) modes and ESP without Angle of Attack (AOA) modes. The ESP option with AOA modes requires a new lift computer. The ESP option without AOA modes uses the existing lift computer. Underspeed Protection: Underspeed Protection (USP) is available when the optional ESP system is installed and the autopilot is on. It is designed to discourage aircraft operation below minimum established airspeeds. When the aircraft decelerates to stall warning, the autopilot will provide input causing the aircraft to pitch down and Page 2-2 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 wings to level. The pitch down force will continue until the aircraft reaches a pitch attitude at which IAS equals the IAS at which stall warning turns off, plus two knots. 2.1.2 GDU 1040A PFD (2) & 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, GWX68 or GWX 70 weather radar, optional GDL59 wi-fi datalink and optional GTS 820/850 or GTS Processor 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 1 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. 2. Electrical power to the MFD 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 ¼-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 2-3 190-00915-01 Revision 9 2.1.3 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 2.1.4 GMC 710 AFCS Control Unit The dedicated AFCS controls 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 2-4 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.1.5 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 2.1.6 Transponder (2) The Garmin GTX 33( ) or GTX 3000 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. This STC installation also allows for installation of two GTX 3000 diversity transponders. Mixing between the GTX 33 and GTX 3000 transponsders is not permissible. Additionally, for TCAS II operations, the GTX 3000 transponder communicates with the GTS Processor through ARINC 429 digital interfaces (transmit and receive). The transponder units are mounted under the floor in the cabin just aft of fuselage station 246.750 or on the upper avionics equipment shelf in the tail section of the airplane. Power is provided by the No. 1 GTX from the Essential Bus. The No. 2 GTX is powered from the Avionics Bus No. 1. All GTX transponders (non-diversity and diversity) interface with a transponder antenna mounted to the bottom of the fuselage. Each GTX diversity transponder (GTX33D and GTX 3000) interfaces to a transponder antenna mounted to the top of the fuselage. GTX 33() GTX 3000 Figure 2-5, Transponder G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-5 190-00915-01 Revision 9 2.1.7 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: • Existing VOR/LOC/Glideslope Antenna System • Existing VHF COM #1 & #2 Antennas • GA 36 and GA 37 GPS/WAAS Antennas • GMA 1347D, #1 & #2 • GEA 71, #1 & #2 • GDU 1040A, #1 & #2 • GSA 80 • GRS 77 or GRS 7800, #1 & #2 • Traffic System (if installed) The GIA 63W #1 interfaces to the following additional equipment: • GDC 74B #1 • GTX 33( ) or GTX 3000 #1 • DME 42 (if installed) • GSR 56 (if installed per stand-alone configuration) The GIA 63W #2 interfaces to the following additional equipment: • GDC 74B #2 • GTX 33 ( ) or GTX 3000 #2 • ADF (if installed) • Stormscope (if installed) • Radar Altimeter (if installed) Figure 2-6, GIA unit Page 2-6 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.1.8 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 system 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. 