G1000 / GFC 700 System Maintenance Manual

2.1.2 GMA 1347D Audio Panel (2) ....................................................................................................... 2-2 2.1.3 GMC 710 AFCS Control Unit ...................................................................................................... 2-2 2.1.4 GCU 475 FMS Control Unit ......................................................................................................... 2-2 2.1.5 GIA 63W Integrated Avionics Unit (2) ......................................................................................... 2-3 2.1.6 GEA 71 Engine/Airframe Unit (2) ................................................................................................ 2-4 2.1.7 GTX 33 Mode S Transponder (2) ................................................................................................ 2-5 2.1.8 GDC 74B Digital Air Data Computer (2) ...................................................................................... 2-5 2.1.9 OAT Probe (2) ............................................................................................................................. 2-5 2.1.10 Attitude & Heading Reference System (2) .................................................................................. 2-6 2.1.11 GMU 44 Magnetometer (2) ......................................................................................................... 2-6 2.1.12 GDL 69A/69A SXM Datalink ....................................................................................................... 2-7 2.1.13 Weather Radar ............................................................................................................................ 2-7 2.1.14 GSA 80/81 Servo Motors and GSM 85A/86 Servo Mounts ........................................................ 2-8 2.1.15 Comant CI428-410 / CI428-200 GPS/WAAS Antennas.............................................................. 2-8 2.1.16 Thommen 5A58.22.26K.28.1.XX Airspeed Indicator .................................................................. 2-8 2.1.17 Thommen 3A43.22.35F.28.1.FU Altimeter ................................................................................. 2-8 2.1.18 Mid-Continent 4200-1( ) Attitude Indicator .................................................................................. 2-8 2.1.19 L-3 PS-835(C or D Model) Emergency Standby Battery............................................................. 2-9 2.1.20 Engine Signal Conditioning ......................................................................................................... 2-9 2.2 G1000 O PTIONAL I NTERFACES ................................................................................... 2-10 Page vi G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.3 ELECTRICAL POWER DISTRIBUTION ............................................................................ 2-10 2.4 SHIELD BLOCK G ROUNDS ........................................................................................... 2-13 2.5 G1000 SYSTEM BLOCK DIAGRAM ............................................................................... 2-14 3 G1000 CONTROL, OPERATION, AND FULL SOFTWARE LOAD ............................ 3-1 3.1 G1000 CONTROL ........................................................................................................ 3-1 3.1.1 GDU 1040A and GDU 1500 Displays ......................................................................................... 3-1 3.1.2 GCU 475 - MFD Controller .......................................................................................................... 3-3 3.1.3 GMC 710 - AFCS Controls .......................................................................................................... 3-3 3.1.4 GMA 1347D Audio Panel ............................................................................................................ 3-4 3.2 G1000 O PERATION ...................................................................................................... 3-6 3.2.1 G1000 Normal Mode ................................................................................................................... 3-6 3.2.2 Reversionary Mode ..................................................................................................................... 3-7 3.2.3 Configuration Mode ..................................................................................................................... 3-8 3.3 G1000 SYSTEM SOFTWARE I NFORMATION .................................................................. 3-13 3.3.1 G1000 Software Image ............................................................................................................. 3-13 3.3.2 Loader Card Creation ................................................................................................................ 3-14 3.3.3 Software Files ............................................................................................................................ 3-18 3.3.4 Configuration File Descriptions ................................................................................................. 3-18 3.3.5 Airframe and Optional Configurations ....................................................................................... 3-19 3.3.6 Configuration File Storage ......................................................................................................... 3-27 3.3.7 G1000 Software Load Summary ............................................................................................... 3-30 3.4 G1000 SYSTEM SOFTWARE AND CONFIGURATION LOAD PROCEDURE .......................... 3-31 3.4.1 Third Party STC Documentation and Optional Equipment List ................................................. 3-31 3.4.2 System Power Up ...................................................................................................................... 3-31 3.4.3 MFD & PFD Software Load ....................................................................................................... 3-31 3.4.4 Initial G1000 System Software and Baseline Configuration Load ............................................ 3-32 3.4.5 GDL 69A Legacy Software/Configuration ................................................................................ 3-34 3.4.6 GDL 69A SXM Software/Configuration ..................................................................................... 3-34 3.4.7 GRS AHRS / GMU 44 Magnetometer Software and Configuration Load ................................. 3-35 3.4.8 GWX 68 / 70 Radar Software and Configuration Load ............................................................. 3-35 3.4.9 GSM 85A / 86 Servo Mount Configuration Load ....................................................................... 3-35 3.4.10 King Air C90 Airframe Configuration ......................................................................................... 3-36 3.4.11 Weight and Airspeed Configuration........................................................................................... 3-37 3.4.12 Non-Garmin Traffic System Option Configuration..................................................................... 3-39 3.4.13 GTS 8XX Traffic System Option Configuration ......................................................................... 3-40 3.4.14 Stormscope (WX-500) Option Configuration ............................................................................. 3-40 3.4.15 ADF – 60 Option Configuration ................................................................................................ 3-40 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page vii 190-00682-01 Revision M 3.4.16 Radar Altimeter Option Configuration ....................................................................................... 3-41 3.4.17 DME 42 Option Configuration ................................................................................................... 3-41 3.4.18 GTX 33 Extended Squitter (ES) Option Configuration .............................................................. 3-41 3.4.19 ESP Support Option Configuration............................................................................................ 3-42 3.4.20 GSR56 ....................................................................................................................................... 3-42 3.4.21 Update Config Module ............................................................................................................... 3-43 3.4.22 Jeppesen ChartView Enable ..................................................................................................... 3-43 3.4.23 FliteCharts Enable ..................................................................................................................... 3-44 3.4.24 TAWS B Enable......................................................................................................................... 3-44 3.4.25 TAWS A Option ......................................................................................................................... 3-45 3.4.26 SVS/Pathways Enable .............................................................................................................. 3-45 3.4.27 ESP Enable ............................................................................................................................... 3-46 3.4.28 Optional Search and Rescue Enable ........................................................................................ 3-46 3.4.29 Aircraft Registration Number Entry ............................................................................................ 3-47 3.4.30 GMA 1347 #1 and GMA 1347 #2 Configuration Settings Check .............................................. 3-48 3.4.31 Clearing Default User Settings and Splash Screen Loading .................................................... 3-48 3.5 SOFTWARE AND CONFIGURATION LOAD VERIFICATION ................................................. 3-50 3.5.1 Software Verification.................................................................................................................. 3-50 3.5.2 Airframe Configuration Verification............................................................................................ 