Garmin | G1000 NXi: Beechcraft King Air 300/B300 | Garmin G1000 NXi: Beechcraft King Air 300/B300 G1000 NXi System Maintenance Manual, King Air 300 Series, Includes Instructions for Continued Airworthiness for STC SA01535WI-D

Garmin G1000 NXi: Beechcraft King Air 300/B300 G1000 NXi System Maintenance Manual, King Air 300 Series, Includes Instructions for Continued Airworthiness for STC SA01535WI-D
System Maintenance Manual
King Air 300 Series
Includes Instructions for Continued Airworthiness
for STC SA01535WI-D
190-00716-N1
2017
Revision 2
© Copyright 2017
Garmin Ltd. or its subsidiaries
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Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913.397.8200
www.garmin.com
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9RB, UK
Phone: +44 (0) 23 8052 4000
Fax: +44 (0) 23 8052 4004
Garmin AT, Inc.
2345 Turner Rd., SE
Salem, OR 97302 USA
Telephone: 503.581.8101
RECORD OF REVISIONS
Revision Revision Date
Description
1
1/30/2017
Initial Release
Update for System Software v2286.02
2
2/24/2017
ECO #
--155168
DOCUMENT PAGINATION
Section
Table of Contents
Section 1
Section 2
Section 3
Section 4
Section 5
Section 6
Section 7
Section 8
Section 9
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Pagination
i – ix
1–6
7 – 44
45 – 94
95 – 137
138 – 227
228 – 257
258 – 339
340 – 371
372 - 389
Page i
Revision 2
INFORMATION SUBJECT TO EXPORT CONTROL LAWS
This document may contain information which is subject to the Export Administration
Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter
VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals
inside or outside the United States without first obtaining an export license. The preceding
statement is required to be included on any and all reproductions in whole or in part of this
manual.
WARNING
This product, its packaging, and its components contain chemicals known to the State of
California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in
accordance with California's Proposition 65. If you have any questions or would like additional
information, please refer to our web site at www.garmin.com/prop65.
CAUTION
The GDU lens is coated with a special anti-reflective coating that is very sensitive to skin oils,
waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTIREFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and
an eyeglass lens cleaner that is specified as safe for anti-reflective coatings.
IMPORTANT
All G1000 screen shots used in this document are current at the time of publication. Screen
shots are intended to provide visual reference only. All information depicted in screen shots,
including software file names, versions and part numbers, is subject to change and may not be
up to date.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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TABLE OF CONTENTS
PARAGRAPH
PAGE
1. INTRODUCTION .................................................................................................................... 1
1.1
Content, Scope, Purpose ................................................................................................. 1
1.2
Organization..................................................................................................................... 2
1.3
Definitions/Abbreviations ................................................................................................. 3
1.4
Units of Measure .............................................................................................................. 4
1.5
Publications...................................................................................................................... 4
1.6
Revision and Distribution ................................................................................................. 6
2. SYSTEM DESCRIPTION ....................................................................................................... 7
2.1
Equipment Descriptions ................................................................................................... 7
2.2
G1000 Optional Interfaces ............................................................................................. 23
2.3
Electrical Power Distribution .......................................................................................... 24
2.4
Electrical Load Utilization ............................................................................................... 27
2.5
Pitot/Static System ......................................................................................................... 35
2.6
Shield Block Grounds .................................................................................................... 37
2.7
G1000NXi /GFC700 Block Diagrams............................................................................. 37
2.8
GDU 1050A and GDU 1550 Displays ............................................................................ 39
2.9
Softkeys ......................................................................................................................... 40
2.10 FMS Knob ...................................................................................................................... 40
2.11 GCU 477 - MFD Controller ............................................................................................ 41
2.12 GMC 710 - AFCS Controls ............................................................................................ 41
2.13 GMA 1347D Audio Panel ............................................................................................... 42
2.14 G1000 Normal Mode...................................................................................................... 43
2.15 Reversionary Mode ........................................................................................................ 44
3. SOFTWARE AND CONFIGURATION ................................................................................. 45
3.1
Configuration Mode Overview........................................................................................ 45
3.2
G1000 System Software Information ............................................................................. 50
3.3
Configuration Mode........................................................................................................ 59
3.4
G1000 Hardware/Software Compatibility Check............................................................ 59
3.5
Equipment Verification (Third Party/Optional Equipment Documentation) .................... 60
3.6
Configuration Checklist .................................................................................................. 65
3.7
G1000 Software/Configuration Procedure ..................................................................... 67
3.8
System Software and Configuration Load ..................................................................... 68
3.9
Feature Enablement ...................................................................................................... 76
3.10 Aircraft Registration Number Entry ................................................................................ 84
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3.11 Configuration Manager .................................................................................................. 86
3.12 Splash Screen Loading .................................................................................................. 86
3.13 Clearing Default User Settings....................................................................................... 87
3.14 Database Loading .......................................................................................................... 87
3.15 Configuration of Navigation Map for Traffic System ...................................................... 89
3.16 Enter Flight ID for GTX 3000 Installations ..................................................................... 89
3.17 GRA 5500 Legacy Software and Configuration (Non Integrated) .................................. 90
3.18 Interface Confirmation.................................................................................................... 93
3.19 MD 302 Configuration and Sensor Calibration .............................................................. 94
4. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS .................................................... 99
4.1
Airworthiness Limitations ............................................................................................... 99
4.2
Servicing Information ................................................................................................... 100
4.3
Maintenance Intervals .................................................................................................. 103
4.4
Visual Inspection .......................................................................................................... 109
4.5
Electrical Bonding Test ................................................................................................ 114
4.6
GSU 75B, GRS 77, or GRS 7800 Earth Magnetic Field Updates................................ 117
4.7
GSA 80 Greasing Procedure ....................................................................................... 117
4.8
Flaps-in-motion Discrete Input Check .......................................................................... 118
4.9
GSM 86 Slip Clutch Torque Check Procedure ............................................................ 119
4.10 G1000 Redundant Connection Check ......................................................................... 122
4.11 Engine Data Check ...................................................................................................... 126
4.12 Trim Annunciator Check .............................................................................................. 128
4.13 G1000 Miscompare Checks......................................................................................... 130
4.14 Nose Avionics Compartment Fans Operational Check................................................ 131
4.15 Instrument Panel Fans Operational Check .................................................................. 132
4.16 Standby Battery Periodic Checks ................................................................................ 132
4.17 Rudder Boost Operational Check ................................................................................ 136
4.18 Exterior Skin Inspection Around Antennas .................................................................. 137
5. TROUBLESHOOTING ....................................................................................................... 138
5.1
System Annunciations ................................................................................................. 139
5.2
G1000 Alerting System ................................................................................................ 163
5.3
Aural & Audio Alerts ..................................................................................................... 164
5.4
King Air 300 Series Specific Alerts .............................................................................. 166
5.5
TAWS Troubleshooting ................................................................................................ 167
5.6
Synthetic Vision and Pathways Troubleshooting ......................................................... 168
5.7
GFC 700 AFCS Troubleshooting ................................................................................. 169
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5.8
General Troubleshooting ............................................................................................. 170
5.9
Backup Communications Path Checks ........................................................................ 182
5.10 GDU 105X Troubleshooting ......................................................................................... 182
5.11 GDU 105X Alerts ......................................................................................................... 184
5.12 GIA 63 Troubleshooting ............................................................................................... 192
5.13 GIA Alert Messages ..................................................................................................... 193
5.14 GEA Troubleshooting................................................................................................... 199
5.15 GTX Troubleshooting ................................................................................................... 200
5.16 GDL 69A or GDL69A SXM Troubleshooting................................................................ 201
5.17 GSU 75B, GRS 77, or GRS 7800 and GMU 44 Troubleshooting ................................ 203
5.18 GSU 75B/GDC 7400 Troubleshooting ......................................................................... 208
5.19 GWX 68 or GWX 70 Troubleshooting .......................................................................... 209
5.20 GMC 710 Troubleshooting ........................................................................................... 210
5.21 GCU 477 Troubleshooting ........................................................................................... 211
5.22 Software/Configuration Troubleshooting...................................................................... 212
5.23 Backshell/Backplate Connectors ................................................................................. 214
5.24 Mechanical Standby Attitude Indicator Troubleshooting .............................................. 222
5.25 Mechanical Standby Airspeed Indicator Troubleshooting ............................................ 222
5.26 Mechanical Standby Altimeter Troubleshooting........................................................... 223
5.27 MD 302 Standby Indicator Troubleshooting................................................................. 223
5.28 GDL 59 Troubleshooting .............................................................................................. 224
5.29 GSR 56 Troubleshooting ............................................................................................. 224
5.30 GTS 820/850 Troubleshooting ..................................................................................... 224
5.31 GTS Traffic Processor Troubleshooting....................................................................... 226
6. EQUIPMENT REMOVAL & INSTALLATION .................................................................... 228
6.1
GDU 1050A/1550......................................................................................................... 229
6.2
GMA 1347D Audio Panel ............................................................................................. 229
6.3
GIA 63W Integrated Avionics Units.............................................................................. 230
6.4
GEA 71 Engine/Airframe Unit ...................................................................................... 230
6.5
GTX 33( ) or GTX 3000 Transponder .......................................................................... 231
6.6
GTX 335R/GTRX 345R Transponder .......................................................................... 232
6.7
GDC 7400 Air Data Computer ..................................................................................... 232
6.8
GTP 59 OAT Probe...................................................................................................... 233
6.9
GRS 77 or GRS 7800 AHRS or GSU 75B ADAHRS ................................................... 233
6.10 GMU 44 Magnetometer ............................................................................................... 234
6.11 GDL 69A or GDL 69A SXM ......................................................................................... 236
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6.12 GSA 80 and GSA 9000 Servo Motors ......................................................................... 236
6.13 GSM 86 and GSM 9100 Servo Gearbox ..................................................................... 238
6.14 GCU 477 ...................................................................................................................... 238
6.15 GMC 710...................................................................................................................... 238
6.16 GWX 68 or GWX 70..................................................................................................... 239
6.17 Configuration Modules ................................................................................................. 239
6.18 GEA 71 Backshell Thermocouple Removal & Replacement ....................................... 244
6.19 GPS/WAAS Antennas.................................................................................................. 245
6.20 Diversity Transponder Antenna ................................................................................... 245
6.21 Iridium Antenna ............................................................................................................ 246
6.22 Wi-Fi Antenna .............................................................................................................. 246
6.23 Signal Conditioners ...................................................................................................... 247
6.24 Instrument Panel Annunciators (Prop Synch and Standby Battery) ............................ 247
6.25 Emergency Frequency Switch/Annunciator ................................................................. 248
6.26 L-3 Avionics (BF Goodrich) PS-835(C or D Model) Emergency Battery ...................... 248
6.27 MD 302 Standby Attitude Module (SAM) ..................................................................... 248
6.28 Mechanical Standby Indicators .................................................................................... 251
6.29 GIA Cooling Fans......................................................................................................... 253
6.30 GDU Cooling Fans ....................................................................................................... 253
6.31 GTS 820/850 and GTS Processor Traffic Units ........................................................... 254
6.32 GPA 65 PA/LNA Unit ................................................................................................... 254
6.33 GA 58 Traffic Antennas................................................................................................ 255
6.34 GDL 59 Wi-Fi Datalink ................................................................................................. 255
6.35 GSR 56 Satellite Receiver ........................................................................................... 256
6.36 GRA 5500 Radar Altimeter .......................................................................................... 256
6.37 GSD 41 Data Concentrator .......................................................................................... 257
7. GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING ......................... 258
7.1
GDU 1050A/1550 PFD & MFD .................................................................................... 258
7.2
GMA 1347D Audio Panel ............................................................................................. 262
7.3
GIA 63W Integrated Avionics Unit ............................................................................... 269
7.4
GEA 71 Engine/Airframe Unit ...................................................................................... 280
7.5
GTX 335R, GTX 345R, GTX 33( ), or GTX 3000 Transponder ................................... 294
7.6
GSU 75B ADAHRS ...................................................................................................... 297
7.7
GDC 7400 Air Data ...................................................................................................... 299
7.8
GRS 77 or 7800 AHRS and GMU 44 Magnetometer .................................................. 305
7.9
GMU 44 Magnetometer ............................................................................................... 307
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7.10 GSU/GRS/GMU Calibration Procedures ..................................................................... 308
7.11 GDL 69A or GDL 69A SXM Data Link ......................................................................... 317
7.12 GSA 80 Servos ............................................................................................................ 319
7.13 GCU 477 FMS Controller ............................................................................................. 321
7.14 GMC 710 AFCS Controller .......................................................................................... 324
7.15 GWX 68 or GWX 70 Weather Radar ........................................................................... 326
7.16 GRA 5500 Radar Altimeter .......................................................................................... 328
7.17 Garmin Traffic Systems (GTS 8XX/GTS 8XXX) .......................................................... 330
7.18 GDL 59......................................................................................................................... 334
7.19 GSR 56 ........................................................................................................................ 337
7.20 GSD 41 ........................................................................................................................ 339
8. SUBSYSTEM FUNCTIONAL CHECKS............................................................................. 341
8.1
Non-Garmin Traffic System Functional Check............................................................. 341
8.2
Stormscope Functional Check ..................................................................................... 342
8.3
TAWS Functional Check .............................................................................................. 344
8.4
FliteCharts Functional Check ....................................................................................... 347
8.5
ChartView Functional Check........................................................................................ 348
8.6
SafeTaxi Functional Check .......................................................................................... 349
8.7
DME Functional Check ................................................................................................ 350
8.8
ADF Functional Check ................................................................................................. 351
8.9
GRA 5500 Radar Altimeter Functional Check ............................................................. 351
8.10 Non-Garmin Radar Altimeter Check (Optional) ........................................................... 351
8.11 Weight on Wheels and Low Speed Awareness Band Check ...................................... 352
8.12 RVSM Checks.............................................................................................................. 353
8.13 ESP Functional Check ................................................................................................. 361
8.14 GTS Traffic System Functional Check ......................................................................... 364
8.15 Activation of Garmin Connext ...................................................................................... 367
8.16 GDL 59 Wi-Fi Data Link Functional Check .................................................................. 369
8.17 GSR 56 Satellite Receiver Functional Check .............................................................. 369
8.18 Search and Rescue Functional Check......................................................................... 371
9. G1000 SYSTEM RETURN TO SERVICE PROCEDURE .................................................. 372
9.1
Display Test ................................................................................................................. 372
9.2
Display Failure Test ..................................................................................................... 375
9.3
Reversion Mode Check................................................................................................ 376
9.4
Cooling Fan Fail Annunciation Check .......................................................................... 377
9.5
GPS Signal Acquisition ................................................................................................ 377
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9.6
GPS Failure Test ......................................................................................................... 378
9.7
GIA Failure Test ........................................................................................................... 380
9.8
GEA Functional Check................................................................................................. 381
9.9
Standby Instrument Electrical Power Checks .............................................................. 382
9.10 G1000 Backup Path Test ............................................................................................. 384
9.11 GFC 700 Ground Checkout ......................................................................................... 384
9.12 Maintenance Records .................................................................................................. 389
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King Air 300 Series
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Revision 2
LIST OF ILLUSTRATIONS
FIGURE
PAGE
Figure 2-1, Display Units ............................................................................................................... 8
Figure 2-2, Flight Stream 510 ....................................................................................................... 9
Figure 2-3, Audio Panel ................................................................................................................ 9
Figure 2-4, AFCS Controller ....................................................................................................... 10
Figure 2-5, FMS Controller ......................................................................................................... 10
Figure 2-6, Transponders ........................................................................................................... 11
Figure 2-7, GIA unit ..................................................................................................................... 13
Figure 2-8, GEA unit ................................................................................................................... 13
Figure 2-9, GSU-75B ADAHRS with Connector and Mounting Tray .......................................... 14
Figure 2-10, GDC 7400 Air Data Computer ................................................................................ 15
Figure 2-11, OAT probe .............................................................................................................. 15
Figure 2-12, AHRS ...................................................................................................................... 16
Figure 2-13, Magnetometer ........................................................................................................ 17
Figure 2-14, GDL 69A/69A SXM Datalink ................................................................................... 17
Figure 2-15, GDL 59 Wi-Fi Datalink ............................................................................................ 18
Figure 2-16, GSR 56 Satellite Receiver ...................................................................................... 18
Figure 2-17, GSD 41 Data Concentrator .................................................................................... 19
Figure 2-18, GTS 820/850 Traffic System .................................................................................. 19
Figure 2-19, GTS Traffic Processor ............................................................................................ 20
Figure 2-20, Weather Radar ....................................................................................................... 20
Figure 2-21, Servo ...................................................................................................................... 21
Figure 2-22, GSA 9000 / GSM 9100 ........................................................................................... 21
Figure 2-23, GRA 5500 Radar Altimeter ..................................................................................... 21
Figure 2-24, MD 302 Standby Attitude Module ........................................................................... 22
Figure 2-25, 300 Series Electrical Distribution (Post G1000 STC) ............................................. 25
Figure 2-26, G1000 Component Power Sources ........................................................................ 26
Figure 2-27, Pitot/Static System with ADC(s) and AHRS(s) Installed ......................................... 35
Figure 2-28, Pitot/Static System with GDU 75B ADAHRS(s) Installed ....................................... 36
Figure 2-29, G1000NXi/GFC 700 Block Diagram with GSU 75B ADAHRS................................ 37
Figure 2-30, G1000NXi/GFC 700 Block Diagram with Separate ADC and AHRS...................... 38
Figure 2-31, GDU 1050A Control Interface ................................................................................. 39
Figure 2-32, GDU 1550 Control Interface ................................................................................... 39
Figure 2-33, G1000 Softkeys ...................................................................................................... 40
Figure 2-34, MFD Controls (GCU 477 shown) ............................................................................ 41
Figure 2-35, AFCS Controls (GMC 710 shown) ......................................................................... 41
Figure 2-36, GMA 1347D Controls ............................................................................................. 42
Figure 2-37, Normal Mode .......................................................................................................... 44
Figure 2-38, Automatic Reversion with MFD failure ................................................................... 44
Figure 2-39, Manual Reversion with pilot PFD failure ................................................................. 44
Figure 3-1, SET>ACTV Diagram ................................................................................................ 46
Figure 3-2, Loss of Communication ............................................................................................ 47
Figure 3-3, Configuration Status ................................................................................................. 47
Figure 3-4, Data Transmission Indicators ................................................................................... 47
Figure 3-5, G1000 LRU Configuration File Storage .................................................................... 57
Figure 3-6, GSU/GRS/GDC Configuration Settings Storage ...................................................... 58
Figure 3-7, Garmin Unit S/N Location ......................................................................................... 61
Figure 3-8, Garmin Unit Listed if Installed ................................................................................... 62
Figure 3-9, Ethernet Connections Page ...................................................................................... 63
Figure 3-10, ESP Status Field .................................................................................................... 64
Figure 3-11, Software/Configuration Overview ........................................................................... 67
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Figure 3-12, MFD Aux - Database Page DB Transfer ................................................................ 88
Figure 3-13, Stormscope Configuration Page ............................................................................. 93
Figure 3-14, Stormscope Configuration ...................................................................................... 93
Figure 4-1, GIA I/O Page .......................................................................................................... 118
Figure 4-2, Discrete Indications ................................................................................................ 118
Figure 4-3, GFC Status Page ................................................................................................... 119
Figure 4-4, Ambient Temperature Conversion Chart ................................................................ 127
Figure 4-5, Standby Battery ...................................................................................................... 133
Figure 4-6, Power Supply Connection ...................................................................................... 136
Figure 4-7, Exterior Skin Inspection Around Antennas ............................................................. 137
Figure 5-1, Aux – System Status Page ..................................................................................... 138
Figure 5-2, System Annunciations ............................................................................................ 139
Figure 5-3, Alerts & Annunciations ........................................................................................... 163
Figure 5-4, Alerts Softkey Annunciation .................................................................................... 163
Figure 5-5, AFCS Annunciation Field ....................................................................................... 169
Figure 5-6, GFC Status Page ................................................................................................... 172
Figure 5-7, Magnetometer Interference Test ............................................................................ 206
Figure 5-8, GIA 63W Backplate Connectors ............................................................................. 214
Figure 5-9, GEA 71 Backplate Connectors ............................................................................... 215
Figure 5-10, GMA 1347D Backplate Connectors ...................................................................... 215
Figure 5-11, GTX 33/33D Backplate Connectors ..................................................................... 215
Figure 5-12, GTX 3000 Connectors (P3301 and P3302) .......................................................... 216
Figure 5-13, GTX 335R/345R Looking at Front of Connector (P3251) ..................................... 216
Figure 5-14, GTX 345R (Only) Looking at Front of Connector (P3252).................................... 217
Figure 5-15, GDU 1050A/1550 Backshell Connector (P10401 or P15001) .............................. 217
Figure 5-16, GRS 77 Backshell Connector (P771) ................................................................... 217
Figure 5-17, GRS 7800 Backshell Connector (P78001) ........................................................... 218
Figure 5-18, GSU 75B Connector View from Front (P751) ....................................................... 218
Figure 5-19, GDC 7400 Mating Connector (P74001) ............................................................... 218
Figure 5-20, GDL 69A/GDL 69A SXM Backplate Connector (P69A1) ...................................... 218
Figure 5-21, GCU 477 Backshell Connector (P4751) ............................................................... 219
Figure 5-22, GMC 710 Backshell Connector (P7101) .............................................................. 219
Figure 5-23, GWX 68 Backshell Connector (P681) .................................................................. 219
Figure 5-24, GWX 70 Backshell Connector (P751) .................................................................. 219
Figure 5-25, GTS 820/850 Mating Connectors (P8001 and P8002) ......................................... 219
Figure 5-26, GTS 820/850 Mating Connector (P8003) (Rear View) ......................................... 220
Figure 5-27, GTS Processor Connector (P8001) ...................................................................... 220
Figure 5-28, GPA 65 Mating Connector (P651) (Rear View) .................................................... 220
Figure 5-29, Signal Conditioner (1PVIB1 and 2PVIB1) ............................................................ 220
Figure 5-30, GDL 59 Mating Connector (1P591) ...................................................................... 221
Figure 5-31, GSR 56 Mating Connector (1P561) ...................................................................... 221
Figure 5-32, GRA 5500 Connector (P55001) ........................................................................... 221
Figure 5-33, GSD 41 Backplate Connector (P411) ................................................................... 221
Figure 5-34, GSA 9000 Mating Connector (P90001) ................................................................ 221
Figure 6-1, GSA 80 Servo Gear ................................................................................................ 237
Figure 6-2, GSM 9100 O-ring ................................................................................................... 237
Figure 6-3, Configuration Module Installation ........................................................................... 240
Figure 6-4, GRS 7800 Configuration Module Installation ......................................................... 241
Figure 6-5, GSU 75B Configuration Module Installation ........................................................... 242
Figure 6-6, GEA Backshell Thermocouple ................................................................................ 244
Figure 6-7, MD 302 Backshell and Config Module ................................................................... 250
Figure 7-1, G1000 Normal Mode Check ................................................................................... 261
Figure 7-2, Aux – GPS Status Page (MFD) .............................................................................. 276
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Figure 7-3, Normal Engine Instrument Markings (MFD) ........................................................... 283
Figure 7-4, Ambient Temperature Conversion Chart ................................................................ 286
Figure 7-5, Aircraft Registration ................................................................................................ 296
Figure 7-6, GRS/GMU Calibration, Pitch/Roll Offset ................................................................ 310
Figure 7-7, GRS/GMU Calibration, Engine Run-Up .................................................................. 314
Figure 7-8, Normal Mode AHRS Check .................................................................................... 316
Figure 8-1, Low Speed Awareness Band Symbolization .......................................................... 353
Figure 8-2, RVSM Critical Region ............................................................................................. 355
Figure 8-3, RVSM Critical Region (modified) ............................................................................ 356
Figure 8-4, Dial Indicator ........................................................................................................... 357
Figure 8-5, Static Port Measurement ........................................................................................ 358
Figure 8-6, Static Port Measurement locations ......................................................................... 359
Figure 8-7, Static Port Measurement Log ................................................................................. 359
Figure 8-8, Traffic Map .............................................................................................................. 364
Figure 8-9, GSR56 Configuration Page .................................................................................... 370
Figure 8-10, Aux-Telephone page ............................................................................................ 370
Figure 9-1, MFD Power Up Page .............................................................................................. 372
Figure 9-2, PFD Power-up System Annunciations ................................................................... 373
Figure 9-3, PFD Normal Operation ........................................................................................... 374
Figure 9-4, GDU Reversionary Mode ....................................................................................... 376
Figure 9-5, AUX-GPS Status Page ........................................................................................... 378
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LIST OF TABLES
TABLE .................................................................................................................................. PAGE
Table 1-1, Required Documents ................................................................................................... 4
Table 1-2, Reference Publications ................................................................................................ 5
Table 2-1, Electrical Loads ......................................................................................................... 27
Table 4-1, Maintenance Intervals .............................................................................................. 103
Table 4-2, Discontinued Maintenance Intervals ........................................................................ 108
Table 4-3, Nose Section Visual Inspection Procedure .............................................................. 109
Table 4-4, Nose Avionics Compartment Visual Inspection Procedure ..................................... 109
Table 4-5, Pilot’s Compartment Visual Inspection Procedure ................................................... 110
Table 4-6, Instrument Panel G1000 Equipment Visual Inspection Procedure .......................... 111
Table 4-7, Cabin Area Visual Inspection Procedure ................................................................. 112
Table 4-8, Rear Fuselage and Empennage Visual Inspection Procedure ................................ 113
Table 4-9, Lightning Strike Inspection Procedure ..................................................................... 114
Table 4-10, GSM 86 Slip Clutch Torque Settings ..................................................................... 121
Table 4-11, Engine Data Check Test Equipment ...................................................................... 126
Table 4-12, ITT Indication Test Points ...................................................................................... 126
Table 4-13, Torque Indication Test Points ................................................................................ 128
Table 4-14, Standby Battery Required Equipment ................................................................... 132
Table 5-1, SVS Troubleshooting ............................................................................................... 168
Table 5-2, SVS-Related Alert Messages .................................................................................. 168
Table 5-3, AFCS Annunciation Troubleshooting ....................................................................... 170
Table 5-4, AFCS General Troubleshooting ............................................................................... 171
Table 5-5, Magnetometer Interference Test Sequence ............................................................ 207
Table 6-1, Configuration Module Kit – 011-00979-00 ............................................................... 240
Table 6-2, GRS 7800 Configuration Module Parts ................................................................... 241
Table 6-3, GSU 75B Configuration Module Kit – 011-00979-20 ............................................... 242
Table 6-4, Thermocouple Kit (011-00981-00) ........................................................................... 244
Table 7-1, ITT Indication Test Points ........................................................................................ 285
Table 7-2, Torque Indication Test Points .................................................................................. 287
Table 7-3, N1 Indication Test Points ......................................................................................... 288
Table 7-4, N2 Indication Test Points ......................................................................................... 290
Table 7-5, Fuel Flow Indication Test Points .............................................................................. 291
Table 7-6, Oil Pressure Test Points .......................................................................................... 292
Table 7-7, Oil Temperature Test Points .................................................................................... 293
Table 7-8, Air Data System Test ............................................................................................... 302
Table 7-9, Vertical Speed Table ............................................................................................... 304
Table 7-10, Required GRS/GMU Calibrations .......................................................................... 309
Table 8-1, RVSM Required Avionics ........................................................................................ 354
Table 8-2, In-Flight Altitude Hold Performance Test ................................................................. 360
G1000 NXi System Maintenance Manual
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Revision 2
1. INTRODUCTION
1.1
Content, Scope, Purpose
This document provides Instructions for Continued Airworthiness (ICA) for the NXi configuration
of the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control
System (AFCS) as installed in the Beechcraft King Air 300 Series, under STC SA01535WI-D.
This document satisfies the requirements for continued airworthiness as defined by 14 CFR
Part 23.1529 and Appendix G. Information in this document is required to maintain the
continued airworthiness of the G1000 and GFC700.
Throughout this document, the GFC 700 autopilot system is included in the G1000NXi system
description and is identified separately only when needed.
References to “300 Series” throughout this document include 300, 300C, B300, B300C,
B300GT, and B300CGT models. Items in this document that are aircraft model(s) specific will
identify the model(s) instead of “300 Series”.
References to “Beechcraft” throughout this document include other Manufacturer names
including Textron Aviation, Hawker Beechcraft, and Raytheon.
1.1.1
Applicability
This document applies to all King Air Model 300 Series aircraft equipped with the G1000NXi
system. All G1000NXi King Air 300 Series airplanes are configured per General Arrangement
drawing 005-00629-N2 Rev 1 or subsequent.
Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft
operator to include the maintenance information provided by this document in the operator’s
Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program.
Aircraft modified by this STC have been shown to qualify for operation in Reduced Vertical
Separation Minimum (RVSM) airspace as a group aircraft in accordance with Title 14 of the
Code of Federal Regulations (14 CFR) Part 91, Appendix G, “Operations in Reduced Vertical
Separation Minimum (RVSM) Airspace”, and Federal Aviation Administration (FAA) Document
No. 91-RVSM, Change 2 dated 2/10/2004, “Guidance Material On the Approval Of
Operators/Aircraft For RVSM Operations”. This qualification is based on analysis of the
configuration and performance of the air data, automatic altitude control, altitude alerting, and
altitude reporting systems. These systems must be maintained in accordance with the
inspections and tests specified in this document and other current maintenance practices to
guarantee continued compliance to RVSM specifications.
1.1.2
Identifying an STC Configuration
The General Arrangement drawing lists the G1000 System Software Version numbers approved
for this STC. This section shows where to find the installed software version and airframe type
in the G1000 system for service if the technician is unsure of what G1000 software and
configuration is installed.
1. Place the G1000 system in configuration mode (reference Section 3.1 for instructions).
2. On PFD1, go to the MANIFEST CONFIGURATION page in the SYSTEM page group.
In the SYSTEM field the G1000 system software part number and version number that
is installed is shown.
3. Next go to the GDU page group and turn to the AIRFRAME CONFIGURATION page.
The airframe series, engine, and prop types are listed in the AIRFRAME box.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
EXAMPLE:
For a configuration that loaded “King Air B300 PT6A-60A”, the AIRFRAME section will display:
SERIES:
ENGINE:
PROP:
1.2
B300
PT6A-60A
HARTZELL 4
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 300 Series. An overview of the G1000 system
interface is also provided.
Section 3: Software and Configuration
Provides software and configuration loading instructions for a complete system software load.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for continued airworthiness of the G1000 system.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with
the G1000 system.
Section 6: Equipment Removal & Replacement
Gives instructions for the removal and replacement of G1000 equipment.
Section 7: Garmin G1000 LRU Replacement/Configuration & Testing
Gives instructions for loading software, configuring, and testing of G1000 equipment.
Section 8: Subsystem Functional Checks
Gives instructions for testing G1000 subsystems.
Section 9: G1000 System Return to Service Procedure
Specifies return-to-service procedures to be performed upon completion of maintenance of the
G1000 system.
G1000 NXi System Maintenance Manual
King Air 300 Series
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Page 2
Revision 2
1.3
Definitions/Abbreviations
ADAHRS:
Air Data and Attitude Heading Reference System
ADF:
Automatic Direction Finder
ADS-B: Automatic Dependent Surveillance – Broadcast
ADTS: Air Data Test Set
AFCS: Automatic Flight Control System
AFM:
Airplane Flight Manual
AFMS: Airplane Flight Manual Supplement
AHRS: Attitude Heading Reference System
CDU:
Control Display Unit
CFR:
Code of Federal Regulations
DME:
Distance Measuring Equipment
EAU:
Engine/Airframe Unit
ESP:
Electronic Stability and Protection
FIS-B: Flight Information Services – Broadcast
FS:
Flight StreamTM
GPS:
Global Positioning System
GPWS: Ground Proximity Warning System
HSDB: High-Speed Data Bus (Ethernet)
IAU:
Integrated Avionics Unit
ICS:
Inter-Com System
ITT:
Interstage Turbine Temperature
LRU:
Line Replaceable Unit
MFD:
Multi-Function Display
MMC: Multi-Media Card
OAT:
Outside Air Temperature
PED:
Personal Electronic Device
PFD:
Primary Flight Display
PVT:
Position Velocity Time
RVSM: Reduced Vertical Separation Minimum
STBY: Standby
STBY ATT: Standby Attitude Indicator
STBY ALT: Standby Altimeter
STBY A/S: Standby Airspeed Indicator
STC:
Supplemental Type Certificate
TAWS: Terrain Awareness & Warning System
TIS:
Traffic Information Services
TIS-A: Traffic Information Services – A
TIS-B: Traffic Information Services – Broadcast
WAAS: Wide Area Augmentation System
VHF:
Very High Frequency
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 3
Revision 2
1.4
Units of Measure
Unless otherwise stated, all units of measure are English units.
1.5
Publications
The following documents are required by this maintenance manual to perform maintenance. It
is the responsibility of the owner / operator to ensure latest versions of these documents are
used during operation, servicing or maintenance of the airplane.
Table 1-1, Required Documents
Part Number
Garmin Document
005-00629-00
Master Drawing List, Garmin G1000/GFC 700 in Beechcraft Model 300/B300 Series King
Air
005-00629-N2
General Arrangement, G1000/GFC 700, King Air 300/B300 Series
005-00629-40
Main Instrument Panel Installation, King Air 300/B300
005-00629-41
Pedestal Re-Configuration, King Air 300/B300
005-00629-42
GWX Radar Install, King Air 300/B300
005-00629-43
Antenna Install, King Air 300/B300
005-00629-44
Electrical Equipment Install, Nose Bay, King Air 300/B300
005-00629-45
Roll Servo Install, King Air 300/B300
005-00629-46
Yaw & Pitch Servo Install, King Air 300/B300
005-00629-48
Pitch Trim Servo Install, King Air 300/B300
005-00629-49
Magnetometer Install, King Air 300/B300
005-00629-50
OAT Sensor Install, King Air 300/B300
005-00629-52
Optional Equipment Install, Tail Shelf, King Air 300/B300
005-00629-54
Wire Harness Installation, Nose, King Air 300/B300
005-00629-55
Wire Harness Installation, Cabin, King Air 300/B300
005-00629-56
Wire Harness Installation, Tail, King Air 300/B300
005-00629-57
Control Wheel Modification, King Air 300/B300
005-00629-59
Circuit Breaker Panel Modification, King Air 300/B300
005-00629-61
Lighting Modification, King Air 300/B300
005-W0226-00
Wiring Diagram, G1000/GFC 700, King Air 300/B300
Beechcraft Documents
101-590097-9
Super King Air 300 and 300LW Maintenance Manual
101-590097-15
Super King Air 300 and 300LW Wiring Diagram Manual
101-590097-161
Super King Air 300 Airworthiness Limitations Manual
130-590031-7
Super King Air B300 and B300C Electrical Wiring Diagram Manual
130-590031-11
Super King Air B300 and B300C Maintenance Manual
130-590031-197
Super King Air B300 and B300C Avionics Wiring Diagram Manual (Proline 21)
130-590031-211
Super King Air B300 and B300C Airworthiness Limitations Manual
101-590097-13
98-39006
King Air Series Component Maintenance Manual
King Air Structural Inspection and Repair Manual
Other Documents
85-292-1-1033
9016182
TP-336
Signal Conditioner Installation Manual (Meggitt Sensing Systems)
Mid-Continent Instruments - Installation Manual and Operating Instructions,
4200 Series Attitude Indicator
L-3 Avionics Systems – Emergency Power Supply Installation Manual, PS-835
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 4
Revision 2
The following publications are recommended to be on hand during the performance of
maintenance activities.
Table 1-2, Reference Publications
Part Number
Garmin Document
190-00716-N2
Airplane Flight Manual Supplement, G1000/GFC 700, Textron Aviation King Air
300/300LW King Air
190-00716-N3
Airplane Flight Manual Supplement, G1000/GFC 700, Textron Aviation King Air
B300/B300C King Air
190-02042-00
G1000 Cockpit Reference Guide for the King Air 300 Series
190-00355-04
GDL 69 Series SiriusXM Satellite Radio Activation Instructions
190-00303-10
GRS77/GMU44 Installation Manual
190-00303-72
GSA8X/GSM85(A) Installation Manual
190-00303-83
GSM 86 Servo Gear Box Installation Manual
190-00313-63
GMU 44 Installation Location Magnetic Interference Survey Procedure
190-00313-12
Circular Connector (and Configuration Module) Installation Instructions
190-01091-00
GRS 7800 Installation Manual
190-01277-00
GRA 5500 Installation Manual
190-01639-00
GSU 75 Installation 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 1.6 for details.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 5
Revision 2
1.6
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 913397-8200, 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 NXi System Maintenance Manual
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Revision 2
2. SYSTEM DESCRIPTION
2.1
Equipment Descriptions
2.1.1
GFC 700 Operation
The GFC 700 is a fail-passive digital flight control system composed of multiple G1000 LRUs
and servos. The following functions are provided by the GFC 700 in this installation:
•
Flight Director
•
Autopilot
•
Pitch Trim
•
Yaw Damper
•
Electronic Stability and Protection (optional)
Flight Director:
The Flight Directors operate within the GIA 63Ws and use data from the G1000 system,
including air, attitude and flight data, to calculate commands for display to the pilot and for the
Autopilot. Flight director command bars and mode annunciations are sent to the PFDs through
a high-speed Ethernet connection for display to the pilot and copilot. The flight directors
operate independently of the autopilot and allow the pilot to hand-fly the command bars, if
desired. The GMC 710 allows the pilot to switch the active director between flight director #1
(GIA1) and flight director #2 (GIA2).
Autopilot:
The autopilot operates within one high-speed GSA 80 servo (pitch trim), two GSA 80 servos
(pitch and roll), and one GSA9000 servo (yaw). Flight director data is processed within the
servos and turned into aircraft flight control surface commands. The autopilot cannot operate
unless the flight director is engaged.
Manual Electric Trim:
When the autopilot is not engaged, the pitch trim servo may be used to provide a Manual
Electric Pitch Trim (MEPT) function. This allows the pilot or co-pilot to adjust pitch trim from the
PITCH TRIM switch on the control wheel in lieu of using the elevator trim wheel. Trim speeds
are scheduled to provide easier control over a wide speed or configuration range. The PITCH
TRIM switch is split into two halves. The left half arms MEPT. The right half controls direction.
Both halves must be actuated at the same time to command the pitch trim servo to operate. If
only one half of the PITCH TRIM switch is actuated for more than 3 seconds, a red PTRM
message will appear on the PFDs.
Yaw Damper:
The yaw damper reduces Dutch roll tendencies and coordinates turns. It can operate
independently of the autopilot and may be used during normal hand-flight maneuvers.
Electronic Stability and Protection:
Electronic Stability and Protection (ESP) is an optional function that is intended to assist the
pilot in maintaining the airplane in a safe flight condition within the aircraft flight envelope. This
envelope is defined by pitch, roll, and airspeed. This feature is only active when in flight and the
autopilot is off.
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Underspeed Protection:
Underspeed Protection (USP) is available when the optional ESP system is installed and the
autopilot is on. It is designed to discourage aircraft operation below minimum established
airspeeds. When the aircraft decelerates to stall warning, the autopilot will provide input
causing the aircraft to pitch down and wings to level. The pitch down force will continue until the
aircraft reaches a pitch attitude at which IAS equals the IAS at which stall warning turns off, plus
two knots.
2.1.2
GDU 1050A PFD (2) & GDU 1550 MFD
Two Garmin GDU 1050A displays and one GDU 1550 display are installed in the King Air
instrument panel. The GDU 1050A units, 10.4 inch LCD displays with 1024x768 resolution, are
configured as PFD 1 and PFD 2; the GDU 1550 unit, a 15 inch LCD display with 1400 x1050
resolution, is configured as a MFD. All displays provide control and display of nearly all
functions of the G1000 integrated cockpit system. The PFD displays are located on either side
of the MFD, with the stand-by instruments located between the Pilot’s PFD (PFD 1) and the
MFD. GMA 1347D Audio Panels are located outboard of each PFD. Additionally, a GMC 710
AFCS Controller is located in the upper instrument panel, above the MFD, and a GCU 477 is
installed in the pedestal. The GCU 477 provides the control interface for the MFD.
The GDU 1550 communicates with the GDU 1050A units, GDL 69A /GDL69 SXM datalink,
GWX68 or GWX 70 weather radar, optional GDL59 Wi-Fi datalink and optional GTS 820/850 or
GTS Processor traffic through a high-speed data bus (HSDB) Ethernet connection. The GDU
1550 communicates with the GCU 477 via RS-232 digital interface.
The GDU 1050A units communicate with each other and the GIA 63W units through a highspeed data bus (HSDB) Ethernet connection.
PFD 1 receives primary electrical power from No. 1 Triple Fed Bus and secondary electrical
power from Center Bus. PFD 2 receives electrical power from No. 3 Triple Fed Bus. Electrical
power to the MFD is provided by No. 2 Triple Fed Bus. The displays will power-up immediately
with external or aircraft power or battery operation.
All displays are installed in the King Air panel using ¼-turn fasteners. Three CDU cooling fans
are also installed behind the panel for PFD and MFD cooling.
Figure 2-1, Display Units
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King Air 300 Series
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2.1.3
Flight Stream 510
The Flight Stream™ 510 (FS 510) is a Wi-Fi/Bluetooth capable multi-media card (MMC)
installed the bottom SD slot of the MFD. It sends position, velocity, time, attitude, heading, FISB, TIS-B traffic, Sirius XM audio control, Sirius XM weather data, and flight plan transfer to
mobile devices via Bluetooth. The FS 510 can also interface with a mobile device via Wi-Fi
pairing for the purposes of updating databases used by the GDU(s). Bluetooth and Wi-Fi are
mutually exclusive with only one interface functional at a time. Connecting via Wi-Fi requires a
pilot-configurable Wi-Fi Protected Access WPA2 security password. By updating databases
wirelessly, new databases may be transferred to the G1000 system without taking the data card
out of the aircraft.
Figure 2-2, Flight Stream 510
2.1.4
GMA 1347D Audio Panel (2)
The Garmin GMA 1347D Audio Panel integrates NAV/COM digital audio, intercom system and
marker beacon controls. The 300 Series installation includes two GMA 1347D panels. The
GMA 1347D panels provide control of all cockpit intercom/mic systems as well as
NAV/COM/ILS audio. The units also provide display reversion mode control through a large red
button. Warning and alert audio received by the GMA 1347Ds is processed by and received
from the GIA 63W Integrated Avionics Units (IAUs). Electrical power to GMA 1 is provided from
No. 1 Triple Fed Bus. Electrical power to GMA 2 is provided from No. 3 Triple Fed Bus. GMA 1
and GMA 2 will be powered immediately with external or aircraft power or battery operation.
The GMA 1347D units interface with the existing marker beacon antenna, as well as existing
mic and phone jacks and oxygen mask mic.
Figure 2-3, Audio Panel
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2.1.5
GMC 710 AFCS Control Unit
The dedicated AFCS controls on the GMC 710 allow crew control interface with the various
GFC 700 autopilot / flight director functions. GMC 710 controls are discussed in detail in the
G1000 King Air 300 Series Cockpit Reference Guide. The GMC 710 is powered by the No. 1
Triple Fed Bus.
Figure 2-4, AFCS Controller
2.1.6
GCU 477 FMS Control Unit
The GCU 477 functions as the primary control interface to the GDU 1550 MFD. The GCU 477
provides alphanumeric, softkey, and flight planning function keys used to interface with the
G1000; the MFD does not possess any knobs or controls other than softkeys. The GCU 477 is
powered by the No. 3 Triple Fed bus. The GCU 477 also provides the crew with the added
functionality of tuning their receivers via the GCU as well as the PFD. Detailed instructions
regarding the controls are discussed in the G1000 Cockpit Reference Guide.
Figure 2-5, FMS Controller
2.1.7
Transponder (2)
The Garmin GTX 33( ), GTX 3000, GTX 345R, or GTX 335R transponders communicate with
the on-side GIA 63W through RS-232 digital interface.
This STC installation allows for installation of two GTX 33 transponders, two GTX 33D diversity
transponders, one of each GTX 33/GTX 33D, two GTX 3000, two GTX 335R, one of each GTX
345R/335R, or one of each GTX 345R/33() transponders. Mixing between the GTX 33 and
GTX 3000 transponders is not permissible. The GTX 345R provides ADS-B In capability.
The GTX 345R also communicates with the G1000 Avionics through an HSDB interface
connected to PFD1. When installed, the GTX 345R communicates and controls the GTS
Processor through the HSDB interface for all TAS/TCAS I operations. The GTX 345R mixes
and coordinates the TAS/TCAS I targets with TIS-B targets to provide one coordinated traffic
display to the crew. The GTX 345R does not support TCAS II. It also communicates with and
controls A429 interface non-Garmin TAS/TCAS I traffic units if installed.
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The GTX 345R can also provide PVT and Traffic data via a Bluetooth interface for cabin
entertainment purposes.
For TCAS II operations, the GTX 3000 transponder communicates with the GTS Processor or
Collins TTR-920/4000 traffic units through ARINC 429 digital interfaces (transmit and receive).
Only the GTX 3000 supports TCAS II operations with the GTS Processor. The GTX 3000 or
Collins TDR-94 transponders support TCAS II operations with the Collins TTR-920/4000 traffic
units.
The transponder units are mounted on the upper avionics equipment shelf in the tail section of
the airplane. Power is provided by the No. 1 GTX from Triple Fed Avionics Bus. The No. 2
GTX is powered from Left Gen Avionics Bus. All GTX transponders (non-diversity and
diversity) interface with a transponder antenna mounted to the bottom of the fuselage. Each
GTX diversity transponder (GTX33D and GTX 3000) interfaces to a transponder antenna
mounted to the top of the fuselage.
GTX 3000
GTX 33()
GTX 345R/GTX 335R
Figure 2-6, Transponders
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2.1.8
GIA 63W Integrated Avionics Unit (2)
Two Garmin GIA 63W Integrated Avionics Units (IAUs) contain the VHF COM/NAV receivers,
WAAS GPS receiver, Flight Director, and system integration microprocessors. The GIAs also
serve as a communication interface to all other G1000 LRUs in the system. Each GIA 63W
communicates directly with the on-side GDU 1050A display using a HSDB Ethernet connection.
Both GIAs are located remotely in the nose equipment bay.
GIA 1 receives primary electrical power from No. 1 Triple Fed Bus and a secondary electrical
power supply from Center Bus. GIA 2 receives electrical power from No. 3 Triple Fed Bus. The
GIA 1’s COM power supply (COM 1) is provided by No. 1 Triple Fed Bus. GIA 2’s COM power
supply (COM 2) is provided by No. 3 Triple Fed Bus. Therefore, both GIAs power-up
immediately with external or aircraft power or battery operation.
Both GIA 63Ws interface to the following equipment:
•
•
•
•
•
•
•
•
Existing VOR/LOC/Glideslope Antenna System
Existing VHF COM #1 & #2 Antennas
GA 36 and GA 37 GPS/WAAS Antennas
GMA 1347D, #1 & #2
GEA 71, #1 & #2
GSA 80 and GSA 9000 Servo Motors
GRS 77 or GRS 7800, #1 & #2
and a
or GSU 75 #1 & #2 (ADAHRS)
GDC 7400 #1 & # 2
A429 Interface Traffic Systems (if installed)
The GIA 63W #1 interfaces to the following additional equipment:
•
•
•
•
GTX 33( )#1, GTX 3000 #1, GTX 345R #1, or GTX 335R#1
DME 42 (if installed)
GSR 56 (if installed per stand-alone configuration)
GDU 1050A #1
The GIA 63W #2 interfaces to the following additional equipment:
•
•
•
•
•
GTX 33( )#2, GTX 3000 #2, or GTX 335R#2
ADF (if installed)
Stormscope (if installed)
Radar Altimeter (if installed)
GDU 1050A #2
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Figure 2-7, GIA unit
2.1.9
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 1550 MFD. Engine parameters are normally displayed
on the MFD. In the event of MFD failure, the engine parameters can be displayed on PFD 1
and/or PFD 2 using display reversion. The GEAs are located behind the instrument panel and
is mounted in a vertical orientation. Electrical power to GEA 1 is provided from No. 1 Triple Fed
Bus and to GEA 2 from No. 2 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
Figure 2-8, GEA unit
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Revision 2
2.1.10 GSU 75B ADAHRS (2)
The GSU 75 ADAHRS is a combined Air Data and AHRS system. The units are mounted in the
nose equipment bay, contain advanced tilt sensors, accelerometers, rate sensors, static
pressure sensors, and pitot pressure sensors. The GSU 75B(s) receive GPS data from onside
and offside GIA 63W(s), and magnetic heading from the onside GMU 44 Magnetometer. The
#2 GSU ADAHRS units can provide heading data to an approved third party TCAS II device
through an ARINC 429 digital interface.
GSU 1 receives primary electrical power from the No. 1 Triple Fed Bus and a secondary power
supply from the Center Bus. GSU 2 receives electrical power from the No. 3 Triple Fed Bus.
The GSU(s) provide electrical power to the onside GMU 44 Magnetometer and the onside GTP
59 OAT probe.
GSU 1 and GSU 2 connect to existing pitot/static ports. Refer to Figure 2-28 for a schematic of
the aircraft’s pitot/static system and its connections to the G1000 STC installed equipment.
Each GSU 75B provides the following information via ARINC 429 busses to both the onside and
offside GIA 63W(s) and PFD(s). GSU #1 also provides this information to the MFD.
•
Aircraft altitude and airspeed
•
Aircraft vertical speed, Mach and outside air temperature
•
Aircraft heading, pitch and roll
•
Aircraft yaw, pitch and roll rates
•
Aircraft body-axis accelerations
•
Rates of change of heading, pitch and roll
•
Aircraft accelerations expressed in a local level frame of reference
GSU 75B(s) are installed in lieu of separate ADC (GDC 7400) and AHRS (GRS 77 or GRS
7800). For this STC, mixed ADAHRS and ADC/AHRS configurations are not permitted.
IMPORTANT!
Aircraft modified by this STC are eligible to be approved for RVSM operation.
RVSM critical maintenance instructions contained in this document must be
followed in order to guarantee performance within RVSM specifications.
Figure 2-9, GSU-75B ADAHRS with Connector and Mounting Tray
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Revision 2
2.1.11 Digital Air Data Computer (2) (optional)
The optional Garmin GDC 7400 air data computers may be installed along with AHRS units in
lieu of GSU 75B(s). The GDC(s) compile information from the pitot/static system and outside
air temperature (OAT) sensors to provide digital air data computations to the G1000 system.
The GDC communicates with the GIA 63W, GDU 1050A, and GRS 77/7800 using ARINC 429
digital interface. The unit is mounted behind the instrument panel. GDC 1 also communicates
using ARINC 429 with the GDU 1550 MFD. GDC 1 receives primary electrical power from the
Essential Bus and a secondary power supply from Dual Fed Bus No. 1. GDC 2 receives power
from Dual Fed Bus No. 2. GDC 1 and GDC 2 connect to existing pitot/static ports. Refer to
Figure 2-27 for a schematic of the aircraft’s pitot/static system and its connections to the G1000
STC installed equipment.