1 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: • Oil Pressure Sensor • Oil Temperature Sensor • Fuel Flow Sensor (via onside Signal Conditioner) • Turbine Speed Sensor (via onside Signal Conditioner) • Propeller Speed Sensor(via onside Signal Conditioner) • Torque Sensor • Interstage Turbine Temperature (ITT) Sensor Figure 2-7, GEA unit G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-7 190-00915-01 Revision 9 2.1.9 Digital Air Data Computer (2) The Garmin GDC 74B or GDC 7400 air data 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 communicates with the GIA 63W, GDU 1040A, and GRS 77/7800 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 2-22 for a schematic of the aircraft’s pitot/static system and 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. GDC 74B GDC 7400 (optional) Figure 2-8, Air Data Computer 2.1.10 OAT Probe (2) The Garmin GTP 59 OAT Probes provide the GDC 74B or optional GDC7400 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 2-8 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.1.11 Attitude & Heading Reference System (2) The Garmin GRS 77 AHRS or GRS 7800 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 Garmin Air Data Computers 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 interfaces with and provides power to the GMU 44 Magnetometer. The GRS supplies attitude and heading information directly to the PFDs, MFD, and GIAs. The #2 GRS AHRS units can provide heading data to an approved third party TCAS II device through an ARINC 429 digital interface. Additionally, the GRS 7800 AHRS provides heading with or without the aiding of the Garmin GMU 44 magnetometer. When operating without the aid of the magnetometer, the GRS 7800 is functionally similar to that of a Directional Gyro. GRS 1 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. GRS 77 GRS 7800 Figure 2-10, AHRS 2.1.12 GMU 44 Magnetometer (2) The GMU 44 provides horizontal and vertical magnetic field information to the GRS AHRS. This allows heading to be calculated and provides assistance during AHRS alignment. The GMU 44 units are mounted in the tailcone or in the horizontal stabilizer. The 011-00870-20 GMU 44 units may only be installed in the horizontal stabilizer. The GMU 44 units were modified to account for low clearance installations and have a 90-degree pig-tail harness versus the straight harness on the 011-08870-10 GMU 44 units. The units receive power directly from the GRS units and communicate with the GRS units via RS-485 digital interface. GMU 44 -00 & -10 Unit GMU 44 -20 Unit Figure 2-11, Magnetometer G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-9 190-00915-01 Revision 9 2.1.13 GDL 69A Datalink The GDL 69A 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 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 Entertainment Bus. Figure 2-12, GDL 69A Datalink 2.1.14 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 is located in the aft cabin floor area, just forward of the cabin door or on the upper avionics equipment shelf in the tail section. The GDL 59 is powered from the Avionics No. 2 bus. Figure 2-13, GDL 59 Wi-Fi Datalink Page 2-10 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.1.15 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 or may be installed as a stand-alone unit with an interface to GIA #1. The GSR 56 is located in the aft cabin floor area, just forward of the cabin door or on the upper avionics equipment shelf in the tail section. The GSR 56 is powered from the Avionics No. 2 bus. With relocation to the tail section, the GSR 56 has an internal heater powered from the Avionics No. 2 bus. Figure 2-14, GSR 56 Satellite Receiver 2.1.16 GTS 820/850 Traffic System (optional) The GTS 820/850 is 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 unit; 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 820/850 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 820/850 traffic system is powered from the Avionics No. 2 bus. Figure 2-15, GTS 820/850 Traffic System 2.1.17 GTS Traffic Processor The GTS Traffic Processor is a microprocessor-based Line Replaceable Unit that uses active interrogations of Mode S and Mode A/C transponders to provide Traffic Advisories and Resolution Advisories (GTS 8000 only) to the pilot. When installed, the GTS Processor can be configured as TAS (GTS 825), TCAS I (GTS 855), or TCAS II (GTS 8000). The GTS traffic processor is installed in the nose avionics bay. The GTS interfaces to the GA58 traffic antennas which are mounted on the upper and lower fuselage. The GTS traffic processor also interfaces with the GTX 3000 through ARINC 429 digital data lines. The GTS traffic processor is powered from the Avionics No. 2 Bus. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-11 190-00915-01 Revision 9 Figure 2-16, GTS Traffic Processor 2.1.18 Weather Radar The GWX 68 or optional GWX 70 Airborne Weather Radar provides weather radar data output to the GDU 1500 MFD. The GWX is mounted forward of the forward bulkhead at F.S. 30. Power to the GWX is received from the Avionics No. 1 bus. Data received from the GWX is routed through the GDL 69A data link unit to the MFD via high-speed data bus (Ethernet). Figure 2-17, Weather Radar 2.1.19 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 the 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 2-18, Servo Page 2-12 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.1.20 GRA 5500 Radar Altimeter The GRA 5500 Garmin Radar Altimeter is designed to calculate the height Above Ground Level (AGL) of the aircraft which is displayed on the PFDs. For King Air installations, the GRA 5500 is configured to output the value height Above Ground Level to the pilot through the GDU. The GRA interfaces to the existing radar altimeter antennas and GIA #2 via the ARINC 429 digital bus. The GRA 5500 is located below the lower avionics equipment shelf in the tail section. The GRA 5500 is powered from the No. 2 Avionics Bus. Figure 2-19, GRA 5500 Radar Altimeter 2.1.21 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. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-13 190-00915-01 Revision 9 2.1.22 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 R ENG 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. 2.1.23 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. 2.1.24 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 standby battery. This unit is connected to the right-hand static system. 2.1.25 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. 2.1.26 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: • standby attitude indicator (operation and internal lighting) • standby altimeter (vibrator and internal lighting) • standby airspeed indicator (lighting only) • 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. Page 2-14 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.1.27 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 located 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, radar 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 2-15 190-00915-01 Revision 9 2.3 Electrical Power Distribution This airplane uses a multi-bus system, as detailed below and in Figure 2-20. 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 2-21 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 is used in this installation 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 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 (including gyro motor and internal instrument lighting), the Standby Altimeter (including vibrator and internal instrument lighting), and the Standby Airspeed Indicator internal instrument lighting 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 2-16 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 L EFT GE NE RA TOR BUS R IGHT GEN ER ATOR BUS ISOLA TION BUS H OT B ATTE RY BUS B AT R ELAY E XT PWR E XT P OWER R ECEP TACLE A VIONICS MSTR N O.1 AV IONICS BUS L EFT S T/GEN R IGHT S T/GEN B ATTER Y BUS L GEN L IN E CONTAC TOR R GEN L IN E CONTAC TOR N O.1 DU AL FED BUS N O.2 DU AL FED BUS N O.3 DU AL FED BUS N O.4 DU AL FED BUS E SSEN TIAL BUS S TAN DBY INS TR UMENT BUS B ATTERY S TANDBY B ATTERY D C TEST JACK AFT EVAPORATOR BLOWER AIR C ON DITIONER C LUTCH VEN T BLOWER PWR AFT ELECTRIC HEAT C OPILOT WINDSHIELD ANT I-ICE F WD ELECT RIC HEAT PILOT WIN DSHIELD ANT I-ICE C ON DENSER BLOWER PWR L AN DING GEAR RELAY L AN DING GEAR MOTOR S TBY ATT S TB Y ALTM S TB Y INSTRU L IGHTS N O.2 AV IONICS BUS A VIONICS N O.2 RE LAY E NTER TA IN MENT BUS E NTER TA IN MENT B US RELAY Figure 2-20, 200/B200 Electrical Distribution (Post G1000 STC) G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-17 190-00915-01 Revision 9 ESS BUS SEC L GEN CTRL OUTSIDE AIR TEMP L BLEED CTRL CABIN