3-51 3.5.3 Stormscope (WX-500) Configuration Load Confirmation. ......................................................... 3-51 3.6 FINAL G1000 SYSTEM SETUP ..................................................................................... 3-52 3.6.1 Navigation Database Loading ................................................................................................... 3-52 3.6.2 Terrain/Obstacle Database Card Loading ................................................................................. 3-53 3.6.3 Configuration of Navigation Map for Non-Garmin Traffic System ............................................. 3-54 3.7 G1000 SYSTEM TESTING ........................................................................................... 3-55 3.7.1 Display Testing .......................................................................................................................... 3-55 3.7.2 Cooling Fan Check .................................................................................................................... 3-58 3.7.3 Reversion Mode Check ............................................................................................................. 3-58 3.7.4 GPS Signal Acquisition ............................................................................................................. 3-59 3.7.5 VHF COMM Operational Check ................................................................................................ 3-60 3.7.6 Marker Beacon Test .................................................................................................................. 3-60 3.7.7 VOR/LOC/GS Test .................................................................................................................... 3-61 3.7.8 GTX 33 Testing ......................................................................................................................... 3-61 3.7.9 Airspeed Indicator Check .......................................................................................................... 3-61 3.7.10 TAWS B Functional Check ........................................................................................................ 3-62 3.7.11 FliteCharts Functional Check .................................................................................................... 3-63 3.7.12 ChartView Functional Check ..................................................................................................... 3-64 Page viii G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 3.7.13 SafeTaxi Functional Check ....................................................................................................... 3-65 3.7.14 Aircraft Weight Configuration Functional Check ....................................................................... 3-66 3.7.15 GWX Weather Radar Check ..................................................................................................... 3-70 3.7.16 Traffic System Functional Check (Optional Installation) ........................................................... 3-71 3.7.17 DME Functional Check (Optional Installation) .......................................................................... 3-72 3.7.18 ADF Functional Check (Optional Installation) ........................................................................... 3-73 3.7.19 Gen Purpose A429 Bus Check (Optional Installation) .............................................................. 3-73 3.7.20 Stormscope Functional Check (Optional Installation) ............................................................... 3-74 3.7.21 Non-Garmin Radio Altimeter Check (Optional Installation) ....................................................... 3-75 3.7.22 ESP Functional Check .............................................................................................................. 3-76 3.7.23 Search and Rescue Functional Check ...................................................................................... 3-78 3.8 FINAL TEST ............................................................................................................... 3-78 4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ............................................ 4-1 4.1 AIRWORTHINESS LIMITATIONS ...................................................................................... 4-1 4.2 SERVICING I NFORMATION ............................................................................................. 4-3 4.2.1 On Condition Servicing ................................................................................................................ 4-3 4.2.2 Required Tools ............................................................................................................................ 4-4 4.2.3 Special Tools ............................................................................................................................... 4-4 4.3 M AINTENANCE I NTERVALS ............................................................................................ 4-5 4.3.1 Discontinued Maintenance ........................................................................................................ 4-10 4.4 VISUAL I NSPECTION ................................................................................................... 4-11 4.5 ELECTRICAL BONDING TEST ....................................................................................... 4-16 4.5.1 Requirements ............................................................................................................................ 4-16 4.5.2 Test Equipment ......................................................................................................................... 4-16 4.5.3 Phase 3 Electrical Bonding Procedure ...................................................................................... 4-17 4.5.4 Phase 4 Electrical Bonding Procedure ...................................................................................... 4-18 4.6 GRS 77 OR GRS 7800 EARTH M AGNETIC FIELD UPDATES .......................................... 4-18 4.7 GSA 8X G REASING PROCEDURE ................................................................................ 4-19 4.8 FLAPS- IN-M OTION DISCRETE I NPUT CHECK ................................................................. 4-20 4.9 SLIP CLUTCH TORQUE AND SERVO CURRENT DISPLAY CHECK PROCEDURE ................. 4-21 4.9.1 Automatic Slip Clutch Test Procedure (SW Version 0636.03 and Subs) .................................. 4-21 4.9.2 Manual Slip Clutch Test Procedure (SW Version 0636.02 and earlier) .................................... 4-23 4.9.3 Servo Adjustment Fixture Procedure ........................................................................................ 4-26 4.9.4 Servo Current Display Check .................................................................................................... 4-27 4.10 G1000 REDUNDANT CONNECTION CHECK .................................................................. 4-29 4.11 ENGINE DATA CHECK ................................................................................................. 4-32 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page ix 190-00682-01 Revision M 4.11.1 Torque ....................................................................................................................................... 4-32 4.11.2 ITT ............................................................................................................................................ 4-33 4.11.3 Oil Pressure ............................................................................................................................... 4-34 4.12 TRIM ANNUNCIATOR CHECK ....................................................................................... 4-35 4.13 G1000 M ISCOMPARE CHECKS.................................................................................... 4-36 4.14 NOSE AVIONICS COMPARTMENT FANS O PERATIONAL CHECK ....................................... 4-38 4.15 I NSTRUMENT PANEL FANS O PERATIONAL CHECK ......................................................... 4-38 4.16 STANDBY BATTERY PERIODIC CHECKS ....................................................................... 4-38 4.16.1 Charge Check ............................................................................................................................ 4-38 4.16.2 Capacity Test............................................................................................................................. 4-40 4.16.3 Cell Isolation Test ...................................................................................................................... 4-41 4.16.4 Charging Procedure .................................................................................................................. 4-41 5 TROUBLESHOOTING ................................................................................................ 5-1 5.1 G1000 ALERTING SYSTEM ........................................................................................... 5-2 5.1.1 Aural & Audio Alerts .................................................................................................................... 5-3 5.2 SYSTEM ANNUNCIATIONS ............................................................................................. 5-4 5.2.1 Failed Path Messages ................................................................................................................. 5-4 5.2.2 System Failure Troubleshooting................................................................................................ 5-20 5.2.3 Engine/Airframe Instrument Failures ......................................................................................... 5-25 5.2.4 ADF/DME Failure ...................................................................................................................... 5-25 5.3 C90 SERIES SPECIFIC ALERTS ................................................................................... 5-27 5.4 TAWS TROUBLESHOOTING ........................................................................................ 5-28 5.5 SYNTHETIC VISION AND P ATHWAYS TROUBLESHOOTING .............................................. 5-29 5.6 GFC 700 AFCS TROUBLESHOOTING .......................................................................... 