IMPORTANT!
Aircraft modified by this STC are eligible to be approved for RVSM operation.
RVSM critical maintenance instructions contained in this document must be
followed in order to guarantee performance within RVSM specifications.
Figure 2-10, GDC 7400 Air Data Computer
2.1.12 OAT Probe (2)
The Garmin GTP 59 OAT Probes provide the GSU 75B or optional GDC 7400 with outside air
temperature data. The OAT probes are mounted to the bottom of the fuselage at F.S. 113.5.
Figure 2-11, OAT probe
G1000 NXi System Maintenance Manual
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Revision 2
2.1.13 Attitude & Heading Reference System (2) (optional)
The optional Garmin GRS 77 AHRS or GRS 7800 AHRS units may be installed along with ADC
units in lieu of GSU 75B(s). They provide attitude and heading information to the G1000
system. The units, mounted in the nose equipment bay, contain advanced tilt sensors,
accelerometers, and rate sensors. The unit interfaces with the Garmin Air Data Computers and
GMU44 Magnetometer and utilizes GPS signals from the GIA 63Ws. Actual attitude and
heading information is sent using ARINC 429 digital interface to both GDU 1050As and GIA
63Ws. The GRS interfaces with and provides power to the GMU 44 Magnetometer. The GRS
supplies attitude and heading information directly to the PFDs, MFD, and GIAs. The #2 GRS
AHRS units can provide heading data to an approved third party TCAS II device through an
ARINC 429 digital interface.
Additionally, the GRS 7800 AHRS provides heading with or without the aiding of the Garmin
GMU 44 magnetometer. When operating without the aid of the magnetometer, the GRS 7800 is
functionally similar to that of a Directional Gyro.
GRS 1 receives primary electrical power from No. 1 Triple Fed Bus and a secondary power
supply from the Center Bus. GRS 2 receives electrical power from No. 3 Triple Fed Bus.
GRS 77
GRS 7800
Figure 2-12, AHRS
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
2.1.14 GMU 44 Magnetometer (2)
The GMU 44 provides horizontal and vertical magnetic field information to the GSU or GRS.
This allows heading to be calculated and provides assistance during ADAHRS/AHRS alignment.
The GMU 44 units are mounted in the tailcone or in the horizontal stabilizer. The 011-00870-20
GMU 44 units may only be installed in the horizontal stabilizer. The GMU 44 units were
modified to account for low clearance installations and have a 90-degree pig-tail harness versus
the straight harness on the 011-08870-10 GMU 44 units. The units receive power directly from
the GSU/GRS units and communicate with the GSU/GRS units via an RS-485 digital interface.
GMU 44 -00 & -10 Unit
GMU 44 -20 Unit
Figure 2-13, Magnetometer
2.1.15 GDL 69A/69A SXM Datalink
The GDL 69A/69A SXM provides the interface to the GWX 68 or GWX 70 weather radar and
optional GDL59 Wi-Fi datalink by acting as a communications hub between the MFD and GWX
68/GWX 70 and GDL 59 via HSDB. The 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/69SXM is
received from Right Gen Avionics 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.
Optional remote control (GRC 10) and remote control transceiver (GRT 10) may be interfaced
with the GDL 69A/69A SXM. Installation of the GRC 10 and GRT 10 is in accordance with
Garmin STC SA01487SE or other approved data. Refer to the approved Instructions for
Continued Airworthiness information for these units. It is recommended that GRT 10 be
powered from the Entertainment Bus.
Figure 2-14, GDL 69A/69A SXM Datalink
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
2.1.16 GDL 59 Wi-Fi Datalink (optional)
The GDL 59 provides a POTS (plain old telephone service) phone interface and a high speed
data link between the aircraft systems and ground computers while the aircraft is on the ground
using the IEEE 802.11g (“Wi-Fi”) protocol. The GDL 59 also provides the interface to an
optional GSR 56 satellite datalink, which adds airborne low speed data link and voice
communication capability. The GDL 59 unit interfaces to the Garmin Integrated Flight Deck via
the GDL 69A or PFD 2 using HSDB. The GDL 59 is located in the aft cabin floor area, just
forward of the cabin door or on the upper avionics equipment shelf in the tail section. The GDL
59 is powered from the Right Gen Avionics bus.
Figure 2-15, GDL 59 Wi-Fi Datalink
2.1.17 GSR 56 Satellite Receiver (optional)
The GSR 56 provides airborne low speed data link and voice communication capability to
Garmin Integrated Flight Deck installations. The GSR 56 contains a transceiver that operates
on the Iridium Satellite network. The GSR 56 interfaces directly to the GDL 59 via an RS-232
interface or may be installed as a stand-alone unit with an interface to GIA 1. The GSR 56 is
located in the aft cabin floor area, just forward of the cabin door or on the upper avionics
equipment shelf in the tail section. The GSR 56 is powered from the Avionics No. 2 bus. With
relocation to the tail section, the GSR 56 has an internal heater powered from the Right Gen
Avionics Bus.
Figure 2-16, GSR 56 Satellite Receiver
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
2.1.18 GSD 41 Data Concentrator (optional)
The GSD 41 interfaces to various airframe discrete outputs to support third party systems such
as Flight Data Recorders. The GSD 41 is located on the avionics shelf in the tail area. The GSD
41 is powered from No. 2 Triple Fed Bus.
Figure 2-17, GSD 41 Data Concentrator
2.1.19 GTS 820/850 Traffic System (optional)
The GTS 820/850 is a traffic surveillance system that uses active interrogation of Mode S and
Mode C transponders to provide traffic advisories to the pilot. The GTS 820 is a TAS unit; the
GTS 850 is a TCAS I unit. The installation includes a top directional antenna (GA 58) paired
with a GPA 65 power amplifier / low noise amplifier (PA/LNA) unit and a bottom, unamplified
GA 58 antenna. The GTS 820/850 is located in the nose avionics bay on the top, left shelf. The
GPA 65 is located in the left sidewall area, just in front of the most forward cabin window. The
GTS 820/850 traffic system is powered from the Right Gen Avionics bus.
Figure 2-18, GTS 820/850 Traffic System
2.1.20 GTS Traffic Processor (optional)
The GTS Traffic Processor is a microprocessor-based Line Replaceable Unit that uses active
interrogations of Mode S and Mode A/C transponders to provide Traffic Advisories and
Resolution Advisories (GTS 8000 only) to the pilot. When installed, the GTS Processor can be
configured as TAS (GTS 825), TCAS I (GTS 855), or TCAS II (GTS 8000). The GTS traffic
processor is installed in the nose avionics bay. The GTS interfaces to the GA 58 traffic
antennas which are mounted on the upper and lower fuselage. The GTS traffic processor also
interfaces with the GTX 3000 (when installed) through ARINC 429 digital data lines. When a
GTX 345R is installed, The GTX communicates with the GTS processor via the G1000 HSBD
bus. The GTS traffic processor is powered from the Right Gen Avionics Bus.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
Figure 2-19, GTS Traffic Processor
2.1.21 Weather Radar
The GWX 68 or optional GWX 70 Airborne Weather Radar provides weather radar data output
to the GDU 1550 MFD and to the GDU 1050A PFD(s). The GWX is mounted forward of the
forward bulkhead at F.S. 30. Power to the GWX is received from the Left Gen Avionics bus. In
most installations, data received from the GWX is routed by HSDB through the GDL 69A data
link unit to the MFD (if a GDL 69 unit is installed) or otherwise wired direct to the MFD via highspeed data bus (Ethernet).
Figure 2-20, Weather Radar
2.1.22 GSA 80 Servos and GSM 86 Servo Gearboxes (3)
The Garmin GFC 700 AFCS uses GSA 80 high torque servos to automatically control aircraft
pitch, pitch trim, and roll. The pitch trim variant of the GSA 80 is a high speed servo actuator.
The GSA 80 contains a motor-control and monitor circuit board, as well as a solenoid and a
brushless DC motor. The GSA 80 servo receives serial RS-485 data packets from the GIA
63Ws. The roll servo is located in the forward cabin lower fuselage at F.S. 185. The pitch, yaw,
and pitch trim servos are located in the tail. The roll servo is located in the forward cabin lower
fuselage near the wing front spar. The pitch and pitch trim servos are located in the tail. Power
to the servos is received from No. 2 Triple Fed Bus. All servos mount to Garmin GSM 86 Servo
Gearboxes. The GSM 86 is responsible for transferring the output torque of the GSA 80 servo
actuators to the mechanical flight control surface linkage. The GSM 86 has a clutch cartridge
that cannot be adjusted to a different torque value.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
Figure 2-21, Servo
2.1.23 GSA 9000 Servo and GSM 9100 Servo Gearbox
The Garmin GFC 700 AFCS uses a GSA 9000 servo to control aircraft yaw damper/turn
coordination and rudder boost. The GSA 9000 contains a motor-control and monitor circuit
board, as well as a solenoid and a brushless DC motor. The GSA 9000 servo receives serial
RS-485 data packets from the GIA 63Ws. The GSA 9000 yaw servo is located in the tail. Power
to the servo is received from No. 2 Triple Fed Bus. The servo mounts to a Garmin GSM 9100
Servo Gearbox. The GSM 9100 is responsible for transferring the output torque of the GSA
9000 servo actuator to the mechanical flight control surface linkage.
Figure 2-22, GSA 9000 / GSM 9100
2.1.24 GRA 5500 Radar Altimeter
The GRA 5500 Garmin Radar Altimeter is designed to calculate the height Above Ground Level
(AGL) of the aircraft which is displayed on the PFDs. For King Air installations, the GRA 5500 is
configured to output the value height Above Ground Level to the pilot through the GDU. The
GRA interfaces to the existing radar altimeter antennas and GIA #2 via the ARINC 429 or RS422 digital bus. The GRA 5500 is located below the lower avionics equipment shelf in the tail
section. The GRA 5500 is powered from the Right Gen Avionics Bus.
Figure 2-23, GRA 5500 Radar Altimeter
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King Air 300 Series
190-00716-N1
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Revision 2
2.1.25 Garmin G36 and 37 GPS/WAAS Antennas
This installation uses one G36 GPS/WAAS antenna and a G37 GPS/WAAS/XM antenna. The
antennas are located in the upper, forward cabin.
2.1.26 Signal Conditioner (2)
Each GEA 71 receives signals from its on-side engine turbine speed sensor, propeller speed
sensor and fuel flow sensors via a Meggitt Signal Conditioner, p/n 85-292-4. 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.
2.1.27 Standby Indicators
This STC has two options for standby primary flight indications. The first option is a MidContinent Instruments MD 302 Standby Attitude Module that provides attitude, airspeed, and
altitude indications in one electronic assembly. The second option consists of three separate
mechanical indicators, one each for airspeed, altitude, and attitude.
2.1.27.1 Mid-Continent Instruments MD 302 Standby Attitude Module (SAM)
Mid-Continent Instruments, part number 6420302-2, is an electronic 3-in-1 standby indicator
assembly instrument with two 2.4” diagonal LCD displays provides standby altitude, airspeed,
and attitude information to the cockpit. It is powered from Standby Instrument Bus and the
emergency standby battery. Lighting Control is connected to the No.1 Dual Fed Bus. It
receives static and pitot pressures from the right-hand pitot/static system. The MD 302 is a
standalone unit and does not interface to any G1000 avionics. The MD302 is installed on the
main instrument panel, between the pilot’s PFD and the MFD.
Figure 2-24, MD 302 Standby Attitude Module
G1000 NXi System Maintenance Manual
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190-00716-N1
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Revision 2
2.1.27.2 Mechanical (Analog) Standby Indicators
2.1.27.2.1
Standby Airspeed Indicator
An optional Standby Airspeed indicator (part numbers listed on General Arrangement drawing)
is installed between PFD 1 and the MFD. The standby airspeed indicator does not require
electrical power for normal operation except for internal instrument lighting, which is powered
from No. 3 Triple Fed Bus and the emergency standby battery. This unit is connected to the
right-side pitot/static system.
2.1.27.2.2
Standby Altimeter
An optional standby altimeter (part numbers listed on General Arrangement drawing) is installed
between PFD 1 and the MFD. This unit incorporates a vibrator to ensure accurate display
altitude information. The vibrator is powered by No. 3 Triple Fed Bus and the emergency
standby battery. Internal lighting of this unit is powered from Left Gen Bus and the emergency
standby battery. This unit is connected to the right-side static system.
2.1.27.2.3
Standby Attitude Indicator
The optional Mid-Continent Electric Attitude Indicator (part number listed on General
Arrangement drawing) is used as the standby attitude indicator. It is powered by No. 3 Triple
Fed Bus and the emergency standby battery. Gyro power and internal lighting of this unit is
powered from Left Gen Bus and the emergency standby battery.
2.1.28 L-3 PS-835 (C or D Model) Emergency Standby Battery
In the event of loss of all normal electrical power, the battery is designed to provide 24 Vdc
(nominal) emergency power source for the following items:
•
standby attitude indicator (operation and internal lighting)
•
standby altimeter (vibrator and internal lighting)
•
standby airspeed indicator (lighting only)
•
pilot side glareshield lighting
•
magnetic compass
The aircraft power buss provides a trickle charge to the PS-835 under normal conditions. This
battery is installed in the nose avionics bay. It is controlled using the standby battery switch
indicator on the instrument panel.
2.2
G1000 Optional Interfaces
Optional equipment interfaces include lightning detection, traffic systems, radar altimeter, ADF
systems and DME systems. The G1000 also provides a general purpose ARINC bus for use
with third party entertainment and cabin equipment. Refer to wiring diagram listed in Table 1-1,
for specific interface information.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
2.3
Electrical Power Distribution
This airplane uses a multi-bus system, as detailed below and in Figure 2-25. This Figure shows
the system post installation of this STC. Although this STC made several bussing changes to
the distribution system, the core electrical generation and distribution system remains
unchanged from the basic airplane design. Figure 2-26 shows the power sources for all
equipment used by this STC. Each bus used or modified by this installation is described below.
Left and Right Generator Buses: The left and right generator buses receive power from their
respective left and right generators. The left and right generator buses also support Center
Buses and Left Gen and Right Gen Avionics Buses, respectively.
Triple Fed Bus: The Triple Fed bus is powered by left and right generator buses and the battery
bus.
Avionics Buses: The Left Gen Avionics bus is powered from the Left Generator Bus via the
Avionics No. 1 relay. The Right Gen Avionics Bus is powered from the Right Generator Bus via
the Avionics No. 2 relay. The Triple Fed Avionics Bus is powered from the Triple Fed bus via
the Avionics No. 3 relay. All avionics relays are controlled using the Avionics Master Switch.
Left and Right Engine Instrument Buses: On serial numbers FL-120, FL-122 through FL-380,
FL-382, FM-009 through FM-11, the electrical system includes the L ENG INSTR and R ENG
INSTR buses. On all other serial numbers, these two buses are not installed and engine
instruments are powered directly from the Triple Fed Buses.
Emergency Standby Battery: The Standby Emergency Battery (STBY BATT) system in the
King Air 300/B300 is designed to provide uninterrupted DC power to the Standby Attitude
indicator (including gyro motor and internal instrument lighting), the Standby Altimeter (including
vibrator and internal instrument lighting), standby airspeed indicator internal instrument lighting
and internal instrument lighting for the magnetic compass from the L-3 PS-835(C or D Model)
Emergency Standby Battery. This standby battery power is independent from the normal
electrical system and provides redundant power for the standby instruments in the event that all
other electrical power is lost.
G1000 NXi System Maintenance Manual
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190-00716-N1
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Revision 2
Figure 2-25, 300 Series Electrical Distribution (Post G1000 STC)
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 25
Revision 2
Figure 2-26, G1000 Component Power Sources
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
2.4
Electrical Load Utilization
The following chart lists the electrical equipment and their associated loads for each of the
standard and optional items installed on the King Air 300 series airplanes with the installation of
G1000. The loads specified are used to verify the electrical buses, generating system and
batteries are operated within their limits and capacity. For electrical load test procedure and
electrical load test report, refer to Garmin documents 190-00716-N0 (Post Installation Checkout
Procedure King Air 300 Series) and 005-00629-22 (Electrical Load Test Report G1000
integrated Avionics System Hawker/Beechcraft Model 300/B300 King Air) respectively.
Table 2-1, Electrical Loads
Equipment
Units
Used
Each
Unit
(Amps
DC)
Part Number
Notes
Battery Bus
Left Generator Bus
Avionics Left Generator Bus
GIA 63W – COM #2
1
4.3 A
Max
011-01105-20
See Note
GTX 33 Transponder #2
0.3 A – Not
Transmitting
4.3 A – Transmitting
1.6 A
011-00779-30
1.6 A
011-00779-21
1.6 A
011-01997-00
GTX 335R #2
0.29 A
011-03301-00
GWX 68 Weather Radar
2.0 A
011-00883-20
2.5 A
011-01768-00
or
GTX 33D Transponder #2
or
1
GTX 3000 Transponder #2
or
or
1
GWX 70 Weather Radar
Right Generator Bus
Avionics Right Generator Fed Avionics Bus
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
Equipment
Units
Used
Each
Unit
(Amps
DC)
GDL 69A XM Data Link
or
Notes
011-00987-00
1
0.35 A
011-03177-10
GDL 69A SXM Data Link
GDL 59 Wi-Fi
Part Number
1
GTS Processor
0.572 A
011-01746-00
2.5 A
011-02571-00
1.6 A
011-01446-00
1.6 A
011-01553-00
or
GTS 820 Traffic Processor
1
or
GTS 850 Traffic Processor
GRA 5500 Radio Altimeter
1
0.5A
011-02537-00
GSR 56 Iridium/Iridium
Heater
1
1.86A
011-02268-00
or 011-0226801
Center Bus
GDU 1050A PFD #1
1
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
0.9 A
Max
See
Notes
Secondary power input
011-03470-10
0.7 A above -15°C
0.9 A below -15°C
Page 28
Revision 2
Equipment
Units
Used
Each
Unit
(Amps
DC)
Part Number
Notes
GRS 77:
0.3 A
See Note
GMU 44:
011-00870-10
011-00870-20
GRS 77/GMU 44 – AHRS
#1
GRS 7800:
or
GRS 7800/GMU 44 –
AHRS #1
011-00868-10
1
0.45 A
See Note
or
011-02278-00
Secondary power input
GMU 44:
Secondary power input
011-00870-10
Secondary power input
011-00870-20
GSU 75B/GMU 44
ADAHRS #1
GSU 75B:
0.38 A
See Note
011-03094-40
GMU 44:
011-00870-10
011-00870-20
GDC 7400 - ADC #1
1
GIA 63W – NAV #1
1
0.230 A
011-02337-00
See Note
011-02337-01
1.0 A
See Note
011-01105-20
Secondary power input
Secondary power input
No. 1 Triple-Fed Bus
PFD #1 - Cooling Fan
GIA 63W #1 - Cooling Fan
1
1
0.1 A
0.4 A
305468-00
(Sandia P/N)
or
013- 0010200 (Garmin
P/N)
305467-00
(Sandia P/N)
or
013-00103-00
Garmin P/N)
G1000 NXi System Maintenance Manual
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190-00716-N1
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Revision 2
Equipment
GIA 63W – NAV #1
GIA 63W – COM #1
GMC 710 – AFCS
Controller
Units
Used
1
1
1
Each
Unit
(Amps
DC)
1.0 A
4.3 A
Max
See
Notes
0.16 A
Part Number
011-01105-20
Notes
Primary power input
Primary power input
011-01105-20
0.3 A – Not
Transmitting
4.3 A – Transmitting
011-01020-10
GRS 77:
0.3 A
See Note
GMU 44:
011-00870-10
011-00870-20
GRS 77/GMU44 –AHRS
#1
GRS 7800:
or
GRS7800/GMU44 – AHRS
#1
011-00868-10
11
0.45 A
See Note
or
011-02278-00
GMU 44:
Primary power input
011-00870-10
011-00870-20
GSU 75B/GMU44
ADAHRS #1
GSU 75B:
0.38 A
See Note
011-03094-40
GMU 44:
011-00870-10
011-00870-20
GDC 7400 #1
GDU 1050A – PFD #1
GMA 1347D #1 – Audio
Panel
1
1
1
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
0.230 A
0.9 A
Max
See
Notes
1.75 A
011-02337-00
011-02337-01
Primary power input
Primary power input
011-03470-10
0.7 A above -15°C
0.9 A below -15°C
011-01257-20
Primary power input
Page 30
Revision 2
Equipment
Units
Used
Each
Unit
(Amps
DC)
Part Number
Meggitt Sig Cond #1
1
0.032 A
85-292-4
GEA 71 #1
1
0.5A
011-00831-00
GSA 80 – Roll Servo
1
1.61 A
011-00877-20
GSA 80 – Pitch Servo
1
1.61 A
011-00877-20
GSA 9000 – Yaw Servo
1
1.80 A
GSA 80 – Pitch Trim Servo
1
1.61 A
011-00877-21
1
0.1 A
305468-00
(Sandia P/N)
or 013-0010200 (Garmin
P/N)
1
1.2 A
Max
Notes
No. 2 Triple-Fed Bus
MFD Cooling Fan
GDU 1550 – MFD
011-02213-00
011-02213-10
011-03472-00
See Note
GSD 41
1
0.5 A
011-01457-00
GEA 71 #2
1
0.5A
011-00831-00
0.9 A – Temp above 15°C
1.2 A – Temp below 15°C
No.3 Triple Fed Bus
GDU 1050A – PFD #2
1
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
0.9 A
Max
See
Notes
011-03470-10
0.7 A above -15°C
0.9 A below -15°C
Page 31
Revision 2
Equipment
Units
Used
Each
Unit
(Amps
DC)
Part Number
Notes
GRS 77:
011-00868-10
0.3 A
Total
GMU 44:
011-00870-10
011-00870-20
GRS 77/GMU 44 – AHRS
#2
GRS 7800:
or
GRS 7800/GMU 44 –
AHRS #2
011-02278-00
1
0.45 A
Total
GMU 44:
011-00870-10
or
011-00870-20
GSU 75B/GMU 44
ADAHRS #2
GSU 75B:
011-03094-40
0.38 A
GMU 44:
011-00870-10
011-00870-20
011-02337-00
GDC 7400 – ADC #2
1
0.230 A
GIA 63W – NAV #2
1
1.0 A
011-01105-20
GMA 1347D #2 – Audio
Panel
1
1.75 A
011-01257-20
GCU 477 – FMS CTL
1
0.085 A
011-01428-00
011-02337-01
501-1228-03
Standby Battery
PFD #2 – Cooling Fan
1
1
See Note
0.1 A
or
2.5 A for model PS835C
501-1228-04
5 A for model PS-835D
305468-00
(Sandia P/N)
or
013-00102-00
(Garmin P/N)
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190-00716-N1
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Revision 2
Equipment
GIA #2 – Cooling Fan
Units
Used
1
Each
Unit
(Amps
DC)
0.4 A
Part Number
Notes
305467-00
(Sandia P/N)
or
013-00103-00
(Garmin P/N)
Meggitt Sig Cond #2
1
0.032 A
85-292-4
1.6 A
011-00779-30
1.6 A
011-00779-21
1.6 A
011-01997-00
0.29 A
011-03301-00
0.36 A
011-03303-00
Avionics Bus Triple-Fed
GTX 33 Transponder #1
or
GTX 33D Transponder #1
or
GTX 3000 Transponder #1
1
or
GTX 335R #1
or
GTX 345R #1
Standby Battery Bus
MD 302 Standby Indicator
1
0.22 A
6420302-2
Standby Attitude Indicator
1
0.25 A
4200-11
(MOD 2)
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
0.9 A max when
charging and heating
battery.
Page 33
Revision 2
Equipment
Units
Used
Each
Unit
(Amps
DC)
See Note
Standby Altimeter
1
0.157 A
total
Standby Airspeed Indicator
3A43.22.35F.
28.1.FU
(Thommen
P/N), or
Notes
Vibrator 0.030 A
Lighting 0.096 A
16650-1172
Aerosonic
P/N)
0.050 A
MD25-300
(MidContinent Inst
P/N), or
0.050 A
25030-0184
(Aerosonic
Corp P/N)
1
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Part Number
Page 34
Revision 2
G1000 NXi System Maintenance Manual
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190-00716-N1
L/H PITOT
MAST
R/H PITOT
MAST
FORWARD PRESSURE
BULKHEAD
#1 AIR DATA
COMPUTER
#2 AIR DATA
COMPUTER
DATA BUS
OAT
PROBE
Standby
Airspeed
OAT
PROBE
PILOT PFD
MFD
COPILOT PFD
Standby
Altimeter
DRAIN
DRAIN
DRAIN
ALTERNATE STATIC
PORT
BOTTOM
TOP
BOTTOM
TOP
AFT PRESSURE
BULKHEAD
ALTERNATE STATIC
SELECTOR VALVE
Electronic Standby
Indicator
With MD 302
Installed
L/H STATIC
PORTS
R/H STATIC
PORTS
2.5
Pitot/Static System
The following schematics shows the pitot-static system as modified by this installation:
Figure 2-27, Pitot/Static System with ADC(s) and AHRS(s) Installed
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Figure 2-28, Pitot/Static System with GDU 75B ADAHRS(s) Installed
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L/H PITOT
MAST
R/H PITOT
MAST
#1 ADAHRS
OAT
PROBE
DATA BUS
FORWARD PRESSURE
BULKHEAD
#2 ADAHRS
Standby
Airspeed
OAT
PROBE
PILOT PFD
MFD
COPILOT PFD
Standby
Altimeter
DRAIN
DRAIN
DRAIN
ALTERNATE STATIC
PORT
BOTTOM
TOP
BOTTOM
TOP
AFT PRESSURE
BULKHEAD
ALTERNATE STATIC
SELECTOR VALVE
Electronic Standby
Indicator
With MD 302
Installed
L/H STATIC
PORTS
R/H STATIC
PORTS
2.6
Shield Block Grounds
The connectors on Garmin G1000 LRUs utilize the Shield Block grounding system to provide
necessary ground reference to wire shielding and/or transducers. The shield block termination
method allows multiple grounds to be terminated directly to a block mounted to the connector
backshell assembly. Shielding and grounding requirements for all other LRUs and connectors
are shown in the respective install drawings.
2.7
G1000NXi /GFC700 Block Diagrams
High-Speed Data Bus GTX 345R Transponder
High-Speed Data Bus
No. 2 GIA 63W
Integrated Avionics Unit
No. 1 GIA 63W
Integrated Avionics Unit
GDL 69A
XM Satellite Datalink
(WX & Radio)
OAT
Airspeed
Altitude
Vertical Speed
Attitude
Rate of Turn
Slip/Skid
OAT
Airspeed
Altitude
Vertical Speed
Attitude
Rate of Turn
Slip/Skid
GDL 59
Wi-Fi Data Link
Weather Radar
GMU 44
Magnetometer
GTS Traffic System
Heading
GTX 345R/335R/
33/33D/3000
Transponder #1
#1 GEA 71
Engine/Airframe
Unit
GSA 80
Pitch Servo
Autopilot Calculations
GSA 80
Roll Servo
Autopilot Calculations
GSR 56
Satellite Receiver
GSA 80
Yaw Servo
Autopilot Calculations
GSA 80
Trim Servo
Autopilot Calculations
GMU 44
Magnetometer
Heading
#2 GEA 71
Engine/Airframe
Unit
GTX 335R/
33/33D/3000
Transponder #2
Figure 2-29, G1000NXi/GFC 700 Block Diagram with GSU 75B ADAHRS
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Figure 2-30, G1000NXi/GFC 700 Block Diagram with Separate ADC and AHRS
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2.8
GDU 1050A and GDU 1550 Displays
Figure 2-31 and Figure 2-32 provide identification of the GDU 1050A PFD and GDU 1550 MFD
controls.
Figure 2-31, GDU 1050A Control Interface
Figure 2-32, GDU 1550 Control Interface
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2.9
Softkeys
Some pages have commands or selections that are activated by the GDU 1050A and
GDU 1550 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 (green bar) shows the current active selection.
Figure 2-33, G1000 Softkeys
2.10
FMS Knob
The FMS knob is the primary control for the G1000 system.
To cycle through different configuration screens:
To change page groups: Rotate the large FMS knob.
To change pages in a group: Rotate the small FMS knob.
To activate the cursor for a page, press the small FMS knob directly in, as one would push a
regular button.
To cycle the cursor through different data fields, rotate the large FMS knob.
To change the contents of a highlighted data field, rotate the small FMS knob. This action
either brings up an options menu for the particular field, or in some cases allows the operator to
enter data for the field.
To confirm a selection, press the ENT key.
To cancel a selection, press the small FMS knob in again, deactivating the cursor. The CLR
key may also be used to cancel a selection or deactivate the cursor.
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2.11
GCU 477 - MFD Controller
The MFD controls are located on the GCU 477 as shown in the following figure:
Range / pan
knob
Flight
planning keys
FMS Ctrl
knob
Comm / Nav /
Tranponder
keys
Alpha entry
keys
Numeric
Entry keys
Figure 2-34, MFD Controls (GCU 477 shown)
2.12
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 2-35, AFCS Controls (GMC 710 shown)
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2.13
GMA 1347D Audio Panel
The following Figure shows the audio panel controls.
Transmitters
Passenger Address
Music
Marker Beacon Mute
Transceiver Audio
Telephone
Speaker
Marker Beacon Signal
Sensitivity
Transceiver Audio
Aircraft Navigation
Radio Audio
Manual Squelch
Intercom System (ICS)
ICS VOL SQ (Small Knob)
Digital Recording Playback
Cabin Intercom
Master VOL (Large Knob)
Reversionary Mode
Figure 2-36, GMA 1347D Controls
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2.14
G1000 Normal Mode
To start the G1000 system in Normal Mode:
1. With a ground power unit connected to the external power receptacle, turn ON the BAT
(battery) and EXT PWR switches. The following G1000 equipment is powered on:
•
PFD displays & MFD display
•
GSU 75 ADAHRS or GRS 77/GRS 7800 AHRS Units
•
GDC 7400 Air Data Computers (if installed)
•
GIA #1 and GIA #2 (COM listed separately)
•
GEA 71 Engine/Airframe Units
•
GCU 477 FMS Control Unit
•
GMC 710 Autopilot Control Unit
•
GMA 1347D Digital Audio Panel Units
•
GSA Servos
•
GSD 41 Data Concentrator (Optional)
2. Turn ON the AVIONICS MASTER switch. The following G1000 equipment is powered
on:
•
GTX Mode S Transponders
•
GDL 69A Datalink Unit
•
GWX 68 or GWX 70 Weather Radar Unit
•
GTS 820/850 or GTS Processor Traffic System
•
GDL 59 / GSR 56 Wi-Fi/Satellite (Optional)
•
GRA 5500 Radar Altimeter (Optional)
The G1000 system is now powered in the normal mode. In the normal operating mode, data
fields that are invalid have large red X’s through them. A valid field does not display a red X.
Allow the displays to initialize for approximately one minute for the red X’s to be removed.
The GDC 7400 air data computers may require a longer initialization period than other G1000
units. This longer initialization period may cause the airspeed, altitude, vertical speed, and OAT
fields to be invalid during PFD power-up which is normal until the GDC 7400 units are
initialized.
The PFDs and MFD will function as specified in the G1000 Cockpit Reference Guide when the
system has been correctly installed and configured.
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Figure 2-37, Normal Mode
2.15
Reversionary Mode
Reversionary mode allows for display of information related to safe flight in the event of a
display communication or hardware failure. The pilot’s PFD automatically goes into
reversionary mode when communication to the MFD is lost. Manual reversionary mode allows
the operator to force the pilot or copilot’s PFD into reversionary mode by pressing the large red
button labeled ‘DISPLAY BACKUP’ on the respective GMA 1347D audio panel.
NOTE
When the ‘DISPLAY BACKUP’ button is pushed to exit reversionary mode, there
is a 5-second delay until the display returns to normal mode. If the ‘DISPLAY
BACKUP’ button is pushed again during this 5-second delay, the display will reset
the five second delay timer.
Figure 2-38, Automatic Reversion with MFD failure
Figure 2-39, Manual Reversion with pilot PFD failure
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3. Software and Configuration
3.1
Configuration Mode Overview
Throughout this document, references are made to the PFD1, PFD2 and/or MFD being in
configuration mode. The configuration mode exists to provide the avionics technician with a
means of configuring, checking, and calibrating various G1000 sub-systems. Troubleshooting
and diagnostics information can also be viewed in this mode.
To start the G1000 system in configuration mode, follow these steps:
1. Apply power to the G1000 system by applying aircraft EXT power, selecting the AVIONICS
MASTER PWR and BATT switches to ON.
2. Pull the MFD, PFD1 (PRI), PFD1 (SEC) and PFD2 circuit breakers.
3. Press and hold the ENT key on PFD2 (co-pilot) while applying power using the PFD2
circuit breaker.
4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD2.
5. Press and hold the far right softkey on the MFD while applying power using the MFD
circuit breaker. (Note that the ENT key on the GCU 477 MFD controller may be used
after initial software loads.)
6. Release the softkey after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the
MFD.
7. Press and hold the ENT key on PFD1 (pilot) while applying power using the PFD1 (PRI)
circuit breaker.
8. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD1.
CAUTION:
The Configuration Mode contains certain pages and settings that are critical to
aircraft operation and safety. These pages are protected and cannot be modified,
unless the technician is properly authorized and equipped. However, most
protected pages are viewable to allow system awareness for troubleshooting.
NOTES
If the specific procedure requires an SD card to be in the top slot of the PFD/MFD,
this card must be inserted prior to applying power to the PFD/MFD. Any time a
card is inserted, the power to the PFD/MFD must be cycled.
For a complete description and breakdown of each Configuration Mode page, refer
to the G1000 System Maintenance Manual listed in Table 1-2.
3.1.1
SET>ACTV Configuration
Throughout the configuration mode pages, there are SET and ACTIVE columns for input/output
settings and other parameters.
SET:
Refers to a setting or group of settings that reside in PFD Internal Memory and/or the
Master Configuration Module.
ACTIVE: Refers to an ‘active’ setting or parameter currently being used by the LRU. LRUs
store the ‘active’ settings within internal memory.
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Data can be manually copied from one column to the other (and consequently from PFD
memory to the LRU memory and vice-versa) by using the following two softkeys, when
available:

SET>ACTV (read ‘Set to Active’) softkey: Allows the installer to send the information in
the SET column (data stored in the master config module) to the ACTV column (data
used by LRU).

ACTV>SET (read ‘Active to Set’) softkey: Causes the LRUs current settings to be copied
to the master configuration module as SET items.
CAUTION:
The ACTV>SET softkey must be used with caution! If an improperly
configured unit is installed, this softkey causes the wrong configuration to
replace the correct aircraft configuration.
In the first example shown in Figure 3-1 the SET columns do not match the ACTIVE
columns. The inequality between SET and ACTIVE indicates a configuration mismatch.
By pressing the SET>ACTV softkey, this copies the SET column to the LRU unit’s
configuration memory. The settings then become the ACTIVE settings for the LRU being
configured.
Figure 3-1, SET>ACTV Diagram
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When troubleshooting the system, technicians can look for inequalities between SET and
ACTIVE columns. Certain problems can be resolved simply by pressing the SET>ACTV
softkey, which reloads settings to the specific LRU from the PFD. (Note that this can also be
accomplished by reloading the configuration files for the LRU. Section 7 describes this process
for each LRU).
A blank active column, as shown in Figure 3-2, represents loss of communication between the
display and the particular unit. See Section 5 for more details on troubleshooting.
Figure 3-2, Loss of Communication
3.1.2
Configuration Prompts
When configuration settings are changed, the technician receives on-screen prompts and/or
confirmations such as those shown in Figure 3-3.
Figure 3-3, Configuration Status
3.1.3
Data Transmission Indicators
Several configuration screens utilize an indicator light system to show discrete (ON/OFF) data
and/or hardware component status. Unless otherwise noted, the following applies to all such
status indicators:
•
Green Checkmark: Expected data is successfully received and is ON. A green check
could also indicate that the parameter/component is working correctly.
•
Red X: Expected data is not received. A red X could also indicate that a
parameter/component is invalid.
•
White N/A: Expected data is OFF, or no data is expected.
Figure 3-4, Data Transmission Indicators
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3.1.4
Configuration Mode Navigation
Using the FMS knob as described in Section 2.10, a user can navigate through different pages
and page groups in the Configuration Mode. For complete description and breakdown of each
page, refer to the G1000 System Maintenance Manual listed in Table 1-2.
System Page Group
1. System Status
7. Transaction Log
13. System Data Path
Configuration
2. Time Configuration
8. Aircraft Configuration
14. System Setup
3. Lighting Configuration
9. File Manager
15. Manifest Configuration
4. System Audio
10. Diagnostics Terminal
16. Maintenance Log
5. System Upload
11. OEM Diagnostics
17. Configuration Manager
6. LRU Replacement
12. System Configuration
GDU Page Group
1. Serial Configuration
6. Diagnostics
11. Airframe Configuration
2. CDU Status Page
7. Ethernet Test
12. TAWS Configuration
3. Key Test
8. Video Test
13. SurfaceWatch
Configuration
4. FS 510 Test
9. Alert Configuration
14. XHTML Test
5. CDU Calibration
10. DAT Configuration
GIA Page Group
1. Serial Configuration
3. GIA I/O Configuration
5. GIA Status Page
2. GIA RS-485 Configuration
4. GIA COM Setup Page
6. GIA CAN Configuration
2. GEA Status Page
3. GEA Configuration
GEA Page Group
1. Engine Configuration
GTX Page Group*
1. Serial Configuration
2. Transponder Configuration
GTX Page Group (Aircraft equipped with GTX 3000)*
1. Transponder Airframe Config
2. Transponder Wiring Config
GTX 3X5 Page Group*
1. Transponder Airframe Config
2. Transponder Wiring Config
Transponder Diagnostics
2. GRS / GMU Calibration
3. GRS Flight Data Log**
GRS Page Group
1. Inputs Configuration
ADC Page Group
1. ADC Configuration
2. GDC Configuration***
GFC Page Group
1. GFC Configuration
2. GFC Status
GMA Page Group
1. GMA Configuration
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GDL Page Group
1. GDL 69 Configuration
3. GDL 59 Configuration*
2. GDL 59 Status*
4. GSR 56 Configuration*
RMT Page Group
1. Remote Controller Status
GWX Page Group
1. GWX Configuration
GTS Page Group *
1. GTS Configuration
GRA Page Group
1. GRA Configuration
OTHER Page Group *
1. Stormscope
CAL Page Group
1. Fuel Tank Calibration
3. HSCM Calibration
2. Flaps & Trim Calibration
4. DAT Calibration
* Appears only if option is installed.
** Appears only of GSU 75B is installed.
*** Does not appear if GSU 75B installed.
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3.2
G1000 System Software Information
NOTE
The following sections provide a detailed description of loading all G1000 software
and configuration files, which may be excessive for individual LRU removal and
replacement. If removing and replacing individual LRUs, refer to Section 6 of this
manual for the necessary steps.
3.2.1
G1000 Software Image
All software and configuration files were certified by Garmin and are considered part of FAAapproved Type Design data. Approved software and hardware definitions for each STC
Configuration are defined on the appropriate General Arrangement drawing listed in Table 1-1.
G1000 software and configuration files are controlled via the approved software image part
number listed on the General Arrangement drawing listed in Table 1-1. This software image is
loaded into the G1000 using a software loader card. The installer shall create this software
loader card by downloading the approved software image in accordance with Section 3.2.2.
NOTE
Only SanDisk brand SD cards are recommended for use with the G1000 system.
Other brand cards have not been tested by Garmin.
IMPORTANT!
To satisfy the G1000/GFC700 STC requirements for the 300 Series aircraft, it
is critical that the technician install correct software image part number
when servicing the G1000 system.
Approved software image part numbers are defined on the appropriate
General Arrangement drawing (see Table 1-1).
CAUTION:
Be cautious when using software loader cards during maintenance. The G1000
system immediately initializes the card upon power-up. On-screen prompts must
be given careful attention in order to avoid potential loss of data. Always read
through procedures given in Sections 5, 6 and 7 before attempting to use the
software loader cards.
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3.2.2
Loader Card Creation
The software image is an executable self-extracting file which builds the correct file structure
onto an SD card for use loading software to the G1000 System. To obtain the current file follow
the procedures outlined below.
NOTE
In order to create a King Air 300 Series system loader card, the installer
completing these procedures must be an authorized Garmin King Air
Service Center to gain access to the necessary data via the Garmin
website.
1. Go to www.garmin.com and click on the Dealer Resource Center link in the lower portion
of the home page. Enter your Garmin Dealer username and password.
2. Select Support button then select Software Downloads.
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3. Choose Search by Keyword tab and enter “2286”. Then click on the Search button.
4. A screen similar to the one shown below will appear. The numbers shown are for
example only.
5. Click on the Select Action button for software file 006-B2286-0(X)_0A.exe (the (X) is
the number from the General Arrangement drawing software part number needed for
this installation) and choose Download to save the software file to the local hard drive.
6. After the file is downloaded, close the web browser.
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7. Insert a blank (empty) SD card in the card reader. The loader card program will delete
all files on the SD card before loading G1000 system software files on it if the card is not
blank.
8. Double-click the .exe file that was downloaded onto the local hard drive. The following
window will pop-up on the screen. Click Yes to continue.
9. Follow the on screen prompts to continue.
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10. Select the SD card reader drive and click Next>.
11. Follow the on screen prompts to continue.
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12. The program will make the SD loader card and prompt you when it’s done.
13. Once successfully completed, the following window will display. Click Finish to close the
program. The SD card can then be removed from the computer and is ready for use in
the aircraft.
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3.2.3
Software Files
Software files are defined by part number and version number on the General Arrangement
drawing. Each G1000 system LRU reports the software version it currently contains to the user
in two places.
•
Normal System Mode: The Aux – System Status page lists each LRU and the
reported software version.
•
Configuration Mode: The System Status page (System page group) reports more
detailed LRU information, including software version, part number, and LRU status.
Software files are loaded to LRUs from the PFD1 System Upload page in configuration mode.
3.2.4
Configuration File Descriptions
There are configuration files for baseline settings and various options. Configuration files
contain preset selections for input/output channels, aircraft-specific settings, and LRU-specific
settings.
IMPORTANT!
Certain software and configuration files are REQUIRED to be re-loaded
during maintenance that involves removal and replacement of G1000
equipment.
Refer to Section 7 for re-configuration requirements for each individual
G1000 LRU. Pay special attention to the selection of option files for the units
to assure a complete load.
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3.2.5
Configuration File Storage
The G1000 system is designed to store all configuration settings in various places so that the
configuration is retained in the aircraft during maintenance of units.
During system configuration, each file is sent directly to the applicable LRU where it is stored in
local LRU memory (reference Figure 3-5.). Each file is also stored in the PFD internal memory.
The applicable PFD also sends a copy of all configuration files to the ‘Master Configuration
module’, located in the connector backshell (see Section 6.17). If the PFD is replaced, the
configuration module retains all configuration files in the aircraft.
The GSU 75B, GRS 77/7800, GMU 44, and GDC 7400 configuration/calibration (reference
Figure 3-6) is different than the LRU’s shown in Figure 3-5.
G1000 Master Configuration Module
(located in PFD backshell connector)
GMC 710
Master configuration module contains identical
backup configuration files of PFD configuration
memory. PFD cross-checks these backup files
against files contained with PFD memory. PFD selfconfigures to match master configuration module.
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
RS-232
No. 1 GDU 1050A PFD
Contains ‘ACTIVE’ PFD settings.
Represents ‘SET’ column for all
LRUs. Stores all configuration files in
internal memory. Uses master
configuration module for backup.
GDU 1550 MFD
Contains ‘ACTIVE’
MFD settings. The
MFD uses PFD
internal
configuration files
for backup.
No. 1 GIA 63W
No. 2 GIA 63W
RS-232
Contains ‘ACTIVE’
settings. Uses PFD
internal configuration
files for backup.
RS-485
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
No. 2 GEA 71
No. 1 GTX
Contains ‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
GMA 1347D
Contains ‘ACTIVE’
GMA settings. Uses
PFD internal
configuration files for
backup.
RS-232
RS-232
No. 1 GEA 71
No. 2 GDU 1050A PFD
Contains ‘ACTIVE’ PFD settings.
Represents ‘SET’ column for all
LRUs. Stores all configuration files in
internal memory. Uses master
configuration module for backup.
Contains ‘ACTIVE’
settings. Uses PFD
internal configuration
files for backup.
RS-232
RS-485
(ETHERNET)
RS-232
GMA 1347D
Contains ‘ACTIVE’
GMA settings. Uses
PFD internal
configuration files for
backup.
RS-232
HIGH-SPEED DATABUS
No. 2 GTX
GCU 477
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
Contains ‘ACTIVE’
settings. Uses PFD
internal
configuration files
for backup.
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
RS-485
RS-485
GDL 69A
GWX 68/70
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
Figure 3-5, G1000 LRU Configuration File Storage
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GRS 77/7800 AHRS and GMU 44 Magnetometer do not have a configuration file. However, the
GRS does store calibration data acquired during the post installation checkout, which are
characteristic to the specific installation. A copy of this calibration data is stored in the GRS
configuration module. While performing maintenance on these units, re-calibration may be
required. See Section 7.10 for more information on re-calibration criteria.
The GSU 75B ADAHRS air data configuration file is loaded directly to GSU 75B internal
memory. A copy of the file is stored in the GSU 75B configuration module. The GSU also
stores AHRS calibration data acquired during the post installation checkout, which is
characteristic to the specific installation. A copy of this calibration data is stored in the GSU
configuration module. While performing maintenance on this unit, re-calibration may be
required. See Section 7.10 for more information on re-calibration criteria.
The GDC 7400 air data computer configuration file is loaded directly to GDC 7400 internal
memory and there is no configuration module for the GDC 7400.
Figure 3-6, GSU/GRS/GDC Configuration Settings Storage
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3.3
Configuration Mode
Throughout this document, references are made to the PFD1, PFD2 and/or MFD being in
configuration mode. To start the G1000 system in configuration mode, follow these steps:
1. With the G1000 system off, open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2
circuit breakers.
2. Connect external power to the aircraft and energize the aircraft and avionics electrical
busses.
3. Press and hold the ENT key on PFD2 (copilot) and close the PFD2 circuit breaker.
4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD2.
5. Press and hold the #12 (far right) softkey on the MFD and close the MFD circuit breaker.
6. Release the #12 softkey after ‘INITIALIZING SYSTEM’ appears in the upper left corner
of MFD.
7. Press and hold the ENT key on PFD1 (pilot) and close the PFD1 (PRI) circuit breaker.
8. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD1.
NOTE
If a software loader card is inserted in the top slot of the display before it
is powered on, the display will automatically enter configuration mode
and it is not needed to press and hold a softkey at power-on.
3.4
G1000 Hardware/Software Compatibility Check
Before installing software, the technician must first ensure that hardware part numbers are
compatible with the G1000 system software image that is to be used. The General
Arrangement drawing shows all available combinations of hardware and software part numbers.
A G1000 system loader card is required to install software and configuration settings to a newly
installed G1000 system. The part number of the software image used to create the loader card
is directly associated with the combination of software file part numbers and version levels that
are defined on the General Arrangement drawing. Should software part numbers or versions
change, a new software image part number is issued.
IMPORTANT
After verifying hardware/loader card compatibility, record the software image
part number and all LRU hardware part numbers in the appropriate aircraft
records before proceeding.
NOTE
Throughout the next section of this document, screen shots and examples are
used to illustrate the software and configuration loading process. These
screen shots are provided as reference only. Always refer to the General
Arrangement drawing for the correct software file names, versions and part
numbers.
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3.5
Equipment Verification (Third Party/Optional Equipment Documentation)
Use the configuration/software checklist in Section 3.6 to determine what configuration software
files to load for the aircraft installation. It is extremely important to know exactly what equipment
the aircraft is equipped with and how it is connected before loading any files. Loading the
incorrect files could lead to longer down time and unplanned removal of equipment.
•
Third Party STCs such as such as BLR Winglet configuration. Find the AFMS part
number for the STCs that are installed in the aircraft documentation as it is important to
determine which configuration files to load for proper engine and airspeed instrument
markings. This information is required for Section 3.6.
•
Garmin optional equipment (i.e. GDC 7400, GRS 77 or 7800 AHRS or GSU 75
ADAHRS, GTX 33 or GTX 3X5 transponder, etc.). Section 3.5.1 helps find which units
are installed without a physical inspection.
•
Third party avionics equipment interfaced to G1000 (ADF, DME, non-Garmin traffic
systems, WX-500, etc.). To determine if the third party equipment is installed, check the
circuit breaker panel for circuit breakers for the units, and check for G1000 controls for
the third party devices. See the Garmin King Air 300 Series Pilot’s Guide P/N 19002043-00 for instructions how to find the G1000 controls for the third party device. If the
G1000 control and/or unit circuit breaker is not present for a third party device, it is not
installed.
•
Ethernet connections used for select Garmin units (i.e. Connected to GDL 69, PFD1,
MFD, or PFD2 Ethernet ports). See Section 3.5.2 for guidance how to determine which
Ethernet connections are used.
•
Check if Autopilot Electronic Stabilization and Protection (ESP) feature is installed. See
Section 3.5.3 for guidance how to check if ESP is installed.
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3.5.1
Determining Installed Garmin Units
Use the table in Appendix A to determine what the unit part number is based on the unit’s serial
number reported on the MFD Aux - System Status page in Normal mode or PFD1 System
Status page in Config mode. This table lists the units that have different loader card option files
so the installer can choose the correct file without requiring the unit to be physically inspected.
Figure 3-7, Garmin Unit S/N Location
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For Garmin units that S/N checking is not required but the technician needs to see if they are
installed such as GSR 56, check for the presence of the unit in the LRU Information list. If the
unit is not listed, it is not installed.
Figure 3-8, Garmin Unit Listed if Installed
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3.5.2
Determining Garmin Unit Ethernet Connections
Place the displays in config mode and go to PFD1 SYSTEM DATA PATHS page. Press the
HSDB softkey at the bottom of the screen and the Ethernet connections will be shown.
Figure 3-9, Ethernet Connections Page
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3.5.3
Determining if Autopilot ESP is Installed
To check if the aircraft has ESP installed, go to the MFD Aux - System Setup page and press
the “Setup 2” softkey at the bottom of the screen. If the “Stability and Protection” field is
present, the aircraft has ESP installed. If the field is not present, the aircraft does not have ESP
installed.
Figure 3-10, ESP Status Field
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3.6
Configuration Checklist
This sheet should be completed and maintained with the aircraft permanent records. Some
loader card options are not shown here if they are not used for initial 300 Series software load.