PRESS CTRL AUTO OXY CTRL STALL WARN L BLEED AIR WARN LANDING GEAR WARN ANNUNCIATOR PWR L FUEL VENT HEAT SURFACE DEICE BRAKE DEICE AVIONICS MASTER SW AURAL WARN L ENG FUEL CTRL HEAT L MAIN ENG ANTIICE L STBY ENG ANTIICE FIRE DETECT L CHIP DETECTOR PROP BALANCE/SYNC PFD NO.2 ADC NO.2 AHRS NO.2 GIA NO.2 PFD/GIA NO.2 FAN CIGARETTE LIGHTER FURNISHING MASTER SW R GEN CTRL R BLEED CTRL CABIN TEMP CTRL CABIN PRES CTRL READING LT INSTR INDIRECT LT OVHD & SUBPANEL LT COPILOT PFD LT LANDGEAR POS IND ANNUNCIATOR IND R FUEL VENT HEAT WINDSHIELD WIPER R ENG FUEL CTRL HEAT R MAIN ENG ANTI-ICE R STBY ENG ANTI-ICE R CHIP DETECTOR AUTO FEATHER DUAL FED BUS 2 ADC NO.1 PRI AHRS NO.1 PRI COMM NO.1 GIA NO.1 PRI PFD NO.1 PRI GTX NO.1 GDL 69 TRAFFIC STORMSCOPE AFCS GMA NO.2 COMM NO.2 GTX NO.2 ESSENTIAL BUS AVIONICS BUS 2 AVIONICS BUS 1 MFD/STBY LT PILT PFD LT L ENG INSTR PWR NO SMK FSB & CABIN LT VOICE RCDR R ENG INSTRU PWR RUDDER BOOST CABIN AUDIO R BLEED AIR WARN RADAR PFD NO.1 SEC ADC NO.1 SEC GIA NO.1 SEC AHRS NO.1 SEC GMC MFD GCU MFD FAN DUAL FED BUS 1 PFD/GIA NO.1 FAN GMA NO.1 STBY ALTM STBY ATT STBY BATTERY STBY INSTR BUS L PITOT HEAT ADF DME ENTERTAINMENT BUS RADIO ALTIMETER GDL 59 GSR 56 Figure 2-21, G1000 Component Power Sources Page 2-18 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 2.4 Pitot/Static System The following schematic shows the pitot-static system as modified by this installation: DRAIN FORWARD PRESSURE BULKHEAD R/H PITOT MAST L/H PITOT MAST #1 AIR DATA COMPUTER #2 AIR DATA COMPUTER STANDBY ALTIMETER STANDBY AIRSPEED AFT PRESSURE 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 Figure 2-22, Pitot/Static System (Post G1000 STC) G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-19 190-00915-01 Revision 9 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 Figure 2-23, G1000/GFC 700 Block Diagram Page 2-20 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 This page intentionally left blank. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 3-1 190-00915-01 Revision 9 3 G1000 Control & 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. Figure 3-1, GDU 1040A Control Interface Page 3-2 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 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. If a 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. 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. 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. G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 3-3 190-00915-01 Revision 9 3.2 GCU 477 - MFD Controller The MFD controls are located on the GCU 477 as shown in Figure 3-4. 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: Figure 3-5, AFCS Controls (GMC 710 shown) Page 3-4 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 9 190-00915-01 3.4 GMA 1347D Audio Panel Figure 3-6 provides the audio panel controls. Transceiver Audio Telephone Speaker Marker Beacon Signal Sensitivity Transceiver Audio Passenger Address Music Marker Beacon Mute Transmitters Digital Recording Playback Cabin Intercom Master VOL (Large Knob) Reversionary Mode Aircraft Navigation Radio Audio Manual Squelch Intercom System (ICS) ICS VOL SQ (Small Knob) Figure 3-6, GMA 1347D Controls G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 3-5 190-00915-01 Revision 9 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 & MFD display • GRS 77 or GRS 7800 AHRS Units • GDC 74B or GDC 7400 Air Data Computers • GIA #1 and GIA #2 (COM listed separately) • GEA 71 Engine/Airframe Units • GCU 477 FMS Control Unit • GMC 710 Autopilot Control Unit • GMA 1347D Digital Audio Panel #1 • COM #1 • GTX 33 or GTX 3000 Mode S Transponder #1 2. Set the AVIONICS MASTER switch to ‘ON’. The following G1000 equipment is powered: • GTX 33 or GTX 3000 Mode S Transponder #2 • GMA 1347D Digital Audio Panel #2 • COM #2 • GDL 69A Datalink Unit • GSA Servos • GWX 68 or GWX 70 Weather Radar Unit • Traffic System • GDL 59 / GSR 56 Wi-Fi/Satellite (Optional) • Iridium Heater (optional) • Radar Altimeter (Optional) 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, ver