5-30 5.6.1 General Troubleshooting ........................................................................................................... 5-31 5.6.2 GFC Configuration Alerts (SW Version 0636.03 and Subs) ..................................................... 5-34 5.6.3 GFC Status Page ...................................................................................................................... 5-34 5.6.4 GIA Fault Log Descriptions ....................................................................................................... 5-35 5.6.5 GIA Pre-Flight Test Steps ......................................................................................................... 5-37 5.7 BACKUP COMMUNICATIONS PATH CHECKS .................................................................. 5-44 5.7.1 Overview .................................................................................................................................... 5-44 5.7.2 Data Path Failures ..................................................................................................................... 5-44 5.8 GDU 104X TROUBLESHOOTING ................................................................................. 5-45 5.8.1 GDU 104X Symptoms ............................................................................................................... 5-45 5.8.2 GDU 104X Alerts ....................................................................................................................... 5-46 5.9 GMA SYMPTOMS ....................................................................................................... 5-54 Page x G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 5.9.1 GMA Alerts ................................................................................................................................ 5-55 5.10 GIA 63 TROUBLESHOOTING ....................................................................................... 5-56 5.10.1 COM Symptoms ........................................................................................................................ 5-56 5.10.2 NAV Symptoms ......................................................................................................................... 5-56 5.10.3 Glideslope Receiver Symptoms ................................................................................................ 5-56 5.10.4 GPS Symptoms ......................................................................................................................... 5-57 5.10.5 GIA Alert Messages................................................................................................................... 5-58 5.11 GEA TROUBLESHOOTING ........................................................................................... 5-65 5.11.1 GEA Alerts ................................................................................................................................. 5-65 5.12 GTX TROUBLESHOOTING ........................................................................................... 5-66 5.12.1 GTX Alerts ................................................................................................................................. 5-66 5.13 GDL 69A OR GDL 69A SXM TROUBLESHOOTING ....................................................... 5-67 5.13.1 GDL 69A or GDL 69A SXM Symptoms ..................................................................................... 5-67 5.13.2 GDL 69A/69A SXM Alerts ......................................................................................................... 5-68 5.14 GRS AND GMU TROUBLESHOOTING ........................................................................... 5-69 5.14.1 AHRS Symptoms....................................................................................................................... 5-69 5.14.2 GRS Alerts ................................................................................................................................. 5-70 5.14.3 GMU Alerts ................................................................................................................................ 5-72 5.14.4 Calibration Procedure E: Magnetometer Interference Test...................................................... 5-72 5.15 GDC 74B TROUBLESHOOTING ................................................................................... 5-76 5.15.1 Air Data Symptoms.................................................................................................................... 5-76 5.15.2 GDC 74B Alerts ......................................................................................................................... 5-76 5.16 GWX 68 OR GWX 70 TROUBLESHOOTING .................................................................. 5-77 5.16.1 GWX Alerts and Problems ........................................................................................................ 5-77 5.17 GMC 710 TROUBLESHOOTING ................................................................................... 5-78 5.17.1 GMC 710 Alerts and Problems .................................................................................................. 5-78 5.18 GCU 475 TROUBLESHOOTING .................................................................................... 5-79 5.18.1 GCU 475 Alerts and Problems .................................................................................................. 5-79 5.19 SOFTWARE/CONFIGURATION TROUBLESHOOTING ........................................................ 5-80 5.19.1 System Communication Hierarchy ............................................................................................ 5-81 5.20 BACKSHELL CONNECTORS ......................................................................................... 5-82 5.21 STANDBY ATTITUDE I NDICATOR TROUBLESHOOTING .................................................... 5-86 5.21.1 Standby Attitude Indicator Symptoms ....................................................................................... 5-86 5.22 STANDBY AIRSPEED I NDICATOR TROUBLESHOOTING .................................................... 5-86 5.22.1 Standby Airspeed Indicator Symptoms ..................................................................................... 5-86 5.23 STANDBY ALTIMETER TROUBLESHOOTING ................................................................... 5-87 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page xi 190-00682-01 Revision M 5.23.1 Standby Altimeter Symptoms .................................................................................................... 5-87 5.24 STANDBY BATTERY TROUBLESHOOTING ...................................................................... 5-87 6 EQUIPMENT REMOVAL & REPLACEMENT ............................................................. 6-1 6.1 GDU 1040A/1500 ....................................................................................................... 6-1 6.2 GMA 1347D AUDIO PANEL .......................................................................................... 6-2 6.3 GIA 63W I NTEGRATED AVIONICS UNITS ........................................................................ 6-2 6.4 GEA 71 ENGINE/AIRFRAME UNIT .................................................................................. 6-2 6.5 GTX 33 TRANSPONDER ............................................................................................... 6-3 6.6 GDC 74B AIR DATA COMPUTER ................................................................................... 6-3 6.7 GTP 59 OAT PROBE ................................................................................................... 6-3 6.8 GRS 77 / GRS 7800 AHRS......................................................................................... 6-4 6.8.1 GRS 77 AHRS ............................................................................................................................. 6-4 6.8.2 GRS 7800 AHRS ......................................................................................................................... 6-4 6.9 GMU 44 M AGNETOMETER ........................................................................................... 6-4 6.10 GDL 69A/ OR GDL69A SXM ....................................................................................... 6-5 6.11 GSA 80/81 SERVOS .................................................................................................... 6-5 6.12 GSM 85A / GSM 86 SERVO M OUNTS ........................................................................... 6-6 6.13 GCU 475 .................................................................................................................... 6-6 6.14 GMC 710.................................................................................................................... 6-6 6.15 GWX 68 / GWX 70...................................................................................................... 6-7 6.16 CONFIGURATION M ODULE ............................................................................................ 6-8 6.16.1 Configuration Module Removal & Replacement ......................................................................... 6-8 6.16.2 GRS 7800 Configuration Module Removal & Replacement ....................................................... 6-9 6.16.3 Configuration Module Checkout ................................................................................................ 6-10 6.17 GEA 71 BACKSHELL THERMOCOUPLE REMOVAL & REPLACEMENT ............................... 6-11 6.18 GPS/WAAS ANTENNAS ............................................................................................. 6-12 6.19 ENGINE SIGNAL CONDITIONERS .................................................................................. 6-12 6.20 SENIOR AEROSPACE PC920 SIGNAL CONDITIONING UNIT ............................................ 6-13 6.21 I NSTRUMENT PANEL ANNUNCIATORS (PROP SYNCH AND STANDBY BATTERY) ............... 6-13 6.22 L-3 AVIONICS (BF G OODRICH) PS-835(C OR D M ODEL ) EMERGENCY BATTERY ............ 6-14 6.23 STANDBY AIRSPEED I NDICATOR .................................................................................. 