 King Air – Dual GTX 3000 Transponders
Date:
With Collins TTR-920
Aircraft Make:
 King Air – Dual GTX 3000 Transponders
Aircraft Registration:
With Collins TTR-4000

King Air - Dual GTX 335R Transponders and
Aircraft Serial #:
No GTS Unit Installed
Loader Card Version:
 King Air - Dual GTX 335R Transponders
With GTS Unit Installed
 King Air -GTX 345R and GTX 33
03) 300 Series Engine-Prop
Transponders and No Active Traffic Source

King Air - GTX 345R and GTX 33
(One selection only)
Transponders With GTS Unit Installed
 King Air 300 PT6A-60 Hartzell 4-Blade
 King Air - GTX 345R and GTX 33
 King Air B300 PT6A-60 Hartzell 4-Blade
Transponders With SkyWatch 429 Traffic
 King Air - GTX 345R and GTX 33
Transponders With Honeywell 429 Traffic
04) AHRS-Air Data
 King Air - GTX 345R and 335R
(Choose either the GSU 75B option or two selections
Transponders and No Active Traffic System
for GRS and GDC combination)
 King Air - GTX 345R and 335R
 King Air - GDC 7400 ADC
Transponders With GTS Unit Installed
 King Air - GRS 77 AHRS and GMU 44
 King Air - GTX 345R and 335R
Magnetometer
Transponders With SkyWatch 429 Traffic
 King Air - GRS 7800 AHRS and GMU 44
 King Air - GTX 345R and 335R
Magnetometer
Transponders With Honeywell 429 Traffic
 King Air - GSU 75B ADAHRS and GMU 44
Magnetometer
07) Connext - SXM
05) Autopilot
(One selection only)
 King Air 300 Series GFC700 - ESP
Installation (No AOA)
 King Air 300 Series GFC700 - Non ESP
Installation
 King Air B300 Series GFC700 - ESP
Installation (No AOA)
 King Air B300 Series GFC700 - Non ESP
Installation
06) Garmin Transponders
(One selection only)
 King Air - Dual GTX 33 Transponders and
No GTS Unit Installed
 King Air - Dual GTX 33 Transponders With
GTS Unit Installed
 King Air - Dual GTX 3000 Transponders With
GTS Processor
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(Multiple selections possible)
 King Air - GDL69A Legacy
 King Air - GDL69A SXM
 King Air - GDL59 Stand Alone (Connected to
GDL 69)
 King Air - GDL59 Stand Alone (Connected to
PFD2)
 King Air - GSR56 Stand Alone,
Voice/SMS/Connext
 King Air - GSR56 Stand Alone, Voice/SMS
Only
 King Air - GSR56 and GDL59 (GDL 59
connected to GDL69), Voice/SMS/Connext
 King Air - GSR56 and GDL59 (GDL 59
connected to PFD2), Voice/SMS/Connext
 King Air - GSR56 and GDL59 (GDL59
connected to GDL69), Voice/SMS Only
 King Air - GSR56 and GDL59 (GDL59
connected to PFD2), Voice/SMS Only
 Disable Flight Stream 510
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08) Radar
Unlock Card Options
(Up to two selections possible)
(Multiple selections possible)













King Air - GRA 5500 Radar Altimeter
King Air - GWX 68 (Connected to GDL69)
King Air - GWX 68 (Connected to MFD)
King Air - GWX 70 (Connected to GDL69)
King Air - GWX 70 (Connected to MFD)
09) Garmin Traffic Systems
(One selection if GTS installed or skip if using third
party traffic device)
 King Air – GTS 820/850 Traffic System
(Connected to GDL69)
 King Air - GTS Traffic Processor TAS/TCAS I
(Connected to GDL69), No GTX 345R
 King Air - GTS Traffic Processor TAS/TCAS I
(Connected to PFD1), No GTX 345R
 King Air - GTS Traffic Processor TAS/TCAS I
(Connected to GDL69), With GTX 345R
 King Air - GTS Traffic Processor TAS/TCAS I
(Connected to PFD1), With GTX 345R
 King Air - GTS Traffic Processor TCAS II
(Connected to GDL69)
 King Air - GTS Traffic Processor TCAS II
(Connected to PFD1)





TAWS-B (010-00330-51)
ChartView Only (010-00330-50)
Synthetic Vision (010-00330-55)
TAWS-A (010-00330-56)
Enhanced AFCS (010-00330-5A)
GTS Traffic TAS to TCAS I (010-00330-A1)
GTS Traffic TAS to TCAS II (010-00330-A2)
GTS Traffic TCAS I to TCAS II (010-00330A3)
Search and Rescue (010-00330-59)
Surface Watch (010-00330-KA)
GWX 70 Turbulence Detection (010-00330J3)
GWX 70 Ground Clutter Suppression (01000330-J4)
Dual Charts (010-00330-KB)
Notes:
1
This selection configures the TAWS-A gear and
flap messages. An unlock card is still required
to unlock feature after loading this file.
2
Disables 1, 2, 3, and 4 hundred foot callouts if
desired.
10) Garmin Feature Support
(Multiple selections possible if installing TAWS-A)
 King Air - TAWS-A Support1
 King Air - TAWS-A Voice No Callout
Installation Option2
11) Non-Garmin Options
(Multiple selections possible)









King Air - ADF Option
King Air - DME Option
King Air - FDR Option
King Air - RAD ALT Option (429 Interface)
King Air - Non-Garmin TCAS II System
Option
King Air - Traffic System Option (429
Interface), No GTX 345R
King Air - V1 Airspeed Option
King Air 300 - BLR Winglet STC
King Air - Lightning System Option
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3.7
G1000 Software/Configuration Procedure
This section summarizes the procedures required to load software and configuration files to the
G1000. It is intended to work as a central guide for technicians to use while performing
maintenance on the aircraft. In sections of this manual where software is required to be
reloaded, these sections will make reference back to this section for instructions. The
technician should use proper judgment regarding the context of maintenance required while
following this section.
The following diagram depicts an overview of the software/configuration sequence for the
G1000 system. This applies mostly to a new G1000 system software installation by Service
Bulletin and is for informative purposes only.
GDU 1050A PFDs / GDU 1550 MFD Software Load
Software is first loaded to the MFD and PFDs. From the factory, G1000 units do
not contain useable software or configuration settings. Load software to PFD2
first then MFD and finally to PFD1.
G1000 System Upload Selection
After software is loaded to the MFD and PFDs, the displays should be placed in
configuration mode. Using PFD1, the technician goes to the System Upload
page. From the System Upload page, software files are selected to create an
automated profile to load. Once all desired files are checked, the G1000
automatically loads the selected files in the correct sequence to the LRUs.
G1000 System Software Verification
After software is loaded to the system, the technician verifies that each LRU
reports the correct version and software part number.
G1000 System Configuration Upload Selection
Following G1000 system software upload and verification, the aircraft specific
configuration files, as defined in the general arrangement drawing are loaded.
The aircraft general arrangement drawing will define the configuration files
appropriate to the specific aircraft serial number, STC modifications and
applicable AFMS.
G1000 Configuration Verification
After system configuration files are loaded, the technician verifies that the
correct configuration on the Airframe Configuration page.
Figure 3-11, Software/Configuration Overview
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3.8
System Software and Configuration Load
3.8.1
System Power Up
Apply power to the G1000 system by connecting external power to the aircraft to energize
the aircraft and avionics electrical busses.
DO NOT RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A
BATTERY CHARGER AS AN EXTERNAL POWER SOURCE DUE TO ELECTRICAL
NOISE IT MAY INJECT IN THE G1000 SYSTEM.
Power loss during a software upgrade may cause a LRU to become corrupted and
unresponsive requiring replacement. Remove power only when told to do so in the
procedure.
3.8.2
MFD & PFD Software Load
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Remove Garmin database cards from bottom slots of PFD1, MFD, and PFD2 if present.
3. Insert the software loader card into PFD2 top card slot.
4. Turn on Avionics electrical busses.
5. Close the PFD2 circuit breaker.
6. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, press the
YES softkey.
7. After the new GDU software is loaded to PFD2, a “DO YOU WANT TO UPDATE THE
SPLASH SCREEN?” prompt may appear. If it does, press the NO softkey. The splash
screen will be loaded later in this procedure.
8. When complete, the PFD2 starts in configuration mode displaying the “System Status”
page. Open PFD2 circuit breaker.
9. Remove the loader card from PFD2 and insert it into the top card slot on the MFD.
10. Repeat Steps 5 through 8 for the MFD using the MFD circuit breaker. The MFD does not
have an ENT key, so instead use softkey #12 for ENT when stated above.
11. When MFD update is complete, open the MFD circuit breaker, remove the loader card
from the MFD and insert it into the PFD1 top card slot.
12. Repeat Steps 5 through 8 for PFD1 using the PFD (PRI) circuit breaker. When
complete, leave PFD1 on with the loader card remaining in the top card slot.
13. Start the MFD and PFD2 in configuration mode by pressing and holding the ENT key or
softkey #12 when closing the circuit breakers. Release the key when the words
“INITIALIZING SYSTEM” appear on the screen.
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3.8.3
01) Baseline Software and Configuration Load
IMPORTANT
If the aircraft being modified has incorporated any modifications beyond
factory configuration that effect engine or airspeed limitations, your
configuration may not be supported at this time. It is the responsibility of
the installer to ensure compatibility with existing modifications.
Do not allow power to be removed from the system when loading software.
Remove power only when instructed by the following procedures.
As a general rule, all displays should be in the same mode (configuration or
normal) unless instructed otherwise.
Follow the order of software and configuration loading, do not skip or
rearrange steps.
Do not operate or turn off MFD and/or PFD2 while loading software and
configuration files unless specifically instructed to do so. A failed or
cancelled load may result.
If an incorrect configuration file is loaded at any time during this procedure,
STOP and start the configuration load over at Step 2 in this Section.
1. Ensure all avionics circuit breakers are closed and the G1000 system is fully powered.
2. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
3. Push in the PFD1 FMS knob to activate the cursor in the Group field. Rotate the small
FMS knob to activate the drop-down menu. Rotate the small FMS knob to highlight “01)
Baseline” in the drop-down menu and press the ENT key to select it.
4. Once “01) Baseline” is selected, the cursor moves to the ITEM window. Rotate the
small FMS knob to activate the drop-down menu. Highlight “King Air 200-300 Series
Baseline Load” and press the ENT key to select it. The PRODUCT field will then
populate.
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NOTES
The PRODUCT window displays information regarding each G1000 LRU. The
LRU column depicts the reported software version of the LRU (may be blank if
PFD1 cannot communicate with the unit yet until after config files are loaded).
The CARD VERS column shows the LRU software version stored on the Loader
Card.
The SOFTWARE column may or may not have all boxes checked automatically.
For the initial software load in the system all software boxes should be checked
to load all files. This is done by pressing the CHK ALL softkey when instructed
below.
The CONFIGURATION column defaults to having all unit configuration boxes
checked.
The hardware serial number is used to determine appropriate software for the
GIA COM, GIA NAV, GMU 44, and GSA 8X units. Until the system
configuration loads sufficiently to access and read these units, they may show a
“INV” invalid status under the LRU VERS and CARD VERS columns with up to
two line items per item (representing different hardware configurations). After
the configuration files are loaded, the units will update and remove the “INV”
status and will load automatically.
5. Press the CHK All softkey.
6. Press the Load softkey.
Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” or White “N/A” in all Configuration and Software columns.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.4
03) 300 Series Engine-Prop Software and Configuration Load
Follow this procedure to configure the airframe type.
1. Move the cursor to the Group window and rotate FMS inner knob to display drop down
menu. Highlight “03) 300 Series Engine-Prop” and press the ENT key to select it.
2. The cursor should automatically move to the ITEM window. Rotate the small FMS knob
to highlight the appropriate airframe, engine, and prop combination that was checked on
the Configuration checklist in Section 3.6, in the 03) 300 Series Engine-Prop checklist
group and press the ENT key to select it.
3. Press the CHK All softkey.
4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
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NOTE
Not all propellers are available for selection with each airframe and
engine configuration. Only those props that are approved for installation
on a particular airframe/engine are available in the drop down selection
window.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” or White “N/A” in all Configuration and Software columns.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.5
04) AHRS – Air Data Software and Configuration Load
Follow this procedure to configure the AHRS, Air Data, or ADAHRS units in the aircraft.
1. Move the cursor to the Group window and rotate FMS inner knob to display drop down
menu. Highlight “04) AHRS – Air Data” and press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the first item that was
checked on the Configuration checklist in Section 3.6 in the 04) AHRS-Air Data checklist
group and press the ENT key to select it.
3. Press the CHK All softkey.
4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. If two selections were made for this section on the Configuration checklist (one AHRS
and one ADC), repeat steps 2-7 to load the second file.
3.8.6
05) Autopilot Software and Configuration Load
Follow this procedure to configure the autopilot type and GSM servo mounts installed.
1. Move the cursor to the Group window and rotate FMS inner knob to display drop down
menu. Highlight “05) Autopilot” and press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the first item that was
checked on the Configuration checklist in Section 3.6 in the 05) Autopilot checklist group
and press the ENT key to select it.
3. Press the CHK All softkey.
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4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Rotate the large FMS knob to highlight the ITEM window and select the second file on
the Configuration checklist. Repeat steps 2-7 to load the second file.
3.8.7
06) Garmin Transponders Software and Configuration Load
Follow this procedure to configure the Garmin transponders.
1. Rotate the large FMS knob until the Group field is highlighted, rotate the small FMS knob
to activate the drop down menu. Rotate the small FMS knob and select “06) Garmin
Transponders” and press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the item that was checked
on the Configuration checklist in Section 3.6 in the 06) Garmin Transponders checklist
group and press the ENT key to select it.
3. Press the CHK All softkey.
4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.8
07) Connext –SXM Software and Configuration Load
Follow this procedure to configure FS 510, GDL69A, GDL59, and GSR 56 options if installed.
1. Rotate the large FMS knob until the Group field is highlighted, rotate the small FMS knob
to activate the drop down menu. Rotate the small FMS knob and select “07) Connext SXM” and press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the first item that was
checked on the Configuration checklist in Section 3.6 in the 07) Connext - SXM checklist
group and press the ENT key to select it.
3. Press the CHK All softkey.
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4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. If multiple selections were made for this section on the Configuration checklist, repeat
steps 2-7 to load each additional item on the Configuration checklist.
3.8.9
08) Radar Software and Configuration Load
Follow this procedure to configure GWX 70 and GRA 5500 if installed.
1. Rotate the large FMS knob until the Group field is highlighted, rotate the small FMS knob
to activate the drop down menu. Rotate the small FMS knob and select “08) Radar” and
press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the first item that was
checked on the Configuration checklist in Section 3.6 in the 08) Radar checklist group
and press the ENT key to select it.
3. Press the CHK All softkey.
4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. If two selections were made for this section on the Configuration checklist, repeat steps
2-7 to load the second item.
3.8.10 09) Garmin Traffic Systems Software and Configuration Load
Follow this procedure to configure Garmin Traffic Systems if installed.
NOTE
The G1000 can only be configured for TIS or TAS/TCAS but not both.
Performing this procedure will automatically disable the TIS function.
Configuration of the GTS Processor will require entering the aircraft
registration number into the unit using Section 3.10 “Aircraft Registration
Number Entry”.
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1. Rotate the large FMS knob until the Group field is highlighted, rotate the small FMS knob
to activate the drop down menu. Rotate the small FMS knob and select “09) Garmin
Traffic Systems” and press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the item that was checked
on the Configuration checklist in Section 3.6 in the 09) Garmin Traffic Systems checklist
group and press the ENT key to select it.
3. Press the CHK All softkey.
4. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
5. Press the Load softkey.
6. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
3.8.11 10) Garmin Feature Support Configuration Load
This section applies only to installations with the TAWS-A option. The procedures outlined in
this section must be followed to load the necessary configuration files required to enable TAWSA gear and flap messages. A TAWS-A enablement card is also required for this option.
NOTE
TAWS-A Voice No Callout applies only to installations with the TAWS-A
option. If TAWS-A voice callouts (400, 300, 200, and 100 feet) are not
desired, follow the procedures outlined in this section to load the
necessary configuration files to disable TAWS-A voice callouts.
1. Rotate the large FMS knob until the Group field is highlighted, rotate the small FMS knob
to activate the drop down menu. Rotate the small FMS knob and select “10) Garmin
Feature Support” and press the ENT key to select it.
2. In the ITEM window, rotate the small FMS knob to highlight the first item that was
checked on the Configuration checklist in Section 3.6 in the 10) Garmin Feature Support
checklist group and press the ENT key to select it.
3. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
4. Press the LOAD softkey.
5. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge the “Upload Complete” box.
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7. If TAWS-A Voice No Callout option is desired, repeat steps 2-6 to load the “King Air TAWS-A Voice No Callout Installation Option” file.
3.8.12 11) Non Garmin Options Configuration Load
Follow this procedure to configure non-Garmin items if installed.
1. Rotate the large FMS knob until the GROUP field is highlighted, rotate the small FMS
knob to activate the drop down menu. Rotate the small FMS knob and select “11) Non
Garmin Items” and press the ENT softkey.
2. In the ITEM window, rotate the small FMS knob to highlight the first item that was
checked on the Configuration checklist in section 3.6 in the 11) Non-Garmin Options
checklist group and press the ENT key to Select it.
3. In the PRODUCT window, move the cyan selection box down with the large FMS knob
to highlight the “CARD COPY” configuration check box. Press the ENT key to uncheck
the configuration check box.
4. Press the Load softkey.
5. Monitor the loading progress and verify the software load completes without errors as
indicated by the following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge the “Upload Complete” box.
7. If multiple selections were made for this Section on the Configuration checklist, repeat
steps 2-6 to load each additional option.
3.8.13 Save Configuration
1. Press the UPDT CFG softkey at the bottom of the SYSTEM UPLOAD page.
2. Press the ENT key to select YES in the pop-up window to start the update.
3. When the config module update is done, press the ENT key to select OK in the pop-up
window to close it.
4. Open PFD 1 circuit breaker, remove the software loader card and continue to the next
Section.
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3.9
Feature Enablement
This section describes how to unlock or enable optional features. The installer will only load the
sections for the features they require. For installing all feature enablement cards, PFD1, PFD2,
and the MFD must be in configuration mode.
The G1000 has various features that require the use of unlock/enable cards to activate the
feature. Throughout this document these cards are generically referred to as ‘enablement
cards’. In some cases, the actual label on the physical card may say ‘unlock’.
If uncertain what SD Card to use, the technician must verify the card part number on the
General Arrangement drawing prior to use to assure the correct feature is unlocked.
3.9.1
ChartView Feature Enablement
Follow this procedure to activate the ChartView-only display feature. This feature disables
display of Garmin FliteCharts. If Dual Charts feature is desired instead, go to Section 3.9.2.
NOTES
The required ChartView databases are subscription-based and need to be
procured by the installing agency from the Garmin or Jeppesen website. The
ChartView database is not present in a new display.
1. Insert the ChartView Enablement card in the top slot of PFD1 and power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable ChartView” and
press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the ChartView enablement card.
3.9.2
Dual Charts Enablement
Follow this procedure to enable the Dual Charts display feature. This enables the pilot to switch
between Garmin FliteCharts and Jeppesen ChartView products on the MFD.
1. Insert the Dual Charts Enablement card in the top slot of PFD1 and power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
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3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Enable_DualCharts” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Dual Charts Feature
Enable” and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the Dual Charts enablement card.
3.9.3
SurfaceWatch Feature Enablement
Follow this procedure to enable the SurfaceWatch feature.
1. Insert the SurfaceWatch Enablement card in the top slot of PFD1 and power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Enable_SurfaceWatch” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “SurfaceWatch Feature
Enable” and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the SurfaceWatch enablement card.
3.9.4
GWX 70 Radar Turbulence Detection Feature Enablement
Follow this procedure to enable the GWX 70 Turbulence Detection feature.
1. Insert the GWX 70 Turbulence Detection Enablement card in the top slot of PFD1 and
power on PFD1 in configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Enable_TD” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “GWX 70 Turbulence
Detection Enable” and press the ENT key to select it.
5. Press the Load softkey.
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6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the Turbulence Detection enablement card.
3.9.5
GWX 70 Ground Clutter Suppression Feature Enablement
Follow this procedure to enable the GWX 70 Ground Clutter Suppression feature.
1. Insert the GWX 70 Ground Clutter Suppression Enablement card in the top slot of PFD1
and power on PFD1 in configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Enable_GCS” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “GWX 70 Ground Clutter
Suppression Enable” and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the Ground Clutter Suppression enablement
card.
3.9.6
TAWS-B Feature Enablement
Follow this procedure to enable the TAWS Class B feature. If TAWS-A is required instead, go
to Section 3.9.7.
1. Insert the TAWS-B Enablement card in the top slot of PFD1 and power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable TAWS-B” and
press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
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•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the TAWS-B enablement card.
3.9.7
TAWS-A Enablement
Follow this procedure to enable the TAWS Class A feature.
NOTES
Ensure that the King Air - TAWS-A Support Configuration file has
been loaded per Section 3.8.11 and that a Radar Altimeter Option
(King Air - GRA 5500 Radar Altimeter or King Air - RAD ALT Option
(429 Interface)) Configuration file has been loaded.
1. Insert the TAWS-A Enablement card in the top slot of PFD1, power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable TAWS-A” and
press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove TAWS-A enablement card.
3.9.8
Synthetic Vision System Enablement
Follow this procedure to enable the Synthetic Vision feature.
1. Insert the SVS Enablement card in the top slot of PFD1, power on PFD1 in configuration
mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Configuration Files” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable SVS Dual PFD”
and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
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•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove SVS enablement card.
3.9.9
Enhanced AFCS (ESP) Enablement
Follow this procedure to enable the Electronic Stability and Protection (ESP) feature.
NOTE
Ensure that the King Air 200/B300 Series GFC700 - ESP Installation (No
AoA) or King Air 200/B300 Series GFC700 - ESP Installation (with AoA)
Configuration file has been loaded.
1. Insert the Enhanced AFCS Enablement card in the top slot of PFD1, power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Enhanced AFCS” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enable Enhanced AFCS”
and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove Enhanced AFCS enablement card.
3.9.10 Search and Rescue Enablement
Follow this procedure to enable the Search and Rescue (SAR) feature.
1. Insert the SAR Enablement card in the top slot of PFD1, power on PFD1 in configuration
mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “Enhanced SAR” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “Enhanced Search and
Rescue” and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
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•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove SAR enablement card.
3.9.11
GTS TCAS I Enablement
Follow this procedure to enable Garmin GTS TCAS I feature. If TCAS II is desired instead, go
to Section 3.9.12.
1. Insert the TCAS I Enablement card in the top slot of PFD1, power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “GTS Processor Enablement” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “GTS Processor TAS to
TCAS I Enablement” and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the Enhanced TCAS I enablement card.
3.9.12 GTS TCAS II Enablement
Follow this procedure to enable the Garmin GTS TCAS II feature.
1. Insert the TCAS II Enablement card in the top slot of PFD1, power on PFD1 in
configuration mode.
2. On PFD1, select the “System Upload” page using the small FMS knob.
3. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “GTS Processor Enablement” and press the ENT key to select it.
4. In the ITEM window, rotate the small FMS knob to highlight “GTS Processor TAS to
TCAS II Enablement” and press the ENT key to select it.
5. Press the Load softkey.
6. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
7. Press the ENT key to acknowledge the “Upload Complete” box.
8. Open PFD1 circuit breaker and remove the Enhanced TCAS II enablement card.
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3.9.13 Flight Stream 510
This file is designed to allow the installer to re-enable the Flight Stream 510 if it was previously
disabled. This file is not required to enable Flight Stream 510 if it was not previously disabled.
Flight Stream 510 is enabled by default in the baseline configuration.
1. Insert the software loader card in the top slot of PFD1, power on PFD1 in configuration
mode.
2. Press the NO softkey (number 11 softkey) to acknowledge the following prompt.
3. On PFD1, select the “System Upload” page using the small FMS knob.
4. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “07) Connext - SXM” and press the ENT key to select it.
5. In the ITEM window, rotate the small FMS knob to highlight “Enable Flight Stream 510”
and press the ENT key to select it.
6. Press the CHK ALL softkey.
7. In the product window, move the cursor to highlight “CARD COPY”. Press the ENT key
to uncheck the configuration check box.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press the ENT key to acknowledge the “Upload Complete” box.
11. Open PFD1 circuit breaker and remove the software loader card.
3.9.14 FliteCharts Enablement
This file is designed to allow the installer to revert the Charts options back to the default
FliteCharts setting if Dual Charts or ChartView features were previously enabled. This file is not
required to enable FliteCharts if Dual Charts or ChartView were not previously enabled.
FliteCharts is enabled by default in the baseline configuration.
1. Insert the software loader card in the top slot of PFD1, power on PFD1 in configuration
mode.
2. Press the NO softkey (number 11 softkey) to acknowledge the following prompt.
3. On PFD1, select the “System Upload” page using the small FMS knob.
4. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “10) Garmin Feature Support” and press the ENT key to select it.
5. In the ITEM window, rotate the small FMS knob to highlight “Activate Garmin
FliteCharts Only (Disables Dual Charts and ChartView” and press the ENT key to
select it.
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6. Press the CHK ALL softkey.
7. In the product window, move the cursor to highlight “CARD COPY”. Press the ENT key
to uncheck the configuration check box.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press the ENT key to acknowledge the “Upload Complete” box.
11. Open PFD1 circuit breaker and remove the software loader card.
3.9.15 TAWS-A Voice Callout Enablement
This file is designed to allow the installer to re-enable the 1, 2, 3, and 4 hundred foot callouts if
the no voice callout option was loaded previously. This file is not required to enable the voice
callouts if the no voice callout option was not loaded previously. The voice callouts are enabled
by default in the baseline configuration.
1. Insert the software loader card in the top slot of PFD1, power on PFD1 in configuration
mode.
2. Press the NO softkey (number 11 softkey) to acknowledge the following prompt.
3. On PFD1, select the “System Upload” page using the small FMS knob.
4. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS
knob to highlight “10) Garmin Feature Support” and press the ENT key to select it.
5. In the ITEM window, rotate the small FMS knob to highlight “Activate Garmin
FliteCharts Only (Disables Dual Charts and ChartView” and press the ENT key to
select it.
6. Press the CHK ALL softkey.
7. In the product window, move the cursor to highlight “CARD COPY”. Press the ENT key
to uncheck the configuration check box.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration column for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press the ENT key to acknowledge the “Upload Complete” box.
11. Open PFD1 circuit breaker and remove the software loader card.
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3.9.16 POTS Handset Configuration
Follow this procedure to enable a POTS handset if installed. Note that the GDL 59 Wi-Fi data
link option must be loaded per Section 3.8.8 prior to loading the POTS handset configuration.
1. Power on PFD1 in configuration mode.
2. On the PFD1, select GDL page group using the large FMS knob.
3. Using the small FMS knob select the GDL 59 Configuration page.
4. Activate the cursor. Use the large FMS knob to select POTS CONNECTED in the PHONE
SETTINGS field.
5. Use the small FMS knob to select YES and press the ENT key.
6. After GDL 59 is configured, press the ENT key.
3.10
Aircraft Registration Number Entry
NOTE
Steps to complete the aircraft registration entry are dependent on
transponder equipment installed. Choose the appropriate procedure from
Section 3.10.1 or 3.10.2 to complete the aircraft registration entry.
3.10.1 Equipped with Dual GTX 33s or GTX 3000s
1. Power on PFD1 in configuration mode. Select the AIRCRAFT CONFIGURATION page
on PFD1.
2. Activate the cursor to select the ”AIRCRAFT REGISTRATION” field and enter the
aircraft’s tail number.
3. For non-US “N” number aircraft registrations, rotate the large FMS knob to select the
“ICAO ADDRESS” and enter the aircraft’s 24 bit ICAO address. US “N” number aircraft
registrations are automatically decoded and entered in this field, do not change the
number.
4. If applicable, rotate the large FMS knob to select the “ICAO REGION” field and select
the ICAO region. Otherwise, leave at “NONE”.
5. If applicable, rotate the large FMS knob to select the ”DOMAIN IDENTIFIER” field and
enter the number. Otherwise, leave blank.
6. Rotate the large FMS knob to select the “VFR CODE” field and enter the desired code
that will become active when the VFR key on a PFD is pressed.
7. For GTX 33 units only, press the Set GTX1 softkey and acknowledge the PFD1 prompt
by pressing the ENT key. Repeat for the Set GTX2 softkey.
8. For GTX 3000 units only, press the SET GTX softkey and acknowledge the PFD1
prompt by pressing the ENT key.
9. Press the Set GTS softkey (if present) and acknowledge the PFD1 prompt by pressing
the ENT key.
10. After completing transponder configuration, deactivate the cursor.
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3.10.2 Equipped with Dual GTX 3X5s
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD1 in configuration mode.
3. Press the NO softkey (number 11 softkey) to acknowledge the following prompt.
4. On PFD1, select the AIRCRAFT CONFIGURATION page.
5. Activate the cursor to select the “AIRCRAFT REGISTRATION” field and enter the
aircraft’s tail number.
6. For non-US “N” number aircraft registrations, rotate the large FMS knob to select the
“ICAO ADDRESS” and enter the aircraft’s 24 bit ICAO address. US “N” number aircraft
registrations are automatically decoded and entered in this field, do not change the
number.
7. If applicable, rotate the large FMS knob to select the ”ICAO REGION” field and select
the ICAO region. Otherwise, leave at “NONE”.
8. If applicable, rotate the large FMS knob to select the ”DOMAIN IDENTIFIER” field and
enter the number. Otherwise, leave blank.
9. Rotate the large FMS knob to select the “VFR CODE” field and enter the desired code
that will become active when the VFR key on a PFD is pressed.
10. Press the SET GTS softkey (if present) and acknowledge the prompt by pressing the
ENT key.
11. Deactivate the cursor.
12. Rotate large FMS knob to select “GTX 3X5” configuration page group.
13. On the “Transponder Airframe Configuration” page, verify the GTX1 and GTX 2
boxes at the top of the page are green and the tail number, ICAO address, and VFR
code that were entered previously are correct.
3.10.3 Equipped with Single GTX 345R (#1) and Single GTX 33 (#2)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD1 in configuration mode.
3. Press the NO softkey (number 11 softkey) to acknowledge the following prompt.
4. Select the AIRCRAFT CONFIGURATION page on PFD1.
5. Activate the cursor to select the ”AIRCRAFT REGISTRATION” field and enter the
aircraft’s tail number.
6. Rotate the large FMS knob to select the “ICAO ADDRESS” and enter the aircraft’s 24
bit ICAO address.
7. If applicable, rotate the large FMS knob to select the ”ICAO REGION” field and select
the ICAO region. Otherwise, leave at “NONE”.
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8. If applicable, rotate the large FMS knob to select the ”DOMAIN IDENTIFIER” field and
enter the number. Otherwise, leave blank.
9. Rotate the large FMS knob to select the “VFR CODE” field and enter the desired code
that will become active when the VFR key on a PFD is pressed.
10. Press the Set GTX2 softkey and acknowledge the PFD1 prompt by pressing the ENT
key.
11. Press the Set GTS softkey (if present) and acknowledge the PFD1 prompt by pressing
the ENT key.
12. Deactivate the cursor.
13. Rotate large FMS knob to select “GTX 3X5” configuration page group.
14. Rotate the small FMS knob to select “Transponder Airframe Configuration” page.
15. Verify the GTX1 box at the top of the page is green and the tail number, ICAO address,
and VFR code that were entered previously are correct.
3.11
Configuration Manager
1. On PFD1, rotate the large FMS knob to select “SYSTEM” configuration page group.
2. Rotate the small FMS knob to select Configuration Manager page.
3. Press the softkey labelled CNFM CFG on PFD1.
4. Press the ENT key on PFD1 to select OK when prompted to confirm configuration as
expected configuration.
5. Open MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
3.12
Splash Screen Loading
When all software and configuration has been loaded, the splash screens must be loaded to all
display units (PFD1, PFD2 and MFD).
1. Insert the software loader card in the upper slot of PFD2.
2. Close PFD2 circuit breaker.
3. When prompted to update system files, press the NO softkey.
4. When prompted to update splash screen files, press the YES softkey.
5. When the SYSTEM STATUS page appears, open the PFD2 circuit breaker.
6. Remove the loader card from PFD2 and insert it into the upper slot of the MFD.
7. Close MFD circuit breaker.
8. When prompted to update system files, press the NO softkey.
9. When prompted to update splash screen files, press the YES softkey.
10. When the SYSTEM STATUS configuration page appears, open MFD circuit breaker.
11. Remove the loader card from the MFD and insert it into the upper slot of PFD1.
12. Close PFD 1 (PRI) circuit breaker.
13. When prompted to update system files, press the NO softkey.
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14. When prompted to update splash screen files, press the YES softkey.
15. Open PFD 1 (PRI) circuit breaker.
3.13
Clearing Default User Settings
1. Open MFD, PFD1 PRI, PFD1 SEC, and PFD2 circuit breakers.
2. While holding the CLR button on PFD1, close PFD1 PRI circuit breaker.
3. When prompted to clear user settings, select the YES softkey.
4. When user settings have been cleared appears on the screen, Open PFD1 PRI circuit
breaker.
5. While holding the second key from the right side (#11 softkey) of the MFD, close the
MFD circuit breaker.
6. When prompted to clear user settings, select the YES softkey.
7. When user settings have been cleared appears on the screen, open MFD circuit
breaker.
8. While holding the CLR button on PFD 2, close the PFD2 circuit breaker.
9. When prompted to clear user settings, select the YES softkey.
10. When user settings have been cleared appears on the screen, open PFD2 circuit
breaker.
3.14
Database Loading
Follow this procedure to load the databases.
1. Obtain the following databases from fly.garmin.com and install on a blank 16GB or larger
card, or by obtaining Garmin SD Card P/N 010-00474-50 which contains some of the
databases below. Databases with an (*) asterisk are not included on the P/N 01000474-50 SD card. If obtaining the databases from fly.garmin.com and using SD cards
smaller than 16GB, you may need to use multiple cards (or reuse one) to load all the
databases into the G1000 system.
a. Terrain (Worldwide, 4.9 Arc Second, TBD2 format)
b. Obstacle (US/Canada/Europe, OBD2 format)
c. AOPA Airport Directory (US)
d. AC-U-KWIK Airport Directory*
e. SafeTaxi (US, North America*, Canada*, Europe*, Full Coverage*)
f.
Basemap (Worldwide)
g. Garmin FliteCharts (US, Canada*, Europe*)
h. Jeppesen ChartView*
i.
IFR/VFR Charts (US)
j.
Navigation*
2. With the displays off, insert the SD card with the databases into the MFD top slot.
3. Apply power to the PFD1, MFD, and PFD2.
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4. On the MFD, database verification messages may appear. If so, follow the on-screen
instructions to continue.
5. Go to the MFD Aux - Databases page to monitor the automatic database update
progress. The new databases will show “Syncing” to the Standby column. After the
databases are synchronized, the system will verify them for use by showing “Verifying” in
the Standby column. After the databases are verified, a cyan double arrow symbol will
appear between the Standby and Active columns to show which databases will be
transferred to Active use on the next power cycle.
Figure 3-12, MFD Aux - Database Page DB Transfer
6. When all database updates are complete, the Database Update field at the top of the
screen will say, “Restart avionics to activate selected standby databases.” If the engines
are not running, a Restart softkey appears at the bottom of the MFD. Press Restart to
cycle power on the displays. If the Restart softkey is not present, turn OFF PFD1, MFD,
and PFD2.
7. Remove the database update card from the top slot of the MFD.
8. Turn ON the displays.
9. The displays may state they are verifying databases at power-up. If so, follow the onscreen instructions to continue.
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10. Go to the MFD Aux - Databases page and verify the uploaded databases transferred
from the Standby column to the Active column. If any did not transfer, follow these steps
to initiate a manual transfer a. Push the FMS knob on the GCU controller to turn on the curser.
b. Turn the FMS knob to highlight the database to transfer to the Active column.
c. Press the ENT key on the GCU and a cyan double arrow will appear between the
Standby and Active columns.
d. Restart the displays.
e. Go to the MFD Aux - Databases page and confirm the databases transferred.
3.15
Configuration of Navigation Map for Traffic System
1. With the MFD in normal mode, use the GCU FMS knob to select the Navigation Map
page then press GCU MENU key to display the PAGE MENU.
2. Turn the small right knob to select or verify selected ‘Map Setup’ and press the ENT key
and verify TRAFFIC is selected ON.
3. Verify the flashing cursor highlights the GROUP field.
4. Turn the GCU small FMS knob to select Traffic and press ENT on GCU.
5. If not already selected, use the GCU FMS knob to make the following selections:
•
Traffic – On
•
Traffic Mode – All Traffic
•
Traffic Symbols – 150NM
•
Traffic Labels – On 150NM
6. Return to the Map Page by pressing the GCU FMS knob or momentarily pressing and
holding the CLR key. Deactivate cursor.
3.16
Enter Flight ID for GTX 3000 Installations
1. On PFD1, press the TMR/REF softkey.
2. Use the large FMS knob and scroll to the bottom of the window and highlight the
FLIGHT ID field.
3. Use the FMS knobs to enter the aircraft registration and press the ENT key to save.
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3.17
GRA 5500 Legacy Software and Configuration (Non Integrated)
Follow this section to download and install software and configure the GRA 5500 using the
retrofit installation tool. This section is only needed for Non-integrated GRA 5500 installations
that do not use the RS-422 connection to the GIA. These instructions are also found in the
GRA 5500 Installation Manual Garmin P/N 190-01277-00.
3.17.1 GRA Software Download
This section describes the GRA 5500 software loading process for airplanes that had previously
installed the G1000 system and subsequently upgraded to the NXi but chose not install the
additional wiring to the optional GRA 5500.
1. Go to www.garmin.com and click on the Dealer Resource Center link in the lower portion
of the home page. Enter username and password.
2. Select Technical Tools then select Software Downloads.
3. In the Keyword(s) filter, enter “GRA” and click on the Go button.
4. A screen similar to the one shown below will appear. The numbers shown are for
example only.
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5. Click on the download symbol for the appropriate Sensor and Main software version part
numbers based upon the information provided in The General Arrangement drawing and
save the files to the local hard drive.
3.17.2 Downloading and Installing the GRA 5500 Retrofit Installation Tool
GRA 5500 configuration, calibration, diagnostics, and software upgrades are performed (in
retrofit/non-GIFD installations) using a personal computer (installed with Microsoft Windows XP
or later) and the GRA 5500 Retrofit Installation Tool, Garmin part number 006-A0451-00. This
tool is also used to assist in the diagnosis and resolution of asserts found in the GRA 5500
assert log during the installation process and during post-installation flight operation. The tool is
available for download from the Dealer Resource Center portion of the Garmin website
(www.garmin.com). See the accompanying “readme” file in the tool installation directory for the
latest instructions.
NOTE
A standard USB-A plug to USB-B plug commercial cable (not provided)
is required to interface between a personal computer USB-A receptacle
and the GRA 5500 USB-B receptacle installed in the wiring harness.
PC Installation of the Installation Tool:
1. Once downloaded, launch the installation file from the directory in which it is stored (or
use the web browser’s download shortcuts).
2. The GRA 5500 Retrofit Installation Tool Setup Wizard will begin.
3. Click “Next” as prompted by the setup wizard, and adjust any settings (e.g. installation
directory) as needed.
4. The last screen of the setup wizard will show “Installation Complete.” Click the “Close”
button to close the setup wizard.
3.17.3 GRA 5500 Setup
The following actions must be performed to load the correct software versions and configure the
GRA for the installation:
1. Connect a PC that has the GRA 5500 Retrofit Installation Tool installed to the GRA
5500 via a USB cable to the installed USB Pigtail located near the GRA 5500.
2. Start the GRA 5500 Retrofit Installation Tool from the “Start Menu” shortcut, or launch
the application from its program folder.
3. Power-up the GRA 5500 by applying aircraft power.
4. The connection status in the lower, right-hand corner of the GRA 5500 Retrofit
Installation Tool will transition from “Not Connected,” to “Connecting,” and finally to
“Connected” once the GRA 5500 is powered.
5. On the Status tab, click “Initiate Calibration Procedure”
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6. Verify that the GRA 5500 Retrofit Installation Tool display a progress dialog during the
calibration procedure and automatically close once the calibration procedure is completed.
7. Verify that the information displayed in the status bar indicates “0 ft” and “Normal”.
8. Go to the Software tab. Check the main system and sensor system software versions
reported by the unit to the General Arrangement drawing. If they do not match, load the
software versions listed on the General Arrangement drawing by performing the
following:
a. Depending on the method of receiving updated software region files, it may be
required to extract the files to a directory on the PC that is/will be connected to
the GRA 5500. The GRA 5500 Retrofit Installation Tool will only recognize
Garmin Aviation binary region files (.bin).
b. Enter the directory where these downloaded files are stored, or click the
“Browse” button to locate the directory.
c. Once the directory is selected, the GRA 5500/55 Retrofit Installation Tool will
display a list of all valid software region files in the directory. If no software region
information is displayed in the list, the selected directory does not contain valid
software region files. Make sure the files have been properly extracted (to .bin
files), and have not been corrupted during transfer.
d. Select the region to upload to the unit by clicking on the entry in the list. The
entry should be highlighted to indicate its selection.
e. Click the “Upload Selected Software Regions” button to initiate the update
procedure. This will produce a progress dialog indicating the software update
progress. Once the software update has completed the GRA 5500 will be
automatically restarted to reload the new software.
f.
Once the progress dialog has closed, check the “Current Software” section to
verify that the previously selected software regions have been successfully
updated. The “Current Software” section displays product information for each
software region currently loaded on the GRA 5500. Each region is shown with its
corresponding Garmin part number and software release version.
9. If any errors are encountered in the software load process or configuration, troubleshoot
the issue using the GRA 5500 Installation Manual, Garmin P/N 190-01277-00.
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3.18
Interface Confirmation
3.18.1 Lightning System Configuration Load Confirmation
Coordinate the StormScope configuration with Section 8.2 “Stormscope Functional Check”.
1. With PFD1 in configuration mode, use the PFD1 large FMS knob to select OTHER and
the Stormscope configuration page.
Figure 3-13, Stormscope Configuration Page
2. Activate the cursor to highlight the DATA field. Use the small FMS knob to open the drop
down menu then select ‘Config’ and press ENT key on the PFD1.
Figure 3-14, Stormscope Configuration
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3. Verify that the DATA window shows the following:
Hdg: None:
J3-1
Jumper
J3-2
Jumper
Hdg Valid Flag
No Fla
Flag Sense
+invld
J3-4
Open
Hdg Value
<aircraft heading>
Inhibit Line
Off
Antenna Mount
Bottom
J3-3
Open
4. Deactivate the cursor.
NOTE
The DATA window is only updated once every five seconds.
3.19
MD 302 Configuration and Sensor Calibration
NOTE
In the MD 302 Configuration Mode, any changes made to any settings will
NOT be saved until you select ACCEPT CHANGES in the menu prior to
exiting the Configuration Mode.
3.19.1 MD 302 Configuration
1. Open STBY INSTR circuit breaker.
2. Press and hold the MD 302 control knob on the front of the unit.
3. Close STBY INSTR circuit breaker.
4. Release the control knob when the introduction screen appears.
5. In the CONFIGURE MENU, select CONFIGURE DISPLAY by rotating the control knob
to highlight the option and press the control knob to select it.
6. In the CONFIGURE DISPLAY menu, select AIRSPEED UNITS.
7. Select KNOTS.
8. In the CONFIGURE DISPLAY menu, select EXIT.
9. In the CONFIGURE MENU, select CONFIGURE AIRCRAFT.
10. Select PANEL TILT.
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a. If the aircraft was not previously equipped with Collins Pro Line 21 avionics
installed at the Beechcraft factory when the aircraft was new, set the tilt value to
00.0 degrees.
b. If the aircraft had Collins Pro Line 21 avionics installed at the Beechcraft factory
when the aircraft was new, set the tilt value to 04.0 degrees.
11. In the CONFIGURE AIRCRAFT menu, select PANEL ROLL.
12. Set the value to 0.0 degrees.
13. In the CONFIGURE AIRCRAFT menu, select RANGE MMO.
14. Set the value to 0.580 MACH.
15. In the CONFIGURE AIRCRAFT menu, select RANGE MARKINGS per the Table below
for the aircraft model and propeller combination installed.
Range
Range
Range
Marking Marking Marking
#
Type
Color
300 (No
Winglets)
KIAS Value
300 (With
Winglets)
KIAS Value
B300,
B300C
KIAS Value
V1
V2
V1
V2
V1
V2
1
RAD
RED
92
None
95
None
94
None
2
FULL
WHITE
81
100
81
100
81
96
3
HALF
WHITE
100
157
100
157
96
158
4
RAD
BLUE
122
None
122
None
125
None
5
FULL
BAR
259
None
259
None
263
None
16. Enter the range markings for the airframe model and propeller combination required:
a. Highlight the row that needs to be edited and press the control knob to select.
b. Highlight the TYPE field and press the control knob to select the field to edit. The
field background will change to green showing that it can be edited.
c. Choose the color bar TYPE needed (HALF, FULL or RAD (radial)) and press the
control knob to select.
d. Highlight the CLR field and select to enter the color needed (RED, WHI (white),
BLU (blue), or BAR (barber pole)).
e. Highlight the V1 field and select to enter the value needed. There are three digits
that need to be entered. Turn the control knob to change the first digit to the
value needed and press the control knob to set. Repeat for the second and third
digits.
f.
Highlight the V2 field and select to enter the value needed using the same
procedure as V1. Not all V2 values will be set, the RAD and FULL TYPES
automatically update V2 value based on the V1 value entered and are not
changeable.
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NOTES
• The V1 value is the start or lower limit of the color bar range and the V2
value is the upper limit.
• When the RAD (radial) TYPE is selected, the V1 and V2 values will be
the same. The installer can only set the V1 value, the V2 value will be
grayed out and unchangeable.
• When the FULL TYPE and BAR (barber pole) CLR is selected, V2 will
automatically default to MAX and is unchangeable.
• For unused rows, the TYPE should be set to OFF, the CLR should be set
to BLU, and V1 and V2 values should be set to “000”.
g. Continue in sequence through all rows to enter the color bands needed and
select EXIT when done.
17. In the CONFIGURE AIRCRAFT menu, select VNE TABLE.
18. Enter the table information below.
300
B300
#
ALT(FT)
KTS
ALT(FT)
KTS
1
00000
259
00000
263
2
21000
259
21000
263
3
25000
239
25000
242
4
30000
214
30000
217
5
35000
191
35000
194
6
UNUSED
000
UNUSED
000
7
UNUSED
000
UNUSED
000
19. Select EXIT when done entering the table.
20. Select EXIT in the CONFIGURE AIRCRAFT menu.
21. In the CONFIGURE MENU, select CONFIGURE BARO SYNC.
22. Select OFF.
23. In the CONFIGURE MENU, select CONFIGURE DIMMING.
24. Select DIMMING CONTROL.
25. Select EXT 28V.
26. In the CONFIGURE DIMMING menu, select DIMMING CURVE.
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27. Set the seven dimming points below by setting the point at the bottom of the scale and
counting the number of clicks up from 0. The active point that can be adjusted is colored
yellow. To move to the next point to change, press the control knob.
Point 1
1
Point 2
5
Point 3
35
Point 4
100 (top of scale)
Point 5
100 (top of scale)
Point 6
100 (top of scale)
Point 7
2
28. In the CONFIGURE DIMMING menu, select EXIT.
29. In the CONFIGURE MENU, select CONFIGURE DISPLAY.
30. Select ROLL DISPLAY.
31. Select FIXED POINTER.
32. In the CONFIGURE DISPLAY menu, select AIRSPEED MINIMUM.
33. Select 40 KNOTS.
34. In the CONFIGURE DISPLAY menu, select DISPLAY ORIENTATION.
35. Select VERTICAL RIGHT.
36. In the CONFIGURE DISPLAY menu, select HORIZON DISPLAY.
37. Select SHADED.
38. In the CONFIGURE DISPLAY menu, select EXIT.
39. In the CONFIGURE MENU, select CONFIGURE HEADING.
40. Select DISPLAY OFF.
41. In the CONFIGURE MENU, select ACCEPT CHANGES.
NOTE
After selecting ACCEPT CHANGES, the unit will automatically reset and
enter Flight Mode.
42. Press and hold the control knob until the OPTIONS MENU appears.
43. Select INFO >.
44. Select REVIEW CFG.
45. Scroll down to the DIMMING CURVE section and confirm the lighting values entered in
Step 27. If any values are incorrect, reenter the dimming curve configuration to correct.
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3.19.2 Sensor Calibration
1. Connect pitot/static test equipment to the aircraft. Leave the aircraft at ground altitude
and zero airspeed to allow the MD 302 to enter configuration mode. It will not enter
configuration mode if it senses an airspeed input from the pitot/static test equipment.
2. Open STBY INSTR circuit breaker.
3. Press and hold the MD 302 control knob on the front of the unit.
4. Close STBY INSTR circuit breaker.
5. Release the control knob when the introduction screen appears.
6. In the CONFIGURE MENU select CALIBRATE PRESSUES.
7. Using the pitot/static test set, apply an altitude of 5000 ft. and airspeed of 120 knots.
Allow the altitude and airspeed to stabilize at these values before continuing.
8. Select CALIBRATE ALTITUDE.
9. Select YES when CALIBRATING ALTITUDE prompt is displayed.
10. When calibration is complete return to CALIBRATE PRESSURES.
11. Select CALIBRATE AIRSPEED.
12. Select YES when CALIBRATING AIRSPEED prompt is displayed.
13. When calibration is complete return to CONFIGURE MENU.
14. Select ACCEPT CHANGES.
15. MD 302 setup is complete.
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4.2
Servicing Information
G1000 LRU maintenance is ‘on condition’ only. No component-level overhaul is required for
this type design change.
A “cycle” for the purposes of determining inspection requirements is defined as: Engine start-up
and increase to full or partial power (as required during a normal flight), one landing gear
retraction and extension and a complete shutdown.
4.2.1
On Condition Servicing
‘On Condition’ replacement and/or servicing should occur when an item exhibits conditions,
symptoms, and/or abnormalities defined in Section 5 of this manual. Replacement and/or
servicing should be made only after the technician troubleshoots the system to the extent
determined necessary by using the guidance in this manual along with common avionics
maintenance practices.
IMPORTANT!
It is impossible to provide guidance for every conceivable failure scenario
within the scope of this manual. Every effort has been made to provide
comprehensive guidance for possible failures. The information in this
document should always be combined with sound aviation maintenance
practices and a thorough knowledge of the system. Use sound avionics
maintenance practices when working around or on G1000 equipment.
The remainder of this document is organized in the following fashion:
•
Section 4.3 lists maintenance requirements related to the G1000 system.
•
Section 6 gives instructions regarding the removal and replacement of physical G1000
equipment and parts.
•
Section 7 gives configuration and testing instructions to be accomplished if G1000
equipment or parts are removed or replaced.
•
Section 9 specifies system return-to-service procedures.
The beginning of Section 6 provides instructions to check the software part number and version
of each LRU before removing a unit. Procedures in Section 7 require the same check after
LRU replacement and software loading.
IMPORTANT!
All structural repairs associated with this installation are to be addressed
in accordance with the Beechcraft Structural Inspection and Repair Manual
listed in Table 1-1.
NOTE
After replacing or servicing electrical components near the GMU 44
magnetometers, the Magnetometer Interference Test (reference Section 5) and
Magnetometer Calibration Procedure (reference Section 7) must be performed.
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4.2.2
Required Tools
The following tools are needed to perform maintenance tasks on G1000 equipment:
•
Calibrated Milliohm meter, OR
o
Agilent 34410A Ammeter or equivalent
o
Fluke 187 Voltmeter or equivalent
o
Variable DC Power Supply capable of providing 1 amp current
•
#2 Non-Magnetic Phillips Screwdriver
•
3/32” Hex tool
•
Calibrated digital level (Required for AHRS ‘Procedure A’ Calibration)
•
Calibrated VHF NAV/COM/ILS ramp tester or equivalent
•
Calibrated transponder ramp tester or equivalent
•
Calibrated pitot/static ramp tester
•
Outdoor line-of-site to GPS satellite signals or GPS indoor repeater
•
Headset/microphone
•
Ground Power Unit (Capable of supplying 28 Vdc)
•
Calibrated Flight Control Cable Tension Meter or equivalent
•
2 Amp, 24 V, DC Power Supply
•
Calibrated torque wrench capable of measuring 0 – 70 in/lbs
•
Standard sockets & wrenches (3/8”, 9/16”, and 13/16”)
•
Calibrated digital thermometer suitable for measuring ambient temperature
•
Laptop with RS232 emulation software
•
M22885/108T8234 extraction tool
•
An 0.060” 6-Spline wrench
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4.2.3
Special Tools
The following tools may be needed to perform maintenance tasks on G1000 equipment and/or
installation:
•
Servo Gearbox Slip Clutch Adjustment Tool – Garmin P/N T10-00110-01
•
WX-PA portable analyzer kit, Part Number 78-8060-5791-1 (If Stormscope is installed)
•
Gauging Equipment Tool SPF-4 (A1M-BCH-GE)*
•
If the GRA 5500 radar altimeter is installed without RS-422 connections to GIA2, obtain
GRA 5500 Sensor and Main Software from the Garmin Dealer Resource Center at
www.garmin.com and load with the GRA Retrofit Installation Tool part number 006A0451-00. Download the software part number and versions listed in the General
Arrangement Drawing for the GRA 5500. Instructions to download the GRA software
and using the GRA Retrofit Installation Tool are in Section 3.17.
*
The gauging equipment tool is used for the static port inspection for RVSM
compliant aircraft only. This tool is available from Beechcraft. Any alternate
tool authorized in the King Air 300 Series Maintenance Manual for RVSM static
port measurements may be substituted for this tool. Refer to Chapter 34-1000 of the King Air 300 Series Maintenance Manual for more details.
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4.3
Maintenance Intervals
Table 4-1 shows systems and items, installed by this STC, which must undergo tests or checks
at specific intervals. If the interval is shown to be in flight time as well as calendar months, the
first interval reached should be used as the limit.
The inspection time tables used for this STC are aligned with the existing maintenance 200 hr
phase inspection program used in the current King Air 300 Series Maintenance Manual. A
complete inspection cycle for the King Air 300 Series is 800 hours or 24 calendar months,
divided into the following four phases:
Inspection Phase 1: To be performed at 200 hours and every 800 hours thereafter.
Inspection Phase 2: To be performed at 400 hours and every 800 hours thereafter.
Inspection Phase 3: To be performed at 600 hours and every 800 hours thereafter.
Inspection Phase 4: To be performed at 800 hours and every 800 hours thereafter.
Those inspections that are based on flight time, calendar elapsed time or cycles shall have
specific intervals stated in Table 4-1.
IMPORTANT!
As allowed in the King Air 300 Series Maintenance Manual, a tolerance of
+/- 20 hours for all phase inspections.
Special Inspection Items - Calendar limited inspections have a tolerance of
± 12 days per 12 calendar months.
The intention of Garmin is to align this maintenance program as best possible with the existing
King Air 300 Series inspection program. For a complete description of the King Air inspection
program, refer to the Beechcraft King Air 300 Series Maintenance Manual listed in Table 1-1.
Table 4-1, Maintenance Intervals
Item
Description/Procedure
Manual
Section No.
Interval
G1000/GFC700 Equipment
G1000/GFC700
System Visual
Inspections
Complete Visual Inspection of GWX 68 or
GWX 70 Equipment and Wiring located in
Nose Section
4.4
(Table 4-3)
Phase 4
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Nose Avionics Compartment
4.4
(Table 4-4)
Phase 4
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Pilot’s Compartment
4.4
(Table 4-5)
Phase 3
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located on and behind Instrument Panel
4.4
(Table 4-6)
Phase 3
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Cabin
4.4
(Table 4-7)
Phase 3
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Rear Fuselage and Empennage
4.4
(Table 4-8)
Phase 4
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Item
GFC700 Periodic
Check
TAWS Functional
Check
GDU 1050A PFD
(Qty 2)
Description/Procedure
Verify proper operation of the GFC700 by
performing the following:
Pre-Flight Test
AFCS Switch Checks
Autopilot Clutch Overpower Check
Autopilot Operation Checks
Manual
Section No.
Interval
9.11.1,
9.11.2,
9.11.3,
Phase 2 and 4
9.11.5
Periodic TAWS function check
8.3
Phase 4
Removal & Replacement
6.1
On Condition
Removal & Replacement
6.2
On Condition
GMA 1347D Test
7.2.3
Phase 2 and 4
Landing Gear Aural Alert Check
7.2.4
Phase 2 and 4
SiriusXM Audio Suppression Check
7.2.5
Phase 2 and 4
GDU 1550 MFD
GMA 1347D (Qty 2)
GIA 63W IAU (Qty 2)
6.3
Removal & Replacement
GEA 71 EAU (Qty 2)
On Condition
6.4
GTX 335R, GTX
345R, GTX 33( ), or
GTX 3000
Transponder (Qty 2)
Removal & Replacement
6.5
On Condition
7.5.4
24 Calendar Months
GDC 7400 Air Data
Computer (Qty 2)
Removal & Replacement
6.7
On Condition
Special Inspection – Perform Air Data Test.
7.7.3
24 Calendar Months
Special inspection – Perform RVSM Checks
8.12
24 Calendar Months
8.12
On Condition
Removal & Replacement
6.9
On Condition
Magnetic variation database update.
4.6
On Condition
Special Inspection – Perform Air Data Test.
7.7.3
24 Calendar Months
Remove nose compartment pitot/static line
caps at T-fittings located forward of GSU
75B units and check for moisture. Refer to
Garmin drawing 005-00629-44 for line cap
part numbers if replacements are needed
and for torque information.
N/A
24 Calendar Months
Special Inspection - Perform GTX 335R,
GTX 345R, GTX 33( ), or GTX 3000 test.
Perform RVSM checks when:
RVSM checks
GSU 75B ADAHRS
(Qty 2)
•
a static port is removed/installed
•
the RVSM critical region is repaired
or painted
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Item
GSU 75B, GRS 77, or
GRS 7800
AHRS/ADAHRS
(Qty 2)
Description/Procedure
Manual
Section No.
Removal & Replacement
6.9
Magnetic variation database update.
4.6
GMU 44
Magnetometer (Qty 2)
6.10
GDL 69A or GDL 69A
SXM
6.11
GWX 68 or GWX 70
6.16
GMC 710
6.15
GCU 477
6.14
GTS 820/850 Traffic
Unit
6.31
GTS Traffic
Processor
Interval
On Condition
Removal & Replacement
6.31
GRA 5500
6.36
GPA 65 PA/LNA Unit
6.32
GDL 59 Wi-Fi
Datalink
6.34
GSR 56 Satellite
Receiver
6.35
GSD 41 Data
Concentrator
6.37
G1000 Cooling Fan
Fail Annunciation
Check
Verify the operation of the fan power and fan
speed monitoring circuits for GIA1 fan and
GIA2 fan.
9.4
G1000 Cooling Fan
Fail Annunciation
Check
Verify the operation of the fan power and fan
speed monitoring circuits for PFD1 fan, MFD
fan and PFD2 fan and fan fail messages.
9.4
Nose Avionics
Compartment Fans
Operational Check
Functional test of the GIA1 and GIA2 ported
fans. Verify airflow from all fan ports.
4.14
Instrument Panel
Fans Operational
Check
Functional test of the PFD1, MFD and PFD2
cooling fans. Verify airflow from each fan.
4.15
G1000 Redundant
Connection Check*
Verify PRI and SEC power sources for PFD
1, GIA 1, GSU 1 (or GRS 1, and GDC 1).
Verify secondary paths for ADAHRS (or
AHRS and ADC), engine parameters and
GPS data.
Verify the operation of PFD and MFD
Ethernet connections.
Verify ARINC connection between GSU 1
(or ADC 1 and GRS 1) and MFD.
Verify DISPLAY BACKUP button function.
4.10
220 hours max
Engine Data Check*
Verify engine data is available and accurate
with GIA 1 or GIA 2 inoperative.
4.11
820 hours max
820 hours max
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 105
Revision 2
Item
Description/Procedure
Manual
Section No.
Interval
Trim Annunciator
Check*
Verify trim annunciators function properly.
4.12
220 hours max
G1000 Miscompare
Check*
Verify attitude, airspeed, and altitude
miscompare monitors function properly.
4.13
820 hours max
G1000 Alerts
Check for and troubleshoot any alerts
provided in the alert window per the
referenced manual section.
5
On Condition
GPS/WAAS
Antennas
Diversity Transponder
Antenna
Iridium antenna
6.19
Removal & Replacement
Refer to Master Drawing List, listed in Table
1-1, for installation drawings.
6.20
6.21
Wi-Fi Antenna
6.22
GA 58 Traffic
Antennas
6.33
On Condition
Flaps-in-motion
Discrete Input Check
Test the Flaps-in-motion discrete inputs to
the G1000 to verify proper operation.
4.8
Phase 1, 2, 3 & 4
GSA 80 and GSA
9000 Servos
Removal & Replacement.
Refer to Master Drawing List, listed in Table
1-1, for installation drawings.
6.12
On Condition
GSM 86 and GSM
9100 Servo Gear Box
Removal & Replacement.
Refer to the servo install drawings listed in
Master Drawing List, listed in Table 1-1.
6.13
On Condition
GSM 86 Servo Gear
Box Slip Clutch
Torque Check *
For installations with the GSM 86 servo
gearbox, verify that the pitch, roll, yaw and
pitch trim GSM 86 slip clutch torque values
are within acceptable limits
4.9
Special
3,000 hours max
GSM 9100 Servo
Gear Box
Remove the GSM 9100 yaw servo gear box
and send to an Authorized Repair Facility for
servicing.
6.13
Special
20 years max
Rudder Boost
Operation Check
Verify the Rudder Boost operation and
annunciation.
4.17
Phase 1, 2, 3 & 4
WOW and Low
Speed Awareness
Band Check*
Verify the integrity of the wiring interface
between the landing gear safety switch
assembly and the No. 1 and No. 2 GIA
inputs and the air ground status logic.
8.11
220 hours max
Exterior skin
inspection around
antennas*
Inspect the exterior skin around antennas for
cracks and loose and missing fasteners.
4.18
Special
10,000 cycles (initial)
1,000 cycles
(repeat)
* Denotes Airworthiness Limitation Maintenance Requirement (See Section 4.1)
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
Item
Manual
Section No.
Description/Procedure
Interval
G1000 Accessories
Configuration Module
Replacement (Qty 5)
Removal & Replacement.
6.17
GEA 71 Backshell
Thermocouple (Qty 2)
Removal & Replacement.
6.18
GTP 59 OAT Probe
(Qty 2)
Removal & Replacement.
6.8
PFD, MFD, and GIA
Cooling Fans (Qty 5)
Removal & Replacement
Refer to Master Drawing List, listed in Table
1-1, for installation drawings.
N/A
Annunciator/Switch –
Emergency
Frequency
Removal & Replacement.
6.25
On Condition
G1000 Lightning Protection
Electrical Bonding
Test
Perform the Phase 3 electrical bonding
resistance check of G1000 equipment.
4.5.3
Phase 3
Perform the Phase 4 electrical bonding
resistance check of G1000 equipment.
4.5.4
Phase 4
4.4
On Condition
Lightning Strike to
GTP 59 OAT Probe
or Antenna Actual or Suspected
Inspect the antenna/probe and surrounding
installation per
Lightning Strike to the
Aircraft
Inspect the GIA cooling fan discrete output
to the GIA.
Table 4-9.
4.4
(
On Condition
Table 4-9)
Engine/Airframe Sensors
ITT Thermocouple
Cable (Qty 2)
Oil Pressure Sensor
(Qty 2)
Oil Temperature
Sensor (Qty 2)
Torque Transmitter
(Qty 2)
Removal & Replacement:
Refer to King Air 300 Series Maintenance
Manual listed in Table 1-1.
N/A
On Condition
Fuel Flow Transmitter
(Qty 2)
Prop Tachometer
(Qty 2)
Engine Speed
Tachometer (Qty 2)
Signal Conditioner
(Qty 2)
6.23
Removal & Replacement
Annunciator/Switch –
Prop Sync
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
On Condition
6.24
Page 107
Revision 2
Manual
Section No.
Interval
6.28.1
On Condition
N/A
24 Calendar Months
6.28.2
On Condition
N/A
24 Calendar Months
Removal & Replacement
6.28.3
On Condition
Removal & Replacement
6.27.1
On Condition
N/A
24 Calendar Months
Removal & Replacement
6.27.2
On Condition
Removal & Replacement
6.26
On Condition
Capacity test of standby battery.
4.16.2
12 Calendar Months
Standby Battery
Charge Check*
Verify the standby battery is being charged.
4.16.1
220 hours max or
6 Calendar Months,
whichever comes first
Standby Instrument
Electrical Power
Checks*
Verify STBY ATT & STBY ALT vibrator
operate and STBY ATT, STBY ALT & STBY
A/S illumination function on aircraft power
and standby battery power.
(Note: standby compass checked during
existing maintenance)
9.9
220 hours max
Annunciator/Switch Standby Battery
Removal & Replacement
6.24
On Condition
Item
Description/Procedure
Other Equipment
Removal & Replacement
Mechanical Standby
Airspeed Indicator
Static pressure system test according to
14 CFR 91.411 and Part 43 Appendix E.
Removal & Replacement
Mechanical Standby
Altimeter
Mechanical Standby
Attitude Indicator
MD 302 Electronic
Standby Instrument
MD 302 Configuration
Module
L-3 PS-835(C or D)
Standby Battery
4.3.1
Test according to 14 CFR 91.411 and
Part 43 Appendix E.
Test according to 14 CFR 91.411 and
Part 43 Appendix E.
Discontinued Maintenance
Table 4-2 shows a list of inspections and tests that are listed in the King Air 300 Series
Maintenance Manual, but may be no longer required post incorporation of this STC. It is the
responsibility of the installer to ensure that there are no post factory installations that would
require these checks to remain.
Table 4-2, Discontinued Maintenance Intervals
Item
AC Inverter
Description/Procedure
Operational Check
Manual
Interval
Phase Inspections
Phases 1, 2, 3 & 4
* Denotes Airworthiness Limitation Maintenance Requirement (See Section 4.1)
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
IMPORTANT!
For installed equipment not listed in this maintenance manual, use the
inspection procedures set forth in Chapter 05 of the King Air 300 Series
Maintenance Manual, or other appropriate maintenance manual, as the
requirements set forth by those manuals are still applicable. The
requirements set forth by this document take precedence over those set
forth by the King Air 300 Series Maintenance Manual, or other appropriate
maintenance manual, in cases where the requirements conflict.
4.4
Visual Inspection
Perform a visual inspection in accordance with requirements in Table 4-1. Check for corrosion,
damage, or other defects for each of the items listed in Table 4-3 through Table 4-8. Replace
any damaged parts as required. Inspection may require the temporary removal of a unit or
units to gain access to connectors. Follow guidance in Section 6 for equipment removal and
replacement. Refer to the King Air 300 Series Maintenance Manual listed in Table 1-1 for
instructions on removing any access panels.
NOTE
It is recommended that the Phase 3 and Phase 4 electrical bonding checks
contained in Section 4.5 are conducted after the Phase 3 and 4 visual
inspections while access to these zones is still open.
Table 4-3, Nose Section Visual Inspection Procedure
Item
Description/Procedure
Initials
Gain access via the Radome for the following Inspection:
a)
Inspect the GWX 68 or GWX 70 unit, mount, and connectors for corrosion or other
defects. Check the integrity of the SHIELD BLOCK ground attachments to the
harness connector assembly as well as the integrity of the individual shields and their
attachment.
b)
Inspect wire harness for chafing, damage, proper routing of wire bundles and security
of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph
11-96 and the Nose Wire Harness Routing drawing, listed in Table 1-1.
GWX 68 or GWX 70
Table 4-4, Nose Avionics Compartment Visual Inspection Procedure
Item
Description/Procedure
Initials
Gain access via the Nose Equipment Compartment access panel for the following Inspection:
GRS 77 or GRS
7800 (Qty 2)
(if installed)
Inspect the GRS 77 or GRS 7800 units, racks, and connectors for corrosion or other defects.
Check the integrity of the SHIELD BLOCK ground attachments to the harness connector
assembly as well as the integrity of the individual shields and their attachment.
a)
Inspect the GSU 75B units, racks, and connectors for corrosion or other defects. Check
the integrity of the SHIELD BLOCK ground attachments to the harness connector
assembly as well as the integrity of the individual shields and their attachment.
b)
Visually inspect the pitot/static plumbing and ensure it is secure and in good condition
and routed to provide positive moisture drainage.
GSU 75B (Qty 2)
(if installed)
GIA 63W (Qty 2)
Inspect the GIA 63W units, racks, and connectors for corrosion or other defects. Check the
integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as
well as the integrity of the individual shields and their attachment.
G1000 NXi System Maintenance Manual
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Revision 2
Item
Description/Procedure
a)
Inspect the standby battery, rack and connectors for corrosion, or other defaults.
b)
Inspect the standby battery fuses and associated bracket for corrosion or other defects.
Initials
Standby Battery
GIA Avionics Fan
(Qty 2)
Inspect remote avionics fans and hoses for dirt accumulation and other damage. Remove
excess dirt as required.
GTS 820/850
Traffic or GTS
Traffic Processor
(option)
Inspect the GTS 820/850 or GTS Traffic Processor unit (if installed), rack and connectors for
corrosion or other defects. Check the integrity of the shield block ground attachments to the
harness connector assembly as well as the integrity of the individual shields and their
attachment.
LMD Rack and
Modules
Inspect the LMD rack, modules, and terminations for corrosion or other defects.
a)
Inspect bulkhead connectors for security of attachment, corrosion or other defects.
b)
Inspect wire and coax for chafing, damage, proper routing of wire bundles and security
of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph 11-96
and the Nose Wire Harness Routing drawing, listed in Table 1-1 . Pay particular
attention to possible areas of wire chafing such as the middle shelf feed-through hole,
wheel well protrusion etc.
c)
Inspect Ground blocks for security of attachment, corrosion or other defects.
d)
Ensure all connectors are securely fastened.
Nose Wiring
harness
Table 4-5, Pilot’s Compartment Visual Inspection Procedure
Item
Placards
Description/Procedure
Initials
Inspect that all required placards are installed on the left and right control wheels.
Placards must be legible, secure and in good condition. Refer to the Control Wheel
Modification drawing listed in Table 1-1.
Locate equipment in the aft pedestal for the following inspection.
GCU 477
Inspect the GCU 477 unit and connector for corrosion or other defects. Check the
integrity of the SHIELD BLOCK ground attachments to the harness connector assembly
as well as the integrity of the individual shields and their attachment.
ADF control unit
(relocated by STC)
Inspect the ADF control unit and connector for corrosion or other defects. Check the
integrity of the SHIELD ground attachments to the harness connector assembly as well
as the integrity of the individual shields and their attachment.
Pedestal Wiring
Inspect all visible wire harness for chafing, damage, proper routing of wire bundles and
security of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8,
Paragraph 11-96 and the Cabin Wire Harness Routing drawing, listed in Table 1-1.
GTP 59 (Qty 2)
a)
Inspect the GTP 59 units and connectors for corrosion or other defects. Check the
integrity of the SHIELD ground attachments to the harness connector assembly as
well as the integrity of the individual shields and their attachment.
b)
Inspect wire harness for chafing, damage, proper routing of wire bundles and
security of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8,
Paragraph 11-96 and the Cabin Wire Harness Routing drawing, listed in Table 1-1.
G1000 NXi System Maintenance Manual
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Revision 2
Table 4-6, Instrument Panel G1000 Equipment Visual Inspection Procedure
Item
Description/Procedure
Initials
Gain access to behind the instrument panel by removing the PFDs and MFD (see below). Gain access to circuit breaker panels
by removing the screws which fasten the edge lit overlays to the panels
GDU 1050A PFD
(Qty 2) & GDU 1550
MFD
a)
Inspect the PFDs and MFD for any visual damage to the display screens or bezels
including buttons and control knobs.
b)
Remove the MFD and PFDs as described in Section 6.
c)
Inspect the mounting surface and connector for corrosion, heavy oxidation, or other
damage. Check the integrity of the SHIELD BLOCK ground attachments to the
harness connector assembly as well as the integrity of the individual shields and their
attachment.
d)
Do not reinstall GDUs at this time. GDU cutouts provide access for visual inspections
below.
a)
Inspect all fwd bulkhead connectors for security of attachment
b)
Inspect all instrument panel wiring and coax for chafing, damage, proper routing of
wire bundles and security of attachment in accordance with AC 43.13-1B, Chapter 11,
Section 8, Paragraph 11-96 and the Cabin Wire Harness Routing drawing, listed in
Table 1-1. Pay particular attention to possible areas of wire chafing.
c)
Inspect all other exposed G1000 System wiring and coax for chafing, damage, proper
routing of wire bundles and security of attachment in accordance with AC 43.13-1B,
Chapter 11, Section 8, Paragraph 11-96 and the Cabin Wire Harness Routing
drawing, listed in Table 1-1. Pay particular attention to possible areas of wire chafing.
a)
Visually inspect each GDC7400 unit, mount, and connector for corrosion or other
defects. Check the integrity of the SHIELD BLOCK ground attachments to the
harness connector assembly as well as the integrity of the individual shields and their
attachment.
b)
Visually inspect the pitot/static plumbing and ensure it is secure and in good condition
and routed to provide positive moisture drainage.
G1000 Wiring
harness
GDC 7400 Air Data
Computer (Qty 2)
(If installed)
GEA 71 Engine/
Airframe Unit (Qty 2)
Inspect the GEA 71 unit, rack, and connectors for corrosion or other defects. Check the
integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as
well as the integrity of the individual shields and their attachment.
GMA 1347D (Qty 2)
Inspect the GMA 1347D unit (including face of unit), rack and connectors for corrosion or
other defects. Check the integrity of the SHIELD BLOCK ground attachments to the
harness connector assembly as well as the integrity of the individual shields and their
attachment.
PFD and MFD Fans
(Qty 3)
Inspect fans for accumulation of dirt and other damage. Remove excess dirt as required.
GDL 69A or GDL
69A SXM
Inspect the GDL 69A unit, rack, and connectors for corrosion or other defects. Check the
integrity of the SHIELD BLOCK ground attachments to the harness connector assembly as
well as the integrity of the individual shields and their attachment.
GMC 710
Inspect the GMC 710 unit (including face of the unit), mount, and connectors for corrosion
or other defects. Check the integrity of the SHIELD BLOCK ground attachments to the
harness connector assembly as well as the integrity of the individual shields and their
attachment.
Signal Conditioner
(Qty 2)
Inspect the signal conditioner unit, mount, and connectors for corrosion or other defects.
a)
Inspect the standby attitude indicator unit (including face of unit) and connector for
corrosion or other defects. Check the integrity of the harness connector assembly in
accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraphs 11-96 and 11-100
and the Cabin Wire Harness Routing drawing, listed in Table 1-1.
b)
Visually inspect the plumbing and harness connector assembly, and ensure it is
secure and in good condition.
MD 302 Standby
Indicator
Mechanical Standby
Attitude Indicator
Inspect the standby attitude indicator unit (including face of unit) and connector for
corrosion or other defects. Check the integrity of the harness connector assembly in
accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraphs 11-96 and 11-100 and
the Cabin Wire Harness Routing drawing, listed in Table 1-1.
G1000 NXi System Maintenance Manual
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Revision 2
Item
Mechanical Standby
Airspeed Indicator
Mechanical Standby
Altimeter
Description/Procedure
a)
Inspect the standby airspeed indicator unit (including face of unit) and connector for
corrosion or other defects.
b)
Visually inspect the plumbing and harness connector assembly, and ensure it is
secure and in good condition.
a)
Inspect the standby altimeter indicator unit (including face of the unit) and connector
for corrosion or other defects.
b)
Visually inspect the plumbing and harness connector assembly, and ensure it is
secure and in good condition.
a)
Inspect circuit breaker panel wiring and circuit breakers for chafing, damage, other
defects and proper routing of wire bundles and security of attachment in accordance
with AC 43.13-1B, Chapter 11, Section 8, Paragraph 11-96, the appropriate Circuit
Breaker Panel Modification drawing, listed in Table 1-1, and the Cabin Wire Harness
Routing drawing, listed in Table 1-1. Pay particular attention to possible areas of wire
chafing.
b)
Inspect edge lit overlay panels for damage or defect.
c)
Reinstall the circuit breaker edge lit overlays to the circuit breaker panels.
Circuit Breaker
Panels
Placards
Initials
Inspect that all required placards are installed. Placards must be legible, secure and in
good condition. Refer to the Main Instrument Panel Installation drawing listed in Table 1-1.
Reinstall the MFD and PFDs as described in Section 6.
Table 4-7, Cabin Area Visual Inspection Procedure
Item
Antennas
Description/Procedure
Initials
Inspect all external antennas for leading edge erosion and condition of base seals
(GPS/WAAS, top diversity transponder(s), Iridium, top and bottom GA 58 traffic antennas,
if installed)
To gain access for the following Inspections, remove floorboards in cabin at FS 185.00 and FS 246.750
Cabin Wiring
Harness
GFC 700 Equipment
Inspect all exposed wire harness for chafing, damage, proper routing of wire bundles and
security of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph
11-96 and the Cabin Wire Harness Routing drawing, listed in Table 1-1.
a)
Using a flashlight, inspect the roll servo, servo gearbox, connectors, support
structure, and control cables to ensure that no corrosion, chafing, cracks, or other
defects exist.
b)
For the roll servo gearbox, check that the retaining bolt for the slip clutch cartridge is
not damaged or loose.
c)
Have an assistant manually move the aileron control surfaces from stop to stop and
visually observe the servo and control cabling/chain. Ensure there is no binding in
the control cabling or chain, and that the capstan/sprocket rotates freely.
d)
Check the servo control cables in accordance with AC 43.13-1B, Chapter 7, Section
8, Paragraph 7-149 to ensure no fraying, corrosion, or other damage exists. If the
condition of any cable is questionable, replace it with a new one.
e)
Check the tension on the control cables. Refer to the Roll Servo Install drawing,
listed in Table 1-1, for cable tension specifications:
f)
Ensure that each cable is correctly attached to the clamps.
g)
Follow recommended checks for checking main control cables, following the
instructions in Chapter 27, Flight Controls, of the King Air 300 Series Maintenance
Manual.
h)
Reinstall the access panels if no other maintenance is to be performed.
To gain access for the following inspection, remove the left cabin sidewall panel at FS 158.
GPA 65
(GTS 820/850 traffic
option only)
Inspect the GPA 65 PA/LNA unit (if installed), brackets and connectors for corrosion or
other defects. Check the integrity of the shield block ground attachments to the harness
connector assembly as well as the integrity of the individual shields and their attachment.
G1000 NXi System Maintenance Manual
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Revision 2
Table 4-8, Rear Fuselage and Empennage Visual Inspection Procedure
Item
Wi-Fi Antenna
Description/Procedure
Initials
Inspect the external Wi-Fi antenna (if installed) for leading edge erosion and condition of
base seals.
To gain access for the following Inspections, refer to the servo installation drawings and the King Air 300 Series Maintenance
Manual, listed in Table 1-1.
a)
Inspect all exposed wire harness for chafing, damage, proper routing of wire bundles
and security of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8,
Paragraph 11-96 and the Tail Wire Harness Routing drawing, listed in Table 1-1.
Pay particular attention to possible areas of wire chafing.
b)
Verify security of aft bulkhead connectors.
a)
Using a flashlight, inspect the servos, servo gearboxes, connectors, support
structure, and control cables to ensure that no corrosion, chafing, cracks, or other
defects exist.
b)
For pitch and pitch trim servo gearboxes, check that the retaining bolt for the slip
clutch cartridge is not damaged or loose.
c)
For the GSM 9100 yaw servo mount, verify the following are tightly secured: two
capstan retaining screws, six drive shaft seal screws, and hole plug. If any of these
items are missing or loose, remove the servo mount and send to an Authorized
Service Center for repair. Also visually inspect the hydrophobic vent and remove any
obstructions if present.
d)
Have an assistant manually move the control surfaces and elevator trim wheel from
stop to stop and visually observe the corresponding servo and control cabling.
Ensure there is no binding in the control cabling, and that the capstan rotates freely.
e)
Check the servo control cables in accordance with AC 43.13-1B, Chapter 7, Section
8, Paragraph 7-149 to ensure no fraying, corrosion, or other damage exists. If the
condition of the cable is questionable, replace it with a new one.
f)
Check the tension on the control cables. Refer to the respective servo installation
drawing listed in Table 1-1 for cable tension specifications.
Tail Wiring Harness
GFC 700 Equipment
g)
Ensure that each cable is correctly attached to the clamps.
h)
Follow recommended checks for checking main control cables, following the
instructions in Chapter 27, Flight Controls, of the King Air 300 Series Maintenance
Manual, listed in Table 1-1.
i)
Reinstall the access panels if no other maintenance is to be performed.
The GMU 44 units are mounted in the tailcone or the horizontal stabilizer. Refer to Section 6.10 for details on gaining access to
the GMU.
For each GMU 44, do the following:
GMU 44 (Qty 2)
a)
Remove the three Phillips screws holding the GMU to the mounting bracket. Be sure
to use a non-magnetic screwdriver to avoid harming the GMU.
b)
Carefully remove the assembly, taking care not to damage unit or wiring, and inspect
the GMU 44 and mounting plate.
c)
Inspect the mounting hardware and GMU 44 for corrosion or other damage.
d)
Inspect all exposed GMU wiring and ensure no chafing, wear, or other damage exists
in accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph 11-96 and the
Wire Harness Installation, Tail drawing, listed in Table 1-1. Pay particular attention to
possible areas of wire chafing.
e)
Reinstall the GMU 44.
GRA 5500 Radar
Altimeter
Inspect the GRA 5500 unit (if installed) and connectors for corrosion or other defects.
Check the integrity of the shield block ground attachments to the harness connector
assembly as well as the integrity of the individual shield and their attachment.
GTX 335R, GTX
345R, GTX 33 ( ) or
GTX 3000 (Qty 2)
Inspect the GTX units, shelf, brackets and connectors for corrosion or other defects.
Check the integrity of the shield block ground attachments to the harness connector
assembly as well as the integrity of the individual shields and their attachment.
GDL 59
(Wi-Fi option only)
Inspect the GDL 59 unit (if installed), shelf, brackets and connectors for corrosion or other
defects. Check the integrity of the shield block ground attachments to the harness
connector assembly as well as the integrity of the individual shields and their attachment.
GSR 56
(iridium option only)
Inspect the GSR 56 unit (if installed), shelf, brackets and connectors for corrosion or other
defects. Check the integrity of the shield block ground attachments to the harness
connector assembly as well as the integrity of the individual shields and their attachment.
G1000 NXi System Maintenance Manual
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Revision 2
Item
GSD 41 (FDR option
only)
Description/Procedure
Initials
Inspect the GSD 41 unit (if installed), shelf, brackets and connectors for corrosion or other
defects. Check the integrity of the shield block ground attachments to the harness
connector assembly as well as the integrity of the individual shields and their attachment.
Table 4-9, Lightning Strike Inspection Procedure
Item
Description/Procedure
GTP 59 OAT Probe
or Antenna
A post lightning strike inspection must be done for a suspected or actual lightning strike to
antennas or the OAT probes. Inspect antenna/probe and surrounding installation to ensure
that there is no structural damage around the areas where lightning may have attached. If
there is visible sign of damage to the probe or antenna, then it should be replaced per
Section 6. Refer to the Beechcraft Structural Inspection and Repair Manual listed in Table
1-1 for any aircraft structural repairs.
GMU 44 (Qty 2)
A “Magnetometer Interference Test” per Section 5.17.4 and “GSU 75B, GRS 77, or GRS
7800 and GMU 44 Magnetic Calibration” per Section 7.10.3 must be performed after a
suspected or actual lightning strike. A lightning strike can result in a change in the
magnetic properties of steel components in the area of the magnetometers which can
cause unacceptable magnetic interference levels.
GIA Fans
Verify the GIA cooling fan discrete out is correctly activating when the fan is not working by
performing tests per Section 9.4.
4.5
Initials
Electrical Bonding Test
The following bonding tests are provided for G1000-equipped King Air 300 Series aircraft as a
requirement beyond what is given in the aircraft maintenance manual. The electrical bonding
checks are split into two tests, Phase 3 Electrical Bonding Test and Phase 4 Electrical bonding
test. This places the bonding test requirement for each G1000 LRU in the same phase as the
visual inspection of that zone to minimize access requirements.
4.5.1
Requirements
All G1000 equipment must be installed. Gain access for the procedure listed below in Section
4.5.3 and 4.5.4 as required and in accordance with the aircraft maintenance manual. It is
recommended that these tests are conducted after visual inspection of the zone to minimize
access requirements.
4.5.2
Test Equipment
A milliohm meter and Kelvin probes are recommended for this test. However, an alternate
method may be used to provide equivalent results by using the following procedure and a
standard voltmeter, power supply with adjustable current limit, and ammeter. The test set up for
this alternate method is described below.
All test equipment used for the bond checks must be calibrated.
1. Connect the positive lead of the power supply to airframe ground. Connect/touch the
positive lead of the voltmeter to the same point.
NOTE
Ensure that the voltmeter and power supply probes do not touch, so as not to
induce contact resistance.
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2. Touch negative lead of power supply to each of the test points listed while performing
Step 3. At each required point, configure the power supply to produce 1 amp before
measuring voltage. (Use an ammeter to ensure current is within minimum of 1 amp
±100 milliamp at each point). Do not allow the reference current to exceed 1.5 amps for
safety.
3. With the current set to 1A, the voltage reading will be the value of the bonding
resistance. Set the voltmeter to measure millivolts and null the reading. Measure the
voltage from airframe ground (step 1) to each required test points and record the
voltage. (Perform Step 2 at each required point and ensure that minimum of 1 amp
±100 milliamp is present when measuring the voltage.)
TIP: When a 1A current is used all the millivolt readings are the same as mΩ, and
required no further calculation of bond resistance. If 1 amp reference current cannot
be maintained and is higher divide the measured voltage by current to get the
resistance value. Alternatively, calculate the percentage increase in current and then
reduce the measured voltage reading by the same percentage. Example: If the
measured current is 1.2 amps, (20% high from the desired 1 amp current) and the
measured voltage is 3.0 mV, then the value recorded will be 3 mV reduced by 20%
which is 2.5 mV which is the same as 2.5 mΩ.
4.5.3
Phase 3 Electrical Bonding Procedure
Using one of the two measurement methods in Section 4.5.2 record the bonding measurement
for the following equipment. Some equipment in the list is optional and may not be installed.
Ensure that the PFD1 unit, PFD2 unit, MFD unit, and GMC 710 test points, no more than 30 mΩ
is present. Ensure that at other unit test points, no more than 5 mΩ is present.
Pilot Compartment
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Top metal case of PFD 1: __________ mΩ
PFD1 Cooling fan metal base: __________ mΩ
Top metal case of PFD 2: __________ mΩ
PFD2 Cooling fan metal base: __________ mΩ
Top metal case of MFD: __________ mΩ
MFD Cooling fan metal base: __________ mΩ
Top metal case of GMA 1347D #1: __________ mΩ
Top metal case of GMA 1347D #2: __________ mΩ
Top metal case of GMC 710: __________ mΩ
GEA 71 #1 body: __________ mΩ
GEA 71 #2 body: __________ mΩ
GDC 7400 #1 body (if installed): __________ mΩ
GDC 7400 #2 body (if installed): __________ mΩ
OAT 1 Probe base nut (inside fuselage): __________ mΩ
OAT 2 Probe base nut (inside fuselage): __________ mΩ
GDL 69A body: __________ mΩ
Engine Signal Conditioner #1 near mounting holes of case: __________ mΩ
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•
•
Engine Signal Conditioner #2 near mounting holes of case: __________ mΩ
Top metal case of GCU 477: __________ mΩ
Cabin Compartment
•
•
4.5.4
GSA 80 (Roll) Servo body: __________ mΩ
GPA 65 body (if installed): __________ mΩ
Phase 4 Electrical Bonding Procedure
Using one of the two measurement methods in Section 4.5.2 record the bonding measurement
for the following equipment. Some equipment in the list is optional and may not be installed.
Ensure that at each other test point, no more than 5 mΩ is present.
Nose Section
•
GWX 68 or GWX 70 body: __________ mΩ
Nose Avionics Compartment
•
•
•
•
•
•
GIA 1 top: __________ mΩ
GIA 2 top: __________ mΩ
GSU 75B, GRS 77, or GRS 7800 #1 metal base: __________ mΩ
GSU 75B, GRS 77, or GRS 7800 #2 metal base: __________ mΩ
Standby battery: __________ mΩ
GTS 820/850/Processor metal base: __________ mΩ
Rear Fuselage and Empennage
•
•
•
•
•
•
•
•
•
•
•
GMU 44 #1 metal base: __________ mΩ
GMU 44 #2 metal base: __________ mΩ
GSA 80 (Pitch) Servo body: __________ mΩ
GSA 80 (Pitch Trim) Servo body: __________ mΩ
GSA 9000 (Yaw) Servo body: __________ mΩ
GRA 5500 Radar Altimeter __________ mΩ
GTX 335R #1, GTX 345R #1, GTX 33 #1, or GTX 3000 #1 top: __________ mΩ
GTX 335R #2, GTX 33 #2, or GTX 3000 #2 top: __________ mΩ
GDL 59 top: __________ mΩ
GSR 56 metal base: __________ mΩ
GSD 41 top: __________ mΩ
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Antennas
Test points are between the inside connector body and nearby exposed structure with coaxes
disconnected.
•
•
•
4.6
GA 36 (GPS #1): __________ mΩ
GA 37 (GPS #2): __________ mΩ
GA 58 (GTS Traffic): __________ mΩ
GSU 75B, GRS 77, or GRS 7800 Earth Magnetic Field Updates
The GSU 75B, GRS 77, or GRS 7800 utilizes an Earth magnetic field model which is updated
once every five years. The update is expected to be available from Garmin every five years, as
long as the GSU 75B, GRS 77, or GRS 7800 remain Garmin-supported products.
The G1000 system alerts the operator that the magnetic field database is out of date by issuing
the message “AHRS SERVICE – AHRS Magnetic-field model needs update”. Garmin will
distribute updates as part of the navigation database cycle. If the IGRF model in the update is
newer than the model installed, a prompt will appear for each GRS/GSU (Select “OK” to update
the IGRF Magnetic Field Model). Use the FM Knob and ENT key to select “OK”.
4.7
GSA 80 Greasing Procedure
The GSA 80 servo greasing procedure is required only when the GSA 80 is removed and
reinstalled. Refer to Section 6.12 for details.
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4.8
Flaps-in-motion Discrete Input Check
To perform this check, all G1000 and GFC 700 equipment must be installed and operational.
Start PFD1 in Configuration Mode and go to the GIA Page Group and select the GIA I/O
Configuration Page using the FMS knob. Perform the following checks:
Figure 4-1, GIA I/O Page
False
Invalid
True
Valid
Figure 4-2, Discrete Indications
1. Verify the DATA indicators of the discrete inputs labeled ‘FLAP EXTEND’ and ‘FLAP
RETRACT’ show an invalid condition.
2. Extend the flaps down. While the flaps are traveling down, check that the DATA
indicator of the discrete input labeled ‘FLAP EXTEND’ changes to a valid condition.
3. When the flap motion is completed, verify the DATA indicators of the discrete inputs
labeled ‘FLAP EXTEND’ and ‘FLAP RETRACT’ show an invalid condition.
4. Retract the flaps up. While the flaps are traveling up, check that the DATA indicator of
the discrete input labeled ‘FLAP RETRACT’ changes to a valid condition.
5. When the flap motion is completed, verify the DATA indicators of the discrete inputs
labeled ‘FLAP EXTEND’ and ‘FLAP RETRACT’ show an invalid condition.
6. Repeat steps 1 through 5 for GIA2.
7. The flap discrete input check is complete.
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4.9
GSM 86 Slip Clutch Torque Check Procedure
Perform the test per Sections 4.9.1 (preferred) or 4.9.2. To perform the procedure, all G1000
system equipment must be installed and operational.
4.9.1
Automated Slip Clutch Test Procedure
1. Before starting test, select the AVIONICS MASTER PWR, EXT PWR, and BATT
switches to OFF.
2. Press and hold the ENT key on PFD1 while selecting the AVIONICS MASTER PWR,
EXT PWR, and BATT switches to ON.
3. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of
PFD1.
(Steps 1 through 3 put PFD1 in Configuration Mode and PFD2 / MFD in normal mode.)
4. With the MFD in Normal Mode, press the red DISPLAY BACKUP button on the pilot’s
GMA audio panel to place the MFD in reversion mode.
5. With PFD1 in Configuration Mode, go to the GFC Page Group and select the GFC
STATUS page using the FMS knobs.
Figure 4-3, GFC Status Page
IMPORTANT!
It is highly recommended that the following test be performed at
temperatures between 50° F and 120° F.
6. Use GIA 1 in the SELECT GIA UNIT field for these tests. Use the FMS knob to select
the desired servo (Pitch, Roll, Yaw or Pitch Trim).
7. Verify that the Monitor Board and Control Board PFT status fields show PASSED.
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8. Verify that the aircraft control surface to be checked is free to travel throughout its range
of motion.
9. Press the Test SVO softkey on the PFD. Follow prompts to begin the test.
IMPORTANT!
If the test must be stopped, firmly grasp the aircraft control being moved
and press the red AP DISC switch on the aircraft control wheel. If an
abnormal disconnect of a servo occurs, reset the AFCS SERVO circuit
breaker and repeat the test.
10. When test is completed, verify the CLUTCH TEST PASS message is displayed on the
MFD.
11. Repeat steps 6 through 10 for each servo axis (Pitch, Roll, and Pitch Trim). Yaw is not
tested.
12. If the CLUTCH TEST FAIL message is displayed on the MFD for any axis, repeat the
test twice in the failed axis. If the tests do not pass, the GSM 86 slip clutch cartridge
must be removed from the aircraft and either be retested using the Manual Slip Clutch
Test Procedure or replaced.
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4.9.2
Manual Slip Clutch Test Procedure
This test is an alternative to the automated and manual slip clutch test procedures. The GSM
86 servo gearbox does not have an adjustable slip clutch; however, the torque value can be
measured using this procedure.
IMPORTANT!
This adjustment requires the use of the Garmin servo adjustment fixture,
P/N T10-00110-01. For detailed operating instructions for the fixture,
refer to GSA8X / GSM85(A) Installation Manual, listed in Table 1-2.
It is highly recommended that the following test be performed at
temperatures between 50° F and 120° F.
1. Remove the GSM 86 servo gearbox as per Section 6.13.
2. Place the GSM 86 servo gearbox on the slip-clutch adjustment fixture and secure with
the toggle clamps. Install the fixture cable between the capstan under test and the
fixture capstan. Remove the slack in the cable using the tension adjustment knob.
Tighten the two wingnuts on bottom of fixture while holding the top thumbscrews.
3. Attach a socket to a calibrated torque wrench of appropriate range and place on top of
the fixture capstan. Adjust the wrench support fixture so that it contacts the handle in
the appropriate location.
4. Connect a 2 Amp, 24 V, DC power supply to the fixture.
5. Place the solenoid switch to "on" and move the direction switch to the clockwise or
counter-clockwise position. Allow the clutch to rotate at least one revolution in each
direction (note: the capstan itself is fixed.)
6. Observe the torque reading for at least two full revolutions in each direction. Ensure the
minimum and maximum torque readings are within the tolerance specified.
7. If the minimum and maximum torque values are within the specified range in Table 4-10,
the GSM slip clutch is acceptable. Reinstall the GSM 86 servo gearbox per Section
6.13.
8. If the minimum and maximum torque values are not within the specified range in Table
4-10, the GSM 86 slip clutch cartridge must be replaced.
Servo
GSM 86
Table 4-10, GSM 86 Slip Clutch Torque Settings
Pitch Trim
Pitch
Roll
66 -9/+10 in-lbs
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135 ±20 in-lbs
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4.10
G1000 Redundant Connection Check
Perform the following steps to verify the following:
(A) The primary (PRI) and secondary (SEC) power sources for GIA 1, GRS 1, PFD 1, and
GDC 1.
(B) The AHRS and ADC data path to PFD.
(C) PFD and MFD Ethernet connection (includes ARINC connection between ADC and MFD
and DISPLAY BACKUP button function).
(D) Engine data availability to the displays and GPS data availability to the AHRS with either
GIA inoperative.
(A) PRI and SEC power sources for PFD 1, GIA 1, GSU 1, GRS 1 and GDC 1 check
1. Connect a ground power unit to the external power receptacle and turn on the ground
power unit.
2. Set the BAT, EXT PWR, and AVIONICS MASTER PWR switches to ON.
3. With the G1000 system in normal mode, pull the following circuit breakers on the right
hand circuit breaker panel:
•
PFD 1 (PRI)
•
AHRS 1 (PRI) or ADAHRS 1 (PRI)
•
ADC 1 (PRI) if installed.
•
GIA 1 (PRI)
4. Wait at least 5 seconds, then verify the data on PFD1 remains valid and the following
alert messages are not present:
•
GIA 1 FAIL (or any related message such as COM1, NAV1, XPDR1, GPS1)
•
AHRS 1 FAIL
•
ADC 1 FAIL
•
FAILED DATA PATH
5. Close the circuit breakers listed in step 3.
6. Repeat step 4.
7. Pull the following circuit breakers on the right hand circuit breaker panel:
•
PFD 1 (SEC)
•
AHRS 1 (SEC) or ADAHRS 1 (SEC)
•
ADC 1 (SEC) if installed
•
GIA 1 (SEC)
8. Wait at least 5 seconds, then repeat step 4.
9. Close the circuit breakers listed in step 7.
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(B) AHRS and ADC data path check
1. Verify there are no AHRS loss of data messages, such as:
•
AHRS not receiving any GPS information
•
AHRS not receiving backup GPS information
•
AHRS using backup GPS source
2. Place the G1000 in configuration mode.
3. In the GIA page group, go to the GIA RS-232/ARINC 429 CONFIG page.
4. With GIA1 selected in the SELECT UNIT window, verify the following indicators are
green:
•
RS232 Channel 1 [(GDC72 #1) or (GDC74 #1)]
•
RS232 Channel 6 [(GRS79 #1), (GRS77 #1), or (GRS7800 #1)]
•
ARINC 429 IN2 [(GSU75 #2), (GRS77 #2) or (GRS7800 #2)]
•
ARINC 429 IN5 [(GDC74 #1)] (only if a GDC 7400 installed)
•
ARINC 429 IN6 [(GSU75 #1), (GRS77 #1), or (GRS7800 #1)]
(Ref. Section 5.1.1.2.)
5. With GIA2 selected in the SELECT UNIT window, verify the following indicators are
green:
•
RS232 Channel 1 [(GDC72 #2) or (GDC74 #2)]
•
RS232 Channel 6 [(GRS79 #2), (GRS77 #2), or (GRS7800 #2)]
•
ARINC 429 IN2 [(GSU75 #1), (GRS77 #1), or (GRS7800 #1)]
•
ARINC 429 IN5 [(GDC74 #2)] (only if a GDC 7400 is installed)
•
ARINC 429 IN6 [(GSU75 #2), (GRS77 #2), or (GRS7800 #2)]
(Ref. Section 5.1.1.2.)
6. In the GDU page group, go to the GIA RS-232/ARINC 429 CONFIG page.
7. With PFD1 selected in the SELECT UNIT window, verify the following indicators are
green:
•
ARINC 429 IN1 [(GSU75 #1), (GRS77 #1), or (GRS7800 #1)]
•
ARINC 429 IN2 [(GDC72 #1) or (GDC74 #1)]
(Ref. Section 5.1.1.1.)
8. With PFD2 selected in the SELECT UNIT window, verify the following indicators are
green:
•
ARINC 429 IN1 [(GSU75 #2), (GRS77 #2), or (GRS7800 #2)]
•
ARINC 429 IN2 [(GDC72 #2) or (GDC74 #2)]
(Ref. Section 5.1.1.1.)
9. Restart the G1000 in normal mode.
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(C) PFD and MFD Ethernet connection check (includes ARINC connection check between
ADC1 and MFD and between GRS1 and MFD, and the DISPLAY BACKUP button check)
1. On the right hand circuit breaker panel, open the MFD circuit breaker:
2. Verify NAV 1, COM 1, NAV 2, and COM 2 remain valid on both PFD 1 and PFD 2.
3. Close the MFD circuit breaker and wait for MFD to initialize.
4. Open the PFD 2 circuit breaker.
5. Press the DISPLAY BACK UP button on the Pilot’s GMA 1347D audio panel.
6. Verify NAV 2 and COM 2 are each replaced by a red X and NAV 1 and COM 1 remain
valid on both the MFD and PFD 1.
7. Press the DISPLAY BACK UP button on the Pilot’s GMA 1347D audio panel to return to
normal mode.
8. Close the PFD 2 circuit breaker and wait for PFD 2 to initialize.
9. Open the PFD 1 (PRI) and PFD 1 (SEC) circuit breakers.
10. Press the DISPLAY BACK UP button on the Co-pilot’s GMA 1347D audio panel.
11. Verify NAV 1 and COM 1 are each replaced by a red X and NAV 2 and COM 2 remain
valid on both the MFD and PFD 2.
12. Verify ADC 1 data and GRS 1 data can be displayed on the MFD.
13. Press the DISPLAY BACK UP button on the Co-pilot’s GMA 1347D audio panel to return
to normal mode.
14. Close the PFD 1 (PRI) and PFD 1 (SEC) circuit breakers and wait for PFD 1 to initialize.
(D) Engine data availability to the displays and GPS data availability to the AHRS with
either GIA inoperative check
1. Open GIA1 primary and secondary CBs.
2. Verify the following:
•
NAV 1 and COM 1 tuning fields on PFD 1 and PFD 2 are invalid (red X).
•
L/R engine data remains valid.