6-14 6.24 STANDBY ALTIMETER ................................................................................................. 6-14 6.25 STANDBY ATTITUDE I NDICATOR .................................................................................. 6-15 6.26 AVIONICS COOLING FANS ........................................................................................... 6-15 6.27 GDU COOLING FANS ................................................................................................. 6-16 Page xii G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 6.28 TRANSPONDER ANTENNA ........................................................................................... 6-16 7 G1000 HARDWARE REPLACEMENT - SOFTWARE LOADING AND TESTING ...... 7-1 7.1 GDU 1040/1500 MFD & PFD ...................................................................................... 7-1 7.1.1 GDU Display Software and Configuration Loading ..................................................................... 7-2 7.1.2 PFD/MFD Test............................................................................................................................. 7-5 7.2 GMA 1347D AUDIO PANEL .......................................................................................... 7-7 7.2.1 GMA Software and Configuration Loading .................................................................................. 7-7 7.2.2 GMA 1347D Test ......................................................................................................................... 7-8 7.3 GIA 63W I NTEGRATED AVIONICS UNIT ........................................................................ 7-11 7.3.1 GIA 63W Software and Configuration Loading ......................................................................... 7-11 7.3.2 GIA 63W Test ............................................................................................................................ 7-12 7.4 GEA 71 ENGINE/AIRFRAME UNIT ................................................................................ 7-15 7.4.1 GEA 71 Software and Configuration Loading ........................................................................... 7-15 7.4.2 GEA 71 Test .............................................................................................................................. 7-16 7.4.3 Additional GEA 71 Functional Tests.......................................................................................... 7-17 7.5 GTX 33 TRANSPONDER ............................................................................................. 7-24 7.5.1 GTX 33 Software and Configuration Loading ........................................................................... 7-24 7.5.2 Aircraft Registration Number Configuration .............................................................................. 7-25 7.5.3 GTX 33 Test .............................................................................................................................. 7-26 7.6 GDC 74B AIR DATA COMPUTER ................................................................................. 7-27 7.6.1 GDC Software and Configuration Loading ................................................................................ 7-27 7.6.2 Air Data Test (GDC 74B and STBY Instruments) ..................................................................... 7-28 7.6.3 Static Port Vertical Speed (Rate of Climb) Test ........................................................................ 7-31 7.6.4 OAT Probe Check ..................................................................................................................... 7-31 7.7 GRS AHRS / GMU 44 MAGNETOMETER ..................................................................... 7-32 7.7.1 GRS/GMU Software and Configuration Loading ....................................................................... 7-32 7.7.2 GRS/GMU Calibration Procedures ............................................................................................ 7-34 7.7.3 Procedure A1: GRS AHRS Pitch/Roll Offset Calibration ......................................................... 7-35 7.7.4 Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure (Optional).................................................................................................................................................. 7-36 7.7.5 Procedure B: GRS AHRS/GMU 44 Magnetic Calibration ........................................................ 7-37 7.7.6 Procedure D: Engine Run-Up Vibration Procedure ................................................................... 7-39 7.7.7 GRS/GMU Test ......................................................................................................................... 7-40 7.8 GDL 69A OR GDL 69A SXM DATA LINK ..................................................................... 7-41 7.8.1 GDL 69A/69A SXM Software and Configuration Loading ......................................................... 7-41 7.8.2 GDL 69A/69A SXM Test ........................................................................................................... 7-42 7.9 GSA 80/81 SERVOS .................................................................................................. 7-42 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page xiii 190-00682-01 Revision M 7.9.1 GSA Software and Configuration Loading ................................................................................ 7-42 7.10 GCU 475 FMS CONTROLLER ..................................................................................... 7-44 7.10.1 GCU Software and Configuration Loading ................................................................................ 7-44 7.10.2 GCU 475 Test............................................................................................................................ 7-44 7.11 GMC 710 AFCS CONTROLLER .................................................................................. 7-45 7.11.1 GMC Software and Configuration Loading ............................................................................... 7-45 7.11.2 GMC 710 Test ........................................................................................................................... 7-46 7.12 GWX 68/70 W EATHER RADAR ................................................................................... 7-47 7.12.1 GWX Software and Configuration Loading ............................................................................... 7-47 7.12.2 GWX Test .................................................................................................................................. 7-49 8 G1000 FUNCTION AND INTERFACE CHECKS ........................................................ 8-1 8.1 L ANDING G EAR AURAL ALERT CHECK ........................................................................... 8-1 8.2 SIRIUSXM AUDIO SUPPRESSION CHECK FOR AIRCRAFT WITH A TONE G ENERATOR ......... 8-1 8.3 SIRIUSXM AUDIO SUPPRESSION CHECK FOR AIRCRAFT W ITHOUT A TONE G ENERATOR .. 8-2 8.3.1 Gear Warning Discrete ................................................................................................................ 8-2 8.3.2 Stall Warning Discrete ................................................................................................................. 8-3 8.4 TAWS B FUNCTIONAL CHECK ...................................................................................... 8-4 8.5 W EIGHT ON W HEELS AND LOW SPEED AWARENESS BAND TEST ..................................... 8-5 9 SYSTEM RETURN TO SERVICE PROCEDURE ........................................................ 9-1 9.1 BACKUP PATH SYSTEM TESTING .................................................................................. 9-1 9.1.1 GPS Failure Test ......................................................................................................................... 9-1 9.1.2 GIA Failure Test .......................................................................................................................... 9-3 9.1.3 Display Failure Test ..................................................................................................................... 9-4 9.1.4 G1000 Backup Path Test ............................................................................................................ 9-5 9.2 M ISCELLANEOUS SYSTEM TESTS .................................................................................. 9-7 9.2.1 G1000 Cooling Fan Fail Annunciation Check ............................................................................. 9-7 9.2.2 Standby Instrument Electrical Power Check ............................................................................... 9-8 9.3 GFC 700 G ROUND TEST .............................................................................................. 9-9 9.3.1 Pre-Flight Test ............................................................................................................................. 9-9 9.3.2 AFCS Switch Check .................................................................................................................. 9-11 9.3.3 Autopilot Clutch Overpower Check ........................................................................................... 9-12 9.3.4 Manual Electric Pitch Trim Speed Check .................................................................................. 9-13 9.3.5 Autopilot Operation Check ........................................................................................................ 9-13 9.3.6 VOR/LOC/GS Test .................................................................................................................... 9-14 10 MAINTENANCE RECORDS ..................................................................................... 10-1 Page xiv G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 LIST OF ILLUSTRATIONS FIGURE ................................................................................................................................................. PAGE FIGURE 2-1, C90 ELECTRICAL DISTRIBUTION .................................................................................. 2-11 FIGURE 2-2, AVIONICS MASTER POWER SCHEMATIC .................................................................... 