•
XPDR1 is Inoperative.
•
GMA1 is Inoperative.
•
AHRS1 is using backup GPS source.
•
AHRS2 not receiving backup GPS Information.
•
An amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2.
•
AHRS and ADC data remain valid on PFD 1 and PFD 2.
3. Close GIA1 primary and secondary CBs. Allow system to re-acquire satellites and
return to normal display modes.
4. Open GIA2 CB.
5. Verify the following:
•
NAV 2 and COM 2 tuning fields on PFD 1 and PFD 2 are invalid (red X).
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•
L/R engine data remains valid.
•
XPDR 2 is Inoperative.
•
GMA 2 Is Inoperative.
•
AHRS 2 is using backup GPS source.
•
AHRS 1 not receiving backup GPS Information.
•
An amber BOTH ON GPS1 is displayed on PFD 1 and PFD 2.
•
AHRS and ADC data remain valid on PFD 1 and PFD 2.
6. Close GIA2 CB. Allow system to re-acquire satellites and return to normal display
modes.
7. Open GIA1 primary and secondary CBs and GIA2 CB.
8. Verify the following:
•
NAV 1, COM 1, NAV 2, and COM 2 flag invalid on both PFD 1 and PFD 2.
•
GPS CDI flags DR on PFD.
•
NAV 1 & NAV 2 CDI loses deviation bar.
•
XPDR field flags invalid on PFD.
•
Engine Instrument field flags invalid on MFD.
•
All AHRS & ADC fields remain valid.
•
Red AFCS status annunciation given.
•
If equipped with TAWS, TAWS FAIL annunciation given.
•
If equipped with ADF and/or DME, ADF/DME windows flag invalid.
9. Restore power to both GIA units. The G1000 Redundant Connections Check is
complete.
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4.11
Engine Data Check
Accomplish this section to verify the engine data availability and validity for ITT and torque.
Remove the left and right engine cowling (Ref. King Air 300 Series Maintenance Manual,
Chapter 71-10-00) to gain access to the engine harness connectors and reinstall cowling when
testing is complete. Required test equipment is provided in Table 4-11. Any product
conforming to the specification listed may be used.
Test Equipment
Requirement
Calibrated DC Power Supply
0-100 mVDC, 0-10 VDC
ITT Tester
200C-1200C
Table 4-11, Engine Data Check Test Equipment
4.11.1 ITT
1. Disconnect all thermocouple wires except for the Alumel-Green #10 and Chromel-White
#8 leads from the left hand engine thermocouple junction block mounted to the gas
generator case.
2. Connect the DC Power Supply or ITT Tester (or equivalent) across the Alumel-Green
#10 (-) and Chromel-White #8 (+) leads of the thermocouple junction block. Make sure
the polarity of the Alumel and Chromel leads are strictly observed when making
connections.
3. Apply external power to aircraft and start the G1000 in normal mode.
4. Verify the gauge indications at the test points in Table 4-12 are within specified
tolerances.
NOTE
If the ITT Tester is not temperature compensated or if using the DC Signal
method, use the chart shown in Figure 4-4 to convert the ambient temperature
to millivolts and subtract from the DC Signal value in Table 4-12.
Test Point
(degC)
DC signal
(mV, subtract
temp offset)
Indication
(degC)
200
8.137
200 +/- 17
400
16.395
400 +/- 17
600
24.902
600 +/- 12
800
33.277
800 +/- 7
1000
41.269
1000 +/- 12
1200
48.828
1200 +/- 17
Table 4-12, ITT Indication Test Points
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5. On the right hand circuit breaker panel, open the GIA1 (PRI) and GIA1 (SEC) circuit
breakers, and verify the last observed ITT indication remains unchanged. Reset the
GIA1 (PRI) and GIA1 (SEC) circuit breakers.
6. Repeat Table 4-12 test for the right engine gauge using the right engine thermocouple
junction block.
7. Pull the GIA 2 circuit breaker, and verify the last observed ITT indication remains
unchanged. Reset the GIA 2 circuit breaker.
8. Turn off the G1000 system and remove external power from aircraft.
9. Reconnect all thermocouple wires to the junction blocks and torque nuts per Beechcraft
King Air 300 Series Maintenance Manual, Chapter 77-00-00.
Figure 4-4, Ambient Temperature Conversion Chart
4.11.2 Torque
1. Disconnect the left engine firewall connector J102 and right engine firewall connector
J103.
2. Inject a DC voltage into GEA 1 by connecting the DC power supply to the left engine
firewall connector-pins J102-C (HI) and J102-R (LO).
3. Apply external power to aircraft and start the G1000 system in normal mode.
4. Verify the gauge indications at the test points in Table 4-13 are within the specified
tolerances.
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Test Point (VDC)
Torque Indication (%)
0.000 +/- .02
0 +/- 2
1.035 +/- .02
42 +/- 2
1.725 +/- .02
75 +/- 2
2.300 +/- .02
100 +/- 2
Table 4-13, Torque Indication Test Points
5. On the right hand circuit breaker panel, open the GIA1 (PRI) and GIA1 (SEC) circuit
breakers, and verify the last observed torque indication remains unchanged. Reset the
GIA1 (PRI) and GIA1 (SEC) circuit breakers.
6. Repeat Table 4-13 test for the right engine by injecting a DC voltage into GEA 2 by
connecting the DC power supply to the right engine firewall connector-pins J103-C (HI)
and J103-R (LO).
7. Pull the GIA 2 circuit breaker, and verify the last observed torque indication remains
unchanged. Reset the GIA 2 circuit breaker.
8. Turn off the G1000 system and remove external power from aircraft.
9. Reinstall and safety the left J102 and right J103 engine firewall connectors.
4.12
Trim Annunciator Check
This procedure checks the pitch trim (PTRM) annunciation from both GIA 1 and GIA 2 and the
mis-trim AFCS status alerts.
1. Ensure the G1000 is in normal mode, autopilot is not engaged, and the AFCS mode
controller XFR key is selected to the pilot side.
2. Press the left part of the pilot’s pitch-trim switch upwards for approximately 10 seconds
and verify that the red PTRM annunciation is displayed on both PFD 1 and PFD 2.
3. Release the switch and wait for the PTRM annunciation to clear.
4. Press the left part of the pilot’s pitch-trim switch downwards for approximately 10
seconds and verify that the red PTRM annunciation is displayed on both PFD 1 and PFD
2.
5. Release the switch and wait for the PTRM annunciation to clear.
6. Repeat Steps 2 through 5 for the right part of the pilot’s pitch-trim switch.
7. Repeat Steps 2 through 6 for the copilot’s pitch-trim switch.
8. Using the AFCS mode controller, select copilot side by pressing the XFR key on the
mode controller (changes active GIA to GIA 2).
9. Repeat Steps 2 through 7 and verify annunciations are displayed on both PFD 1 and
PFD 2.
10. Using the AFCS mode controller, re-select pilot side by pressing XFR key on the mode
controller (changes active GIA back to GIA 1).
11. Hold the control yoke with elevators and ailerons in the neutral positions (control wheel
level and at the mid-point position between full forward and full aft). Position the pitch
trim wheel to 0° degrees.
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12. Press the Go Around button on the throttle and engage the autopilot. Apply a forward
load on the control yoke. Verify that the pitch trim wheel rotates in the UP direction.
13. Disengage the autopilot and flight director. Use the pitch-trim switch (or the pitch-trim
wheel) to trim full down.
14. Hold the control yoke in the full forward position.
15. Engage the autopilot, apply firm aft pressure on the control yoke for approximately 10
seconds, allowing the pitch-trim wheel to move freely. Verify that the amber ELE↓
annunciator is displayed on both PFD 1 and PFD 2.
16. Disengage the autopilot and use the pitch-trim switch (or the pitch-trim wheel) to trim full
up.
17. Move the control yoke to the full aft position and hold.
18. Press the Go Around button on the throttle and engage the autopilot. Apply firm forward
pressure on the control yoke for approximately 10 seconds, allowing the pitch-trim wheel
to move freely. Verify that the amber ELE↑ annunciator is displayed on both PFD 1 and
PFD 2.
19. Disengage the autopilot.
NOTE
If the ELE annunciation appears during any of the following steps, reset the trim
wheel and repeat the test step.
20. Use the pitch-trim switch (or the pitch-trim wheel) to trim full down.
21. Hold the elevator in the neutral position (control wheel at the mid-point position between
full forward and full aft), press the HDG and ALT buttons on the mode controller and
center the heading bug.
22. Engage the autopilot and turn the heading knob to set the heading bug to the right of
center. Hold the control yoke centered for approximately 10 seconds. Verify that the
amber AIL→ annunciator is displayed on both PFD 1 and PFD 2.
23. Turn the heading knob to set the heading bug to the left of center. Hold the control yoke
centered for approximately 10 seconds. Verify that the amber ←AIL annunciator is
displayed on both PFD 1 and PFD 2.
24. Disengage the autopilot and clear all flight director modes.
25. Ensure the aircraft is on the ground and the nose wheel is approximately straight.
NOTE
In the following steps, slow, continuous rudder pedal movement is needed
to overcome clutch torque. If pedal movement is stopped before the
annunciation is displayed, return the rudder pedals to the neutral position
and repeat step.
26. Engage the yaw damper.
27. Begin to apply pressure slowly to the right rudder pedal. When pedal resistance is felt,
continue to apply pressure slowly for approximately 20 to 30 seconds.
28. Verify that the amber ←RUD annunciator is displayed on both PFD 1 and PFD 2.
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29. Reposition the rudder pedals to the neutral position.
30. Begin to apply pressure slowly to the left rudder pedal. When pedal resistance is felt,
continue to apply pressure slowly for approximately 20 to 30 seconds.
31. Verify that the amber RUD→ annunciator is displayed on both PFD 1 and PFD 2.
32. Reposition the rudder pedals to the neutral position.
33. Disengage yaw damper.
34. The Trim Annunciator Check is complete.
4.13
G1000 Miscompare Checks
This procedure will check the AHRS, airspeed and altitude miscompare monitors. Accomplish
the following checks with the aircraft positioned where it can receive GPS signals and magnetic
heading. Access to AHRS 1/ADAHRS 1 and AHRS 2/ADAHRS 2 is required during this test.
1. Unfasten the AHRS 1/ADAHRS 1 and 2 units and set loose in their racks. Do not
disconnect connectors or pitot/static lines.
2. Connect a pitot/static test set to the aircraft left side pitot and static ports (pilot’s side).
Do not connect a pitot/static test set to the right side pitot/static ports (copilot’s side) at
this time.
3. Ensure the G1000 is operating in normal mode.
4. Set the baro-correction on PFD 1 and PFD 2 to STD.
5. On the AFCS mode controller, press the ALT, HDG, and AP buttons and verify autopilot
engages.
6. Slowly increase the altitude to simulate an altitude miscompare of greater than 200 ft.
Verify PFD 2 altitude does not increase, autopilot does not disconnect, and an amber
ALT box is displayed in the altitude tape of PFD 1 and PFD 2.
7. Reduce left side altitude to ambient pressure. Verify the amber ALT box is removed
from both PFD(s).
8. Repeat Steps 6 and 7 except reducing the altitude to simulate a miscompare greater
than 200ft.
9. Connect a pitot/static test set to the right side pitot and static ports (copilot’s side).
10. Use the pitot/static test set to simulate an airspeed of 85 kts for the left (pilot’s) side and
95 kts for the right (copilot’s) side. Verify the autopilot does not disconnect and an
amber IAS box is displayed on the airspeed tape of PFD 1 and PFD 2.
11. Use the pitot/static test set to simulate an airspeed of 95 kts for the left (pilot’s) side and
85 kts for the right (copilot’s) side. Verify the autopilot does not disconnect and amber
IAS box is displayed on the airspeed tape of PFD 1 and PFD 2.
12. Reduce the airspeeds to 0 kts.
13. Slowly rotate AHRS 1/ADAHRS 1 along the lateral (pitch) axis to a pitch attitude of
greater than 5 degrees, verify the following:
•
PFD 2 pitch attitude does not change
•
An amber PIT box is annunciated on PFD1 and PFD2 adjacent to the pitch
scale.
•
Autopilot disconnects at approximately 5° miscompare
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•
The autopilot disconnect audio alert (two hi-low tones) sounds
•
A red flashing AP annunciator on PFD 1 and PFD 2
•
Flight director command bars remain in view with autopilot in HDG and ALT
mode
14. Return AHRS 1/ADAHRS 1 to normal attitude and verify that attitude display on PFD 1
displays current aircraft attitude.
15. Use the AFCS mode controller to re-engage autopilot.
16. Slowly rotate AHRS 1/ADAHRS 1 along the longitudinal (roll) axis to a roll attitude of
greater than 5 degrees, verify the following:
•
PFD 2 roll attitude does not change
•
An amber ROL box is annunciated on PFD 1 and PFD 2 adjacent to the roll
scale.
•
Autopilot disconnects at approximately 5° roll miscompare
•
The autopilot disconnect audio alert (two hi-low tones) sounds
•
A red flashing AP annunciator on PFD 1 and PFD 2
•
Flight director command bars remain in view with autopilot in HDG and ALT
mode
17. Return AHRS 1/ADAHRS 1 to normal attitude and verify that attitude display on PFD1
displays current aircraft attitude.
18. Repeat Steps 13 through 17 for AHRS 2/ADAHRS 2. For this test, PFD 1 attitude
should not change and PFD 2 attitude should be used as the AHRS 2/ADAHRS 2
reference.
19. Reinstall AHRS/ADAHRS 1 and 2 units in their racks per Section 6.9.
20. The G1000 Miscompare checks are complete. If no further air data tests are required,
disconnect pitot/static test sets.
4.14
Nose Avionics Compartment Fans Operational Check
This procedure will verify that airflow is present from the ported avionics cooling fans to the #1
and #2 GIA units. The fan speed monitoring circuits and annunciations are checked by the
G1000 Cooling Fan Fail Annunciation Check in Section 9.4 and a Visual Inspection of the fan
and its hoses is accomplished in Section 4.4. This check requires the G1000 to be powered on.
1. Gain access to the nose avionics compartment.
2. Disconnect cooling fan hose from the pilot side GIA and verify airflow is present.
3. Reconnect the cooling fan hose to the GIA and secure using MS3367-5-9 cable tie.
4. Repeat Steps 2 through 3 for the copilot side GIA.
5. The Nose Avionics Compartment Fans Operational Check is complete.
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4.15
Instrument Panel Fans Operational Check
This procedure will verify that airflow is present from the PFD1, MFD and PFD2 cooling fans.
The fan speed monitoring circuits and annunciations are checked by the G1000 Cooling Fan
Fail Annunciation Check in Section 9.4. This check requires the G1000 to be powered on.
1. Remove PFD1 as described in Section 6.1, steps 1 and 2 (Removal).
2. Identify the PFD1 cooling fan and verify airflow is present.
3. Reinstall PFD1 as described in Section 6.1, steps 2 through 4 (Reinstallation).
4. Repeat Steps 1 through 3 for the MFD and PFD2.
5. The Instrument Panel Fans Operational Check is complete.
4.16
Standby Battery Periodic Checks
4.16.1 Charge Check
Refer to the PS-835 Emergency Power Supply Installation Manual listed in Table 1-1.
With the PS-835 battery installed in the aircraft, connect 28VDC ground power to the aircraft.
Turn the ground power and aircraft power on, then verify all four Battery Voltage LEDs are lit to
indicate the battery is being charged (see Figure 4-5).
With the PS-835 battery installed in the aircraft and no ground or aircraft power on, press the
TEST SWITCH (Figure 4-5, Item 4) into TEST position for 5 seconds. The PS-835 indicates
that it is adequately charged when the VOLTAGE LEVEL 24Vdc LED (Figure 4-5, Item 2)
illuminates momentarily, AND the 20Vdc LED (Figure 4-5, Item 6) remains lit during the test. If
the VOLTAGE LEVEL 24Vdc LED does not, at least momentarily, illuminate while the 20Vdc
LED is illuminated, perform the Section 4.16.3 Cell Isolation Test because the battery is
incapable of providing adequate power.
Table 4-14, Standby Battery Required Equipment
DESCRIPTION
VENDOR/SPECIFICATION
Power Supply
DVM
Load Resistor
Stopwatch
0-30 VDC, 20A capacity
Fluke Model 8050A
7Ω +/- 1% 250 watt
Capable of measuring to the minute
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Figure 4-5, Standby Battery
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4.16.2 Capacity Test
NOTE
The PS-835 Emergency Power Supply must have completed a full charge prior to
any discharge testing. This test is performed with the battery removed from the
aircraft.
A. Press and hold TEST SWITCH (Figure 4-5, Item 4) and observe the OUTPUT
VOLTAGE MONITOR LED's.
1. If the 24VDC OUTPUT VOLTAGE MONITOR LED comes on, proceed with
Discharge Test procedure.
2. If OUTPUT VOLTAGE MONITOR LED's do not come on, check fuses at bracket
next to battery and replace if blown. Perform Cell Isolation Test if no fuses are
blown.
B. Discharge Test (Load Resistor)
1. Prepare for test by first constructing an X-Y graph similar to the one shown
below. If possible, use pre-printed graph paper to create a record of the
discharge period along the X-axis and voltage readings along the Y-axis.
2. Position all INDIVIDUAL CELL DIP SWITCHES (Figure 4-5, Item 5) to the ON
position. If the INDIVIDUAL CELL MONITOR LED DS12 is the only LED not
illuminated, proceed to the Cell Isolation Test.
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3. Connect Digital Voltmeter leads to J1 connector pins 11 (+) and 7 (-).
4. Connect the Load Resistor across J1 connector pins 11 (+) and 7 (-) and start
timing the discharge period with a stopwatch.
5. Monitor and plot voltage values at 10-minute intervals.
6. Note voltage on Digital Voltmeter at 48.0 minutes (PS-835D) or at 20.0 minutes
(PS-835C). This voltage must be greater than 20.0 Vdc.
a. All INDIVIDUAL CELL MONITOR LED’s (Figure 4-5, Item 1) must remain
on.
b. Any LED that does go OFF will represent a defective individual cell, which
must be replaced.
7. Remove the Load Resistor from J1 connector pins 11 (+) and 7 (-).
8. Position all INDIVIDUAL CELL DIP SWITCHES (Figure 4-5, Item 5) to the OFF
position.
9. Compare the voltage vs. time plot created during this test to that of curve
identified as typical for the External Load test method on the chart above. If the
plot reveals a discharge curve that meets or exceeds the MINIMUM
ACCEPTABLE DISCHARGE CURVE, the unit is considered satisfactory.
10. If unit discharge plot is satisfactory and no other failures were revealed, perform
the Charging Procedure within 2 hours of completion of the discharge test.
Return the unit into service.
4.16.3 Cell Isolation Test
NOTE
No power should be applied to PS-835 Emergency Power Supply
during test. This test is performed with the battery removed from
the aircraft.
A. Press and hold TEST SWITCH (Figure 4-5, Item 4). If no OUTPUT VOLTAGE
MONITOR LED's come on:
1. Position all INDIVIDUAL CELL DIP SWITCHES (Figure 4-5, Item 5) to the ON
position.
2. Press and hold TEST SWITCH (Figure 4-5, Item 4) and observe the INDIVIDUAL
CELL MONITOR LED's (Figure 4-5, Item 1).
a. If all INDIVIDUAL CELL MONITOR LED’s come on except DS12, the unit
is damaged and requires repair at an authorized repair station.
b. If all INDIVIDUAL CELL MONITOR LED’s are on, a low-battery voltage
condition exists.
B. Perform the Charging Procedure. See 4.16.4.
4.16.4 Charging Procedure
(Constant-Voltage Charging Method)
Locally manufacture a power cable using 16AWG wire and the appropriate mating connector.
Include a Diode (15 Adc (min), 50.0 PIV or greater) to prevent battery discharge in case of loss
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of power from the power source. Using the external power supply apply 30.0 Vdc (10A
maximum current limited) to J1 connector pins 11 (+) and 7 (-) and charge the unit for 16 hours.
The batteries should reach 80% capacity within 1 hour and full charge at 16 hours.
Figure 4-6, Power Supply Connection
4.17
Rudder Boost Operational Check
1. Place the RUDDER BOOST switch to the OFF position. For Model 300 aircraft, set the
left and right bleed air control switches to the OPEN position.
2. Verify the amber RUD BOOST OFF annunciator on the aircraft’s caution and advisory
panel is illuminated.
3. Place the RUDDER BOOST switch to the RUDDER BOOST position. Verify the amber
RUD BOOST OFF annunciator on the aircraft caution and advisory panel is
extinguished.
4. Pull GIA 1 primary and secondary circuit breakers. Verify RUD BOOST OFF annunciator
is extinguished.
5. Pull GIA 2 circuit breaker. Verify RUD BOOST OFF annunciator illuminates.
6. Reset GIA 1 and GIA 2 circuit breakers. Verify RUD BOOST OFF annunciator
extinguishes.
7. Pull the AFCS SERVO circuit breaker. Verify RUD BOOST OFF annunciator
illuminates.
8. Reset AFCS SERVO circuit breaker. Verify RUD BOOST OFF annunciator extinguishes.
9. Press and hold the AP/DISC switch on the pilot’s control wheel and verify RUD BOOST
OFF annunciator illuminates.
10. Release the AP/DISC switch and verify the RUD BOOST OFF annunciator extinguishes.
11. Repeat steps 9-10 for the copilot’s control wheel.
NOTE
Steps 12-15 are only applicable to Model 300 aircraft.
12. Place the L BLEED AIR CONTROL SWITCH in the PNEU & ENVIR OFF position. Verify
RUD BOOST OFF annunciator illuminates.
13. Place the L BLEED AIR CONTROL SWITCH in the OPEN position. Verify RUD BOOST
OFF annunciator extinguishes.
14. Place the R BLEED AIR CONTROL SWITCH in the PNEU & ENVIR OFF position. Verify
RUD BOOST OFF annunciator illuminates.
15. Place the R BLEED AIR CONTROL SWITCH in the OPEN position. Verify RUD BOOST
OFF annunciator extinguishes.
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4.18
Exterior Skin Inspection Around Antennas
Perform a visual inspection of the exterior skin for cracks and loose and missing fasteners in an
area at least 1-inch around the following antennas:
•
GA 36 GPS antenna
•
GA 37 GPS/XM antenna
•
GA 58 Traffic Antenna, Upper (if Garmin traffic system is installed)
•
GA 58 Traffic Antenna, Lower (if Garmin traffic system is installed)
•
Transponder Antenna, Upper #1 (if Garmin GTX 33D or GTX 3000 transponder is
installed)
•
Transponder Antenna, Upper #2 (if Garmin GTX 33D or GTX 3000 transponder is
installed)
•
Iridium Antenna (if Garmin GSR 56 satellite receiver is installed)
•
Wi-Fi Antenna (if Garmin GDL 59 Wi-Fi data link is installed)
The antennas do not need to be removed to perform this inspection.
Figure 4-7, Exterior Skin Inspection Around Antennas
Should damage be detected in any structural component during this inspection, all adjacent
structures must be carefully investigated for indications of related damage. All damage must be
repaired using data obtained from the Structural Inspection and Repair Manual (SIRM),
Beechcraft Repair Design Office (RDO), or other approved sources.
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5. TROUBLESHOOTING
This section provides instructions and guidance for G1000 system troubleshooting as installed
in the King Air 300 Series.
IMPORTANT!
Sections 6, 7 and 9 provide detailed instructions on equipment removal,
replacement, configuration, and return-to-service testing. Anytime a G1000
component or LRU is removed, swapped, or replaced, the technician must
follow the procedures given in Sections 6, 7 and 9 to ensure proper operation
of the system.
Troubleshoot the G1000 system by first identifying, then isolating the specific failure to the
responsible LRU. There are several indications that the G1000 presents to the pilot or
technician, showing overall system condition. A course of action should be determined based
on the information presented on the display. This section shows possible scenarios likely to be
encountered during normal operation and gives troubleshooting guidance to the technician to
resolve problems.
Figure 5-1, Aux – System Status Page
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The Aux – System Status page displays the following information for each LRU and subfunction:
•
Status: A green check is displayed for properly operating LRUs. A red ‘x’ appears when
an internal LRU fault is detected and it has taken itself offline, or if the MFD cannot
communicate with the LRU.
•
Serial Number: Each LRU serial number is displayed (functions such as GPS and GS
are contained within an LRU; therefore, serial numbers are not shown for these).
•
Current SW Version Loaded.
When troubleshooting, first check to ensure that each LRU status is ‘green’ and that the correct
software is loaded in each unit. Additional airframe and database information is also displayed
on this page.
5.1
System Annunciations
If data fields become invalid due to an LRU failure, the PFD/MFD typically annunciates the
failure with a large red X, as shown in Figure 5-2.
Figure 5-2, System Annunciations
5.1.1
Failed Path Messages
The following message indicates there is a data path connected to the GDU (PFD1, PFD1, or
MFD) or the GIA 63W (1 or 2) that has failed.
FAILED PATH – A data path has failed.
The FAILED PATH message is triggered by a timeout of any one digital channel. The channels
that are checked are listed on these pages in config mode:
1) GDU RS-232 / ARINC 429 CONFIG (PFD1/2, and MFD)
2) GIA RS-232 / ARINC 429 CONFIG (GIA1 and GIA2)
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3) GIA CAN / RS-485 CONFIGURATION (GIA1 and GIA2)
IMPORTANT!
Once the FAILED PATH message has been triggered, it will remain on the list
of messages until the next power cycle. This latching was implemented so
that for intermittent failures, the message would remain at the end of the
flight (to alert maintenance crew). Also, this keeps the crew from having to
acknowledge message repeatedly in the case of intermittent failures.
The box next to each channel indicates the current status of the channel per the below:
•
Red X = data path is known to be failed
•
Amber question mark (?) = data path status is unknown
•
Green checkmark ()= data path is known to be good
The applicable data paths can be verified by viewing the following configuration mode pages.
5.1.1.1
GDU RS-232 / ARINC 429 CONFIG Page
PFD 1 RS-232
Channel
LRU
Indicator
Green
CHNL 2
GMC 710
Red
Amber
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Status
PFD1/GMC 710 data path is functioning correctly.
PFD1/GMC 710 data path is not functioning correctly.
• Verify GMC710 is powered on.
o If GMC 710 will not power on, remove unit and
verify power and ground are present at the
GMC connector.
 If power or ground is not present,
troubleshoot aircraft wiring for faults.
 If power and ground are present,
replace GMC 710.
• Load PFD1 and GMC 710 configuration files.
• Swap PFD1and PFD2 to confirm if the problem is in
the original PFD1.
o Replace original PFD1 if box turns green after
swapping displays.
• Check the PFD1/GMC 710 interconnect wiring for
faults.
Replace GMC 710 if problem remains.
PFD1/GMC 710 data path functionality is unknown.
Reload PFD1 configuration file.
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PFD 1 ARINC 429
Channel
LRU
Indicator
Green
IN 1
IN 2
GRS 77 or
GRS 7800
or GSU 75
#1
GDC7400
or GDC 72
#1
Red
Status
PFD1/GRS or GSU 1 data path is functioning correctly.
PFD1/GRS or GSU 1 data path is not functioning correctly.
• Verify GRS or GSU 1 status is “OK” using the Aux –
System Status page on the MFD. If it is not, correct
condition before proceeding, reference GRS
troubleshooting sections.
o Swap GRS1 and GRS2 (no reconfiguration
required) to confirm if the problem is in the
original GRS1.
o Replace original GRS1 if box turns green after
swapping units.
• Load PFD1 configuration file.
• Swap PFD1 and PFD2 to confirm if the problem is in
the original PFD1.
o Replace original PFD1 if box turns green after
swapping displays.
• Swap GRS1 and GRS2 (no reconfiguration required)
to confirm if the problem is in the original GRS1.
o Replace original GRS1 if box turns green after
swapping units.
Check the PFD1/ GRS or GSU 1 interconnect wiring for
faults.
Amber
PFD1/GRS or GSU 1 data path functionally is unknown.
Reload PFD1 configuration file.
Green
PFD1/GDC #1 data path is functioning correctly
Red
PFD1/GDC #1 data path is not functioning correctly.
• Verify GDC #1 status is “OK” using the Aux – System
Status page on the MFD. If it is not, correct condition
before proceeding, reference GDC troubleshooting
sections.
• Load PFD1 and GDC #1 configuration files.
• Swap PFD1 and PFD2 to confirm if the problem is in
the original PFD1.
o Replace original PFD1 if box turns green after
swapping displays.
• Check the PFD1/GDC #1 interconnect wiring for faults.
Replace GDC #1 if problem remains.
Amber
PFD1/GDC #1 data path functionality is unknown. Reload
PFD1 configuration file.
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PFD 2 RS-232
Channel
LRU
Indicator
Green
CHNL 2
GMC 710
Red
Status
PFD2/GMC 710 data path is functioning correctly.
PFD2/GMC 710 data path is not functioning correctly.
• Verify GMC 710 is powered on.
o If GMC 710 will not power on, remove unit and
verify power and ground are present at the
GMC connector.
 If power or ground is not present,
troubleshoot aircraft wiring for faults.
 If power and ground are present,
replace GMC 710.
• Load PFD2 and GMC 710 configuration files.
• Swap PFD2 and PFD1 to confirm if the problem is in
the original PFD2.
o Replace original PFD2 if box turns green after
swapping displays.
•
Check the PFD2/GMC 710 interconnect wiring for
faults.
Replace GMC 710 if problem remains.
Amber
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PFD2/GMC 710 data path functionality is unknown.
Reload PFD2 configuration file.
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PFD 2 ARINC 429
Channel
LRU
Indicator
Green
IN 1
IN 2
GRS 77 or
GRS 7800
or GSU 75
#2
GDC 7400
or
GDC 72 #2
Red
Status
PFD2/GRS or GSU 2 data path is functioning correctly.
PFD2/GRS or GSU 2 data path is not functioning correctly.
• Verify GRS or GSU 2 status is “OK” using the Aux –
System Status page on the MFD. If it is not, correct
condition before proceeding, reference GRS
troubleshooting sections.
o Swap GRS1 and GRS2 (no reconfiguration
required) to confirm if the problem is in the
original GRS1.
o Replace original GRS1 if box turns green after
swapping units.
• Load PFD2 configuration file.
• Swap PFD2 and PFD1 to confirm if the problem is in
the original PFD2.
o Replace original PFD2 if box turns green after
swapping displays.
• Swap GRS1 and GRS2 (no reconfiguration required)
to confirm if the problem is in the original GRS1.
o Replace original GRS1 if box turns green after
swapping units.
• Check the PFD2/GRS or GSU 2 interconnect wiring for
faults.
Amber
PFD2/GRS or GSU 2 data path functionality is unknown.
Reload PFD2 configuration file.
Green
PFD2/GDC #2 data path is functioning correctly.
Red
PFD2/GDC #2 data path is not functioning correctly.
• Verify GDC #2 status is “OK” using the Aux – System
Status page on the MFD. If it is not, correct condition
before proceeding, reference GDC troubleshooting
sections.
• Load PFD2 and GDC #2 configuration files.
• Swap PFD2 and PFD1 to confirm if the problem is in
the original PFD2.
o Replace original PFD2 if box turns green after
swapping displays.
• Check the PFD2/GDC #2 interconnect wiring for faults.
Replace GDC #2 if problem remains.
Amber
PFD2/GDC #2 data path functionality is unknown. Reload
PFD2 configuration file.
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MFD1 RS-232
Channel
LRU
Indicator
Green
CHNL 1
GCU 477
Red
Amber
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Status
MFD1/GCU 477 data path is functioning correctly.
MFD1/GCU 477 data path is not functioning correctly.
• Verify GCU 477 is powered on.
o If GCU 477 will not power on, remove unit and
verify power and ground are present at the
GCU connector.
 If power or ground is not present,
troubleshoot aircraft wiring for faults.
 If power and ground are present,
replace GCU 477.
• Load MFD1 and GCU 477 configuration files.
• Check the MFD1/GCU 477 interconnect wiring for
faults.
• Replace GCU 477.
Replace MFD if problem remains.
MFD1/GCU data path functionality is unknown. Reload
MFD1 configuration file.
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5.1.1.2
GIA RS-232 / ARINC 429 CONFIG Page
GIA1 RS-232
Channel
LRU
Indicator
Green
CHNL 1
CHNL 2
GDC 72 or
GDC7400
#1
GRS 77 or
GRS 7800
or GRS 79
#2 (output
only)
CHNL 5
GIA1/GDC #1 data path is functioning correctly.
Red
GIA1/GDC #1 data path is not functioning correctly.
• Load GIA1 and GDC #1 configuration files.
• Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o Replace original GIA1 if box turns green after
swapping units.
• Check the GIA1/GDC #1 interconnect wiring for faults.
Replace GDC #1 if problem remains.
Amber
GIA1/GDC #1 data path functionality is unknown. Reload
GIA1 configuration files.
White N/A
GIA1/GRS or GSU 2 output data path is not monitored. A
white N/A box is normal.
Green
GTX 33ES
or GTX
3000 or
GTX 3x5 #1
Status
Red
Amber
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GIA1/GTX 1 data path is functioning correctly.
GIA1/GTX 1 data path is not functioning correctly.
• Load GIA1 and GTX 1 configuration files.
• Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o Replace original GIA1 if box turns green after
swapping units.
• Check the GIA1/GTX 1 interconnect wiring for faults.
Replace GTX 1 if problem remains.
GIA1/GTX 1 data path functionality is unknown. Reload
GIA1 configuration files.
Page 145
Revision 2
GIA1 RS-232 (continued)
Channel
LRU
Indicator
Green
CHNL 6
CHNL 7
GRS 77 or
GRS 7800
or GRS 79
#1
GMA
1347 #1
Red
Status
GIA1/GRS or GSU 1 data path is functioning correctly.
GIA1/ GRS or GSU 1 data path is not functioning correctly.
• Load GIA1 configuration files.
• Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o Replace original GIA1 if box turns green after
swapping units.
• Swap GRS1 and GRS2 (no reconfiguration required)
to confirm if the problem is in the original GRS1.
o Replace original GRS1 if box turns green after
swapping units.
Check the GIA1/GRS or GSU 1 interconnect wiring for
faults.
Amber
GIA1/GRS or GSU 1 data path functionality is unknown.
Reload GIA1 configuration files.
Green
GIA1/GMA 1347D #1 data path is functioning correctly.
Red
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
GIA1/GMA 1347D #1 data path is not functioning correctly.
• Load GIA1 and GMA 1347D #1 configuration files.
• Swap GMA 1347D #1 and GMA 1347D #2, reconfigure
both GMA’s to their new locations, to confirm if the
problem is in the original GMA 1347D #1.
o Replace original GMA 1347D #1 if box turns
green after swapping units.
• Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o Replace original GIA1 if box turns green after
swapping units.
Check the GIA1/GMA 1347D #1 interconnect wiring for
faults.
GIA1/GMA 1347D #1 data path functionality is unknown.
Reload GIA1 configuration files.
Page 146
Revision 2
GIA1 ARINC 429
Channel
LRU
Indicator
Green
Status
GIA1/GRS or GSU 2 data path is functioning correctly.
GIA1/GRS or GSU 2 data path is not functioning correctly.
IN 2
GRS 77 or
GRS 7800
or GSU 75
#2
•
Reload GIA1 configuration file.
•
Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o
Red
•
Swap GRS1 and GRS2 (no reconfiguration required)
to confirm if the problem is in the original GRS2.
o
•
Replace original GIA1 if box turns green after
swapping units.
Replace original GRS2 if box turns green after
swapping units.
Check the GIA1/GRS or GSU 2 interconnect wiring for
faults.
Amber
GIA1/GRS or GSU 2 data path functionality is unknown.
Reload GIA1 configuration files.
Green
GIA1/GDC #1 data path is functioning correctly.
GIA1/GDC #1 data path is not functioning correctly.
IN 5
GDC7400
#1
•
Load GIA1 and GDC #1 configuration files.
•
Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
Red
o
•
Replace original GIA1 if box turns green after
swapping units.
Check the GIA1/GDC #1 interconnect wiring for faults.
Replace GDC #1 if problem remains.
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
GIA1/GDC #1 data path functionality is unknown. Reload
GIA1 configuration files.
Page 147
Revision 2
Channel
LRU
Indicator
Green
Status
GIA1/GRS or GSU 1 data path is functioning correctly.
GIA1/GRS or GSU 1 data path is not functioning correctly.
IN 6
GRS 77 or
GRS 7800
or GSU 75
#1
•
Load GIA1 configuration files.
•
Swap GIA1 and GIA2, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o
Red
•
Swap GRS1 and GRS2 (no reconfiguration required,
ref. GRS Configuration and Testing sections) to
confirm if the problem is in the original GRS1.
o
•
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Replace original GIA1 if box turns green after
swapping units.
Replace original GRS1 if box turns green after
swapping units.
Check the GIA1/GRS or GSU 1 interconnect wiring for
faults.
GIA1/GRS or GSU 1 data path functionality is unknown.
Reload GIA1 configuration files.
Page 148
Revision 2
GIA2 RS-232
Channel
LRU
Indicator
Green
CHNL 1
CHNL 2
GDC 72 or GDC 7400
#2
GRS 77 or GRS 7800
or GRS 79 #1 (output
only)
GTX 33ES or
GTX3000 or GTX 3x5
#2
Red
Amber
GIA2/GDC #2 data path functionality is unknown.
Reload GIA2 configuration files.
White N/A
Red
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
GIA2/GDC #2 data path is functioning correctly.
GIA2/GDC #2 data path is not functioning
correctly.
• Load GIA2 and GDC #2 configuration files.
• Swap GIA2 and GIA1, reconfigure both GIA’s
to their new locations to confirm if the problem
is in the original GIA1.
o Replace original GIA2 if box turns
green after swapping units.
• Check the GIA1/GDC #2 interconnect wiring
for faults.
Replace GDC #2 if problem remains.
Green
CHNL 5
Status
GIA2/GRS or GSU 1 output data path is not
monitored. A white N/A box is normal.
GIA2/GTX 2 data path is functioning correctly.
GIA2/GTX 2 data path is not functioning correctly.
• Load GIA2 and GTX 33 or GTX 3000 #2
configuration files.
• Swap GIA2 and GIA1, reconfigure both GIA’s
to their new locations to confirm if the problem
is in the original GIA1.
o Replace original GIA2 if box turns
green after swapping units.
• Check the GIA2/GTX 2 interconnect wiring for
faults.
Replace GTX 2 if problem remains.
GIA2/GTX 2 data path functionality is unknown.
Reload GIA2 configuration files.
Page 149
Revision 2
GIA2 RS-232 (continued)
Channel
LRU
Indicator
Green
CHNL 6
CHNL 7
GRS 77 or
GRS 7800
or GRS 79
#2
GMA
1347D #2
Red
Status
GIA2/GRS or GSU 2 data path is functioning correctly.
GIA2/GRS or GSU 2 data path is not functioning correctly.
• Load GIA2 configuration files.
• Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA1.
o Replace original GIA2 if box turns green after
swapping units.
• Swap GRS2 and GRS1 (no reconfiguration required)
to confirm if the problem is in the original GRS2.
o Replace original GRS2 if box turns green after
swapping units.
Check the GIA2/GRS or GSU 2 interconnect wiring for
faults.
Amber
GIA2/GRS or GSU 2 data path functionality is unknown.
Reload GIA2 configuration files.
Green
GIA2/GMA 1347D #2 data path is functioning correctly.
Red
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
GIA2/GMA 1347D #2 data path is not functioning correctly.
• Load GIA2 and GMA 1347D #2 configuration files.
• Swap GMA 1347D #2 and GMA 1347D #1, reconfigure
both GMA’s to their new locations to confirm if the
problem is in the original GMA 1347D #2.
o Replace original GMA 1347D #2 if box turns
green after swapping units.
• Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA2.
o Replace original GIA2 if box turns green after
swapping units.
Check the GIA1/GMA 1347D #2 interconnect wiring for
faults.
GIA1/GMA 1347D #2 data path functionality is unknown.
Reload GIA2 configuration files.
Page 150
Revision 2
GIA2 ARINC 429
Channel
LRU
Indicator
Green
Status
GIA2/GRS 77 or GRS 7800 #1 data path is functioning
correctly.
GIA2/GRS or GSU 1 data path is not functioning correctly.
IN 2
GRS 77 or
GRS 7800
or GSU 75
#1
•
Reload GIA2 configuration file.
•
Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA2.
o
Red
•
Swap GRS1 and GRS2 (no reconfiguration required)
to confirm if the problem is in the original GRS1.
o
•
Replace original GIA2 if box turns green after
swapping units.
Replace original GRS1 if box turns green after
swapping units.
Check the GIA2/GRS or GSU 1 interconnect wiring for
faults.
Amber
GIA2/GRS or GSU 1 data path functionality is unknown.
Reload GIA2 configuration files.
Green
GIA2/GDC #2 data path is functioning correctly.
GIA2/GDC #2 data path is not functioning correctly.
IN 5
GDC7400
#2
•
Load GIA2 and GDC #2 configuration files.
•
Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA2.
Red
o
•
Replace original GIA2 if box turns green after
swapping units.
Check the GIA2/GDC #2 interconnect wiring for faults.
Replace GDC #2 if problem remains.
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
GIA2/GDC #2 data path functionality is unknown. Reload
GIA2 configuration files.
Page 151
Revision 2
Channel
LRU
Indicator
Green
Status
GIA2/GRS or GSU 2 data path is functioning correctly.
GIA2/GRS or GSU 2 data path is not functioning correctly.
IN 6
GRS 77 or
GRS 7800
or GSU 75
#2
•
Load GIA2 configuration files.
•
Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA2.
o
Red
•
Swap GRS2 and GRS1 (no reconfiguration required)
to confirm if the problem is in the original GRS2.
o
•
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Replace original GIA2 if box turns green after
swapping units.
Replace original GRS2 if box turns green after
swapping units.
Check the GIA2/GRS or GSU 2 interconnect wiring for
faults.
GIA2/GRS or GSU 2 data path functionality is unknown.
Reload GIA2 configuration files.
Page 152
Revision 2
5.1.1.3
GIA CAN / RS-485 CONFIGURATION Page
GIA1 RS-485
Channel
LRU
Indicator
Green
CHNL 1
CHNL 2
GEA1
GEA2
Status
GIA1/GEA1 data path is functioning correctly.
Red
GIA1/GEA1 data path is not functioning correctly.
• Verify GEA1 is powered on using the GEA Status page.
• Load GIA1 and GEA1 configuration files.
• Swap GIA1 and GIA2, reconfigure both GIA’s to their new
locations to confirm if the problem is in the original GIA1.
o Replace original GIA1 if box turns green after
swapping units.
• Swap GEA1 and GEA2, reconfigure both GEA’s to their
new locations to confirm if the problem is in the original
GEA1.
o Replace original GEA1 if box turns green after
swapping units.
Check the GIA1/GEA1 interconnect wiring for faults.
Amber
GIA1/GEA1 data path functionality is unknown. Reload GIA1
configuration files.
Green
GIA1/GEA2 data path is functioning correctly.
Red
GIA1/GEA2 data path is not functioning correctly.
• Verify GEA2 is powered on using the GEA Status page.
• Load GIA1 and GEA2 configuration files.
• Swap GIA1 and GIA2, reconfigure both GIA’s to their new
locations to confirm if the problem is in the original GIA1.
o Replace original GIA1 if box turns green after
swapping units.
• Swap GEA2 and GEA1, reconfigure both GEA’s to their
new locations to confirm if the problem is in the original
GEA2.
o Replace original GEA2 if box turns green after
swapping units.
Check the GIA1/GEA2 interconnect wiring for faults.
Amber
GIA1/GEA2 data path functionality is unknown. Reload GIA1
configuration files.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 153
Revision 2
Channel
LRU
Indicator
Green
CHNL 4
GFC 700
Status
GIA1/GFC 700 data path is functioning correctly.
Red
GIA1/GFC 700 data path is not functioning correctly.
• Load GIA1 configuration files, GIA Gains file and GSA
software and gains file (if LRU and Card versions are
different).
Reference GFC section for further troubleshooting.
Amber
GIA1/GFC 700 data path functionality is unknown. Reload
GIA1 configuration files.
GIA2 RS-485
Channel
LRU
Indicator
Green
CHNL 1
GEA1
Red
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Status
GIA2/GEA1 data path is functioning correctly.
GIA2/GEA1 data path is not functioning correctly.
• Verify GEA1 is powered on using the GEA Status
page.
• Load GIA2 and GEA1 configuration files.
• Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA2.
o Replace original GIA2 if box turns green after
swapping units.
• Swap GEA1 and GEA2, reconfigure both GEA’s to
their new locations to confirm if the problem is in the
original GEA1.
o Replace original GEA1 if box turns green after
swapping units.
Check the GIA2/GEA1 interconnect wiring for faults.
GIA2/GEA1 data path functionality is unknown. Reload
GIA2 configuration files.
Page 154
Revision 2
Channel
LRU
Indicator
Green
CHNL 2
GEA2
Red
Status
GIA2/GEA2 data path is functioning correctly.
GIA2/GEA2 data path is not functioning correctly.
• Verify GEA2 is powered on using the GEA Status
page.
• Load GIA2 and GEA2 configuration files.
• Swap GIA2 and GIA1, reconfigure both GIA’s to their
new locations to confirm if the problem is in the original
GIA2.
o Replace original GIA2 if box turns green after
swapping units.
• Swap GEA2 and GEA1, reconfigure both GEA’s to
their new locations to confirm if the problem is in the
original GEA2.
o Replace original GEA2 if box turns green after
swapping units.
Check the GIA2/GEA2 interconnect wiring for faults.
Amber
GIA2GEA2 data path functionality is unknown. Reload
GIA2 configuration files.
Green
GIA2/GFC 700 data path is functioning correctly.
GIA2/GFC 700 data path is not functioning correctly.
•
CHNL 4
GFC 700
Red
Load GIA2 configuration files, GIA Gains file and GSA
software and gains file (if LRU and Card versions are
different).
Reference GFC section for further troubleshooting.
Amber
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
GIA2/GFC 700 data path functionality is unknown. Reload
GIA2 configuration files.
Page 155
Revision 2
5.1.2
System Failure Troubleshooting
The following table provides basic troubleshooting guidance for LRU failures. Refer to G1000
Wiring Diagram, listed in Table 1-1, as needed to verify interconnects.
Invalid Data Field
Associated
LRU(s)
Solution
Low Speed Awareness Band
permanently displayed
•
With aircraft weight on wheels and the G1000 in
Configuration Mode, check that the RH GEAR ON GROUND
Discrete In indication for GIA2, on GIA I/O CONFIGURATION
page is illuminated.
•
With aircraft weight on wheels and the G1000 in
Configuration Mode, check that the LH GEAR ON GROUND
Discrete In indication for GIA1, on GIA I/O CONFIGURATION
page is illuminated.
•
If both indications are illuminated Green, switch GIA1 and
GIA2, to verify location of problem:
 If problem is resolved, replace faulty unit.
 If indication is not illuminated, check for wiring faults
between the GIAs and aircraft squat switch system.
•
With aircraft weight on wheels and the G1000 in
Configuration Mode, check that the RH GEAR ON GROUND
Discrete In indication for GIA2, on GIA I/O CONFIGURATION
page is illuminated.
•
With aircraft weight on wheels and the G1000 in
Configuration Mode, check that the LH GEAR ON GROUND
Discrete In indication for GIA1, on GIA I/O CONFIGURATION
page is illuminated.
•
If both indications are illuminated Green, switch GIA1 and
GIA2, to verify location of problem:
 If problem is resolved, replace faulty unit.
 If indication is not illuminated, check for wiring faults
between the GIAs and aircraft squat switch system.
•
Check configuration settings for GIA1 and PFD1.
•
Swap GIA1 and GIA2, to verify location of problem:
 If problem follows GIA1, replace GIA1.
•
Check Ethernet interconnect from GIA1 to PFD1.
 If problem persists, replace PFD.
GDU
Low Speed Awareness Band
permanently inhibited
GDU
NAV1 & COM1
GIA1
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 156
Revision 2
Invalid Data Field
Associated
LRU(s)
NAV2 & COM2
Solution
•
Check configuration settings for GIA2 and PFD2.
•
Swap GIA1 and GIA2, to verify location of problem:
 If problem follows GIA2, replace GIA2.
•
Check Ethernet interconnect from GIA2 to PFD2.
 If problem persists, replace PFD.
•
Ensure that a cell phone or a device using cell phone
technology is not turned on (even in a monitoring state) in the
cabin.
Check GPS1 and GPS2 signal strength on Aux – GPS
Status page. Refer to GIA GPS section if GPS cannot
acquire a position lock for troubleshooting.
Check corresponding GPS antenna and cable for faults.
Check Ethernet interconnect between the PFD1 to GIA1 or
PFD2 to GIA2 for faults.
Swap GIA1 and GIA2, to verify location of problem:
 If problem follows the GIA, replace the GIA.
 If problem persists, replace the PFD1 or PFD2.
GIA2
GPS LOI
•
GIA1 or GIA2
•
•
•
•
XPDR FAIL
GTX 335R,
GTX 345R,
GTX 33( ), or
GTX 3000
•
•
•
•
Check GTX 335R/345R/33/33D/3000 configuration settings
for GIA1 and GIA2.
Check GTX 335R/345R/33D/3000 and GIA1 interconnect.
Check GTX 335R/345R/33D/3000 and GIA2 interconnect.
Perform a SET>ACTV configuration reset on the GTX Config
page for each GTX, and verify the aircraft registration is
present.
Replace GTX 335R/345R/33/33D/3000.
 If problem persists, replace GIA.
TAS FAIL
AIRSPEED FAIL
ALTITUDE FAIL
VERT SPEED FAIL
GSU 75B or
GDC 7400
OAT
GTP 59
GSU 75B, or
GDC 7400
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
•
•
Inspect GSU 75B/GDC 7400 pitot/static plumbing integrity.
Inspect pitot/static ports and associated equipment for faults.
For TAS failure, also check GTP 59 probe.
Check GSU 75B/GDC 7400 configuration settings for the
PFDs, MFD, GIA1, and GIA2.
 If problem persists, replace the GSU 75B/GDC 7400.
•
•
Check OAT probe wiring and connectors for faults.
Replace GSU 75B/GDC 7400 with a known good unit:
 If problem persists, replace the GTP 59.
Page 157
Revision 2
Invalid Data Field
Associate
d LRU(s)
Solution
•
•
•
•
ATTITUDE FAIL
GSU 75B,
GRS 77, or
GRS 7800
•
•
•
•
•
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Ensure that a cell phone or a device using cell phone
technology is not turned on (even in a monitoring state) in
the cabin.
Cycle GSU 75B, GRS 77, or GRS 7800 power to restart
initialization.
Ensure GSU 75B, GRS 77, or GRS 7800 connecter is
secure and proper wire harness strain relief is provided.
Ensure the GSU 75B, GRS 77, or GRS 7800 is fastened
down tightly in it’s mounting rack and that the mounting
rack is not loose (CAUTION - do not loosen the mounting
rack hardware to the airframe shelf or the aircraft will need
to be re-leveled and the PITCH/ROLL OFFSET procedure
performed).
Ensure GPS has acquired at least four satellites, has a 3D
navigation solution, and a DOP of less than 5.0. This is
particularly important for an ATTITUDE FAIL that appears
during ground operation only.
Perform an Engine Run-Up Test to check if engine
vibration is causing the GSU 75B, GRS 77, or GRS 7800 to
go offline.
Load configuration files to the PFD, MFD, GIA1, and GIA2.
Calibrate the GSU 75B, GRS 77, or GRS 7800 (Pitch/Roll
Offset and Magnetometer Calibration).
Replace GSU 75B, GRS 77, or GRS 7800.
 If problem persists replace GSU 75B, GRS 77, or GRS
7800 configuration module.
 Contact Garmin Aviation Product Support if condition
continues after replacing the GSU 75B, GRS 77, or
GRS 7800 and config module for additional
assistance.
Page 158
Revision 2
Invalid Data Field
Associate
d LRU(s)
Solution
•
•
HDG FAIL
GSU 75B,
GRS 77, or
GRS 7800
&
GMU 44
•
•
•
•
•
•
•
GSU 75B,
GRS 77, or
GRS 7800
&
•
Ensure metal objects (tool boxes, power carts, etc.) are not
interfering with the magnetometer and aircraft is not in
hangar, near other buildings, parked over metal drainage
culverts or on hard surfaces that may contain steel
reinforcements
The GMU 44 magnetometers located in the tail cone are
vulnerable to magnetized rudder torque tube lower fittings
and control rod ends. This magnetism may be caused by
an improperly functioning aircraft static discharge system
which is dependent on static dischargers (wicks) and
electrical bonding of the static dischargers and surrounding
structure. The bonding straps on the elevators and rudder
should be visually inspected to verify they are not missing,
broken or frayed. Refer to the King Air 300 Series
Maintenance Manual, chapter 23-60-00, to verify the
following items are within specification:
1.
The resistance from the tip to the base of each static
discharger
2.
The resistance between the base of each static
discharger and the surface to which it is attached
3.
The resistance between the elevators/rudder and the
airplane structure
Ensure that a cell phone or a device using cell phone
technology is not turned on (even in a monitoring state) in
the cabin.
Cycle power after moving aircraft away from metal objects
to determine if metal objects were the source of the
interference. Allow up to five minutes for the heading to
reinitialize.
Perform a Magnetometer Interference Test to check for
interference from onboard electrical system components
(e.g. NAV lights). Pay particular attention to any new
electrical devices that have been installed since the aircraft
was new. Correct any discrepancies that do not allow this
test to pass before continuing.
Ensure GSU 75B, GRS 77, or GRS 7800 and GMU 44
connectors are secure.
Check the wiring and any inline connectors between the
GSU/GRS and GMU for faults.
Recalibrate the GMU 44,
Load configuration files to the PFD1, PFD2, GIA1, and
GIA2
 If problem persists replace the GMU 44.
 If problem persists, replace the GSU 75B, GRS 77, or
GRS 7800.
If this message persists longer than five minutes, perform
AHRS calibration procedures as described in Section 7.10.
GMU 44
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 159
Revision 2
Invalid Data Field
Associate
d LRU(s)
Engine/Airframe Sensors (All
Invalid)
Solution
•
•
•
GEA 71
&
GIA 63W
•
•
•
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
If software was loaded to a new GDU display, be sure that
the user settings for the replaced display were cleared.
Clear user settings by pressing the CLR key on the
replaced display while applying power to it. Acknowledge
the on-screen prompt by pressing the ENT key or the rightmost softkey.
Check for GEA related Alert messages on the PFD.
Correct any Alerts concerning software or configuration
errors by reloading software or configuration as noted.
Verify GEA internal power supply, configuration, and
calibration status in configuration mode.
 The internal power supply, configuration and
calibration boxes should be green. If they are red,
replace the GEA 71.
Verify internal, external, and reference voltages listed in the
Main Analog and I/O A Analog boxes are not dashed out
(does not include Aircraft Power 1 and 2).
 If any voltages are dashed out, replace the GEA.
Ensure the GEA is online (green checkmark on the Aux –
System Status page).
 If GEA is not online verify unit is receiving power at the
rack connector.
 Check the GIA/GEA interconnects for faults.
 Reload configuration files to both GIA’s and the GEA.
If problem persists, replace the GEA 71.
Page 160
Revision 2
5.1.3
Engine/Airframe Instrument Failures
The following table provides guidance for troubleshooting individual engine/airframe sensor
failures. Be sure to also follow previous guidance given for the GEA 71. The technician should
troubleshoot to isolate the fault by checking sensor-to-GEA wiring, replacing the suspect
sensor, and finally by replacing the GEA 71. Replace one part at a time. Refer to Section 7.4.3
to check for correct operation of the sensors and GEA 71 after any part has been replaced.
Refer to G1000 Wiring Diagram and King Air 300 Series Maintenance Manual (listed in Table
1-1) as needed.
Invalid Field
Sensor
Possible Solutions (for applicable engine/system)
ITT
•
•
•
Check thermocouple cable.
Replace thermocouple cable.
Replace GEA 71.
Torque
•
•
•
•
Check torque transmitter – GEA wiring.
Check power input to torque transmitter.
Replace torque transmitter.
Replace GEA 71.
Prop RPM
•
•
•
•
•
•
Check prop tachometer – Signal Conditioner wiring.
Check Signal Conditioner – GEA wiring.
Check power input to Signal Conditioner.
Replace prop tachometer sensor.
Replace Signal Conditioner. Refer to Section 6.23.
Replace GEA 71.
Turbine RPM
•
•
•
•
•
•
Check engine speed tachometer – Signal Conditioner wiring.
Check Signal Conditioner – GEA wiring.
Check power input to Signal Conditioner.
Replace engine speed tachometer sensor.
Replace Signal Conditioner. Refer to Section 6.23.
Replace GEA 71.
Fuel Flow
•
•
•
•
•
Check Signal Conditioner unit wiring.
Check power input to Signal Conditioner
Replace fuel flow transmitter.
Replace Signal Conditioner. Refer to Section 6.23.
Replace GEA 71.
Oil Pressure
•
•
•
Check oil pressure sensor – GEA wiring.
Replace oil pressure sensor.
Replace GEA 71.
Oil Temperature
•
•
•
Check oil temperature sensor – GEA wiring.
Replace oil temperature sensor.
Replace GEA 71.
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5.1.4
ADF/DME Failure
A DME or ADF failure is represented by the following red X’s. Refer to G1000 Wiring Diagram
and King Air 300 Series Maintenance Manual (listed in Table 1-1,) as needed.
Invalid Field
or
Sensor
Solutions
•
•
•
ADF
•
•
•
•
•
DME
•
•
G1000 NXi System Maintenance Manual
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Ensure that GIA 63 #2 is properly functioning.
Reload the ADF option configurations.
Check for proper operation of the ADF receiver. Ensure that
the receiver is receiving power.
Check ADF – GIA2 interconnect.
For other failures of the ADF system, refer to King Air 300
Series Maintenance Manual, listed in Table 1-1.
Ensure that GIA 63 #1 is properly functioning.
Reload the DME option configurations.
Check for proper operation of the DME receiver. Ensure that
the receiver is receiving power.
Check DME – GIA1 interconnect.
For other failures of the DME system, refer to the King Air 300
Series Maintenance Manual, listed in Table 1-1.
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5.2
G1000 Alerting System
Figure 5-3, Alerts & Annunciations
The G1000 Alert System conveys alerts to the pilot using combinations of the following
features:
Alert Window:
The Alert window displays alert text messages. Pressing the Alerts softkey displays the Alerts
window. Pressing the ALERTS softkey again removes the Alerts window from the display.
Softkey Annunciation:
When the G1000 Alerting System issues an alert, the Alerts softkey is used as a flashing
annunciation to accompany the alert. During the alert, the Alerts softkey label flashes between
white letters on black to black letters on a white. The flashing continues until the alert is
acknowledged by a press of the Alerts softkey. The alerts softkey remains black letters on white
until the condition causing the alert is corrected, or a new alert triggers the flashing.
Figure 5-4, Alerts Softkey Annunciation
System Failure Annunciations:
Typically, a large red X appears in windows when a failure is detected in the LRU providing the
information to the window.
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5.3
Aural & Audio Alerts
The G1000 system is capable of issuing audio and aural (voice) alerts for various situations.
The following alerts are utilized by the G1000:
Alert Name
Purpose
Traffic (voice)
Traffic Advisory
No Traffic (voice)
Traffic Unavailable
“Minimums, Minimums” (voice)
Minimums Aural Alert
Alt Alert (aural)
Altitude Alerting Function
“Caution Terrain, Caution Terrain” (voice) and
TAWS Caution alert: Reduced required terrain clearance
“Terrain Ahead, Terrain Ahead” (voice)
Or Imminent impact with terrain.
“Terrain Terrain, Pull Up Pull Up” (voice) and
TAWS Warning alert: Reduced required terrain clearance
“Terrain Ahead Pull Up, Terrain Ahead Pull Up” (voice)
Or Imminent impact with terrain.
“Terrain Terrain” (voice)
TAWS Caution alert: GPWS mode 2, Excessive Closure Rate
“Too Low Terrain” (voice)
TAWS Caution alert: GPWS mode 4A/B/C, Flight into terrain,
takeoff or high speed
“Too Low Gear” (voice)
TAWS Caution alert: GPWS mode 4A/B, Flight into terrain, gear
not extended
“Too Low Flaps” (voice)
TAWS Caution alert: GPWS mode 4B, Flight into terrain, flaps
not extended
“Sink Rate” (voice)
TAWS Caution alert: GPWS mode 1, Excessive Descent Rate
“Pull Up” (voice)
TAWS Warning alert: GPWS mode 1 or 2, Excessive Descent
Rate
Or Excessive Closure Rate
“Don’t Sink” (voice) or
“Too Low Terrain” (voice)
“Glide Slope” (voice) or
“Glide Path” (voice)
TAWS Caution alert: GPWS mode 3, altitude loss after takeoff
or go-around
TAWS Caution alert: GPWS mode 5, Glide Slope/Path deviation
“Five Hundred” (voice) or
“Four Hundred” (voice) or
“Three Hundred” (voice) or
TAWS voice callout: GPWS mode 6, voice callout as appropriate
per altitude
“Two Hundred” (voice) or
“One Hundred” (voice)
“Caution Obstacle, Caution Obstacle” (voice) or
TAWS Caution alert: Reduced required obstacle clearance
“Obstacle Ahead, Obstacle Ahead ” (voice)
Or Imminent impact with obstacle.
“Obstacle Obstacle Pull Up Pull Up” (voice) or
“Obstacle Ahead Pull Up, Obstacle Ahead Pull Up” (voice)
TAWS Warning alert: Imminent impact with obstacle.
“TAWS System Failure” (voice)
TAWS status alert: Terrain failure
“TAWS Not Available” (voice)
TAWS status alert: Terrain not available
“TAWS System Test, OK” (voice)(If passed) or
“TAWS System Failure” (voice) (If test failed)
TAWS status alert: Terrain self-test
“TAWS Available” (voice)
TAWS status alert: Terrain available
“Vertical Track” (voice)
Vertical navigation alerting function
*“Climb, Climb” (voice)
TCAS II Resolution Advisory: Climb at the rate depicted by the
solid green bar on the vertical speed tape on the PFD.
*”Descend, Descend” (voice)
TCAS II Resolution Advisory: Descend at the rate depicted by
the solid green bar on the vertical speed tape on the PFD.
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Alert Name
Purpose
*”Monitor Vertical Speed” (voice)
TCAS II Resolution Advisory: Verify vertical speed is out of the
solid red bar on the vertical speed tape on the PFD.
*”Level Off, Level Off” (voice)
TCAS II Resolution Advisory: Reduce vertical speed to zero feet
per minute.
*”Clear of Conflict” (voice)
TCAS II Resolution Advisory: Range is increasing and separation
is adequate to return to the applicable clearance unless
otherwise directed by ATC.
*”Climb, Crossing Climb, Climb, Crossing Climb” (voice)
TCAS II Resolution Advisory: Climb at the rated depicted by the
solid green bar on the vertical speed tape on the PFD. Safe
separation is achieved by climbing through the threat’s flight
path.
*”Descend, Crossing Descend, Descend, Crossing Descend”
(voice)
TCAS II Resolution Advisory: Descend at the rated depicted by
the solid green bar on the vertical speed tape on the PFD. Safe
separation is achieved by descending through the threat’s flight
path.
*”Maintain Vertical Speed, Maintain” (voice)
TCAS II Resolution Advisory: Maintain the existing climb or
descent rate as depicted by the solid green bar on the vertical
speed tape on the PFD. Safe separation is achieved by not
altering the existing vertical speed.
*”Maintaining Vertical Speed, Crossing Maintain” (voice)
TCAS II Resolution Advisory: Maintain the existing climb or
descent rate as depicted by the solid green bar on the vertical
speed tape on the PFD. Safe separation is achieved by not
altering the existing vertical speed and climbing or descending
through the threat’s flight path.
*”Increase Climb, Increase Climb” (voice)
TCAS II Resolution Advisory: Climb at the rate depicted by the
solid green bar on the vertical speed tape on the PFD. Received
after a “CLIMB” resolution advisory and indicates additional climb
rate is required to achieve safe vertical separation from the
maneuvering threat aircraft.
*”Increase Descent, Increase Descent” (voice)
TCAS II Resolution Advisory: Descent at the rate depicted by the
solid green bar on the vertical speed tape on the PFD. Received
after a “DESCEND” resolution advisory and indicates additional
Descent rate is required to achieve safe vertical separation from
the maneuvering threat aircraft.
*”Climb – Climb Now, Climb – Climb Now” (voice)
TCAS II Resolution Advisory: Climb at the rate depicted by the
solid green bar on the vertical speed tape on the PFD. Received
after a “DESCEND” resolution advisory and indicates a reversal
in direction is required to achieve safe vertical separation from
the maneuvering threat aircraft.
*”Descend – Descend Now, Descend – Descend Now” (voice)
TCAS II Resolution Advisory: Descend at the rate depicted by
the solid green bar on the vertical speed tape on the PFD.
Received after a “CLIMB” resolution advisory and indicates a
reversal in direction is required to achieve safe vertical
separation from the maneuvering threat aircraft.
*These aural alerts are specific to installations with the GTS Processor configured as a GTS
8000 (TCAS II) unit. For installations of other approved TCAS II systems, these alerts and
visual indications may be slightly different. For instance, “MONITOR VERTICAL SPEED” in the
GTS processor installation is “ADJUST VERTICAL SPEED” for the third-party TCAS II
installation.
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5.4
King Air 300 Series Specific Alerts
The following alerts are configured specifically for the King Air 300 Series installation:
5.4.1
ANNUNCIATION Alerts
Message Alert
Solution
TAWS GEAR FAULT – Landing Gear detected in
the DOWN position
•
Check the gear down wiring input to the GIAs. Refer to
G1000 Wiring Diagram, listed in Table 1-1.
TAWS FLAP FAULT – Flaps detected in the LDG
position
•
Check the flap full down wiring input to the GIAs. Refer
to G1000/ Wiring Diagram, listed in Table 1-1.
WOW Invalid
•
Ensure that the GIA1 (PRI) and (SEC) and GIA2 circuit
breakers are closed.
Check weight on wheels switch inputs to GIA1 and GIA2.
Refer to G1000 Wiring Diagram, listed in Table 1-1,
•
WOW Fault
•
•
Ensure that the GIA1 (PRI) and (SEC) and GIA2 circuit
breakers are closed.
Check weight on wheels switch inputs to GIA1 and GIA2.
Refer to G1000 Wiring Diagram, listed in Table 1-1.
AVN 1 FAN FAIL – Avionics cooling fan #1 is
inoperative.
AVN 2 FAN FAIL – Avionics cooling fan #2 is
inoperative.
•
PFD 1 FAN FAIL – PFD #1 cooling fan is
inoperative.
•
PFD 2 FAN FAIL – PFD #2 cooling fan is
inoperative.
•
Ensure that the PFD/GIA FAN (LEFT and RIGHT) and
MFD FAN circuit breakers are closed.
Check cooling fan wiring. Refer to G1000/GFC 700
Wiring Diagram, listed in Table 1-1,
Replace cooling fan. Refer to Sections 6.29 and 6.30.
MFD FAN FAIL – MFD cooling fan is inoperative.
ESP FAIL – ESP is inoperative.
ESP OFF – ESP selected off.
ESP DEGRADE - ESP IAS mode is inoperative.
Troubleshoot the GFC 700 AFCS. Refer to Section 5.7.
•
Check that the MFD Aux – System Setup 2 page shows
“Stability & Protection” status is “ENABLED”.
•
Ensure ADC1 and ADC2 circuit breakers are closed and
units are providing valid airspeed data.
•
Ensure that the correct ESP Support was installed per
Section 3.8.6.
Ensure that the “Enhanced AFCS unlock card” has been
installed per Section 3.9.9.
If the ESP option needs to be removed, reload the
baseline configuration for the specific airframe and all
applicable options as described in Section 3.8.
Reloading the baseline configuration disables all
previously enabled options.
•
ESP CONFIG – ESP config error. Config service
req’d.
•
NOTE
From this point forward, all message alerts presented are common to all G1000
systems and are not specific to the King Air 300 Series. Messages are grouped
according to LRU.
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5.5
TAWS Troubleshooting
Annunciation
Cause
Solution
•
•
•
A TAWS system failure has
occurred.
•
•
If message occurred on the first
power up after unlocking TAWS,
cycle power to initialize TAWS.
Ensure each GDU contains the
correct database data card.
Ensure the G1000 is configured for
TAWS:
 If the system is not configured
for TAWS, configure per Section
3.9.
Verify GIAs are online.
Ensure a database or GDU SW
mismatch has not occurred.
 If a mismatch has occurred,
load correct database/software
files or replace the terrain card.
TAWS system is currently
being tested.
N/A – Test will be conducted up to two
minutes
TAWS system alerting is
disabled
Enable TAWS system alerting by
pressing the INHIBIT softkey on the
Map – TAWS Map page.
•
GPS system integrity not
high enough to enable
TAWS
•
•
A GPWS system failure has
occurred.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
•
Ensure valid GPS position is
received from the Aux – GPS
Status page.
Check GPS antenna & associated
coaxial cabling.
Troubleshoot GIAs.
Verify GIAs are online.
Verify radar altimeter input is valid.
Verify baro altitude and vertical
speed input are valid.
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5.6
Synthetic Vision and Pathways Troubleshooting
The SVS/Pathways software feature requires the following G1000 sensors/data to be valid:
•
AHRS
•
Heading
•
GPS Position
•
9 Arc-Second Terrain Data
In the event that one the above items fails or is unavailable, the SVS/Pathways feature is
automatically removed from the PFD. The following table describes possible symptoms
associated with the SVS/Pathways feature, and provides corresponding actions for
troubleshooting:
Table 5-1, SVS Troubleshooting
Recommended Action
Symptom
“SYN VIS” softkey does not
appear on PFD softkey tier.
Follow the steps in Section 3.9.8 to reactivate the SVS/Pathways feature.
3D terrain presentation does not
appear on PFD.
•
Verify that P/N 010-00330-43 terrain data cards are installed in the lower
slot of the PFD and MFD.
•
Verify that the alert messages shown in Table 5-2 are not displayed on
the PFD Alerts Window. If so, follow the solutions described in Table 5-2.
•
Verify that the G1000 AHRS and heading data are valid on the PFD.
Verify that a valid GPS 3D position solution is being received.
Troubleshoot these systems in accordance with Sections 5.12.4 and
5.17.
•
If a terrain database update has just been performed, allow the system
time to initialize and verify the data. When the databases have been
verified, the current database cycle and version are reported on the MFD
Aux – System Status page.
The following table provides SVS/Pathways specific alert messages which may appear in the
Alerts Window on the PFD (press the ALERTS softkey on the PFD to view the Alerts Window):
Failure Message
Table 5-2, SVS-Related Alert Messages
Cause
Solution
SVS – SVS DISABLED: Out of
available terrain region.
SVS is disabled because the
aircraft exceeded the boundaries
of the loaded terrain database.
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Geographical operation limitations are
defined in the AFMS listed in Table 1-1.
Ensure that operations are within this
geographic area.
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5.7
GFC 700 AFCS Troubleshooting
The GFC 700 is a digital Automatic Flight Control System (AFCS) which is integrated into
various components of the G1000. This section touches upon key items to note while
troubleshooting the GFC 700.
Should a problem be encountered during the operation of the GFC 700, the pilot and technician
should first evaluate the overall status and condition of the G1000 system at the Aux – System
Status page (on MFD). Any alert messages, annunciations, or other abnormal behaviors
should be noted in an effort to pinpoint the fault. The object is to locate the fault within a LRU or
LRUs in efforts to replace the faulty equipment.
The GFC 700 AFCS Annunciation field is located above the altitude tape on the PFD as shown:
Figure 5-5, AFCS Annunciation Field
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5.8
General Troubleshooting
The following annunciations may appear in the AFCS Annunciation field:
Table 5-3, AFCS Annunciation Troubleshooting
Annunciation
Condition
Resolution
•
•
•
•
AFCS System Failure
•
•
•
•
•
•
Pitch Axis Failure
Pitch Trim Axis
Failure
•
•
•
•
Yaw Axis Failure
•
Roll Axis Failure
Elevator Mistrim Up
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Check the Aux – System Status page to see if the servo is
online (green check).
Check that the affected servo is receiving power.
Check the servo wiring and connector.
For pitch trim, check pitch trim switch operation to verify switch
contacts are not stuck.
If failure condition still exists, remove and replace the affected
servo.
•
If the AHRS inputs have been determined to be “unreasonable”
while the AP is engaged, in air, this message will be displayed
until AHRS inputs are determined reasonable for 5 seconds.
•
If elevator mistrim annunciations persist, check the pitch and
pitch trim servos for proper operation. Verify that the servo is
online at the Aux – System Status page.
Check the servo wiring and connectors. Ensure the servo is
receiving power.
Check the aircraft control adjustments.
If mistrim condition still exists, remove and replace the affected
servo.
AHRS Monitor
Failure
Elevator Mistrim
Down
Confirm AFCS Servos circuit breaker IN
Ensure that the G1000 system is in proper working order.
Check specifically for proper operation of the:
 GIA 63 Integrated Avionics Units
 GRS 77 or GRS 7800 AHRS or GSU 75B ADAHRS Units
 GDC 7400 Air Data Computers
 All GSA 80 Servos
Check that no red X’s are present on the MFD and PFD
displays.
Check that no related alert messages are present on the PFD
displays (press the ALERTS softkey).
Go to the Aux – System Status page on the MFD and verify
that all LRUs have a ‘green’ check (see Section 5).
In Configuration mode, review the GFC 700 equipment status,
software, and certification gains.
Reload software, configuration, and certification gains to the
GIAs and GSA 80 servos.
Check the GFC Status page for additional GFC 700 system
information.
Review the fault and assert logs for the GIAs and servos (see
Section 5.8.2)
Isolate the fault to an LRU. Replace this LRU and confirm the
resolution of the annunciation.
•
•
•
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Annunciation
Condition
Resolution
Aileron Mistrim Right
•
•
•
Check for possible fuel imbalance.
Check aileron control adjustments.
If mistrim condition still exists remove and replace the roll servo.
•
•
Check rudder control adjustments.
If mistrim condition still exists remove and replace the yaw
servo.
•
•
Allow the system to complete pre-flight tests.
The preflight test should finish within 2 minutes. If it does not
pass, the red ‘PFT’ annunciation is shown. In case of PFT
failure, see Section 5.8.3 for additional PFT diagnostics.
Aileron Mistrim Left
Rudder Mistrim Right
Rudder Mistrim Left
Pre-Flight Test Fails
Table 5-4, AFCS General Troubleshooting
Condition
Resolution
•
Poor AP Performance
(Limited AP Authority)
•
•
•
•
AP DISC Problems
•
•
Loss of Manual Electric Trim
AutoTrim Inoperative
G1000 NXi System Maintenance Manual
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Check each servo gearbox slip clutch per Section 4.9. Verify the
clutches are not excessively loose and are within torque limits.
Check aircraft controls for proper balancing and adjustment per
the King Air 300 Series Maintenance Manual.
Check aircraft control cables for proper tension per the King Air
300 Series Maintenance Manual.
For intermittent nuisance disconnects with no AFCS of PFT alert,
check A/P disconnect switch and wiring for intermittent faults.
If an AFCS or PFT alert is displayed at the time of the disconnect,
troubleshoot per Section 5.8.
Check the GIA AFCS Fault Logs according to Section 5.8.2. If a
Mon Prmtr Invalid message is received, check for valid true
airspeed. A faulty GTP 59 OAT probe may cause TAS to become
invalid, which will flag the Mon Prmtr Invalid message.
Contact Garmin Product Support for assistance
•
•
Check pitch trim servo status.
Check MET switch discrete inputs to both GIAs by going to the
GIA I/O Configuration page and selecting DISCRETE IN inputs.
•
Check flap-in-motion discrete inputs to both GIAs for proper
operation by going to the GIA I/O Configuration page and selected
DISCRETE IN inputs. See Section 4.8.
If DATA indicator fails to illuminate or illuminates incorrectly,
troubleshoot flap motor & discrete input wiring (refer to G1000
Wiring Diagram, listed in Table 1-1,).
•
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5.8.1
GFC Status Page
The GFC Status page is presented in configuration mode and gives status information
regarding the GFC 700.
Figure 5-6, GFC Status Page
GIA STATUS
AP DISCONNECT: Shows the condition of the AP DISC +28 VDC input to the GIAs and
servos, which is required for the Autopilot to operate. A green status indicator shows the AP
DISC switch is closed and the GFC 700 is actively receiving 28. volts. A red X indicates the
GIAs and servos are no longer receiving the +28 VDC AP DISC power (switch open or other
fault).
MONITOR/CONTROL BOARD STATUS
Shows the condition of various monitor board components.
SERVO PROGRAM (1-3): Servo program discretes are used to determine the HW strapping for
each GSA to define the servo type. This information can be cross-referenced against the
system interconnects to verify proper servo grounding.
AP DISCONNECT: Same as GIA Status.
PFT: Indicates whether the pre-flight test has passed or failed.
HIGH RES & HIGH RNG Load CELL CAL: Shows the condition of the high resolution and high
range load cells on the monitor board. If box is black, this indicates a corrupt or missing load
cell calibration; return the servo to Garmin.
NOTE
For the Yaw GSA 9000 servo, the HIGH RNG LOAD CELL CAL box will have a
Red-X. This is normal since this servo motor does not have this component.
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DRIVE SERVO
Allows the technician to enter a desired RPM at which to manually drive the selected servo.
Direction of rotation is controlled by the polarity of the RPM (+ or -). After the speed is entered,
the technician may use the ENG CLCH and DRV SRVO softkeys to drive the servo.
NOTE
Be especially certain that the flight controls are clear and safe to operate before
manually driving the servo.
SERVO DATA
Shows real-time reported data including servo voltage, speed, motor current, load cell torque,
and clutch solenoid status. A green box indicates the servo clutch is engaged.
SLIP CLUTCH TEST RESULTS
This window is used during the automatic slip clutch torque measurement check.
5.8.2
GIA Fault Log Descriptions
The section was created to help determine why the GFC 700 has failed the Pre-Flight Test
indicated by the red
annunciation, it defines the PFT sequence for the servos and the
GFC 700 system and then provides troubleshooting information to help resolve failures.
There are 16 steps to the GFC 700 PFT. The PFT is performed by both GIA’s at startup, and
needs to pass on both GIA’s before the autopilot can be engaged.
The PFT is only started if the AHRS has aligned, the GIA’s and servos are configured and the
certification gains are valid. If the PFT has not completed after one minute from when the
initialization started, the PFT will fail. After the system PFT has passed, it will be performed
again if a servo resets, if the autopilot servo breaker is reset or the cross side GIA restarts it.
Generally, the PFT failure fault is logged in the GIA Maintenance Log and not in the Servo
Maintenance Logs unless the GIA log fault identifies a servo problem.
NOTE
Thoroughly understanding the operation of the G1000 system in Configuration
mode is recommended before starting this procedure. The GFC Status page may
be used to check the status of the servos and engage them to aid in
troubleshooting
To access the GIA and GSA Maintenance Logs, perform the following steps –
1. Start the G1000 in Configuration mode.
2. Use the FMS knob on PFD1 to go to the Diagnostics Terminal page in the System
group. This page allows the technician to view maintenance logs associated with the
GFC 700.
3. Choose ‘GIA 1’ or ‘GIA 2’ in the LRU window.
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4. In the SERVO window, choose ‘NONE’ to view the GIA Maintenance Log, or choose
a servo to view their logs.
5. Using the FMS knob, choose ‘VIEW MAINTENANCE LOG’ in the COMMAND
window.
6. Press the ENT key.
7. When the Maintenance Log data starts to display in the OUTPUT window, you may
see "More...press any key to continue..." at the bottom of the OUTPUT window. This
informs you there is more data to display and the system has paused allowing you to
view the data before continuing. To see more of the data, reselect the "VIEW
MAINTENANCE LOG" in the COMMAND window and press the ENT key. The
"...press any key to continue..." function is not active at this time.
8. Scroll through the OUTPUT list by pressing the OUTPUT softkey.
9. The GIA Maintenance Log can record any of the following faults:
•
FCS Task not started: Bad gains
The FCS task has not started because the gains are not present or have been
corrupted. Reload the gain files to correct.
•
FCS Task not started: Gain structure out of range
The FCS task has not started because the gains are not compatible with the GIA
software. Reload the gain files to correct.
•
PFT FAIL: Timeout, <STEP>
Pre-flight test has failed because the specified step has not passed in the allotted
time. See the GIA pre-flight steps for a description of the possible values for
<STEP> on the failed GIA and corrective actions.
•
PFT FAIL: Cross GIA Failed, State: <STEP>
Pre-flight test has failed on opposite GIA. <STEP> specifies the pre-flight test
step on selected GIA that was in progress when the pre-flight test failed on the
opposite GIA. See the GIA pre-flight steps for a description of the possible
values for <STEP> on the failed GIA and corrective actions.
•
PFT FAIL: <STEP>
Pre-flight has failed because the step specified has failed. See the GIA pre-flight
test steps for a description of the possible values for <STEP> on the failed GIA
and corrective actions.
•
AHRS MON invalid: <STATE>
The AHRS monitor has detected that the AHRS data is invalid. The possible
values for <STATE> are:
a. Mon Prmtr Invalid: The ARINC 429 data used by one of the monitors
has not been received.
b. Attitude Prmtr Invalid: The ARINC 429 pitch or roll angle has not been
received.
c. Exceeded Attitude Limits: The pitch or roll angle has exceeded the
engagement limits.
d. Cross Hdg Accel Fail: Cross heading acceleration monitor failed.
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e. Vert Accel Fail: Vertical acceleration monitor failed.
f.
Fltrd Cross Hdg Accel Fail: Filtered cross heading acceleration monitor
failed.
g. Fltrd Vert Accel Fail: Filtered vertical acceleration monitor failed.
h. Roll Accel Fail: Roll acceleration monitor has failed.
i.
Normal Accel Fail: Normal acceleration has failed.
Troubleshoot the GRS 77, GRS 7800, or GSU 75B for the cause of the failure.
•
Stuck switch invalidated parameter: <AXIS>
A MET switch in the specified axis is stuck.
Check the MET (trim) switches for proper operation.
•
PRMTR: <PARAMETER> MODE:<MODE> Parameter lost
The mode specified by <MODE> has been disengaged because the parameter
specified by <PARAMETER> has become invalid. The following is a list of some
of the possible values for <PARAMETER>:
a. AD TDM Comm Valid: The specified mode has been disengaged
because communication with the servos, via the Time Division Multiplexer
protocol, has been lost.
b. AP Pitch MET not stuck: The specified mode has been disengaged due
to a stuck pitch MET switch.
Check the MET (trim) switches for proper identification.
5.8.3
GIA Pre-Flight Test Steps
PFT step 0: System initialization, verify GFC powered
This step is checking to make sure the GFC is powered up. It checks to make sure the GIA AP
disconnect input is connected to 28 volts, and makes sure the Servos are up and
communicating.
If this step fails, make sure the GIA is connected to AP disconnect by using the GFC
configuration page. Also make sure all configured Servos are communicating by checking for
Servo product data in configuration mode.
PFT step 1: System initialization, verify GIA audio is valid.
This step is checking to make sure that the GIA audio region has been loaded and configured.
If this step fails, load GIA audio region and audio configuration.
PFT step 2: System initialization, verify required servos are configured
This step is checking to make sure the current Servo configuration matches the Servo
configuration specified in the certification gain file.
If this step fails, then make sure the Servo configuration on the GFC configuration page
matches the Servo configuration specified in the configuration gain (.cgn) file.
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PFT step 3: System initialization, verify selected side
This step is checking to make sure the PFD1 is online and sending the selected AFCS side
data over HSDB to GIA1.
If this step fails, then make sure the PFD is powered up and there is an Ethernet connection
from the PFD to the GIA.
PFT step 4: System initialization, verify AHRS monitor
This step is checking to make sure the AHRS monitor is valid and not reporting an AHRS
failure.
NOTE: AHRS monitor will be assumed valid if on the ground.
If this step fails, then make sure the AHRS and ADC or ADAHRS is powered up and sending
valid attitude data to the G1000.
PFT step 5: System initialization, verify servo PFT is complete
This step is checking to make sure that all servos have completed their own PFT. This does
not check whether the servo PFT passed or failed. It verifies that the servo PFT is no longer in
progress.
PFT step 6: Verify cross GIA is initialized
This step is checking to make sure the other GIA is also on step 6 of its PFT.
If this step fails, try cycling power on GIA1, GIA2, and all servos. If PFT still fails at step 6 then
you will need to go check the PFT status of the other GIA and see what step it is failing (it
should be prior to step 6). NOTE: The PFT status is communicated between GIA1 and GIA2
using HSDB. As a result, both the PFD and MFD must be powered for this state to pass.
PFT step 7: Verify servo type
This step is checking to make sure the Servos are the correct type (torque and speed).
If this step fails, make sure the Servo configuration on the GFC configuration page matches the
Servos installed in the aircraft.
PFT step 8: Verify servo first certification data
This step is checking to make sure the servos have the same certification gains loaded in them
as the GIAs have.
If this step fails, reload the certification gains in GIA1, GIA2, and all servos.
PFT step 9: Verify servo second certification data
This step is checking to make sure the servos have the same certification gains loaded in them
as the GIAs have.
If this step fails, reload the certification gains in GIA1, GIA2, and all servos.
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PFT step 10: Updating servo RTC
This step is setting the system time in the servos to by the same time as the GIA system time.
This step should never fail.
PFT step 11: Verify servo PFT status
This step is checking to make sure the servos have all passed their own PFT.
If this step fails, please proceed to servo PFT explanation below.
PFT step 12: Verify AP disconnect enabled
This step is checking to make sure GIA1, GIA2, and all servos have are connected to a 28 volt
AP disconnect.
If this step fails, make sure the AP disconnect input to GIA1, GIA2, and all servos is connected
and registering 28 volts. Make sure the AP disconnect switch has been installed in the aircraft.
Make sure no one is holding the AP disconnect switch down on the yoke.
PFT step 13: Verify servo validity
This step is checking to make sure all the Servos are up and communicating with valid data to
the GIA in TDM mode.
If this step fails, then make sure all Servos are turned on and communicating by checking for
green boxes on the GFC configuration page.
PFT step 14: Verify servo enable/disable discrete input
This step is checking the servo discrete inputs. It is not used on King Air.
PFT step 15: Verify cross GIA PFT is completed
This step is checking to make sure the other GIA is also on step 15 of its PFT.
If this step fails, try cycling power on GIA1, GIA2, and all servos. If PFT still fails at step 15 then
you will need to go check the PFT status of the other GIA and see what step it is failing. NOTE:
The PFT status is communicated between GIA1 and GIA2 using HSDB. As a result, both the
PFD and MFD must be powered for this state to pass.
PFT step 16: PFT completed
The PFT has successfully completed.
PFT step 17: PFT failed
The PFT has failed.
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5.8.3.1
Servo Faults and Troubleshooting
Whenever a servo fault occurs, a status message is logged to the corresponding servo control
or monitor maintenance log. This information is also accompanied by a time and date stamp.
An “RTC DATE” entry is made every time a servo is powered on, it is normally not useful for
troubleshooting.
The following is a listing of possible faults that could be reported in a GSA fault log. Faults can
occur in either the monitor board processor or the control board processor, both of which are
contained in the GSA unit.
5.8.3.1.1 Monitor Processor
The monitor processor contains the logs that are found in these processors 2 – Pitch Servo
4 – Roll Servo
6 - Yaw
8 – Pitch Trim Servo
There are two main groupings of faults that can occur in the monitor processor:
The first grouping of faults can occur during the GSA unit pre-flight test (PFT). If there is a fault
during PFT the unit will not be able to transition to normal mode and the only way to clear this
state would be to cycle unit power.
The second grouping of faults can occur during normal mode. These faults generally cause a
removal of power to the GSA and report that a fault has occurred to the GIA.
The Notes column indicates any actions that can be taken to troubleshoot the problem in the
aircraft by the technician. Any faults that are not listed here indicate an internal problem
requiring replacement of the servo. If the items in the Notes column check out ok, replace the
servo.
PFT Faults
MONITOR PFT STEP
NOTES
"INTERNAL COMM FAIL"
This can sometimes be a result of a failure on the other internal
servo board, check faults on the other processor
"UNSW POWER INV"
Check unit power
"MON SOL PWR ON FAIL"
Check unit power and AP Disconnect power
"CTL SOL PWR ON FAIL"
Check unit power and AP Disconnect power
"SOL PWR FAIL"
Check unit power and AP Disconnect power
"CERT DATA
UNINSTALLED"
Upload the certification gain file to the Monitor board
"STRAP CODE
MISMATCH"
Check the connector strap inputs to the unit
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Normal Mode Faults
MONITOR FAULT
NOTES
"GIA DIS FAULT"
Check the AP Disconnect power into the unit
"HOST DATA DIF"
Check the AHRS wiring to the system
"HOST DATA INV"
Check the AHRS wiring to the system
"SVO PWR INV"
Check unit power and AP Disconnect power
“STRP CODE CHNG”
Check the connector strap inputs to the unit
“MET STUCK SWTCH”
Check the MET switch inputs into the system
“MET STATUS DIF”
Check the MET switch inputs into the system
5.8.3.1.2 Control Processor
The control processor contains the logs that are found in these processors –
3 – Pitch Servo
5 – Roll Servo
7 - Yaw
9 – Pitch Trim Servo
There are two main groupings of faults that can occur in the control processor.
The first grouping of faults can occur during the GSA unit pre-flight test (PFT). If there is a fault
during PFT the unit will not be able to transition to normal mode and the only way to clear this
state would be to cycle unit power.
The second grouping of faults can occur during normal mode. These faults generally cause a
disconnect of power to the GSA and report that a fault has occurred to the GIA.
The Notes column indicates any actions that can be taken to troubleshoot the problem in the
aircraft by the technician. Any faults that are not listed here indicate an internal problem
requiring replacement of the servo. If the items in the Notes column check out ok, replace the
servo.
PFT Faults
CONTROL PFT STEP
NOTES
"INT COMM TEST FAIL"
This can sometimes be a result of a failure on the other board,
check faults on other processor
"CTL MOT PWR ON FAIL"
Check unit power and AP Disconnect power
"MON MOT PWR ON FAIL"
Check unit power and AP Disconnect power
"HALL 1 FAIL"
Check unit power and AP Disconnect power
"HALL 2 FAIL"
Check unit power and AP Disconnect power
"HALL 3 FAIL"
Check unit power and AP Disconnect power
"HALL 4 FAIL"
Check unit power and AP Disconnect power
"HALL 5 FAIL"
Check unit power and AP Disconnect power
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CONTROL PFT STEP
NOTES
"HALL 6 FAIL"
Check unit power and AP Disconnect power
"CURR OFFST FAIL"
Check unit power and AP Disconnect power
"SVO TYPE FAIL"
Check unit power and AP Disconnect power
"CERT DATA
UNINSTALLED"
Upload the certification gain file to the Control board
"STRAP CODE
MISMATCH"
Check the connector strap inputs to the unit
Normal Mode Faults
CONTROL FAULT
NOTES
"GIA DIS FAULT"
Check the AP Disconnect power into the unit
"HOST DATA DIF"
Check the AHRS wiring to the system
"HOST DATA INV"
Check the AHRS wiring to the system
"SVO PWR INV"
Check unit power and AP Disconnect power
“STRP CODE CHNG”
Check the connector strap inputs to the unit
“MET STUCK SWTCH”
Check the MET switch inputs into the system
“MET STATUS DIF”
Check the MET switch inputs into the system
5.8.3.2
Downloading GIA and GSA Maintenance Logs
If additional assistance is needed troubleshooting autopilot faults, the Maintenance logs can be
downloaded to an SD card as a text file (.txt) and emailed to Garmin Aviation Product Support.
Please call Garmin Aviation Product Support before you send a Maintenance Log to notify them
you are sending it to prevent a delay in response. You may download multiple GIA and GSA
Maintenance Logs to the same file, however in your email to Garmin you must furnish the order
in which they were downloaded (i.e. GIA1, then GIA2, then SRVO PTCH MON, then SRVO
PTCH CTL, etc.).
1. Insert a FAT 32 formatted SD card into the top slot of the PFD before turning on the
displays.
2. Power up PFD1, PFD2 and MFD in the configuration mode.
3. On the PFD1 in the System page group, use the small FMS knob to scroll to the
Diagnostics Terminal page.
4. Press the LG2CRD softkey at the bottom of the PFD1.
5. Enable the cursor by pressing the FMS knob, select “GIA1” in the LRU drop down menu
and then press the ENT key to select it.
6. Skip the SERVO box and move the cursor to the COMMAND box and select “View
Maintenance Log” in the drop down menu then press the ENT key. The error log data
will be displayed in the OUTPUT box. If you see the “more…press any key to continue”
text at the bottom of the screen, you may need to reselect “View Maintenance Log” for
GIA data to allow it to continue scrolling down the screen (pressing any key will not
continue, disregard the text instruction you to do so). Continue to scroll through all the
OUTPUT data until you see the text, “End of Fault Log”.
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7. Move the cursor back to the LRU box, select “GIA2” in the LRU drop down menu and
then press the ENT key to select it.
8. Skip the SERVO box and move the cursor to the COMMAND box and select “View
Maintenance Log” in the drop down menu then press the ENT key. The error log data
will be displayed in the OUTPUT box. If you see the “more…press any key to continue”
text at the bottom of the screen, you may need to reselect “View Maintenance Log” for
GIA data to allow it to continue scrolling down the screen (pressing any key will not
continue, disregard the text instruction you to do so). Continue to scroll through all the
OUTPUT data until you see the text, “End of Fault Log”.
9. If you need to download Servo fault logs (usually done at the request of Garmin Product
Support), perform the following steps. Otherwise, skip to step 10.
a) In the LRU box, you may select either “GIA1” or “GIA2”.
b) In the SERVO box, choose a servo using the FMS knobs. Each servo contains
two logs, one in the Monitor (MON) processor and one in the Control (CTL)
processor. You must download both for each servo separately.
c) In the COMMAND box, select “View Maintenance Log” and press the ENT key.
d) The log will appear in the OUTPUT box. It will scroll to the end automatically.
When it is complete, repeat steps a-c for the other servos in the aircraft. Be sure
to note the order the servos were downloaded in including the Monitor or Control
logs to email to Garmin Product Support. Without knowing the order in which the
logs were downloaded, Garmin will be unable to process them and will ask for
another full download.
10. Press the LG2CRD softkey to turn off the recording function.
11. Wait 1 minute for the system to save the data from the download to the SD card.
12. While you are waiting for the data to be saved to the SD card, record the order of the
LRU’s and/or Servos were downloaded so that you can provide that information to
Cessna or Garmin to help decipher the order of the error data.
13. Power down the G1000 System and remove the SD card.
14. Insert the SD card in the card reader of a laptop or desktop computer and open the
“diag_buf_log.txt” file from the SD card using the WordPad program. Verify that all of the
fault logs were downloaded by checking for the “End of Fault Log” message at the end of
the GIA data, and that the last servo log entry has the current date.
15. Insert the fault log as an attachment to an email and include the LRU order how the data
was downloaded and send to Garmin Aviation Product Support at
avionics@Garmin.com.
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5.9
5.9.1
Backup Communications Path Checks
Overview
The G1000 system architecture is designed with redundant communication ports for several
LRUs so that critical information can continue to be displayed in the event of an equipment or
wiring failure. Of most importance is flight attitude, heading, and air data information. The GRS
77/7800 and GDC 7400 each have four separate ARINC 429 data lines which are all capable of
sending data to the displays. The GEA 71, GTX 33(D) or GTX 3000, and GMA 1347D each
have two redundant serial communication paths for the same purpose. See Figure 2-30 for a
basic G1000 block diagram depicting this architecture. Several other diagrams are shown later
in this section for illustrative purposes. When troubleshooting, refer to the G1000 Wiring
Diagram listed in Table 1-1.
NOTE
Refer to Section 9.10 for procedures on checking the status of each configured
G1000 / GFC 700 backup data path.
5.9.2
Data Path Failures
Failure Message
Cause
FAILED PATH – A data path has
failed.
A communications data path
status is not being received by the
G1000.
Solutions
•
•
•
5.10
Determine which data path has
failed: See Section 5.1.1.
Check wiring continuity for the failed
path.
Swap or replace the affected LRU.
GDU 105X Troubleshooting
5.10.1 GDU 105X Symptoms
Symptom
Recommended Action
•
Display is blank
•
•
Display resets
•
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Ensure that a cell phone or a device using cell phone technology is not turned
on (even in a monitoring state) in the cabin.
Cycle power.
 If GDU recovers, observe display for yellow text containing error
information at the top of the screen. If message indicates software need
to be re-loaded, then re-load software. Otherwise, replace the GDU.
Use a bright light to verify LCD is active.
 Adjust avionics dimmer control full clockwise.
 Manually turn up backlight on the PFD and load configuration files to the
GDU.
Ensure slide lock is fully engaged with the locking tabs on the back of the unit.
 If slide lock is not fully engaged, remove connector and verify the locking
tabs on the GDU are perpendicular to the connector. If necessary,
straighten them before reseating connector.
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Symptom
Recommended Action
•
Display flickers
•
•
•
•
•
•
SD card is stuck in GDU
•
•
•
•
Display will not track dimmer bus
Keyboard will not track dimmer bus
DO NOT insert a screwdriver of any length into the card slot.
DO NOT pry against the overlay.
DO NOT force the SD Card out.
Use a small screwdriver in the groove on the side of the exposed end of the
card to help pull out the card.
Push the card in further to release the card locking mechanism.
Check SD Card for having more than one label. Two or more labels on the
card will cause sticking.
 Remove all but one label.
Ensure the SD card is from SanDisk. Use of other SD Cards is not
recommended.
If card was inserted with the label facing to the right, do not attempt to remove.
Return the unit to an authorized repair facility for service.
•
Go to the GDU TEST page in configuration mode and verify button, knob, or
joystick operates correctly by observing a change in color from red to green in
the button/knob/joystick icon when the button/knob/joystick is pressed. If a
button is stuck, the button icon will be green without pressing the button as
soon as you turn to the GDU TEST page.
 If problem is verified, replace GDU.
•
Allow the system to verify the data in internal memory for approximately five
minutes after power-up.
If a database does not activate, reload the problem database.
A button/knob/joystick does not
appear to function
Terrain/Obstacle/SafeTaxi does not
display
Ensure GDU is receiving power. If a circuit breaker is tripped, determine
source of short before resetting breaker.
Ensure circuit breakers have not failed and power wire connections are secure.
Swap PFD1 and PFD2.
 If problem follows unit, replace the display. Please note the position it
failed in (PFD1/2).
 If problem does not follow unit, troubleshoot aircraft wiring for fault.
•
•
•
•
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Reload GDU configuration files.
If display is a PFD, swap PFD1 and PFD2 to see if problem remains with
display.
 Replace display if condition remains with the same unit.
 If condition remains in original position after swapping displays, check GDU
dimmer input to verify voltage is present.
If display is the MFD, check dimmer input to verify voltage is present.
 Replace MFD if dimmer voltage is present.
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5.11
GDU 105X Alerts
5.11.1 Software/Configuration Alerts
Failure Message
Cause
SW MISMATCH – GDU software
version mismatch. Xtalk is off.
The system has found the PFDs
and/or MFD software versions do
not match.
MANIFEST – PFD 1 software
mismatch. Communication
Halted.
MANIFEST – PFD 2 software
mismatch. Communication
Halted.
MANIFEST – MFD1 software
mismatch. Communication
Halted.
The system has detected an
incorrect software version loaded
in the specified PFD.
Solution
Load correct software version. See
Section 3.8.2 for GDU 1050A Software
Loading procedure.
The system has detected an
incorrect software version loaded
in MFD.
•
CNFG MODULE – PFD 1
configuration module is
inoperative.
The PFD master configuration
module has failed.
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Check master configuration module
connector and wiring for damage
inside the GDU connector
backshell.
 Replace master configuration
module wiring and pins.
 If problem persists, replace
master configuration module.
NOTE
New Terrain/Obstacle cards, Jeppesen
Aviation Database and other optional
features (i.e. TAWS unlock card) will
need to be replaced if the master
configuration module is changed. The
G1000 System ID number will change
to a new number when installing a new
master config module. The old Terrain
and other databases will no longer
work as they will remain locked to the
old System ID number.
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Failure Message
Cause
Solution
•
•
MFD1 CONFIG – MFD1
configuration error. Config service
req’d.
PFD 1 CONFIG – PFD 1
configuration error. Config service
req’d.
A configuration mismatch has
occurred between the display and
the Master Configuration Module.
PFD 2 CONFIG – PFD 2
configuration error. Config service
req’d.
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Reload the display configuration
files from SD Loader Card.
Reload system configuration files
by pressing the UPDT CFG
softkey on the Configuration
Upload Page in the PFD1 System
Page Group to load configuration
files into the configuration module.
 If message persists, check
PFD1 config module wiring for
faults and replace if necessary.
 If issue continues, replace
PFD1 master configuration
module.
 If problem persists, replace the
display.
NOTE
New Terrain/Obstacle cards, Jeppesen
Aviation Database and other optional
features (i.e. TAWS unlock card) will
need to be replaced if the master
configuration module is changed. The
G1000 System ID number will change
to a new number when installing a new
master config module. The old Terrain
and other databases will no longer
work as they will remain locked to the
old System ID number.
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5.11.2 Database Alerts
Failure Message
Cause
MFD1 DB ERR – MFD1 aviation
database error exists.
PFD 1 DB ERR – PFD 1 aviation
database error exists.
The MFD or specified PFD has
encountered an error in the
Jeppesen aviation database.
Solution
•
•
PFD 2 DB ERR – PFD 2 aviation
database error exists.
MFD1 DB ERR – MFD1 terrain
database error exists.