2-12 FIGURE 2-3, G1000 COMPONENT POWER SOURCES ..................................................................... 2-13 FIGURE 2-4, G1000 SYSTEM BLOCK DIAGRAM ................................................................................ 2-14 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 475) ............................................................................................. 3-3 FIGURE 3-5, AFCS CONTROLS (GMC 710) ........................................................................................... 3-3 FIGURE 3-6, GMA 1347D PN 011-01257-00 CONTROLS ...................................................................... 3-4 FIGURE 3-7, GMA 1347D PN 011-01257-20 CONTROLS ...................................................................... 3-5 FIGURE 3-8, NORMAL MODE ................................................................................................................. 3-6 FIGURE 3-9, MANUAL REVERSION WITH MFD FAILURE .................................................................... 3-7 FIGURE 3-10, MANUAL REVERSION WITH PILOT PFD FAILURE ....................................................... 3-7 FIGURE 3-11, SET AND ACTV SOFTKEYS AND COLUMNS ................................................................ 3-9 FIGURE 3-12, LOSS OF COMMUNICATION ........................................................................................ 3-10 FIGURE 3-13, CONFIGURATION STATUS ........................................................................................... 3-10 FIGURE 3-14, DATA TRANSMISSION INDICATORS ........................................................................... 3-11 FIGURE 3-15, G1000 LRU CONFIGURATION FILE STORAGE........................................................... 3-28 FIGURE 3-16, GRS/GDC CONFIGURATION SETTINGS STORAGE .................................................. 3-29 FIGURE 3-17, SOFTWARE/CONFIGURATION OVERVIEW ................................................................ 3-30 FIGURE 3-18, AIRCRAFT REGISTRATION .......................................................................................... 3-47 FIGURE 3-19, SYSTEM STATUS .......................................................................................................... 3-50 FIGURE 3-20, STORMSCOPE CONFIGURATION PAGE (REFERENCE ONLY)................................ 3-51 FIGURE 3-21, MFD POWER UP PAGE (FORMAT REFERENCE) ....................................................... 3-55 FIGURE 3-22, PFD POWER-UP SYSTEM ANNUNCIATIONS ............................................................. 3-56 FIGURE 3-23, PFD NORMAL OPERATION .......................................................................................... 3-57 FIGURE 3-24, GDU REVERSIONARY MODE ....................................................................................... 3-58 FIGURE 3-25, AUX – GPS STATUS PAGE ........................................................................................... 3-59 FIGURE 3-26, MARKER BEACON SYMBOLOGY ................................................................................ 3-60 FIGURE 4-1, SERVO GEAR................................................................................................................... 4-19 FIGURE 4-2, GIA I/O PAGE ................................................................................................................... 4-20 FIGURE 4-3, DISCRETE INDICATIONS ................................................................................................ 4-20 FIGURE 4-4, AIRFRAME CONFIGURATION PAGE ............................................................................. 4-21 FIGURE 4-5, GFC STATUS PAGE ........................................................................................................ 4-22 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page xv 190-00682-01 Revision M FIGURE 4-6, GFC STATUS PAGE ........................................................................................................ 4-23 FIGURE 4-7, GFC STATUS PAGE ........................................................................................................ 4-28 FIGURE 4-8, STANDBY BATTERY ........................................................................................................ 4-39 FIGURE 4-9, POWER SUPPLY CONNECTION .................................................................................... 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............................................................................................... 5-4 FIGURE 5-5, AFCS ANNUNCIATION FIELD ......................................................................................... 5-30 FIGURE 5-6, GFC STATUS PAGE ........................................................................................................ 5-34 FIGURE 5-7, MAGNETOMETER INTERFERENCE TEST .................................................................... 5-73 FIGURE 5-8, MAGNETOMETER INTERFERENCE TEST COMPLETE ............................................... 5-75 FIGURE 5-9, GIA 63W BACKSHELL CONNECTORS ........................................................................... 5-82 FIGURE 5-10, GEA 71 BACKSHELL CONNECTORS ........................................................................... 5-83 FIGURE 5-11, GMA 1347D BACKSHELL CONNECTORS ................................................................... 5-83 FIGURE 5-12, GTX 33/33D BACKSHELL CONNECTORS ................................................................... 5-83 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) ............................................................ 5-84 FIGURE 5-17, GDL 69A/GDL 69A SXM BACKSHELL CONNECTOR (P69A1) .................................... 5-85 FIGURE 5-18, GCU 475 BACKSHELL CONNECTOR (P4751) ............................................................. 5-85 FIGURE 5-19, GMC 710 BACKSHELL CONNECTOR (P7101) ............................................................ 5-85 FIGURE 5-20, GWX 68 BACKSHELL CONNECTOR (P681) ................................................................ 5-85 FIGURE 5-21, GWX 70 BACKSHELL CONNECTOR (P751) ................................................................ 5-85 FIGURE 5-22, SIGNAL CONDITIONER MATING CONNECTOR (PVIB1) ............................................ 5-86 FIGURE 6-1, CONFIGURATION MODULE INSTALLATION ................................................................... 6-8 FIGURE 6-2, GRS 7800 CONFIGURATION MODULE INSTALLATION ................................................. 6-9 FIGURE 6-3, GEA BACKSHELL THERMOCOUPLE ............................................................................. 6-11 FIGURE 7-1, G1000 NORMAL MODE CHECK........................................................................................ 7-5 FIGURE 7-2, MARKER BEACON SYMBOLOGY .................................................................................. 7-10 FIGURE 7-3, AUX – GPS STATUS PAGE (MFD) .................................................................................. 7-12 FIGURE 7-4, NORMAL ENGINE INSTRUMENT MARKINGS (MFD) .................................................... 7-17 FIGURE 7-5, AIRCRAFT REGISTRATION ............................................................................................ 7-25 FIGURE 7-6, GRS PITCH/ROLL OFFSET CALIBRATION PAGE ......................................................... 7-35 FIGURE 7-7, ENGINE RUN-UP TEST PAGE ........................................................................................ 7-39 FIGURE 7-8, NORMAL MODE AHRS CHECK ...................................................................................... 7-40 Page xvi G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 FIGURE 8-1, LOW SPEED AWARENESS BAND SYMBOLIZATION ..................................................... 8-5 FIGURE 9-1, GDU DATA VERIFICATION (ARINC 429) .......................................................................... 9-5 FIGURE 9-2, GIA DATA VERIFICATION (ARINC429/RS-232) ............................................................... 9-6 FIGURE 9-3, GIA DATA VERIFICATION (RS-485) ................................................................................. 9-7 FIGURE 9-4, PRE-FLIGHT TEST ........................................................................................................... 9-10 LIST OF TABLES TABLE ................................................................................................................................................... PAGE TABLE 1-1, MDL CONFIGURATIONS SUMMARY .................................................................................. 1-1 TABLE 1-2, REQUIRED DOCUMENTS ................................................................................................... 1-5 TABLE 1-3, REFERENCE PUBLICATIONS ............................................................................................. 1-6 TABLE 3-1, DATA INDICATOR SYMBOLS............................................................................................ 3-11 TABLE 3-2, LRU TO CONFIGURATION FILE RELATIONSHIP ............................................................ 3-23 TABLE 3-3, OPTIONAL AIRFRAME WEIGHT CONFIGURATIONS ..................................................... 3-37 TABLE 4-1, MAINTENANCE INTERVALS ............................................................................................... 4-5 TABLE 4-2, DISCONTINUED MAINTENANCE INTERVALS................................................................. 4-10 TABLE 4-3, NOSE SECTION VISUAL INSPECTION PROCEDURE .................................................... 4-11 TABLE 4-4, NOSE AVIONICS COMPARTMENT VISUAL INSPECTION PROCEDURE...................... 4-11 TABLE 4-5, PILOT’S COMPARTMENT VISUAL INSPECTION PROCEDURE .................................... 4-11 TABLE 4-6, INSTRUMENT PANEL G1000 EQUIPMENT VISUAL INSPECTION PROCEDURE ........ 4-13 TABLE 4-7, CABIN AREA VISUAL INSPECTION PROCEDURE.......................................................... 4-14 TABLE 4-8, REAR FUSELAGE AND EMPENNAGE VISUAL INSPECTION PROCEDURE ................ 4-15 TABLE 4-9, LIGHTNING STRIKE INSPECTION PROCEDURE............................................................ 4-15 TABLE 4-10, MEASURED TORQUE ...................................................................................................... 