PFD 1 DB ERR – PFD 1 terrain
database error exists.
PFD 2 DB ERR – PFD 2 terrain
database error exists.
MFD1 DB ERR – MFD1 obstacle
database error exists.
PFD 1 DB ERR – PFD 1 obstacle
database error exists.
PFD 2 DB ERR – PFD 2 obstacle
database error exists.
MFD1 DB ERR – MFD1 airport
terrain database error exists.
PFD 1 DB ERR – PFD 1 airport
terrain database error exists.
PFD 2 DB ERR – PFD 2 airport
terrain database error exists.
The MFD has encountered an
error in the terrain database.
Reload aviation database into the
display.
Contact Garmin Aviation Product
Support for assistance if needed.
•
•
Reload the database.
Contact Garmin Aviation Product
Support for further assistance if
needed.
•
•
Reload the database.
Contact Garmin Aviation Product
Support for further assistance if
needed.
•
•
Reload the database.
Contact Garmin Aviation Product
Support for further assistance if
needed.
The specified PFD has
encountered an error in the terrain
database.
The MFD has encountered an
error in the obstacle database.
The specified PFD has
encountered an error in the
obstacle database.
The MFD has encountered an
error in the airport terrain
database.
The specified PFD has
encountered an error in the airport
terrain database.
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5.11.3 Cooling Alerts
Failure Message
Cause
Solution
•
MFD1 COOLING – has poor
cooling. Reducing power usage.
MFD1 has exceeded its operating
temperature range.
•
•
PFD 1 COOLING – has poor
cooling. Reducing power usage.
PFD 1 has exceeded its operating
temperature range.
•
•
PFD 2 COOLING – has poor
cooling. Reducing power usage.
PFD 2 has exceeded its operating
temperature range.
•
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Check cooling fan and wiring for
proper operation (if applicable).
 Replace cooling fan if unable
to determine if operating
correctly.
 If problem persists, replace the
MFD.
If problem continues contact
Garmin Aviation Product Support
for assistance.
Check cooling fan and wiring for
proper operation (if applicable).
 Replace cooling fan if unable
to determine if operating
correctly.
 If problem persists, replace the
PFD1.
If problem continues contact
Garmin Aviation Product Support
for assistance.
Check cooling fan and wiring for
proper operation (if applicable).
 Replace cooling fan if unable
to determine if operating
correctly.
 If problem persists, replace the
PFD2.
If problem continues contact
Garmin Aviation Product Support
for assistance.
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5.11.4 Key Alerts
Failure Message
Cause
Solution
MFD1 “key” KEYSTK – key is
stuck.
The SYSTEM has determined a
key is stuck on MFD1.
•
PFD 1 “key” KEYSTK – key is
stuck.
The system has determined a key
is stuck on the PFD 1.
•
PFD 2 “key” KEYSTK – key is
stuck.
The system has determined a key
is stuck on the PFD 2.
Go to the GDU TEST page in
configuration mode and verify key
is stuck (if key is stuck the
corresponding indicator will be
green).
Exercise suspected stuck key and
reset GDU TEST page to see if
indicator remains green without
pressing the key.
 If problem persists replace the
display.
5.11.5 Miscellaneous Alerts
Failure Message
Cause
Solution
•
XTALK ERROR – A flight display
cross talk error has occurred.
A communication error has
occurred between the MFD and/or
PFDs.
•
•
•
DATA LOST – Pilot stored data
lost. Recheck settings.
•
Pilot stored data has been lost.
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Ensure a database error has not
occurred (identified in the ALERTS
window on the PFD).
 If a database error has
occurred, correct error before
proceeding.
Check display Ethernet
interconnect wiring.
Replace PFD1 with a known good
unit, to verify location of problem:
 If problem persists, reinstall
original PFD1 and replace
PFD2.
 If problem persists, reinstall
PFD2 and replace MFD.
If the CLR key was held during a
power cycle, disregard message.
Cycle power to PFD1:
 Ensure CLR key is not stuck
on the GDU TEST page.
 If problem persists, replace
PFD1.
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Failure Message
MFD1 SERVICE – needs service.
Return unit for repair.
PFD 1 SERVICE – needs service.
Return unit for repair.
PFD 2 SERVICE – needs service.
Return unit for repair.
PFD 1 VOLTAGE – PFD 1 has
low voltage. Reducing power
usage.
PFD 2 VOLTAGE – PFD 2 has
low voltage. Reducing power
usage.
MFD1 VOLTAGE – MFD1 has low
voltage. Reducing power usage.
Cause
The G1000 has determined MFD1
needs service.
The G1000 has determined the
specified PFD needs service.
The specified PFD supply voltage
is low.
The MFD supply voltage is low.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Solution
•
Ensure the MFD connector is fully
seated and locked.
•
Return unit to an Authorized Repair
Facility for service.
•
Ensure the PFD connector is fully
seated and locked.
•
Return unit to an Authorized Repair
Facility for service.
•
Check input voltage to PFD.
•
If input voltage is ok, replace PFD.
•
Check input voltage to MFD.
•
If input voltage is ok, replace MFD.
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5.11.6 GMA Symptoms
Symptom/Failure
Message
Recommended Action
Noise in Audio
Most often the cause of the noise is external to the GMA. Try the following to locate
the source of the noise before replacing the GMA:
•
Try a different pair of headsets. Noise cancelling headsets may pick up and/or
generate more noise than standard headsets from their own circuitry.
•
Check for noise with the engine turned off.
 If the noise is present only when the engine is running, check the generator
and/or ignition system as possible sources of noise (see applicable airframe
specific maintenance manual).
•
Check for noise as all electrical equipment is turned on and off (strobes, other
radios, etc.).
 If the noise is identified from one electrical system or component refer to the
applicable airframe specific maintenance manual.
•
Ensure the NAV/COM squelch is not open.
•
Ensure the ADF and DME audio is not active.
•
Ensure the marker beacon audio is not active.
•
Ensure the ICS squelch is not open.
 Master squelch level can be adjusted on the GMA CONFIGURATION page
for higher noise environments.
•
Replace unit only after all possible external sources of noise are eliminated.
Buttons Do Not Work.
•
Some buttons are disabled in the GMA CONFIGURATION page by default.
This is to remove potential sources of audio noise for inputs that are not used. If
in doubt as to which buttons should be disabled, reload GMA config files and
other config files for optional equipment installed in the aircraft (i.e. ADF, HF,
etc.) from the loader card.
COM Bleedover
•
Verify on the GMA CONFIGURATION page that “Disable Split COM” has a
green box. Due to the closeness of the COM antennas and high power of the
COM transceivers, Split COM operation is not approved. If the box is black
(indicating COM ½ button is active), highlight “Disable Split COM” with the
cursor and press the ENT key to turn the box green which will deactivate Split
COM mode.
Speaker Cuts Out
•
Reduce volume level of the item that caused the speaker to cut out when turned
up. A speaker protection circuit disables the speaker output if the volume is too
high. If the volume is not sufficient, replace aircraft cabin speaker, reference the
Airframe Maintenance Manual.
Mic Audio Heard in
Speaker
•
Reduce ICS Volume.
GMA XTALK – GMA
crosstalk error has
occurred.
•
•
•
•
•
Ensure both GMA units are receiving power.
Ensure both units are properly configured by verifying there are no GMA alert
messages.
Check interconnect wiring between the GMA’s for faults.
Replace GMA1.
If problem persists, reinstall GMA1 and replace GMA2.
G1000 NXi System Maintenance Manual
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Page 190
Revision 2
5.11.7 GMA Alerts
Failure Message
GMA1 SERVICE – GMA1 needs
service. Return unit for repair.
GMA2 SERVICE – GMA2 needs
service. Return unit for repair.
Cause
Solution
The system has determined that
the specified GMA 1347D needs
service.
•
•
Replace GMA unit.
Return unit to an Authorized Repair
Facility for service.
•
•
Ensure GMA1 is receiving power.
Ensure both GIAs are receiving
power.
Ensure all GDUs are receiving
power.
Ensure the GMA/GIA RS-232 data
lines are working properly.
Ensure the GIA/GDU Ethernet data
lines are working properly.
GMA1 FAIL – GMA1 in
inoperative.
•
GMA2 FAIL – GMA2 in
inoperative.
The system has detected a failure
in the specified GMA 1347D.
•
•
•
MANIFEST – GMA1 software
mismatch. Communication
Halted.
MANIFEST – GMA2 software
mismatch. Communication
Halted.
The system has detected an
incorrect software version loaded
in the specified GMA 1347D.
Load the correct unit software. See
Section 3.8 for the Software Loading
procedure.
•
GMA1 CONFIG – GMA1
configuration error. Config service
req’d.
GMA2 CONFIG – GMA2
configuration error. Config service
req’d.
Replace GMA1.
The system has detected a GMA
1347D configuration mismatch for
the specified unit.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Load GMA configuration files, see
Section 3.8.
•
Replace GMA.
•
If problem persists, replace
master configuration module,
check config module wiring for
faults and replace if necessary.
NOTE
New Terrain/Obstacle cards, Jeppesen
Aviation Database and other optional
features (i.e. TAWS unlock card) will
need to be replaced if the master
configuration module is changed. The
G1000 System ID number will change
to a new number when installing a new
master config module. The old Terrain
and other databases will no longer
work as they will remain locked to the
old System ID number.
Page 191
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5.12
GIA 63 Troubleshooting
5.12.1 COM
Symptom
Recommended Action
•
Switch GIA1 and GIA2, to verify location of problem:
 If problem follows unit, replace GIA.
 If problem does not follow unit, check COM antenna and cabling for
faults.
•
Switch GIA1 and GIA2, to verify location of problem:
 If problem follows unit, replace GIA.
 If problem does not follow unit, check COM antenna and cabling for
faults.
•
Switch GIA1 and GIA2, to verify location of problem:
 If problem follows unit, replace GIA.
 If problem persists, replace GMA1 with a known good unit.
 If problem persists, reinstall original GMA1 and replace GMA2.
Weak COM transmit power
Weak COM receiver
No COM sidetone
5.12.2 NAV
Symptom
Recommended Action
•
•
Weak NAV receiver
Set up a NAV/COM Ramp Test Set to radiate a test signal.
Switch GIA1 and GIA2, to verify location of problem:
 If problem follows unit, replace GIA.
 If problem does not follow unit, check NAV antenna, coupler, and
cabling for faults.
5.12.3 G/S
Symptom
Recommended Action
•
•
Weak G/S receiver
Set up a NAV/COM Ramp Test Set to radiate a test signal.
Switch GIA1 and GIA2, to verify location of problem:
 If problem follows unit, replace GIA.
 If problem does not follow unit, check NAV antenna, coupler, and
cabling for faults.
G1000 NXi System Maintenance Manual
King Air 300 Series
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Page 192
Revision 2
5.12.4 GPS
Symptom
Recommended Action
•
•
Will Not Acquire Satellites
•
•
5.13
Ensure that a cell phone or a device using cell phone technology is not
turned on (even in a monitoring state) in the cabin.
Using the MFD Aux – GPS Status page, verify the signal strength bars are
not erratic. If so, this indicates outside interference is affecting the GPS
receivers. Find and remove the source of interference (i.e. cell phones,
FBO datalink antennas, etc.).
Check date and time on Date/Time Setup Page.
 If date and time are incorrect, enter the correct date and time.
Switch GIA1 and GIA2, to verify location of problem:
 If problem follows unit, replace the GIA.
 If problem does not follow unit, check GPS antenna and cabling.
GIA Alert Messages
5.13.1 COM Alerts
Failure Message
Cause
Solutions
COM1 SERVICE – COM1 needs
service. Return unit for repair.
The system has determined
COM1 needs service.
•
•
Replace GIA1.
Return unit to an Authorized Repair
Facility for service.
COM2 SERVICE – COM2 needs
service. Return unit for repair.
The system has determined
COM2 needs service.
•
•
Replace GIA2.
Return unit to an Authorized Repair
Facility for service.
•
Press the push-to-talk switch(s) again
to cycle its operation.
Check push-to-talk switch(s) and
wiring.
Check GIA1/GMA 1347D #1
interconnect.
Switch GIA1 and GIA2, to identify
whether the unit or connectors/wiring
is at fault (Both GIAs must be
configured when swapped; see
Section 7.3):
 If problem follows the unit,
replace GIA1.
 If problem persists, replace
GMA 1347D #1.
•
•
COM1 PTT – COM1 push-to-talk
key is stuck.
The COM1 external push-to-talk
(PTT) switch is stuck in the
enabled (or “pressed”) state.
•
•
•
•
COM2 PTT – COM2 push-to-talk
key is stuck.
The COM2 external push-to-talk
(PTT) switch is stuck in the
enabled (or “pressed”) state.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
Press the push-to-talk switch(s) again
to cycle its operation.
Check push-to-talk switch(s) and
wiring.
Check GIA2/GMA 1347D #2
interconnect.
Switch GIA1 and GIA2, to identify
whether the unit or connectors/wiring
is at fault (Both GIAs must be
configured when swapped, see
Section 7.3):
 If problem follows the unit,
replace GIA2.
 If problem persists, replace
GMA 1347D #2.
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Revision 2
Failure Message
COM1 RMT XFR – COM1 remote
transfer key is stuck.
COM2 RMT XFR – COM2 remote
transfer key is stuck.
COM1 TEMP – COM1 over temp.
Reducing transmitter power.
COM2 TEMP – COM2 over temp.
Reducing transmitter power.
Cause
Solutions
The COM1 external remote
transfer switch is stuck in the
enabled (or “pressed”) state.
Press the COM1 external remote transfer
switch again to cycle its operation.
Check COM1 external remote transfer
switch and wiring.
Switch GIA1 and GIA2, to identify
whether the unit or connectors/wiring is
at fault (Both GIAs must be configured
when swapped, see Section 7.3)
 If problem follows the unit,
replace GIA1.
 If problem persists, continue to
troubleshoot remote transfer
switch & wiring.
The COM2 external remote
transfer switch is stuck in the
enabled (or “pressed”) state.
Press the COM2 external remote transfer
switch again to cycle its operation.
Check COM2 external remote transfer
switch and wiring.
Switch GIA1 and GIA2, to identify
whether the unit or connectors/wiring is
at fault (Both GIAs must be configured
when swapped, see Section 7.3):
 If problem follows the unit,
replace GIA2.
 If problem persists, continue to
troubleshoot remote transfer
switch & wiring.
•
The specified COM transceiver
is reporting a high temperature
condition and is reducing
transmit power to prevent
damage.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
•
Check fan, wiring and air tubing for
proper operation (if applicable).
Replace cooling fan if unable to
determine if operating correctly.
Replace GIA.
If problem persists, contact Garmin
Aviation Product Support for
assistance.
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Revision 2
5.13.2 NAV Alerts
Failure Message
Cause
Solution
NAV1 SERVICE – NAV1 needs
service. Return unit for repair.
The system has detected a failure
in NAV1 receiver.
•
•
Replace GIA1.
Return unit to an Authorized Repair
Facility for service.
NAV2 SERVICE – NAV2 needs
service. Return unit for repair.
The system has detected a failure
in NAV2 receiver.
•
•
Replace GIA2.
Return unit to an Authorized Repair
Facility for service.
NAV1 RMT XFR – NAV1 remote
transfer key is stuck.
NAV2 RMT XFR – NAV2 remote
transfer key is stuck.
The NAV1 external remote
transfer switch is stuck in the
enabled (or “pressed”) state.
Press the NAV1 external remote
transfer switch again to cycle its
operation.
Check NAV1 remote transfer switch and
wiring.
Switch GIA1 and GIA2, to identify
whether the unit or connectors/wiring is
at fault (Both GIAs must be configured
when swapped, see Section 7.3):
 If problem follows unit, replace
GIA1.
 If problem persists, continue to
troubleshoot remote transfer
switch & wiring.
The NAV2 external remote
transfer switch is stuck in the
enabled (or “pressed”) state.
Press the NAV2 external remote
transfer switch again to cycle its
operation.
Check NAV2 remote transfer switch and
wiring.
Switch GIA1 and GIA2, to identify
whether the unit or connectors/wiring is
at fault (Both GIAs must be configured
when swapped, see Section 7.3):
 If problem follows unit, replace
GIA1.
 If problem persists, continue to
troubleshoot remote transfer
switch & wiring.
G1000 NXi System Maintenance Manual
King Air 300 Series
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Revision 2
5.13.3 Glideslope Alerts
Failure Message
Cause
Solution
G/S1 SERVICE – G/S1 needs
service. Return unit for repair.
The system has detected a failure
in G/S1 receiver.
•
•
Replace GIA1.
Return unit to an Authorized Repair
Facility for service.
G/S2 SERVICE – G/S2 needs
service. Return unit for repair.
The system has detected a failure
in G/S2 receiver.
•
•
Replace GIA2.
Return unit to an Authorized Repair
Facility for service.
•
Switch GIA1 and GIA2 to verify
location of problem:
 If problem follows the unit,
replace GIA.
G/S1 FAIL – G/S1 is inoperative.
The system has detected a failure
in G/S1 receiver.
 If problem does not follow unit,
check G/S1 antenna and
cabling.
•
G/S2 FAIL – G/S2 is inoperative.
The system has detected a failure
in G/S2 receiver.
Switch GIA1 and GIA2 to verify
location of problem:
 If problem follows the unit,
replace GIA.
 If problem does not follow unit,
check G/S2 antenna and
cabling.
5.13.4 GPS Alerts
NOTE
Before troubleshooting, ensure that no cell phones or devices using cell phone
technology are turned on, even in a monitoring state, in the cabin.
Failure Message
Cause
MANIFEST – GPS1 software
mismatch. Communication
halted.
The system has detected an
incorrect software version loaded
in GIA1.
MANIFEST – GPS2 software
mismatch. Communication
halted.
The system has detected an
incorrect software version loaded
in GIA2.
GPS1 SERVICE – GPS1 needs
service. Return unit for repair.
The system has detected a failure
in GPS1 receiver.
GPS2 SERVICE – GPS2 needs
service. Return unit for repair.
The system has detected a failure
in GPS2 receiver.
GPS1 FAIL – GPS1 is inoperative.
The system has detected a failure
in GPS1 receiver.
GPS2 FAIL – GPS2 is inoperative.
The system has detected a failure
in GPS2 receiver.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Solution
Load the correct GPS software. See
Section 7.3 for the Software Loading
procedure.
•
•
Replace GIA unit.
Return unit to an Authorized Repair
Facility for service.
•
Switch GIA1 and GIA2, to verify
location of problem:
 If problem follows the unit,
replace GIA.
 If problem does not follow the
unit, check GPS antenna and
cabling.
Page 196
Revision 2
Failure Message
Cause
Solution
LOI – GPS integrity lost.
Crosscheck with other NAVS.
If the primary receiver is a WAAS
sensor, the alert indicates that
GPS position data has timed out.
•
GPS NAV LOST – Loss of GPS
navigation. Insufficient satellites.
There is no GPS position fix
available or the system is in dead
reckoning mode.
GPS NAV LOST – Loss of GPS
navigation. Position error.
The G1000 has detected an
internal position warning has
occurred.
GPS NAV LOST – Loss of GPS
navigation. GPS fail.
The G1000 has detected a GPS
engine failure.
•
•
Verify the area the aircraft was
traveling through did not have loss
of GPS coverage. FAA NOTAMs
may be issued for periods of
outages, or the US Coast Guard
website
http://navcen.uscg.gov/pdf/gps/gpsn
otices/GPS_Interference.pdf will
have notices posted.
Using the MFD Aux – GPS Status
page, verify the signal strength bars
are not erratic. If so, this indicates
outside interference is affecting the
GPS receivers. Find and remove
the source of interference (i.e. cell
phones, FBO datalink antennas,
etc.).
If GPS receivers cannot acquire a
position lock, troubleshoot per the
“Will not acquire satellites” section.
5.13.5 GIA Cooling Alerts
Failure Message
Cause
Solution
GIA1 COOLING – GIA1
temperature too low.
GIA1 operating temperature is too
low.
Allow unit to warm up.
GIA2 COOLING – GIA2
temperature too low.
GIA2 operating temperature is too
low.
Allow unit to warm up.
•
•
GIA1 COOLING – GIA1 over
temperature.
GIA1 has exceeded its operating
temperature range.
•
•
•
•
GIA2 COOLING – GIA2 over
temperature.
GIA2 has exceeded its operating
temperature range.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
Check fan, wiring and air tubing for
proper operation (if applicable).
Replace cooling fan if unable to
determine if operating correctly.
Replace GIA1.
If problem persists, contact Garmin
Aviation Product Support for
assistance.
Check fan, wiring and air tubing for
proper operation (if applicable).
Replace cooling fan if unable to
determine if operating correctly.
Replace GIA2.
If problem persists, contact Garmin
Aviation Product Support for
assistance.
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5.13.6 GIA Configuration Alerts
Failure Message
Cause
MANIFEST – GIA1 software
mismatch. Communication
Halted.
The system has detected an
incorrect software version loaded
in GIA1.
MANIFEST – GIA2 software
mismatch. Communication
Halted.
The system has detected an
incorrect software version loaded
in GIA2.
GIA1 CONFIG – GIA1 audio
config error. Config service req’d.
GIA2 CONFIG – GIA2 audio
config error. Config service req’d.
The GIA’s audio configuration files
are incorrect or missing.
Solution
Load the correct software. See Section
7.3 for the Software Loading procedure.
Reload audio configuration files.
•
•
GIA1 CONFIG – GIA1
configuration error. Config service
req’d.
The system has detected a GIA
configuration mismatch. If GIAs
are not properly configured after
being swapped/replaced, this
message appears.
•
GIA2 CONFIG – GIA2
configuration error. Config service
req’d.
GIA1 SERVICE – GIA1 needs
service. Return unit for repair.
GIA2 SERVICE – GIA2 needs
service. Return unit for repair.
The G1000 has detected a failure
in the specified GIA.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
Load the configuration files for that
GIA. See Section 7.3 3.8for GIA 63
Configuration Loading procedure.
If problem persists, replace master
configuration module, check config
module harness for faults and
replace if necessary.
NOTE
New Terrain/Obstacle cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new
number when installing a new
master config module. The old
Terrain and other databases will no
longer work as they will remain
locked to the old System ID number.
Replace GIA unit.
Return unit to an Authorized Repair
Facility for service.
Page 198
Revision 2
5.14
GEA Troubleshooting
5.14.1 GEA Alerts
Failure Message
MANIFEST – GEA1 software
mismatch. Communication
halted.
MANIFEST – GEA2 software
mismatch. Communication
halted.
Cause
Solution
The system has detected an
incorrect software version loaded
in the specified GEA 71.
Load the correct software version. See
Section 7.4 for GEA 71 Software Load
Procedure.
•
GEA1 CONFIG – GEA1
configuration error. Config service
req’d.
•
GEA1 CONFIG – GEA2
configuration error. Config service
req’d.
The system has detected a
configuration mismatch in the
specified GEA 71.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Load GEA configuration files. See
Section 7.4 for GEA 71
Configuration Procedure.
If problem persists, replace master
configuration module, check config
module harness for faults and
replace if necessary.
NOTE
New Terrain/Obstacle cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be
replaced if the master configuration
module is changed. The G1000
System ID number will change to a
new number when installing a new
master config module. The old
Terrain and other databases will no
longer work as they will remain
locked to the old System ID
number.
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Revision 2
5.15
GTX Troubleshooting
5.15.1 GTX Alerts
Failure Message
MANIFEST – GTX1 software
mismatch. Communication
halted.
MANIFEST – GTX2 software
mismatch. Communication
halted.
Cause
Solutions
The system has detected an
incorrect software version loaded
in the specified GTX unit.
Reload software.
XPDR1 CONFIG – XPDR1
configuration error. Config service
req’d.
•
Perform a SET>ACTV
configuration reset on the GTX
Config page and verify the aircraft
registration is present.
•
XPDR2 CONFIG – XPDR2
configuration error. Config service
req’d.
XPDR1 SRVC – XPDR1 needs
service. Return unit for repair.
XPDR2 SRVC – XPDR2 needs
service. Return unit for repair.
XPDR1 FAIL – XPDR 1 is
inoperative.
XPDR2 FAIL – XPDR 2 is
inoperative.
XPDR 1 ADS-B NO POS –
Transponder ADS-B is not
transmitting - OR XPDR 1 ADS-B NO TX –
Transponder ADS-B out failed
XPDR 2 ADS-B NO POS –
Transponder ADS-B is not
transmitting - OR XPDR 2 ADS-B NO TX –
Transponder ADS-B out failed.
The system has detected a
configuration mismatch for the
specified GTX unit.
The G1000 has detected a failure
in the specified GTX
The specified GTX is not
responding.
If error is still present, reload config
files from a loader card.
 If problem persists, replace
master configuration module,
check config module harness
for faults and replace if
necessary.
NOTE
New Terrain/Obstacle cards, Jeppesen
Aviation Database and other optional
features (i.e. TAWS unlock card) will
need to be replaced if the master
configuration module is changed. The
G1000 System ID number will change
to a new number when installing a new
master config module. The old Terrain
and other databases will no longer work
as they will remain locked to the old
System ID number.
•
•
Replace GTX unit.
Return unit to an Authorized Repair
Facility for service.
•
Check wiring between GIA’s and
GTX.
Replace GTX unit.
Return unit to an Authorized Repair
Facility for service.
•
•
•
The specified GTX transponder is
not able to transmit ADS-B data.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
Wait for GPS receivers to obtain a
position lock.
Check wiring between GIA’s and
GPS antenna.
Check wiring between GIA’s and
GTX.
Page 200
Revision 2
5.16
GDL 69A or GDL69A SXM Troubleshooting
5.16.1 GDL 69A or GDL69A SXM Symptoms
Symptom
Recommended Action
No SiriusXM audio is heard
•
•
•
•
No SiriusXM weather information is
displayed
Ensure the following items are not preventing the audio panel from
distributing SiriusXM audio (reference applicable G1000 Pilot’s Guide):
 Verify the SiriusXM volume is not muted on the Aux – XM Radio
page on the MFD.
 Verify the COM squelch is not open.
 Verify the ICS squelch is not open.
 Verify the marker beacon tones are not being received.
 Verify the headphone (if equipped) volume is turned up.
Go to the Aux – System Status page on the MFD and ensure unit is
online.
 If a red X is present, verify the unit is receiving power at the rack
connector.
Ensure there are no GDL alerts in the alert window. If there is an Alert
for software or configuration error or mismatch, reload the file noted in
the Alert.
Restart the PFD’s and MFD in configuration mode and go to the GDL
page.
 Verify unit is active.
 Verify the Signal number is “2” or “3”. If it is “0” or “1” check the
GDL 69A/69A SXM antenna and cabling for faults.
 Reseat the 69A/69A SXM to verify the coax connector is fully
seated.
 If unit is not active, contact SiriusXM Customer service to have a
refresh signal sent to your unit. You will need to provide them the
Audio Radio ID (and Data Radio ID number for SiriusXM weather)
numbers. Also verify with SiriusXM that the correct Weather
package (Aviator Lite or Aviator) is on the account, and that no
traffic service has been activated against that Radio ID. The unit
must be on for approximately one hour after the request for the
refresh has been sent to receive the signal.
 Alternatively, go to SiriusXM’s website and enter the radio ID’s
to have a refresh signal sent.
 If there is still problems receiving weather products after performing
the above step, call SiriusXM and have the account deactivated,
and a new account activated to clear out any corrupt account
information.
 Verify there is a good ground connection through the aircraft
between the MFD and the GDL69/69A unit. Reference the Aircraft
Maintenance Manual for instructions on how to check bonding and
ground points.
 If problem persists, replace the GDL 69A/69A SXM. Return unit to
an Authorized Repair Facility for service.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 201
Revision 2
5.16.2 GDL 69A Alerts
Failure Message
GDL 69 FAIL – GDL 69 has failed.
Cause
The G1000 has detected a failure
in the GDL 69A/69A SXM.
Solutions
•
•
Replace GDL 69A/69A SXM.
Check GDL 69A/69A SXM antenna
and cabling.
•
Check the GDL 69A/69A SXM and
MFD interconnect.
•
GDL69 CONFIG – GDL 69
configuration error. Config service
req’d.
The G1000 has detected a GDL
69A/69A SXM configuration
mismatch.
Reload configuration file. See
Section 3.8 for the Configuration
Procedure.
•
If problem persists, replace master
configuration module, check config
module harness for faults and
replace if necessary.
NOTE
New Terrain/Obstacle cards, Jeppesen
Aviation Database and other optional
features (i.e. TAWS unlock card) will
need to be replaced if the master
configuration module is changed. The
G1000 System ID number will change
to a new number when installing a new
master config module. The old Terrain
and other databases will no longer work
as they will remain locked to the old
System ID number.
MANIFEST – GDL software
mismatch. Communication
halted.
The system has detected an
incorrect software version loaded
in the GDL 69A/69A SXM.
Load correct software version.
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5.17
GSU 75B, GRS 77, or GRS 7800 and GMU 44 Troubleshooting
5.17.1 AHRS Symptoms
Symptom
Recommended Action
•
•
AHRS/ADAHRS does not complete
initialization
•
•
•
•
Attitude appears unstable
•
•
•
•
•
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Ensure that a cell phone or a device using cell phone technology is not turned
on (even in a monitoring state) in the cabin.
Ensure GPS has acquired at least four satellites, has a 3D navigation solution,
and a DOP of less than 5.0. This is particularly important if this issue appears
during ground operation only.
Calibrate the GSU75B, GRS 77, or GRS 7800.
Check GSU75B, GRS 77, or GRS 7800 configuration module wiring for
damage.
Check GSU75B, GRS 77, or GRS 7800 connector for bent pins.
 If no damage can be found, replace GSU75B, GRS 77, or GRS 7800
configuration module.
 If problem persists, replace the GSU75B, GRS 77, or GRS 7800.
Ensure that a cell phone or a device using cell phone technology is not turned
on (even in a monitoring state) in the cabin. (Wi-Fi and Bluetooth may be
operational)
GRS 77
•
Ensure the four mounting screws are tight. Finger tight is not sufficient, a
screwdriver must be used to verify.
GRS 7800
•
Ensure the hold down clamps are tight.
GSU 75B
•
Ensure the two mounting jack screws are tight.
Ensure mounting rack and airframe shelf are secure and all hardware and
brackets are present (CAUTION - do not loosen the mounting rack hardware to
the airframe shelf or the aircraft will need to be re-leveled and the PITCH/ROLL
OFFSET procedure performed).
Ensure the GSU 75B, GRS 77, or GRS 7800 connector is securely fastened
and proper strain relief is provided.
Remove the GSU 75B, GRS 77, or GRS 7800 connector and verify there are
no bent pins.
Replace the GSU 75B, GRS 77, or GRS 7800.
Contact Garmin for further troubleshooting if required.
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5.17.2 GRS/GSU Alerts
Failure Message
MANIFEST – GRS1 software
mismatch. Communication
halted.
MANIFEST – GRS2 software
mismatch. Communication
halted.
AHRS1 SERVICE – AHRS1
magnetic-field model needs
update.
AHRS2 SERVICE – AHRS2
magnetic-field model needs
update.
GEO LIMITS – AHRS1 too far
north/south, no magnetic
compass.
GEO LIMITS – AHRS2 too far
north/south, no magnetic
compass.
AHRS1 TAS – AHRS1 not
receiving airspeed.
AHRS2 TAS – AHRS2 not
receiving airspeed.
Cause
Solutions
The system has detected an
incorrect software version loaded
in the specified GRS unit.
Load correct software version.
The AHRS magnetic field model
should be updated for the
specified unit. Appears on ground
only.
Load updated AHRS magnetic field file.
See Section 4.6.
No magnetic compass information
available due to being too far
north or south.
Operate the aircraft only within the limits
as specified in the G1000 King Air 200
AFMS, listed in Table 1-2
•
The specified GSU 75B, GRS 77,
or GRS 7800 is not receiving
airspeed from the air data card, or
GDC 7400.
•
•
AHRS1 GPS – AHRS1 not
receiving backup GPS
information.
The GSU 75B, GRS 77, or GRS
7800 #1 is not receiving backup
GPS information from either GIA
63.
•
AHRS1 GPS – AHRS1 operating
exclusively in no-GPS mode.
The GSU 75B, GRS 77, or GRS
7800 #1 is operating in the
absence of GPS.
•
AHRS1 GPS – AHRS1 not
receiving any GPS information.
The GSU 75B, GRS 77, or GRS
7800 #1 is not receiving GPS data
from the GPS receivers.
•
The GSU 75B, GRS 77, or GRS
7800 #1 is using the backup GPS
data path.
•
AHRS1 GPS – AHRS1 using
backup GPS source.
AHRS2 GPS – AHRS2 not
receiving backup GPS
information.
The GSU 75B, GRS 77, or GRS
7800 #2 is not receiving backup
GPS information from either GIA
63.
•
AHRS2 GPS – AHRS2 operating
exclusively in no-GPS mode.
The GSU 75B, GRS 77, or GRS
7800 #2 is operating in the
absence of GPS.
•
AHRS2 GPS – AHRS2 not
receiving any GPS information.
The GSU 75B, GRS 77, or GRS
7800 #2 is not receiving GPS data
from the GPS receivers.
•
AHRS2 GPS – AHRS2 using
backup GPS source.
The GSU 75B, GRS 77, or GRS
7800 #2 is using the backup GPS
data path.
•
AHRS MAG DB – AHRS magnetic
model database version
mismatch.
The G1000 has detected a
magnetic model database version
mismatch.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Check GRS/GDC interconnect for
faults. (Internal fault between the
ADC and AHRS cards in the GSU
75B)
Replace the GSU 75B or GDC 7400
If problem persists, replace the GSU
75B, GRS 77, or GRS 7800.
Ensure that a cell phone or a device
using cell phone technology is not
turned on (even in a monitoring
state) in the cabin.
Check GPS status for GIA 1 and 2
on MFD Aux – GPS Status page. If
one or both GPS receivers cannot
acquire a position lock, see GPS
troubleshooting section
Troubleshoot GIA1/2 –GRS1 wiring
for faults (ref. Failed Path
troubleshooting section).
Replace the GRS or GSU #1.
Ensure that a cell phone or a device
using cell phone technology is not
turned on (even in a monitoring
state) in the cabin.
Check GPS status for GIA 1 and 2
on MFD - Aux – GPS Status page.
If one or both GPS receivers cannot
acquire a position lock, see GPS
troubleshooting section
Troubleshoot GIA1/2 – GSU/GRS2
wiring for faults (ref. Failed Path
troubleshooting section).
Replace the GRS or GSU #2.
Load AHRS magnetic model field in both
GSU/GRS units.
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Failure Message
Cause
Solutions
•
If flying near large radio towers or
other sources of possible
electromagnetic interference, the
condition should correct itself as the
aircraft leaves the area.
If problem persists, run magnetic
interference check in Section 5.17.4
to check for magnetic interference in
the aircraft.
MAG VAR WARN – Large
magnetic variance. Verify all
course angles.
Magnetic variance value from
GMU 44 is not accurate.
PIT (amber pitch flag)
Pitch Miscompare:
Difference in the pitch sensors is
greater than 5 degrees.
Perform Calibration Procedure A1: GSU
75B, GRS 77, or GRS 7800 Pitch/Roll
Offset Calibration (reference Section
7.10.1).
ROL (amber roll flag)
Roll Miscompare:
Difference in the roll sensors is
greater than 6 degrees.
Perform Calibration Procedure A1: GSU
75B, GRS 77, or GRS 7800 Pitch/Roll
Offset Calibration (reference Section
7.10.1).
•
5.17.3 GMU Alerts
Failure Message
MANIFEST – GMU1 software
mismatch. Communication
halted.
MANIFEST – GMU2 software
mismatch. Communication
halted.
HDG FAULT – AHRS1
magnetometer fault has occurred
HDG FAULT – AHRS2
magnetometer fault has occurred.
HDG (amber heading flag)
Cause
The system has detected an
incorrect software version loaded
in the specified GMU 44.
Solutions
Load the correct software version.
•
A fault has occurred in the
specified magnetometer; heading
will be flagged invalid.
Check GMU 44/GSU 75B, GRS 77,
or GRS 7800 interconnect for faults.
 Replace GMU 44.
 If problem persists, replace
GSU 75B, GRS 77 or
GRS 7800.
Heading Miscompare:
Difference in the heading sensors
is greater than 6 degrees.
Perform Calibration Procedure E:
Magnetometer Interference Test
(reference Section 5.17.4) and
Procedure B: GSU 75B, GRS 77, or
GRS 7800 and GMU 44 Magnetometer
Calibration (reference Section 7.10.3).
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5.17.4 Calibration Procedure E: Magnetometer Interference Test
A magnetometer interference test is available for troubleshooting and/or verifying a magnetically
‘clean’ installation of the GMU 44. This test exercises various devices on the aircraft that could
potentially affect the magnetic field as measured by the GMU 44.
NOTE
This test is used to validate that no electronic device or magnetized components
produce a magnetic field sufficient to interfere with the operation of the GMU 44
magnetometer. It is highly recommended that this test be performed after
installation or maintenance of electrical components on the aircraft and/or for
troubleshooting the GMU 44.
Figure 5-7, Magnetometer Interference Test
1. Initiate the AHRS magnetometer interference test procedure by performing the following
steps:
2. On PFD1, enter Configuration Mode and go to GRS/GMU Calibration page as shown in
Figure 5-7.
3. This page is protected and requires a keystroke password to perform this test. Press the
following softkeys in sequence: (as counted from left to right on lower bezel of MFD)
•
softkey 9
•
softkey 10
•
softkey 11
•
softkey 12
4. Select MAG INTERFERENCE TEST and press the PFD1 ENT key.
5. Follow the checklist items displayed on the PFD1, and press the ENT key as each one is
completed or confirmed.
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NOTE
3rd
item on the checklist instructs the operator to “prepare a detailed test
The
sequence with precise start and stop times for exercising all electronic devices”.
The list of relevant electronic devices are given in Table 5-5. Begin test with flaps
retracted, flight controls in a neutral position, all lights selected OFF.
Elapsed Time since Start of Test
(min:secs)
Action
0:00
0:05
0:10
0:20
0:30
0:40
0:50
1:00
1:20
1:40
1:50
2:00
2:10
2:20
2:30
2:40
2:50
3:00
3:10
3:20
3:30
Test begins
Tail Flood lights on
Tail Flood lights off
Navigation lights on
Navigation lights off
Landing lights on
Landing lights off
Taxi lights on
Taxi lights off
Strobes on
Strobes off
Recognition lights on
Recognition lights off
Beacon on
Beacon off
Rudder full left
Rudder full right
Rudder Trim full left
Rudder Trim full right
Elevator full nose UP
Elevator full nose DN
Elevator trim full nose UP
3:40
(manual electric)
Elevator trim full nose DN
3:50
(manual electric)
4:00
End of test
Table 5-5, Magnetometer Interference Test Sequence
6. When the CALIBRATE field is blinking, press the ENT key to begin the procedure, and
have a stopwatch ready to begin recording the elapsed time.
NOTE
It is important that the “time equals zero” moment corresponds with the
moment the PFD first displays the blinking TEST COMPLETE? Message.
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7. The operator should carry out the actions called for in the prepared test sequence.
NOTE
It is important that all actions are carried out in the order and at the precise
elapsed time as specified in the prepared test sequence.
8. When the operator has completed the actions specified in the test sequence, press the
ENTER button to indicate that the process is complete. When this is done, the TEST
COMPLETE field stops blinking.
9. PFD1 informs the operator if the installation has passed or failed the magnetometer
interference test. If the test passes, no further action is required for this test.
If the test fails, the installation should be considered unreliable until the source of
magnetic interference is identified and remedied. When the magnetometer interference
test fails, record the three magnetometer maximum deviation values and their
corresponding timestamps. Reference the appropriate installation manual for the GSU
75B (190-01639-00), GRS 77 (190-00303-10), and GRS 7800 (190-01091-00) for
acceptable magnetic interference limits. Compare the corresponding timestamps with
the prepared test sequence to identify which action produced the problem. Contact
Garmin for assistance in resolving the problem.
NOTE
Three common reasons for a failed magnetometer interference test are: 1)
rudder bellcrank or other structure has become magnetized, 2) new
equipment is installed in close proximity to the GMU 44 magnetometer, and
3) an existing or new electronic device has become grounded through the
aircraft structure instead of via the proper ground wire in a twisted shielded
pair.
10. Press the ENT key on the PFD to conclude this procedure.
5.18
GSU 75B/GDC 7400 Troubleshooting
5.18.1 Air Data Symptoms
Symptom
Recommended Action
•
•
Altitude shown on PFD is different
than standby altimeter
Perform a pitot/static leak and accuracy check.
Determine which instrument is outside limits and replace.
Note: The GSU 75B and GDC 7400 software/configuration for the 300
Series contains error correction at 19,000 feet and above. The
standby altimeter does not contain any correction.
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5.18.2 GSU75/GDC 7400 Alerts
Failure Message
MANIFEST – GDC1 software
mismatch Communication halted.
MANIFEST – GDC2 software
mismatch Communication halted.
5.19
Cause
Solutions
The system has detected an
incorrect software version loaded
in the specified GDC/GSU.
Load correct software version.
GWX 68 or GWX 70 Troubleshooting
5.19.1 GWX 68 or GWX 70 Alerts and Problems
WARNING:
Before energizing the equipment, be sure microwave radiation safety precautions
including both fuel and personnel safety considerations have been observed. These
include clearing all personnel to an area beyond the maximum permissible exposure
level (MPEL) boundary. The MPEL for the GWX 68 is 11 feet and GWX 70 is 10 feet.
Failure Message
Cause
Solutions
GWX CONFIG – GWX configuration
error. Configuration service
required.
The G1000 has detected a
GWX 68 or GWX 70
configuration mismatch.
• Load GWX configuration files,
• Replace GWX.
• If problem persists, replace master
configuration module, check config
module wiring for faults and replace
if necessary.
NOTE
New Terrain/Obstacle cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
databases will no longer work as
they will remain locked to the old
System ID number.
GWX FAIL – GWX is inoperative.
The G1000 has detected a
failure in the GWX 68 or GWX
70.
GWX SERVICE – Needs service.
Return unit for repair.
The G1000 has detected a
failure in GWX 68 or GWX 70.
MANIFEST – GWX software
mismatch. Communication halted.
The system has detected an
incorrect software version
loaded in the GWX 68 or GWX
70.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
•
•
Check Ethernet connection between
the GWX and GDL69A for faults.
Replace the GWX 68 or GWX 70
Replace the GWX 68 or GWX 70.
Return unit to an Authorized Repair
Facility for service.
Load correct software version.
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5.20
GMC 710 Troubleshooting
5.20.1 GMC 710 Alerts and Problems
Failure Message
GMC CNFG – GMC Config error.
Config service req’d.
Cause
Solutions
•
•
•
Load GMC configuration files.
Replace GMC.
If problem persists, replace master
configuration module, check config
module wiring for faults and replace
if necessary.
NOTE
New Terrain/Obstacle cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
databases will no longer work as
they will remain locked to the old
System ID number.
•
Check wiring for faults (ref Failed
Path troubleshooting Sections 5.1.1
and 5.9).
Replace the GMC 710.
Return unit to an Authorized Repair
Facility for service.
The G1000 has detected a
GMC 710 configuration
mismatch.
GMC FAIL – GMC is inoperative.
The G1000 has detected a
failure in the GMC 710.
MANIFEST – GMC software
mismatch. Communication halted.
The system has detected an
incorrect software version
loaded in the GMC 710.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
Load the correct software version.
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5.21
GCU 477 Troubleshooting
5.21.1 GCU 477 Alerts and Problems
Failure Message
GCU CNFG – GCU Config error.
Config service req’d.
Cause
Solutions
•
•
•
Load GCU configuration files.
Replace GCU.
If problem persists, replace master
configuration module, check config
module wiring for faults and replace
if necessary.
NOTE
New Terrain/Obstacle cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
databases will no longer work as
they will remain locked to the old
System ID number.
•
Check wiring for faults (ref Failed
Path troubleshooting section).
Replace the GCU 477.
Return unit to an Authorized Repair
Facility for service
The G1000 has detected a
GCU 477 configuration
mismatch.
GCU FAIL – GCU is inoperative.
The G1000 has detected a
failure in the GCU 477.
MANIFEST – GCU software
mismatch. Communication halted.
The system has detected an
incorrect software version
loaded in GCU 477.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
Load the correct software version.
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5.22
Software/Configuration Troubleshooting
Problem
Solutions
MFD or PFD displays do not power up:
•
•
•
Software file load fails:
•
•
•
•
•
Configuration file load fails:
•
•
•
•
•
GIA1 and/or GIA2 to ‘LRU’ data path not working
•
•
•
Software File Mismatch Alert appears in lower right
corner of PFD when started in normal mode:
•
•
•
After being in configuration mode, the PFD displays a
red AFCS annunciation and cycling of the transponder
field between valid and invalid states.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Ensure that the criteria listed in Section 5.22.1 are
fulfilled for the applicable situation.
Ensure power is present at display backshell
connector.
Troubleshoot per the “Blank Display” GDU section.
Ensure that criteria listed in Section 5.22.1 are
fulfilled for the applicable situation.
Ensure that LRU is reporting data on Aux –
System Status page (LRU is ‘ONLINE’). Check
data path wiring as needed.
Retry software file load or try using a different card.
Ensure that the MFD is not touched during the
loading process.
Ensure that LRU part number is compatible with
software version and Card Loader. Refer to
Section 3.2.3.
Replace LRU.
Ensure that the criteria listed in Section 5.22.1 are
fulfilled for the applicable situation.
Ensure that LRU is reporting data on the Aux –
System Status page (LRU is ‘ONLINE’). Check
data path wiring as needed.
Retry configuration file load or try using a different
card. Ensure that the MFD is not touched during
the loading process.
Ensure that LRU part number is compatible with
Card Loader. Refer to Section 3.2.3.
Replace LRU.
Ensure that the criteria listed in Section 5.22.1 are
fulfilled for the applicable situation.
Ensure GIA1 and GIA2 are configured correctly.
Check wiring, connectors & pins as needed.
Ensure that proper software file part number and
version were loaded to LRU. Refer to Section
5.22.1.
Check and ensure that correct Card Loader was
used during load process. Refer to the General
Arrangement Drawing.
Reload software to LRU.
With the G1000 system powered on, open the MFD,
PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers
for approximately 30 seconds, then close the circuit
breakers.
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5.22.1 System Communication Hierarchy
The following criteria must be satisfied to be able to perform the desired operation:
Desired Operation
Criteria for Success
Load Software to MFD or PFD Displays
•
•
•
Load AIRFRAME, SYSTEM, MFD1, PFD 1, PFD 2 and
MANIFEST configuration files to MFD and PFDs
•
•
•
Load Software/Configuration files to GIA 63Ws
•
•
•
•
Load Software/Configuration files to:
- GMA 1347D
- GSU 75B
- GDC 7400
- GEA 71
- GRS 77 or GRS 7800 (software only)
- GMU 44 (software only)
- GTX 33, or GTX 3000
- GTX 335R and/or GTX 345R
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
•
•
•
•
•
•
SW Loader Card must be inserted in top slot for
each display to be loaded.
CLR & ENT keys must be held during power up of
display.
Power on only one display at a time during
software loading.
SW Loader Card must be inserted in top slot of
PFD 1.
PFD 1 and MFD must be powered on.
PFD 1 and MFD must have correct software.
SW Loader Card must be inserted in top slot of
PFD 1.
G1000 system must be powered on.
PFD and MFD must have correct software.
PFD 1 and MFD must be successfully configured
with AIRFRAME, SYSTEM, MANIFEST, MFD1,
PFD 1 and PFD 2 configuration files.
SW Loader Card must be inserted into PFD 1 top
slot.
G1000 must be powered on.
PFD 1 and MFD must have correct software and
configuration settings.
GIA 63Ws must have correct software.
GIA 63Ws must be successfully configured with
GIA1 and GIA2 configuration files.
Data path from GIA1 to each LRU must be
operational.
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5.23
Backshell/Backplate Connectors
The following figures depict the backplate connectors as viewed with the LRU removed.
COM ANTENNA CONNECTOR
COOLING PORT
COM BOARD CONNECTOR (P601)
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15
16 17 18 19 20 21 2223 24 25 26 2728 2930
31 32 3334 35 3637 3839 40 41 42 43 44
MAIN DISCRETE CONNECTOR (P604)
MAIN SERIAL CONNECTOR (P603)
GPS ANTENNA CONNECTO
I/O CONNECTOR #2 (P606)
I/O CONNECTOR #1 (P605)
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39
40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59
40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
G/S ANTENNA CONNECTOR
VOR/ILS CONNECTOR (P60
NAV ANTENNA CONNECTOR
Figure 5-8, GIA 63W Backplate Connectors
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P712
1
2
3
4
5
6
7
8
P711
9 10 11 12 13 14 15 16 17 18 19 20
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38
40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
Figure 5-9, GEA 71 Backplate Connectors
P13472
P13471
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20
21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39
40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59
60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
Figure 5-10, GMA 1347D Backplate Connectors
COOLING PORT
P331
1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21
22 23 24 25 26 2728 29 30 31 32 33 34 35 36 37 38 39 40 41 42
43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62
TOP ANTENNA CONNECTOR
BOTTOM ANTENNA CONNECTOR
Figure 5-11, GTX 33/33D Backplate Connectors
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(P3301)
Figure 5-12, GTX 3000 Connectors (P3301 and P3302)
Figure 5-13, GTX 335R/345R Looking at Front of Connector (P3251)
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Figure 5-14, GTX 345R (Only) Looking at Front of Connector (P3252)
Figure 5-15, GDU 1050A/1550 Backshell Connector (P10401 or P15001)
Figure 5-16, GRS 77 Backshell Connector (P771)
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Figure 5-17, GRS 7800 Backshell Connector (P78001)
Figure 5-18, GSU 75B Connector View from Front (P751)
Figure 5-19, GDC 7400 Mating Connector (P74001)
Figure 5-20, GDL 69A/GDL 69A SXM Backplate Connector (P69A1)
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Figure 5-21, GCU 477 Backshell Connector (P4751)
Figure 5-22, GMC 710 Backshell Connector (P7101)
Figure 5-23, GWX 68 Backshell Connector (P681)
Figure 5-24, GWX 70 Backshell Connector (P751)
Figure 5-25, GTS 820/850 Mating Connectors (P8001 and P8002)
(Rear View)
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Figure 5-26, GTS 820/850 Mating Connector (P8003) (Rear View)
Figure 5-27, GTS Processor Connector (P8001)
Figure 5-28, GPA 65 Mating Connector (P651) (Rear View)
Figure 5-29, Signal Conditioner (1PVIB1 and 2PVIB1)
(Rear View)
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60
40
61
62
21
1
22
2
63
43
41 42
23
64
44
24
3
65
45
25
4
5
66
46
26
67
47
27
6
68
48
28
7
69
49
30
29
8
9
70
50
71
31
10
72
51 52
11
32
12
73
53
33
13
74
54
34
14
75
55
35
15
76
56
36
16
77
37
17
78
58
57
38
18
59
39
19
20
Figure 5-30, GDL 59 Mating Connector (1P591)
(Rear View)
15
14
30
13
29
44
12
28
43
11
27
42
10
26
41
9
8
25
40
7
24
39
6
23
38
5
22
37
4
21 20
36
35
2
3
19
34
1
18
33
17
32
16
31
Figure 5-31, GSR 56 Mating Connector (1P561)
(Rear View)
Figure 5-32, GRA 5500 Connector (P55001)
60
40
61
21
1
62
41 42
22
2
63
43
23
3
64
44
24
4
65
45
25
5
66
46
26
6
67
47
27
7
68
48
28
8
69
49
29
9
30
10
70
50
71
72
51 52
31
11
32
12
73
53
33
13
74
54
34
14
75
55
35
15
76
56
36
16
77
37
17
78
58
57
38
18
59
39
19
20
Figure 5-33, GSD 41 Backplate Connector (P411)
(Rear View)
Figure 5-34, GSA 9000 Mating Connector (P90001)
(Rear View)
G1000 NXi System Maintenance Manual
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Revision 2
5.24
Mechanical Standby Attitude Indicator Troubleshooting
Symptom
Warning flag pops into view,
indicating that the gyro motor is
not receiving sufficient power to
operate
Unit fails to perform to
specifications
5.25
Recommended Action
•
•
•
Perform the Standby Instrument Electrical Power Checks in Section 9.9.