4-25 TABLE 4-11, SLIP CLUTCH TORQUE SETTINGS ............................................................................... 4-27 TABLE 4-12, STANDBY BATTERY REQUIRED EQUIPMENT ............................................................. 4-39 TABLE 5-1, SVS TROUBLESHOOTING ................................................................................................ 5-29 TABLE 5-2, SVS-RELATED ALERT MESSAGES ................................................................................. 5-29 TABLE 5-3, AFCS ANNUNCIATION TROUBLESHOOTING ................................................................. 5-31 TABLE 5-4, AFCS GENERAL TROUBLESHOOTING ........................................................................... 5-33 TABLE 5-5, MAGNETOMETER INTERFERENCE TEST SEQUENCE (EXAMPLE) ............................ 5-74 TABLE 6-1, CONFIGURATION MODULE KIT – 011-00979-03............................................................... 6-8 TABLE 6-2, GRS 7800 CONFIGURATION MODULE PARTS ................................................................. 6-9 TABLE 7-1, AIRSPEED AND ALTITUDE TABLE ................................................................................... 7-29 TABLE 7-2, VERTICAL SPEED TABLE ................................................................................................. 7-31 TABLE 7-3, REQUIRED GRS/GMU CALIBRATIONS ............................................................................ 7-34 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 1-1 190-00682-01 Revision M 1 INTRODUCTION 1.1 Content, Scope, Purpose This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G1000 integrated avionics and GFC700 Automatic Flight Control System (AFCS) as installed in the King Air C90 Series using STC #SA01456WI-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 system. 1.2 Applicability This document applies to all Model C90A/C90GT/C90GTi King Air aircraft equipped with the G1000 and GFC700 AFCS systems. References to “C90 Series” throughout this document include C90A, C90GT, and C90GTi models. Items in this document that are aircraft model(s) specific will identify the model(s) instead of “C90 Series”. The GFC 700 AFCS system is an integral part of the G1000 system and is included in “G1000 system” references throughout this document. 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. 1.3 Identifying an STC Configuration Table 1-1 lists the approved configurations for this STC as defined by the Master Drawing List (MDL) listed in Table 1-2. Software loads are governed primarily by the G1000 System Software Version number. The following table identifies the System Software Version for this STC. NOTE G1000 System Software Version 0636.07 is added with STC MDL Rev. 17 and is the recommended software version for new installations. G1000 System Software Versions 0636.01, 0636.02, 0636.03, 0636.05 and 0636.06 will remain to support fielded aircraft. Software Version 0636.04 is not approved for installation. Table 1-1, MDL Configurations Summary MDL Configuration Aircraft Model G1000 System Software Version Notes -1 C90A/C90GT King Air 0636.01 STC MDL Rev. 4 Approval -1 C90A/C90GT King Air 0636.02 STC MDL Rev. 5 Approval -1 C90A/C90GT/C90GTi King Air 0636.03 STC MDL Rev. 6 Approval -1 C90A/C90GT/C90GTi King Air 0636.05 STC MDL Rev. 11 Approval -1 C90A/C90GT/C90GTi King Air 0636.06 STC MDL Rev. 13 Approval -1 C90A/C90GT/C90GTi King Air 0636.07 STC MDL Rev. 17 Approval This STC addresses multiple C90 Series configurations. These configuration variants are added by loading the applicable airframe configuration and related options. Refer to the General Arrangement drawing listed in Table 1-2 for additional information. Page 1-2 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 1.4 G1000 System Software Version and Aircraft Configuration Check Follow these steps before any G1000 System Software is loaded for unit replacement to assure the correct software and configuration files are loaded. 1. Inspect the aircraft maintenance logs for records of non-Garmin STCs installed. Inspect aircraft records for signs of other alterations, including field updates and Service Bulletins. 2. Power on the G1000 system by setting the BAT switch to ON, then the EXT PWR switch to ON and finally the AVIONICS MASTER switch to ON. 3. On the MFD start-up screen, check the upper right section of MFD splash screen for G1000 system software version and airframe configuration number. 4. Write these numbers down for reference when loading software and configuration files. An alternate location to find the G1000 system software version and airframe configuration number is on the MFD AUX – SYSTEM STATUS page. On this page, this information is displayed in the AIRFRAME window in the upper right corner of the display. The display shows the current G1000 airframe configuration and system software version number. The system software version number is shown in the following format: ‘System Software Version XXXX.XX’. It correlates to the G1000 software used to load the software to the system in the example below: System Software Version ‘0636.07’ = G1000 Software P/N 006-B0636-07 The General Arrangement drawing defines the approved G1000 software versions for this STC. G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 1-3 190-00682-01 Revision M 1.5 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 King Air C90 Series. An overview of the G1000 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 system. Section 6: G1000 Equipment Removal & Replacement Gives instructions for the removal and replacement of G1000 equipment. Section 7: G1000 Hardware Replacement - Software Loading and Testing Gives instructions for loading software, configuring, and testing of individual G1000 hardware removed for service. Section 8: G1000 Function and Interface Checks Gives instructions for checking G1000 functions and interfaces for proper operation. Section 9: 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/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 1.6 Definitions/Abbreviations ADC: Air Data Computer ADF: Automatic Direction Finder ADTS: Air Data Test Set AFCS: Automatic Flight Control System AFM: Aircraft Flight Manual AFMS: Aircraft Flight Manual Supplement AHRS: Attitude Heading Reference System CFR: Code of Federal Regulations DME: Distance Measuring Equipment EAU: Engine/Airframe Unit ESP: Electronic Stability and Protection GPS: Global Positioning 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 Flight Display OAT: Outside Air Temperature PFD: Primary Flight Display 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 1.6.1 Units of Measure Unless otherwise stated, all units of measure are English units. Publications The following documents are required by this maintenance manual to perform maintenance: G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 1-5 190-00682-01 Revision M Table 1-2, Required Documents Part Number Garmin Documents 005-00375-30 STC Master Drawing List 005-W0022-00 Wiring Diagram, G1000/GFC 700 King C90 005-00375-22 General Arrangement, G1000/GFC700 AFCS, King Air C90 005-00375-19 GWX Radar Install, King Air C90A 005-00375-21 Antenna Install, King Air C90A 005-00375-28 Main Instrument Panel Installation, King Air C90 005-00375-34 Electrical Equipment Install, Nose Bay, King Air C90A 005-00375-41 Roll Servo Install, King Air C90A 005-00375-42 Yaw Servo Install, King Air C90A 005-00375-43 Pitch Servo Install, King Air C90A 005-00375-44 Pitch Trim Servo Install, King Air C90A 005-00375-53 Magnetometer Install, King Air C90A 005-00375-54 OAT Sensor Install, King Air C90A 005-00375-71 Standby Battery Install, King Air C90A 005-00375-78 Cabin Speaker Amplifier Installation, King Air C90 005-00375-79 Fwd Bulkhead Connector Plate Installation, King Air C90 320-00326-XX Wire Harness Assembly, G1000/GFC 700 005-00375-55 Wire Harness Routing, Nose, King Air C90 005-00375-56 Wire Harness Routing, Cabin, King Air C90 005-00375-31 Wire Harness Routing, Tail, King Air C90 005-00375-23 Control Wheel Modification,G1000/GFC 700, King Air C90 005-00375-25 Overhead Control Panel Modification, G1000/GFC 700, King Air C90A 005-00375-26 Pedestal Re-Configuration, King Air C90A 005-00375-29 Circuit Breaker Panel Modification, King Air C90A 005-00375-70 Circuit Breaker Panel Modification, King Air C90A 005-00375-83 Glareshield Lighting Modification, King Air C90 005-00375-AA GTX 33D Transponder Option, King Air C90 Part Number Beechcraft Documents 90-590024-11 King Air C90 Series Wiring Diagram Manual 90-590012-13 King Air Model 90 Series Maintenance Manual 101-590097-13 King Air Series Component Maintenance Manual Page 1-6 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 Part Number Other Documents 523-0772458-00611A Collins DME-42 Transceiver Repair Manual (If DME is installed) 9016182 Mid-Continent Instruments - Installation Manual and Operating Instructions, 4200 Series Attitude Indicator 85-292-1-1033 Signal Conditioner Installation Manual (Meggitt Sensing Systems) TP-336 L-3 Avionics Systems – Emergency Power Supply Installation Manual, PS- 835 The following publications are recommended to be on hand during the performance of maintenance activities. Table 1-3, Reference Publications Part Number Garmin Document 190-00682-02 G1000/GFC 700, King Air C90A/C90GT Airplane Flight Manual Supplement 190-00664-XX G1000 King Air C90 Cockpit Reference Guide 190-00355-04 GDL 69 Series SiriusXM Satellite Radio Activation Instructions 190-00907-00 G1000 System Maintenance Manual 190-00303-72 GSA8X/GSM85(A) Installation Manual 190-00303-83 GSM 86 Servo Gear Box Installation Manual 190-00313-12 Circular Connector (and Configuration Module) Installation Instructions Part Number Beechcraft Document 98-39006 Structural Inspection and Repair Manual Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealer Resource Center’ section of the Garmin web site; refer to Section 1.8 for details. 1.8 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/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-1 190-00682-01 Revision M 2 SYSTEM DESCRIPTION 2.1 Equipment Descriptions 2.1.1 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 1347 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 475 is installed in the pedestal. The GCU 475 provides the control interface for the MFD. The GDU 1500 communicates with the GDU 1040A units and the GDL 69A through a high-speed data bus (HSDB) Ethernet connection. The GDU 1500 communicated with the GCU 475 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. Electrical power to PFD 1, MFD, and PFD 2 is provided by the triple-fed bus. The triple-fed bus is powered by the battery and both generator buses. Additionally, a secondary power source is provided to PFD 1 by the center bus, which is fed by both generator buses and the battery. Therefore, the displays 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 GDU cooling fans are also installed behind the panel for PFD and MFD cooling. Page 2-2 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.1.2 GMA 1347D Audio Panel (2) The Garmin GMA 1347D Audio Panel integrates NAV/COM digital audio, intercom system and marker beacon controls. The C90 installation includes two GMA 1347 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. Power to the audio panels is provided by the avionics bus. These units only power up when the avionics master switch is turned on. The GMA 1347D units interface with the existing marker beacon antenna, as well as existing mic and phone jacks and oxygen mask mic. 2.1.3 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 Cockpit Reference Guide. The GMC 710 is powered by the triple fed bus. 2.1.4 GCU 475 FMS Control Unit The GCU 475 functions as the primary control interface to the GDU 1500 MFD. The GCU 475 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 475 is powered by the triple-fed bus. Detailed instructions regarding the controls are discussed in the G1000 Cockpit Reference Guide. G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-3 190-00682-01 Revision M 2.1.5 GIA 63W Integrated Avionics Unit (2) Two Garmin GIA 63W Integrated Avionics Units (IAUs) contains 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. Power is provided to both GIAs by the triple-fed bus. The triple-fed bus is powered by the battery and both generator buses. Additionally, a secondary power source is provided to GIA1 by the center bus, which is fed by both generator buses and the battery. The GIA 1’s COMM power supply (COM 1) is provided by No.1 Avionics Bus. GIA 2’s COMM power supply (COM 2) is provided by No.2 Avionics Bus. Therefore, both GIAs power-up immediately with external or aircraft power or battery operation, with the exception of both COMs, which will become active after selection of Avionics Master on. Both GIA 63s interface to the following equipment: • Existing VOR/LOC/Glideslope Antenna System • Existing VHF COM #1 & #2 Antennas • GPS/WAAS Antennas • GMA 1347D, #1 & #2 • GEA 71, #1 & #2 • GDU 1040A, #1 & #2 • GSA Servos • GRS AHRS, #1 & #2 • Traffic System (if installed) The GIA 63W #1 interfaces to the following additional equipment: • GDC 74B #1 • GTX 33 #1 • DME 42 (if installed) The GIA 63W #2 interfaces to the following additional equipment: • GDC 74B #2 • GTX 33 #2 • ADF 60 (if installed) • Stormscope (if installed) • Radio Altimeter (if installed) Page 2-4 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.1.6 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 are mounted in a vertical orientation. Power is received from the triple-fed bus. Both GEA units will power-up immediately with external or aircraft power or battery operation. 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 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-5 190-00682-01 Revision M 2.1.7 GTX 33 Mode S Transponder (2) The GTX 33 Non-Extended Squitter or GTX 33 Extended Squitter (ES) (Optional) or GTX 33D Diversity (Optional) transponders communicate with the on-side GIA 63W through RS-232 digital interface. The units are mounted in the nose equipment bay. Power is provided by the No. 1 and No. 2 avionics bus for GTX 33 No. 1 and No. 2 respectively. The GTX 33 Non-Extended Squitter and Extended Squitter units interface with the existing transponder antennas. The GTX 33D units interface with newly installed diversity transponder antennas. NOTE A model designation of GTX 33 in this manual will imply either the GTX 33 Non-Extend Squitter or GTX 33 Extended Squitter (ES) or GTX 33D Diversity transponder. 2.1.8 GDC 74B Digital Air Data Computer (2) The Garmin GDC 74B computers compile information from the pitot/static system and various outside air temperature (OAT) and awareness sensors and provide digital air data computations to the G1000 system. The GDC 74B communicates with the GIA 63W, GDU 1040A, and GRS AHRS using ARINC 429 digital interface. The unit is mounted behind the instrument panel. Power is provided to both GDC 74B units by the triple-fed bus. Additionally, a secondary power source is provided to the No. 1 computer by the center bus. The GDC 74B connects to existing pitot/static ports via existing tubing in C90A and C90GT airframes. For C90GTi airframes new pitot/static tubing and hardware is purchased from Beechcraft Company. Reference the Main Instrument Panel Installation drawing for details. 2.1.9 OAT Probe (2) The Garmin GTP 59 OAT Probes provide the GDC 74B with air temperature data. The OAT probes are mounted to the bottom of the King Air fuselage at F.S. 113.5. The probes receive power directly from the GDC 74B air data computers. Page 2-6 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.1.10 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 nose equipment bay, contain advanced tilt sensors, accelerometers, and rate sensors. The unit interfaces with the GDC 74B and GMU44 Magnetometer and utilizes GPS signals from the GIA 63Ws. Actual attitude and heading information is sent using ARINC 429 digital interface to both GDU 1040As and GIA 63Ws. Power is provided to both GRS 77 or GRS 7800 units by the triple-fed bus. Additionally, a secondary power source is provided to the No. 1 GRS by the center bus. 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. 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. NOTE A model designation of GRS or GRS AHRS in this manual will imply either the GRS 77 or GRS 7800 unit unless one model is specifically named. GRS 77 GRS 7800 2.1.11 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 vertical tail. The units receive power directly from the GRS units and communicate with the GRS units via RS-485 digital interface. G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-7 190-00682-01 Revision M 2.1.12 GDL 69A/69A SXM Datalink The GDL 69A/69A SXM provides the interface to the GWX 68 or GWX 70 weather radar by acting as a communications hub between the MFD and GWX via HSDB. The GDL 69A/69A SXM also provides SiriusXM Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A/69A SXM is mounted behind the instrument panel. Power to the GDL 69A/69A SXM is received from the avionics No. 3 bus. The GDL 69A/69A SXM 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. 2.1.13 Weather Radar The GWX 68 or 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. 2 bus. Data received from the GWX is routed through the GDL 69A data link unit to the MFD via high-speed data bus (Ethernet). NOTE A model designation of GWX in this manual will imply either the GWX 68 or GWX 70 unit unless one model is specifically named. Page 2-8 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.1.14 GSA 80/81 Servo Motors and GSM 85A/86 Servo Mounts The GSA 81 (low-torque) Servo Actuator is an electromechanical unit that will provide automatic control of pitch trim. The Garmin GSA 80 (high-torque) Servo Actuator is an electromechanical unit that will provide pitch, roll and yaw damp and turn coordination. The GSA 80/81 contains a motor-control and monitor circuit board, as well as a solenoid and a brushless DC motor. The GSA 80/81 servo receives serial RS-485 data packets from the GIA 63Ws. The roll servo is located in the 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 Mount. The GSM 85A/86 is responsible for transferring the output torque of the GSA 80/81 servo actuators to the mechanical flight control surface linkage. The GSM 85A has a slip clutch that is field adjustable to the required torque value. The GSM 86 has a clutch cartridge that is not field adjustable but can be replaced if the specified torque value is not within limits. NOTES A model designation of GSA in this manual will imply either the GSA 80 or GSA 81 unit unless one model is specifically named. A model designation of GSM in this manual will imply either the GSM 85A or GSM 86 unit unless one model is specifically named 2.1.15 Comant CI428-410 / CI428-200 GPS/WAAS Antennas The Comant CI428-410 GPS/WAAS/XM and CI428-200 GPS/WAAS antennas meet the GPS WAAS Gamma 3 specifications required for G1000. For procedural instructions on accessing the GPS antennas, refer to the King Air Model 90 Series Maintenance Manual listed in Table 1-2. 2.1.16 Thommen 5A58.22.26K.28.1.XX Airspeed Indicator A Thommen 5A58.22.26K.28.1.XX unit is installed as the standby airspeed indicator. The General Arrangement drawing Table 4 shows available part numbers signified by the XX notation above and aircraft effectivity. The standby airspeed indicator is self illuminated and is connected to the left generator bus. The internal lights are also connected to the emergency standby battery. 2.1.17 Thommen 3A43.22.35F.28.1.FU Altimeter The Thommen 3A43.22.35F.28.1.FU altimeter with internal vibrator is used as the standby altimeter. The vibrator is powered by the No. 1 triple-fed bus. This unit is self illuminated and its internal lighting is connected to the left generator bus. Both the vibrator and the internal lighting are also connected to the emergency standby battery. 2.1.18 Mid-Continent 4200-1( ) Attitude Indicator The Model 4200-1( ) Electric Attitude Indicator is used as the standby attitude indicator and is connected to the No. 3 triple-fed bus. This unit is self illuminated and its internal lighting is connected to the left generator bus. The unit along with its internal lighting is also connected to the emergency standby battery. The Model 4200-11 Mod 2 is applicable only to installations using STC SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 16 and later approved revisions. G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-9 190-00682-01 Revision M 2.1.19 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) The aircraft power buss provides a trickle charge to the PS-835 under normal conditions. This battery is existing in the rear fuselage of aircraft previously equipped with Collins EFIS and is installed in the nose avionics bay by this STC, on aircraft that were not previously equipped with Collins EFIS. 2.1.20 Engine Signal Conditioning Changes to the engine signal conditioning components were initiated with STC SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 5. The Sandia ST26 Tach Generator Unit (PN 305662-00), Senior Aerospace PC920 Signal Conditioning Unit (PN PC920-6A00PH-2A1) and the Garmin 005-00375-93 Tach- Gen Filter Assembly were replaced by the Vibro-Meter (Meggit) Signal Conditioner Signal Conditioner. Reference the Main Instrument Panel Installation drawing listed in Table 1-2 for the locations of the Signal Conditioner Components. 2.1.20.1 Sandia Aerospace ST26 Tach Generator Adapter Units (2) The ST26 Tach Generator Adapter Units are used for converting the signal from the propeller speed and turbine speed sensors into a signal that is usable by the GEAs. The output signal from this adapter unit will be represented by a 5 VDC square wave signal at same frequency of input signal. The No. 1 ST26 (left side) unit is connected to the No. 1 Triple-fed bus and the No. 2 ST26 (right side) unit is connected to the No. 2 triple-fed bus. The Sandia Aerospace ST26 Tach Generator Adapter Unit is applicable only to installations using STC SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions. 2.1.20.2 Senior Aerospace PC920 Signal Conditioning Unit The PC920 unit was installed per this STC only for aircraft with Senior Aerospace Ketema fuel flow transducer, part number 1/2-2-81-306. The PC920 unit is used for converting the signal from the fuel flow sensor into a variable 0 to 5 VDC signal that is proportional to flow rate. The PC920 unit No. 1 channel is connected to the No. 1 triple-fed bus and the No. 2 channel is connected to the No.2 triple-fed bus. The No. 1 channel (connector P9201) converts the fuel flow signal for the left engine and the No. 2 channel (connector P9202) converts the fuel flow signal for the right engine. The Senior Aerospace PC920 Signal Conditioner Unit is applicable only to installations using STC SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions. 2.1.20.3 Garmin 005-00375-93 Tach-Gen Filter Assembly (2) The Tach-Gen Filter Assembly is used to filter out high frequency signal noise and is installed between the Sandia ST26 Signal Conditioner and both the propeller speed and turbine speed sensors. There is one tach- gen filter installed for each engine. The left engine tach-gen filter is installed on the underside of the floor panel located forward of the pilots seat position. The right engine tach-gen filter is installed on the underside of the floor panel located forward of the co-pilots seat position. There are no power requirements for the tach- gen filter assembly. The Garmin Tach-Gen Filter Assembly, Part Number 005-00375-93, is applicable only to installations using STC SA01456WI-D Master Drawing List Revision 4 and previously approved revisions. Page 2-10 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.1.20.4 Vibro-Meter (Meggit) 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 Vibro-Meter (Meggit) 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 No. 1 Triple-fed bus and to the No. 2 Engine Signal Conditioner from No. 2 triple-fed bus. Both signal conditioners will power-up immediately with external or aircraft power or battery operation. The Vibro-Meter (Meggit) Signal Conditioner is applicable only to installations using STC SA01456WI-D Master Drawing List Revision 5 and subsequent approved revisions or fielded installations modified in accordance with Garmin Document 190-00682-06. 2.2 G1000 Optional Interfaces Optional equipment includes BF Goodrich WX-500 Stormscope, Rockwell Collins ADF-60A, and Rockwell Collins DME-42. Additional interfaces (such as Garmin GTS 8XX Traffic Systems, GSR 56 Iridium Communications, and TAWS-A) require separate installation approval other than this STC. Refer to wiring diagram listed in Table 1-2, for connection information for optional interfaces. 2.3 Electrical Power Distribution This airplane uses a multi-bus system, as detailed below and in Figures 2-1 and Figure 2-2. In normal operation, all buses are automatically tied into a single-loop system where all sources supply power through individual protective devices. The battery and generator switches on the pilot’s left subpanel are used to control power from the ship battery and generators into the airplane electrical system. Switches in the cockpit that receive power from the center and triple-fed buses are identified by a white ring on the panel around the switch. Left and Right Generator Buses: The left and right generator buses receive power from their respective left and right generators (ref. Figure 2-1). The left and right generator buses also support the No. 2 and No. 3 avionics buses, respectively, via the avionics master switch (ref. Figure 2-2). The No. 2 avionics bus supplies power to the following G1000 equipment: GMA 2, GTX 2, GWX, GSA servos. The No. 3 avionics bus supplies power to the GDL 69(). The No. 2 and No. 3 avionics buses also supply power to optional interface equipment. Center Bus: The center bus is fed by two generator buses and the hot battery bus, which automatically connects those components whenever the bus ties are closed (ref. Figure 2-1). The center bus provides a secondary power source for the following G1000 equipment: PFD 1, GIA 1, GDC 1, and GRS 1. Triple-fed Bus: The triple-fed is powered from the hot battery bus and both generator buses (ref. Figure 2-1.) The triple-fed bus also supports avionics no.1 bus via the avionics master switch (ref. Figure 2-2). The following G1000 equipment is supported by the triple-fed bus: MFD, PFD 1, PFD 2, GCU 475, GMC 710, GIA 1, GIA 2, GEA 1, GEA 2, GDC 1, GDC 2, OAT, GRS 1, and GRS 2. The No. 1 avionics bus provides power for the following G1000 equipment: GMA 1 and GTX 1. The No. 1 triple-fed bus provides power to the No.1 Sandia Aerospace ST26 tach generator adapter, No 1 channel of the Senior Aerospace PC 920 fuel flow conditioner, No.1 Vibro-Meter (Meggit) Signal Conditioner (if installed), and Thommen standby altimeter vibrator (under normal conditions.) The No 2 triple-fed bus provides power to the No. 2 Sandia Aerospace ST26 tach generator adapter, the No. 2 channel of the Senior Aerospace PC 920 fuel flow conditioner, and the No.2 Vibro-Meter (Meggit) Signal Conditioner (if installed). The No. 3 triple-fed bus provides power to the Mid-Continent standby attitude indicator (under normal conditions) and provides power for charging the L-3 emergency standby battery. Emergency Standby Battery Function: The Standby Emergency Battery (STBY BATT) system in the King Air C90 is designed to provide uninterrupted DC power to the Standby Attitude indicator (gyro motor) and the Standby Altimeter (vibrator) from the L-3 PS-835(C or D Model) Emergency Standby Battery. In addition, the STBY BATT system supplies a fixed lighting voltage to the Standby Attitude Indicator, the Standby Altimeter, and the Standby Airspeed Indicator in the event of a total loss of DC power (ref. Figure 2-1.) For aircraft retrofitted using STC SA01456WI-D Master Drawing List Revision 6 or later, the STBY “whiskey” compass will also receive lighting from the STBY BATT in the event of a total loss of DC power. The STBY BATT system G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-11 190-00682-01 Revision M is a redundant power source to the Standby Attitude indicator, Standby Altimeter, and the Standby Airspeed Indicator. The electrical system is protected from excessively high current flow by the bus tie system. A bus tie sensor and relay is located between each generator bus and the center bus and also between the battery bus and the center bus. When the battery switch is on, battery bus voltage energizes and closes the relay. Similarly, when a generator or external power is brought on-line, the generator bus tie relays are energized and closed. Figure 2-1, C90 Electrical Distribution Page 2-12 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 Figure 2-2, Avionics Master Power Schematic G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-13 190-00682-01 Revision M Figure 2-3, G1000 Component Power Sources 2.4 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. Page 2-14 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 2.5 G1000 System Block Diagram Figure 2-4, G1000 System Block Diagram G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 3-1 190-00682-01 Revision M 3 G1000 Control, Operation, and Full Software Load All control and operation of G1000 equipment as normally used in flight occurs through the PFDs, MFD, GMC 710, GCU 475, and GMA 1347D audio panel. Figures 3-1 thru 3-7 identifies various interface buttons for these units. 3.1 G1000 Control 3.1.1 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/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 Figure 3-2, GDU 1500 Control Interface 3.1.1.1 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 3.1.1.2 FMS Knob The FMS knobs shown in Figure 3-1 and Figure 3-4 are the primary controls for the G1000 system. • To cycle through different configuration screens: o To change page groups: Rotate the large FMS knob. o 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/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 3-3 190-00682-01 Revision M 3.1.2 GCU 475 - MFD Controller The MFD controls are located on the GCU 475 as show in Figure 3-4. Figure 3-4, MFD Controls (GCU 475) 3.1.3 GMC 710 - AFCS Controls The dedicated AFCS controls located on the GMC 710 are discussed in detail in the G1000 Cockpit Reference Guide. The following figure is provided for reference: Figure 3-5, AFCS Controls (GMC 710) Page 3-4 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Revision M 190-00682-01 3.1.4 GMA 1347D Audio Panel Figure 3-6 provides the audio panel controls for GMA 1347D PN 011-01257-00. The GMA 1347D PN 011- 01257-00 is applicable only to installations using STC SA01456WI-D Master Drawing List Revision 4 and previously approved revisions . Figure 3-6, GMA 1347D PN 011-01257-00 Controls