Remove the unit per Section 6.28.3 and inspect the electrical connector.
Check to ensure appropriate electrical power is being supplied to the
instrument.
•
If input electrical power is not adequate, troubleshoot the wiring
harness.
•
If input power is appropriate, the unit must be removed and serviced
by a qualified service facility. Contact the manufacturer to find a
qualified service facility
The unit must be removed and serviced by a qualified service facility. See
Section 6.28.3 for removal instructions. Contact the manufacturer to find a
qualified service facility.
Mechanical Standby Airspeed Indicator Troubleshooting
Symptom
Recommended Action
•
•
•
Airspeed Indicator lighting is
inoperative or malfunctioning
•
Airspeed displayed is incorrect
Perform the Standby Instrument Electrical Power Checks in Section 9.9.
Remove standby airspeed indicator per Section 6.28.1 and inspect the
electrical connector.
Check that electrical power is being appropriately supplied to the
instrument.
•
If the input electrical power is not adequate, troubleshoot the wiring
harness.
•
If the input electrical power is appropriate, replace the standby
airspeed indicator or contact the manufacturer for further
troubleshooting.
Using a pitot-static ramp tester, check airspeed displayed on standby
altimeter against airspeed display from ADC2.
•
If the airspeeds are the same, inspect the pitot/static ports and
associated equipment for faults.
•
If the airspeeds are different, replace the standby altimeter or contact
the manufacturer for further troubleshooting. See Section 6.28.1 for
removal instructions.
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5.26
Mechanical Standby Altimeter Troubleshooting
Symptom
Altimeter lighting is inoperative or
malfunctioning
Recommended Action
•
•
•
Altimeter Vibrator is inoperative or
malfunctioning or fail flag is
displayed
•
Altitude displayed is incorrect
5.27
•
•
Perform the Standby Instrument Electrical Power Checks in Section 9.9.
Remove standby altimeter per Section 6.28.2 and inspect the electrical
connector.
Check that electrical power is being appropriately supplied to the
instrument.
•
If the input electrical power is not adequate, troubleshoot the wiring
harness.
•
If the input electrical power is appropriate, replace the standby
altimeter or contact the manufacturer for further troubleshooting.
Using a pitot-static ramp tester, check altitude displayed on standby
altimeter (Note that PFD2 has error correction above 19,000 ft. and will
not be the same as the non-corrected standby altimeter.)
Inspect the pitot/static ports and associated equipment for faults.
Replace the standby altimeter or contact the manufacturer for further
troubleshooting. See Section 6.28.2 for removal instructions.
MD 302 Standby Indicator Troubleshooting
Symptom
Recommended Action
•
•
•
Standby indicator is inoperative
•
Perform the Standby Instrument Electrical Power Checks in Section 9.9.
Remove standby indicator per Section 6.27.1 and inspect the electrical
connector.
Check that electrical power is being appropriately supplied to the
instrument.
•
If the input electrical power is not adequate, troubleshoot the wiring
harness.
•
If the input electrical power is appropriate, replace the standby
altimeter or contact the manufacturer for further troubleshooting.
Using a pitot-static ramp tester, check altitude displayed on standby
altimeter for accuracy.
Perform airspeed and altitude calibration per Section 3.19.2
Inspect the pitot/static ports and associated equipment for faults.
Replace the standby altimeter or contact the manufacturer for further
troubleshooting. See Section 6.27.1 for removal instructions.
Displayed altitude or airspeed
appears incorrect
•
•
•
Red X’s on display.
Troubleshoot per Mid-Continent Instruments and Avionics MD 302 Installation
Manual number 9017782 available at www.flysam.com/specifications/ or call
US 316-630-0101.
Warning or Error Messages
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5.28
GDL 59 Troubleshooting
Symptom
No communication with GDL 59
No or low-quality Wi-Fi signal
Connects to Wi-Fi but cannot send
report data
5.29
Recommended Action
•
Check power wiring and pin out of GDL 59 unit.
•
Ensure GDL 59 configuration option has been loaded.
•
Verify that a Wi-Fi network is configured and available.
•
Ensure the Wi-Fi antenna is within range of a Wi-Fi network.
•
Remove any obstacles between the aircraft Wi-Fi antenna and the Wi-Fi
network hub that may be blocking the signal.
•
•
Check the Wi-Fi antenna cable and connectors.
Verify antenna ground plane is adequate.
Activate Garmin Connext (reference Section 8.15). Note that a replacement
GDL 59 unit must be registered again, even if the MFD already shows
REGISTERED.
GSR 56 Troubleshooting
Symptom
No communication with GSR 56
No or low-quality Iridium signal
Recommended Action
•
Check power wiring and pin out of GSR 56 unit.
•
Ensure GSR 56 configuration option has been loaded.
•
Ensure the Iridium antenna has an unobstructed view of satellite
constellation.
•
•
Check the Iridium antenna cable and connectors.
Verify antenna ground plane is adequate.
No audio output
• Check wiring from GSR 56 to GDL 59 or from GSR 56 to GIA #1 (standalone), as applicable to the installation.
• Verify subscription with Garmin Connext (reference Section 8.15).
Unable to make a phone call
• Verify signal quality is adequate
• Verify communication between GSR 56 and the display/control device
• Verify subscription with Garmin Connext (reference Section 8.15).
5.30
GTS 820/850 Troubleshooting
Problem
Cause
Solution
Unit does not power up – Data
failed message
Improper wiring; circuit breaker open
Ensure power is properly wired to the
GTS 820/850 and the TRFC circuit
breaker is closed.
Improper configuration
Verify that the GTS 820/850 is
configured correctly for the desired
display.
Suppression bus I/O fault
Check the mutual suppression line to
ensure it is connected to the correct
pins at the GTS 820/850 as well as
the installed transponder. Ensure
there are no fractures in the wire, and
that the suppression line is
functioning properly.
Traffic Display erroneously
indicates TA at own ship position
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Problem
Cause
Solution
No Audio alerts
Improper wiring; Volume not set correctly
Ensure the audio is properly wired
from the GTS 820/850 (if using
analog audio output) and volume is
not set too low.
Calibration Fault
Factory calibration invalid
If the unit fails to go into operate
mode then return unit to an
authorized Repair Facility for service.
Configuration Fault
Both internal and external configuration
checks failed
Verify the configuration.
Verify wiring to the configuration
module and replace if necessary.
FPGA Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
ROM Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
Execution Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
Electrical Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
Whisper Shout Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
Transmit Power Fault
Internal voltages are out of tolerance
Check power connections to the GPA
65 to verify that they are not
connected to ground or each other.
Ensure that power and ground
connections to the GPA 65 are
connected in their proper place.
Verify input voltage and if it continues
return unit to an authorized Repair
Facility for service.
1030 MHz Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
1090 MHz Fault
Internal Fault
Return unit to an authorized Repair
Facility for service.
PA/LNA Fault
Antenna connections or internal fault
Ensure all antenna connections are
correct otherwise return unit to an
authorized Repair Facility for service.
Receiver Fault
Antenna connections or internal fault
Ensure all antenna connections are
correct otherwise return unit to an
authorized Repair Facility for service.
Transmitter Fault
Antenna connections or internal fault
Ensure all antenna connections are
correct otherwise return unit to an
authorized Repair Facility for service.
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Problem
Cause
Solution
Baro Altitude Fault
Baro Altimeter is not powered on or
improper wiring.
Verify that the baro altimeter has
power and is properly wired.
Improper configuration settings
Verify the configuration correct.
Temperature Fault
Fan is not operating, Poor ventilation at the
mounting location
Verify the fan is running and the unit
is getting adequate ventilation.
TCAS Equipage Fault
Broken wire, improper configuration
Verify configuration settings on the
transponder and the GTS. Ensure
proper wiring between the
transponder and the GTS.
Radio Altitude Fault
Radar Altimeter is not powered on or
improper wiring.
Verify that the radar altimeter has
power and is properly wired.
Improper configuration settings
Verify the configuration is correct.
Improper wiring; wrong port or speed
selected
Ensure the port is properly wired to
the GTS 820/850 and the correct
settings are selected on the
configuration page.
Red ‘X’ on a data port on the
configuration page
5.31
GTS Traffic Processor Troubleshooting
Symptom
Unit does not power up – Data
failed message
Recommended Action
• Ensure power is properly wired to the GTS Traffic Processor and the
TRFC circuit breaker is closed
• Verify that the GTS Traffic Processor is configured correctly for the
desired display
Traffic Display erroneously
indicates TA at own ship position
Check the mutual suppression line to ensure it is connected to the correct
pins at the GTS Processor as well as the installed transponder. Ensure there
are no fractures in the wire, and that the suppression line is functioning
properly.
Calibration Data Fault
Return unit to an authorized Repair Facility for service
Configuration Data Fault
• Attempt configuration per the configuration
• Download the assert log and send to Garmin for diagnosis
FPGA Fault
If upload of FPGA image was recently attempted, retry the upload. Otherwise
return unit to an authorized Repair Facility for service.
ROM Fault
If upload of audio image or IGRF magnetic field image was recently
attempted, retry the upload. Otherwise return unit to an authorized Repair
Facility for service.
Execution Fault
• Cycle power and retry self-test.
• Download the assert log and send to Garmin for diagnosis.
• Return unit to an authorized Repair Facility for service if fault persists.
Electrical Fault
• Check aircraft power supply
• Download the assert log and send to Garmin for diagnosis.
• Return unit to an authorized Repair Facility for service if fault persists.
Whisper Shout Fault
• Check cable loss configuration, antenna installation and all cable
connections and retry self-test.
• Return unit to an authorized Repair Facility for service if fault persists.
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Symptom
Recommended Action
Transmit Power Fault
• Check aircraft power supply
• Return unit to an authorized Repair Facility for service if fault persists
1030 MHz Fault
• Cycle power and retry self-test
• Return unit to an authorized Repair Facility for service if fault persists
1090 MHz Fault
• Cycle power and retry self-test
• Return unit to an authorized Repair Facility for service if fault persists
Receiver Cal Fault
• Check antenna installation and all cable connections and retry self-test.
Ensure that self-test occurs in area free of buildings and large objects that
can reflect signals.
• Download the assert log and use Assert Log Diagnosis Tool or send to
Garmin for diagnosis.
• Return unit to an authorized Repair Facility for service if fault persists
Transmitter Cal Fault
• Check antenna installation and all cable connections and retry self-test.
Ensure that self-test occurs in area free of buildings and large objects that
can reflect signals.
• Download the assert log and use Assert Log Diagnosis Tool or send to
Garmin for diagnosis.
• Return unit to an authorized Repair Facility for service if fault persists
Baro Altitude Fault
Check wiring to source of barometric altitude and ensure that source is
operating.
Temperature Fault
Download the assert log and send to Garmin for diagnosis
TCAS Equipage Fault
Check wiring to TCAS Equipage data source and ensure that source is
operating
Radio Altitude Fault
Check wiring to source of radio altitude and ensure that source is operating
Display Fault
• Check the HSDB connection between the GTS Processor and the display
• Verify that the display is operational.
• For non-HSDB installations, ensure that the Traffic Display Status Valid
inputs (TAS/TCAS I) and RA Display Status Valid inputs (TCAS II) are
wired properly to the Display Status Valid output of the display device.
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6. Equipment Removal & Installation
This section describes how to remove and replace equipment in the King Air 300 Series
associated with this STC. After removal and replacement, LRUs must be configured and tested
as described in Section 7.
CAUTION:
When removing and/or replacing any G1000 component, always ensure that
aircraft power is off. Unplug any auxiliary power supplies. Before
performing maintenance, it is required that the technician verify the LRU
software part number and version number matches the software
configuration listed in the General Arrangement drawing, listed in Table 1-1.
NOTE
After installation or maintenance of electrical components near the GMU 44
magnetometers (either tail or horizontal stabilizer locations), perform the
Calibration Procedure E: Magnetometer Interference Test (reference Section 5)
and Procedure B: GRS 77, GRS 7800, or GSU 75B and GMU 44 magnetic
calibration (reference Section 7).
To check an LRU software part number and/or version, follow the procedure defined in Section
3.2.3.
If a faulty LRU is not reporting its software version and part number, check aircraft maintenance
logs for last software version loaded and verify against the General Arrangement drawing. The
Software Manifest page may also be used to check part numbers and versions.
The General Arrangement drawing allows alternate part number units to be installed with
certain hardware/software combination restrictions. Refer to the applicable “Garmin
Equipment/Software List” contained in the General Arrangement drawing for details.
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6.1
GDU 1050A/1550
Removal:
1. Using a 3/32” hex tool, rotate all four (GDU 1050A) or six (GDU 1550) ¼-turn fasteners
counter-clockwise until they reach their stops.
2. Carefully remove the display from the panel.
3. While supporting the display, disconnect the connector.
Reinstallation:
1. Visually inspect the connector and pins for signs of damage. Repair any damage.
2. While supporting the display, connect the connector to the rear of the unit. Verify the
connector is fully locked by rocking the connector up and down to verify the connector
stays attached to the unit.
3. Carefully insert the display into the panel cutout, ensuring that all 4 ¼-turn fasteners
align with the corresponding holes.
4. Seat the display in the panel cutout. Do not use excessive force while inserting the
display.
5. Once seated, rotate all four (GDU 1050A) or six (GDU 1550) ¼-turn fasteners clockwise
to lock the display to the panel.
6. Configure and test the MFD and/or PFD according to Section 7.1.
6.2
GMA 1347D Audio Panel
Removal:
1. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the GMA 1347D is
unlocked from its location.
2. Carefully remove the GMA 1347D from its rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the lock tab stops.
3. Gently insert the GMA 1347D into the rack until the locking tab engages the rack.
4. Tighten the hex nut until resistance is felt and the unit stops sliding into the rack. Do not
over-tighten the nut.
5. Configure and test the GMA 1347D according to Section 7.2.
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6.3
GIA 63W Integrated Avionics Units
Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Unlock the GIA 63W handle by loosening the Phillips screw on the handle.
3. Pull the handle upward to unlock the GIA 63W. Gently remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Lift the handle and gently insert the GIA 63W into its rack. The handle should engage
the dogleg track.
3. Press down on the GIA 63W handle to lock the unit into the rack.
4. Lock the handle to the GIA 63W body using the Philips screw. Torque the handle screw
to 10-14 in-lbs.
5. Configure and test the GIA 63W(s) according to Section 7.3.
6.4
GEA 71 Engine/Airframe Unit
Removal:
1. Gain access by removing the appropriate GDU 1050A display unit (see Section 6.1.).
GEA 1 is located behind PFD1 and GEA 2 is located behind PFD2.
2. Unlock the GEA 71 handle by unscrewing the Phillips screw.
3. Firmly grasp the GEA 71 handle and pull it up vertically. This unlocks the unit from the
rack.
4. Gently remove the GEA 71 from its rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Lift the handle and gently insert the GEA 71 into the rack. The handle should engage
the dogleg track.
3. Press down on the handle to lock the unit into place.
4. Lock the handle to the GEA 71 body using the Philips screw. Torque the handle screw
to 10-14 in-lbs.
5. Reinstall the GDU 1050A display unit.
6. Configure and test the GEA 71 according to Section 7.4.
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6.5
GTX 33( ) or GTX 3000 Transponder
GTX 33 () Removal:
1. Gain access to the unit based on location a) If the unit is installed under the cabin floor, remove the cabin center floor panel at the
main entry door. Remove the remote equipment shelf or detach the two rack mount
angles from the shelf. Retain all mounting hardware.
b) If the unit is installed in the tail, open the tailcone access door on the bottom of the
tailcone.
2. Unlock the GTX 33( ) handle by loosening the Phillips screw on the handle.
3. Pull the handle upward to unlock the GTX 33( ). Gently remove the unit from the rack.
GTX 33 () Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Lift the handle and gently insert the GTX 33( ) into its rack. The handle should engage
the dogleg track.
3. Press down on the GTX 33( ) handle to lock the unit into the rack.
4. Lock the handle to the GTX 33( ) body using the Philips screw. Torque the handle screw
to 10-14 in-lbs.
5. If the unit is installed under the cabin floor, reinstall the remote equipment shelf or two
rack mount angles using the retained hardware and the cabin center floor panel.
6. If the unit is installed in the tail, close the tailcone access door.
7. Configure and test the GTX 33( ) according to Section 7.5.
GTX 3000 Removal:
1. Gain access to the avionics shelf in the tail area.
2. Pull back on the lockdown mechanism and simultaneously turn counterclockwise until
free.
3. Disengage the lockdown mechanism collar from the GTX 3000 hook and gently slide the
GTX 3000 from the mounting rack.
GTX 3000 Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Place the GTX 3000 on the mounting rack.
3. Slide the GTX 3000 back until the foot is fully engaged with the mounting rack.
4. Lift the lockdown mechanism collar in place on the GTX 3000 hook and hand turn
lockdown mechanism knobs clockwise until the GTX 3000 is secure.
5. Configure and test the GTX 3000 according to Section 7.5.
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6.6
GTX 335R/GTRX 345R Transponder
GTX 335R/GTX 335R Removal:
1. Gain access to the avionics shelf in the tail area.
2. Insert a 3/32” hex drive tool into the access hole in the front of the unit.
3. Turn hex drive tool counterclockwise until the hex drive tool stops.
4. Pull the unit from the rack using the spring-loaded tab on the front of the unit.
GTX 335R/GTX 335R Reinstallation:
1. Visually inspect the connectors in the back of the rack to ensure there are no bent or
damaged pins. Repair any damage if found.
2. Insert a 3/32” hex drive tool into the access hole in the front of the unit.
3. Turn hex drive tool counterclockwise until the hex drive tool stops.
4. Slide the unit in the rack until it stops. The unit will appear to stick out of the rack
approximately 3/8”.
5. Insert a 3/32” hex drive tool into the access hole in the front of the unit.
6. Push on the left side of the unit and turn hex drive tool clockwise until it stops. Do not
apply more than 8 in-lbs of torque on the hex tool to seat the unit.
7. Configure and test the GTX 3000 according to Section 7.5.
6.7
GDC 7400 Air Data Computer
Removal:
1. Gain access by removing the appropriate GDU 1050A display unit (see Section 6.1.)
GDC 1 is located behind PFD1 and GDC 2 is located behind PFD2.
2. Disconnect the pitot/static plumbing from the rear of the unit. Disconnect the single
connector.
3. Loosen each thumbscrew on the hold-down clamp and remove the clamp.
4. Carefully remove the unit from its mount.
Reinstallation:
1. Inspect the connector and pins for damage. Inspect the pitot/static plumbing for
damage. Repair any damage.
2. Place the unit in the mounting tray. Position the locking clamp and fasten using the
thumbscrews.
3. Connect the backshell assembly and pitot/static plumbing to the unit.
4. Reinstall the GDU 1050A display unit.
5. Configure and test the GDC 7400 according to Section 7.7.
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6.8
GTP 59 OAT Probe
Removal:
Using a deep-socket to hold the probe in place on the outside of the aircraft, loosen the GTP
59 mounting nut and remove the GTP 59.
Reinstallation:
1. Installation is the reverse of removal.
2. No configuration is required for the GTP 59. Test according to Section 7.7.5.
6.9
GRS 77 or GRS 7800 AHRS or GSU 75B ADAHRS
GRS 77 Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Disconnect the AHRS connector.
3. Loosen the four Phillips thumbscrews with a screwdriver until they are free from the rack.
4. Gently lift the GRS 77 from the mounting rack. Do NOT loosen the remote rack
hardware fastening it to the avionics shelf or the GRS 77 must be re-calibrated per
Section 7.10.
GRS 77 Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Place the GRS 77 on the mounting plate, ensuring the orientation is correct.
3. Use a #2 Phillips screwdriver to torque the GRS 77 mounting screws to the rack to 22-25
in-lbs.
4. Connect the connector to the GRS 77.
5. Calibrate and test the GRS 77 according to Section 7.10.
GRS 7800 Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Disconnect the AHRS connector.
3. Pull back on the lockdown mechanisms and turn counterclockwise until free.
4. Disengage the lockdown mechanism collars from the GRS 7800 hooks and gently slide
the GRS 7800 from the mounting rack. Do NOT loosen the remote rack hardware
fastening it to the avionics shelf or the GRS 7800 must be re-calibrated per Section 7.10.
GRS 7800 Reinstallation:
1. Visually inspect the connector to ensure there are no bent or damaged pins. Repair any
damage.
2. Place the GRS 7800 on the mounting rack, ensuring the orientation is correct.
3. Slide the GRS 7800 back until the feet are fully engaged with the mounting rack.
4. Lift the lockdown mechanism collars in place on the GRS 7800 hooks and hand turn
lockdown mechanism knobs clockwise until the GRS 7800 is secure.
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5. Connect the connector to the GRS 7800.
6. Calibrate and test the GRS 7800 according to Section 7.10
GSU 75B Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Disconnect the ADAHRS connector.
3. Disconnect the pitot and static lines.
4. Turn each retention screw counterclockwise until they disconnect from the remote rack.
5. Gently slide the unit from the remote rack. Do NOT loosen the remote rack hardware
fastening it to the avionics shelf or the GSU 75B must be re-calibrated per Section 7.10)
GSU 75B Installation:
1. Visually inspect the connector to ensure there are no bent or damaged pins. Also
inspect the pitot and static fittings for damage. Repair any damage.
2. Place the GSU 75B unit on the remote rack and slide the unit back until the feet are fully
engaged with the remote rack.
3. Push down and turn each retention screw clockwise. Torque each retention screw to
15-20 in-lbs.
4. Connect the pitot and static lines.
5. Connect the ADAHRS connector to the unit.
6. Calibrate and test the GSU 75B per Section 7.10.
6.10
GMU 44 Magnetometer
NOTES
The GMU 44 magnetometers may be located in the tailcone or in the horizontal
stabilizer.
Always use a non-magnetic Phillips screwdriver when removing or installing all screws
near the magnetometers.
Reference the “Magnetometer Install” and “Wire Harness Installation, Tail” drawings
listed in Table 1-1 for more details.
For Tailcone Location:
Removal:
1. Disconnect electrical wiring harnesses and remove the tailcone.
2. Remove three screws connecting the unit to the aircraft mounting bracket.
3. Remove the cable tie attaching the magnetometer pigtail harness to the shelf.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Fasten the GMU to the aircraft mounting bracket.
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3. Attach the magnetometer pigtail harness to the shelf with a cable tie
4. Reinstall tailcone and connect the electrical wiring harnesses.
5. Calibrate and test the GMU 44 according to Section 7.10.
For Horizontal Stabilizer Location (left or right side):
Removal:
1. Remove inspection access panel (second from inboard) from lower side of the horizontal
stabilizer to gain access to the GMU electrical wiring harness.
2. Disconnect GMU pigtail harness from the electrical wiring harness.
3. Remove the screws and flux valve access cover from the upper side of horizontal
stabilizer.
4. Mark the orientation of the GMU adapter plate assembly to the flux valve mounting dish.
5. Remove three screws/washers connecting the GMU adapter plate assembly to the flux
valve mounting dish.
6. Remove three screws connecting the GMU to the GMU adapter plate assembly.
7. If the unit is to be replaced, remove cable ties attaching the phenolic wire guard to the
unit and retain the wire guard and grommet from the pigtail harness.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Reinstall the three screws attaching the GMU to the GMU adapter plate assembly.
3. If a new GMU is installed, use two MS3367-7-1 cable ties through the retained phenolic
wire guard to secure the guard and connector harness to the GMU.
4. Ensure the MS35489-4 grommet is installed on the unit pigtail harness and secured in
the slot in the aft side of the GMU adapter plate assembly.
5. Use the orientation marks on the GMU adapter plate assembly to align the adapter plate
assembly to the flux mounting dish and reinstall the three screws/washers attaching the
adapter plate.
6. Ensure there is a gap of at least 0.2 inch between the unit pigtail harness and the flux
valve access cover.
7. Reinstall the screws and flux valve access cover on the upper side of horizontal
stabilizer.
8. Connect the GMU pigtail harness to the electrical wiring harness.
9. Reinstall the inspection access panel (second from inboard) on the lower side of the
horizontal stabilizer.
10. Calibrate and test the GMU 44 according to Section 7.10.
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6.11
GDL 69A or GDL 69A SXM
Removal:
1. Gain access by removing the right side GDU 1050A display unit (see Section 6.1.)
2. Unlock the GDL 69A/69A SXM handle by loosening the Phillips screw on the handle.
3. Pull the handle upward to unlock the GDL 69A. Gently remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Lift the handle and gently insert the GDL 69A/69A SXM into its rack. The handle should
engage the dogleg track.
3. Press down on the GDL 69A/69A SXM handle to lock the unit into the rack.
4. Lock the handle to the GDL 69A/69A SXM body using the Philips screw. Torque the
handle screw to 10-14 in-lbs.
5. Configure and test the GDL 69A/69A SXM according to Section 7.11.
6.12
GSA 80 and GSA 9000 Servo Motors
Removal:
1. Gain access to the desired servo(s).
2. Disconnect the servo harness connector.
3. Use a socket or open-wrench to loosen and remove the servo attachment bolts.
4. Carefully remove the servo and place a protective cover on the output gear.
5. Place a protective cover over the GSM 86 or GSM 9100 servo gearbox.
Reinstallation:
1. For GSA 80 Servo motors only –
a. Inspect the servo output gear for abnormal wear.
b. Using a lint-free cloth, remove excess grease build-up from the servo output
gear.
IMPORTANT!
It is not necessary to remove all of the grease from the output gear, only the
excess grease. DO NOT USE SOLVENTS TO CLEAN THE OUTPUT GEAR!
c. Using a brush or other applicator, apply a thin coat of Aeroshell 33MS (Lithiumcomplex based) grease to the servo output gear
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Figure 6-1, GSA 80 Servo Gear
Figure 6-2, GSM 9100 O-ring
2. For GSA 9000 Yaw servo motor only, install a new O-ring P/N AS568-043 on the GSM
9100 servo gearbox (see Figure 6-2).
3. Carefully place the servo into the servo gearbox, ensuring proper orientation and
alignment.
4. Fasten the servo to the servo gearbox using the existing hardware. Follow the
installation instructions provided in the respective servo installation drawing(s) listed in
Table 1-1.
5. Inspect the harness connectors and check that no pins are bent or otherwise damaged.
Connect the harness and secure it appropriately.
6. If no further maintenance is required, continue to Section 7.12.
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6.13
GSM 86 and GSM 9100 Servo Gearbox
Removal:
1. Remove the desired servo motor(s) per Section 6.12.
2. For the Roll, Pitch and Yaw Servos: remove the servo bridle cables from the control
cable clamps. For the Pitch-Trim Servo: disconnect the servo cable at the forward
turnbuckle and aft terminal.
3. Use a socket or open-wrench to loosen and remove the servo attachment bolts.
4. Carefully remove the servo gearbox(es).
5. Remove the cable retention pins and ring (or cover) and then remove the servo cable
from the capstan.
Reinstallation:
1. Ensure cable retention pins are oriented correctly. Follow the installation instructions
provided in the respective servo installation drawing(s) listed in Table 1-1.
2. If no other maintenance is to be performed, reinstall the servo(s) per Section 6.12.
6.14
GCU 477
Removal:
1. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn
counterclockwise until they reach their stops.
2. Disconnect backshell assembly from unit.
Reinstallation:
1. Inspect connector(s) for damaged pins.
2. Connect backshell assembly to unit.
3. Hold unit flush with the pedestal, ensuring locking stud alignment marks are in the
vertical position.
4. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn clockwise. This
may require applying a small amount of forward pressure to engage the ¼ turn sockets.
5. Configure and test the GCU 477 according to Section 7.13.
6.15
GMC 710
Removal:
1. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn
counterclockwise until they reach their stops.
2. Disconnect backshell assembly from unit.
Reinstallation:
1. Inspect connector(s) for damaged pins.
2. Connect backshell assembly to unit.
3. Hold unit flush with the mounting bracket, ensuring locking stud alignment marks are in
the vertical position.
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4. Use a 3/32” hex drive tool to turn each of the four locking sockets ¼ turn clockwise. This
may require applying a small amount of forward pressure to engage the ¼ turn sockets.
5. Configure and test the GMC 710 according to Section 7.14.
6.16
GWX 68 or GWX 70
Removal:
1. Gain access by removing nose radome.
2. Disconnect backshell assembly from unit.
3. Use a 3/16” hex drive tool to remove each of the four mounting screws.
Reinstallation:
1. Inspect connector for damaged pins.
2. Hold unit flush with the radar mount.
3. Use a 3/16” hex drive tool to tighten each of the four mounting screws.
4. Connect backshell assembly to unit.
5. Configure and test the GWX 68 or GWX 70 according to Section 7.15.
6.17
Configuration Modules
6.17.1 Configuration Module Removal & Replacement
Configuration modules (Reference Figure 6-3 and Table 6-1, Item 1 shown below) are located in
the following LRU harness connector backshells: GDU 1050A PFD1, GRS 77 AHRS, and the
GEA 71 Engine/Airframe Unit. Additionally, the GRS 7800, GSU 75B, and MD 302 have
different style configuration modules that are located in their connector backshells. Refer to
Section 6.17.2 for the GRS 7800 configuration module removal and replacement instructions.
Refer to Section 6.17.3 for the GSU 75B configuration module removal and replacement
instructions. Refer to Section 6.27.2 for the MD 302 configuration module removal and
replacement instructions. Refer to the Master Drawing List, listed in Table 1-1, for specific
installation drawings.
NOTE
Garmin Configuration Modules are not ESD sensitive. Configuration modules do
not require special ESD protection for handling during installation or
maintenance.
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Figure 6-3, Configuration Module Installation
Table 6-1, Configuration Module Kit – 011-00979-00
Item
1
2
3
4
Description
Qty Needed
Configuration Module PCB Board Assembly w/EEPROM & Temp
Sensor
Spacer, Config Module
Cable, 4-Conductor Harness
Pins, #22 AWG (HD)
1
1
1
5
Garmin Part
Number
012-00605-00 or -02
213-00043-00
325-00122-00
336-00021-00
Removal:
1. Disconnect connector from LRU.
2. Remove 2 screws (8) from cover (7) and remove cover.
3. Unplug connector from configuration module (1).
4. Remove configuration module.
Installation:
1. Inspect connector for damaged pins (4).
2. Place configuration module (1) in position.
3. Insert connector into configuration module (1).
4. Assembly of the connector is the reverse of disassembly.
5. Checkout per Section 6.17.4.
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6.17.2 GRS 7800 Configuration Module Removal & Replacement
The GRS 7800 configuration module is located on the LRU harness connector strain relief.
Refer to the Master Drawing List, listed in Table 1-1, for specific installation drawings.
2X
WASHERS, RING TERMINALS
4X
Figure 6-4, GRS 7800 Configuration Module Installation
Table 6-2, GRS 7800 Configuration Module Parts
Item
Description
Qty Needed
Part Number
Vendor
4
5
Configuration Module, Circular Connector
Socket, Contact
1
4
011-02582-00
M39029/56-348
Garmin
Best Source
Removal:
1. Disconnect connector (1) from LRU.
2. Remove 2 screws (3), washers, ring terminals and configuration module (4) from strain
relief (2).
3. Disconnect the strain relief (2) from the connector (1).
4. Remove the 4 configuration module contact pins from the connector (1).
5. Remove the configuration module (4).
Installation:
1. Inspect connector (1) for damaged pins.
2. Install 4 contact pins (5) on the new configuration module (4) wires.
3. Install the 4 configuration module contact pins (5) into the connector (1).
4. Assembly of the connector and strain relief is the reverse of the disassembly.
5. Checkout per Section 6.17.4.
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6.17.3 GSU 75B Configuration Module Removal & Replacement
CONFIGURATION MODULE
Figure 6-5, GSU 75B Configuration Module Installation
Table 6-3, GSU 75B Configuration Module Kit – 011-00979-20
Item
Description
Qty Needed
Garmin Part
Number
1
Sub-Assy, Potted, Config Mdl, w/EEPROM,Jackscrew
1
011-02179-00
2
3
4
Cable, 4-Conductor Harness
Pins, #22 AWG (HD)
Pan Head Screw
1
4
1
325-00122-00
336-00021-00
211-60232-07
Removal:
1. Disconnect connector from LRU.
2. Remove two screws from cover.
3. Remove one screw from configuration module attaching it to the backshell.
4. Lift up configuration module and unplug the connector.
Installation:
1. Inspect connector for damaged pins.
2. Plug in the configuration module.
3. Set configuration module in backshell and attach using one screw.
4. Reinstall the cover using two screws.
5. Reattach connector to LRU.
6. Checkout per Section 6.17.4.
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6.17.4 Configuration Module Checkout
If a GRS 77 or GRS 7800 AHRS Configuration Module is replaced:
GRS 77 or GRS 7800 and GMU 44 calibration procedures must be performed. Proceed to
Section 7.10.3.
If a GSU 75 Configuration Module is replaced:
Configuration settings must be reloaded to the GSU 75B per Section 7.6, then proceed to
Section 7.7.3.
Additionally, GSU 75B and GMU 44 calibration procedures must be performed. Proceed to
Section 7.10.
If a GEA 71 Configuration Module is replaced:
Proceed to Section 7.4.3.
If only the Master Configuration Module is replaced:
NOTE
New Terrain/Obstacle cards, Jeppesen Aviation Database and other optional
features (i.e. TAWS unlock card) will need to be replaced if the master
configuration module is changed. The G1000 System ID number will change to a
new number when installing a new master config module. The old databases and
feature enable cards will no longer work as they will remain locked to the old
System ID number.
1. Start the G1000 system in configuration mode.
2. Go to the Configuration Upload Page on PFD 1.
3. Press the UPDT CFG softkey and press ENT.
If both PFD 1 and Master Configuration Module are replaced:
NOTE
New Terrain/Obstacle cards, Jeppesen Aviation Database and other optional
features (i.e. TAWS unlock card) will need to be replaced if the master
configuration module is changed. The G1000 System ID number will change to a
new number when installing a new master config module. The old databases and
feature enable cards will no longer work as they will remain locked to the old
System ID number.
1. The entire G1000 system must be re-configured. Insert the correct G1000 software
loader card into PFD 1.
2. Start the G1000 in configuration mode. Go to the System Upload Page on PFD 1.
3. See Section 3.8 for instructions on how to use the System Upload page. Check all
configuration files and reload them.
4. After reloading configuration files, examine the G1000 installation for any installed
configuration options. Options are listed in Section 3.8. Load optional files as
necessary.
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5. Continue to Section 9 and conduct the return to service checkout.
6.18
GEA 71 Backshell Thermocouple Removal & Replacement
The GEA 71 has a K-Type thermocouple (Item 1 shown below) installed in its backshell, in
addition to the configuration module. The thermocouple is used in conjunction with the
configuration module temperature sensor to compensate for temperature probe errors resulting
from the dissimilar metals at the pin contacts.
Figure 6-6, GEA Backshell Thermocouple
Item #
Table 6-4, Thermocouple Kit (011-00981-00)
Description
Qty Needed
Garmin Part Number
1
3” Thermocouple, K type
1
925-L0000-00
2
Pins #22 AWG
2
336-00021-00
3
Screw
1
211-60234-08
Removal:
1. Remove GEA 71 per Section 6.4.
2. Remove GEA connector backplate.
3. Remove connector assembly J711 from the backplate.
4. Remove screws, item 7, and cover, item 6, from the backshell, item 5.
5. Unscrew thermocouple from boss on backshell. Extract the thermocouple pins from the
connector.
Replacement:
1. Crimp pins, item 2, onto each of the thermocouple wires, item 1. Ensure that prestripped wire length is 1/8” prior to crimping.
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2. Insert newly crimped pins and wires into the appropriate connector housing location,
item 4, as specified by King Air 300 Series Wiring Diagram, listed in Table 1-1.
3. Place thermocouple body, item 1, onto the backshell boss, item 5. Place the
thermocouple as shown in Figure 6-6 so that the wires exit towards the bottom of the
backshell.
4. Fasten thermocouple tightly to backshell using the provided screw, item 3.
5. Fasten cover, item 6, to backshell using screws, item 7.
6. Continue to Section 7.4.3 and verify that the ITT indications are valid on the MFD.
6.19
GPS/WAAS Antennas
Removal:
1. Gain access to the antenna coaxial cable connector by removing the cabin interior
ceiling panel. Refer to the Antenna Install drawing listed in Table 1-1.
2. Disconnect the antenna coaxial cable.
3. Remove the antenna mounting screws.
4. Remove antenna.
Reinstallation:
1. Install antenna using retained mounting screws.
2. Connect the antenna coaxial cable.
3. Fillet seal around antenna. Refer to the Antenna Install drawing listed in Table 1-1.
4. Reinstall cabin interior ceiling panel.
5. Proceed to Section 7.3.3 GPS Signal Acquisition for testing.
6.20
Diversity Transponder Antenna
Removal:
1. Gain access to the antenna coaxial cable connector and mounting hardware by
removing the cabin interior ceiling panel. Refer to the Antenna Install drawing listed in
Table 1-1.
2. Disconnect the antenna coaxial cable.
3. Remove the two nuts and washers securing the antenna.
4. Remove antenna.
Reinstallation:
1. Install antenna using retained hardware.
2. Connect the antenna coaxial cable.
3. Fillet seal around antenna. Refer to the Antenna Install drawing listed in Table 1-1.
4. Reinstall cabin interior ceiling panel.
5. Proceed to Section 7.5.4 for testing of the GTX33D or GTX 3000.
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6.21
Iridium Antenna
Removal:
1. Gain access to the antenna coaxial cable connector by removing the aft cabin ceiling
panel. Refer to the Antenna Install drawing listed in Table 1-1.
2. Disconnect the antenna coaxial cable.
3. Remove the antenna mounting screws.
4. Remove antenna.
Reinstallation:
1. Install antenna using retained mounting screws.
2. Connect the antenna coaxial cable.
3. Fillet seal around antenna. Refer to the Antenna Install drawing listed in Table 1-1.
4. Reinstall the aft cabin ceiling panel.
5. Proceed to Section 8.17 for testing of the GSR 56.
6.22
Wi-Fi Antenna
Removal:
1. Gain access to the antenna coaxial cable connector by opening the tail access door
behind the aft pressure bulkhead. Refer to the Antenna Install drawing listed in Table
1-1.
2. Disconnect the antenna coaxial cable.
3. Remove the antenna mounting screws.
4. Remove antenna.
Reinstallation:
1. Install antenna using retained mounting screws.
2. Connect the antenna coaxial cable.
3. Fillet seal around antenna. Refer to the Antenna Install drawing listed in Table 1-1.
4. Secure the tail access door.
5. Proceed to Section 8.16 for testing of the GDL 59.
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6.23
Signal Conditioners
Removal:
1. For Signal Conditioner No. 1, remove PFD1 from the instrument panel per Section 6.1.
For Signal Conditioner No. 2, remove PFD2 from the instrument panel per Section 6.1.
2. Remove 3 top screws from Signal Conditioner rack.
3. Slide mounting tray out from rack and disconnect the unit connector. If needed, remove
MFD as per Section 6.1 to access the Signal Conditioner connector.
4. Remove the four mounting bolts and remove the Signal Conditioner unit.
5. If planning to reinstall the same unit, it is not necessary to disconnect the ground strap
from the unit ground stud. If replacing with a new unit, disconnect the ground strap from
the removed unit and retain the ground strap and associated hardware for reinstallation
on the new unit.
Reinstallation:
1. Reinstallation of the Signal Conditioners is the reverse of the removal. Reference the
Main Instrument Panel Installation drawing, listed in Table 1-1, for more details.
2. Proceed to Section 7.4.3 for testing.
6.24
Instrument Panel Annunciators (Prop Synch and Standby Battery)
Removal:
1. Remove MFD from the instrument panel as per Section 6.1.
2. Using a M22885/108T8234 extraction tool, disconnect connector from the back of the
switch.
3. Pull the pushbutton cap fully out of the switch body and allow the cap to rotate 90° where
it is held by the retaining element.
4. While holding the retaining sleeve (back side of the instrument panel), loosen the two
screws inside the switch body until the switch is free to come out.
5. Remove the mounting sleeve and switch from the instrument panel.
Reinstallation:
1. Reinstallation of the Prop Synch and Standby Battery switches is the reverse of the
removal. Reference the Main Instrument Panel Installation drawing, listed in Table 1-1,
for more details.
2. Press and hold the cockpit annunciator “Press To Test” switch located to the left of the
annunciator panel, and verify the following:
• For the Standby Battery Annunciator/Switch: STBY Battery Switch legends
illuminates and reflects “STANDBY BATTERY” in white, “ARM” in green, and
“ON” in amber.
• For the Prop Synch Annunciator/Switch: Prop Synch Switch legends illuminates
and reflects “PROP SYNC” in white, and “ON” in green.
3. Release cockpit annunciator “Press To Test” switch.
4. If further maintenance is not required, proceed to Section 9.
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6.25
Emergency Frequency Switch/Annunciator
Removal:
1. Remove the switch plate from the pedestal using a screw driver to loosen the quarter
turn fasteners.
2. Using a M22885/108T8234 extraction tool, disconnect connector from the back of the
switch.
3. Pull the pushbutton cap fully out of the switch body and allow the cap to rotate 90° where
it is held by the retaining element.
4. While holding the retaining sleeve (back side of the switch plate), loosen the two screws
inside the switch body until the switch is free to come out.
5. Remove the mounting sleeve and switch from the switch plate.
Reinstallation:
1. Reinstallation of the Emergency Frequency switch/annunciator is the reverse of the
removal. Reference the Pedestal Re-Configuration drawing, listed in Table 1-1, for more
details.
2. Press and hold the cockpit annunciator “Press To Test” switch located to the left of the
annunciator panel, and verify the following:
• Legends illuminate and reflect “EMERG FREQ” in white and “121.5” in white.
3. Release cockpit annunciator “Press To Test” switch.
4. If further maintenance is not required, proceed to Section 9.
6.26
L-3 Avionics (BF Goodrich) PS-835(C or D Model) Emergency Battery
Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Unscrew the knurled hold-down nut to allow it to move free of the unit.
3. Remove the unit from the rack.
Reinstallation:
1. Install the emergency battery in accordance with the Electrical Equipment Install, Nose
Bay drawing (refer to Master Drawing List, listed in Table 1-1, for specific drawing
number). Refer to the King Air 300 Series Maintenance Manual, listed in Table 1-1, for
access requirements as needed.
2. If further maintenance is not required, proceed to Section 9.
6.27
MD 302 Standby Attitude Module (SAM)
The MD 302 SAM installed by this STC has two components, an electronic indicator, and a
configuration module. The indicator is installed on the instrument panel, between the pilot’s
PFD and the MFD. The configuration module in installed inside the 15-pin D-subminiature
connector that mates to the back of electronic indicator. It is required for proper operation of the
unit.
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6.27.1 MD 302 Electronic Standby Indicator
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect pitot-static plumbing from the back of the standby airspeed indicator. Take
necessary precautions to prevent foreign object debris from entering the pitot-static lines
during maintenance.
3. Disconnect the electrical connector from the indicator.
4. Use a nut driver to remove the four hex head attachment screws from the front of the
indicator.
5. Remove the indicator.
Reinstallation:
1. Reinstall the electronic standby indicator referencing the Main Instrument Panel
Installation drawing, listed in Table 1-1, for more details.
2. Connect the pitot-static plumbing and electrical connector.
3. Reinstall the MFD.
4. If the Configuration Module was not changed, Configuration Setup is automatic at first
power on and no additional action is required.
5. If a new unit is installed with a new configuration module, Configuration Setup per
Section 3.19 is required.
6. Test MFD per Section 9.1.
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6.27.2 Configuration Module
Removal:
CAUTION: The Configuration Module PC Board Assembly contains sensitive electronics that
can be damaged by electrostatic discharge (ESD). Appropriate precautions should be applied
prior to handling this component.
1. Remove Electronic Standby Indicator per Section 6.27.1.
2. Use a Phillips screwdriver to remove the two countersunk screws from the cover on the
connector backshell.
3. Remove the backshell cover. The Configuration Module PC Board Assembly is located
directly beneath the cover.
4. Using an appropriate extraction tool remove the pins of the Configuration Module PC
Board Assembly from the D-Sub connector (D-Sub pins 15, 14, 10, and 5).
5. Remove the Configuration Module PC Board Assembly.
SCREW, 2-56 (90-208-10011)
BACKSHELL COVER (9017274)
CFG MODULE ASSY (9017184-1)
SCREW, 4-40 (90-406-00011)
SPRING (part of 9016479)
TAPE (NOT SHOWN)
(AA59163-1II0020
OR 605980-1)
BACKSHELL (9017218)
CABLE CLAMP (part of 9016479)
SLIDE LOCK (part of 9016479)
SCREW, 4-40 (part of 9016479)
CONNECTOR, 15 POSN,
HI-DENS D-SUB (9016479)
TERMINAL (MS25036-149)
SCREW, 4-40 (part of 9016479)
Figure 6-7, MD 302 Backshell and Config Module
Reinstallation:
CAUTION: The Configuration Module PC Board Assembly contains sensitive electronics that
can be damaged by electrostatic discharge (ESD). Appropriate precautions should be applied
prior to handling this component.
1. The wires coming from the Configuration Module PC Board Assembly are marked as
follows on the circuit board: TP1, TP2, TP3, and TP4.
2. With the D-Sub oriented up (pin locations 1-5 on top), orient the Configuration Module
PC Board Assembly with the electronic parts facing UP.
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3. Using an appropriate insertion tool, install each pin into the rear of the D-Sub connector
as follows:
•
Board TP1 = config return = D-Sub pin 15
•
Board TP2 = config data = D-Sub pin 14
•
Board TP3 = config clock = D-Sub pin 10
•
Board TP4 = config power = D-Sub pin 5
4. Bend the wires of the Configuration Module PC Board Assembly 180 degrees so that the
PC Board has its electrical components facing down as shown. Be careful not to place
excess strain on the solder connections between the wires and the PC Board.
5. Capture the Configuration Module PC Board Assembly into the Backshell by placing the
Backshell Cover on top of the Backshell. Ensure the holes of the cover align with the
holes of the PC board and the backshell.
6. Using a Phillips screwdriver, re-install the two counter sunk screws and secure the
cover.
7. Configure MD 302 unit per Section 3.19.
8. Test MFD per Section 9.1.
6.28
Mechanical Standby Indicators
6.28.1 Standby Airspeed Indicator
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect pitot-static plumbing from the back of the standby airspeed indicator. Take
necessary precautions to prevent foreign object debris from entering the pitot-static lines
during maintenance.
3. Disconnect the electrical connector from the standby airspeed indicator.
4. Use a Phillips screwdriver to remove the attachment screws from the front of the standby
airspeed indicator.
5. Remove the standby airspeed indicator.
Reinstallation:
1. Reinstallation of the standby airspeed indicator is the reverse of the removal. Reference
the Main Instrument Panel Installation drawing, listed in Table 1-1, for more details.
2. Test MFD per Section 9.1.
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6.28.2 Standby Altimeter
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect pitot-static plumbing from the back of the standby altimeter. Take necessary
precautions to prevent foreign object debris from entering the pitot-static lines during
maintenance.
3. Disconnect the electrical connector from the standby altimeter.
4. Use a Phillips screwdriver to remove the attachment screws from the front of the standby
altimeter.
5. Remove the standby altimeter.
Reinstallation:
1. Reinstallation of the standby altimeter is the reverse of the removal. Reference the Main
Instrument Panel Installation drawing, listed in Table 1-1, for more details.
2. Test MFD per Section 9.1.
6.28.3
Standby Attitude Indicator
Ensure the standby attitude indicator gyro is not spinning—this may take 10 minutes or longer
after the unit has been turned off. This unit is very delicate; handle like eggs. Refer to the 4300
Series Attitude Indicator Installation Manual, listed in Table 1-1, for more handling instructions.
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect the electrical connector of the standby attitude indicator.
3. Use a 0.060” 6-Spline wrench to remove the knob from the front of the standby attitude
indicator.
4. Use a Phillips screwdriver to remove the three attachment screws from the front of the
standby attitude indicator.
5. Remove the standby attitude indicator.
Reinstallation:
1. Ensure the lighting control voltage switches on rear of unit are set for 28V.
28V
2. Reinstallation of the standby attitude indicator is the reverse of the removal. Reference
the Main Instrument Panel Installation drawing, listed in Table 1-1, for more details.
3. Test MFD per Section 9.1.
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6.29
GIA Cooling Fans
Removal:
1. Gain access into the nose avionics equipment bay.
2. Disconnect the cooling fan hoses from the cooling fan. Take necessary precautions to
prevent any foreign debris from entering the fan hoses during maintenance.
3. Disconnect the electrical connector of the cooling fan.
4. Use a Phillips screwdriver to remove the attachment screws and fan inlet duct (if
installed) from the cooling fan.
5. Remove the cooling fan.
Reinstallation:
1. Reinstallation of the avionics cooling fan is the reverse of the removal. Reference the
Electrical Equipment Install, Nose Bay drawing, listed in Table 1-1, for more details.
2. Test per Section 9.4.
6.30
GDU Cooling Fans
Removal:
1. Remove the display associated with the cooling fan, per Section 6.1.
2. Disconnect the electrical connector of the cooling fan.
3. Use a Phillips screwdriver to remove the attachment screws from the cooling fan.
4. Remove the cooling fan.
Reinstallation:
1. Reinstallation of the Sandia GDU cooling fan is the reverse of the removal. Reference
the Main Instrument Panel Installation drawing, listed in Table 1-1, for more details.
2. Test per Section 9.4.
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6.31
GTS 820/850 and GTS Processor Traffic Units
CAUTION:
After any maintenance or modification is made to the GTS
820/850/processor TAS/TCAS cables such as replacing a connector or
entire cable, be sure to adhere to all of the specifications and limitations
such as minimum and maximum cable attenuation, attenuation balance
between cables, phase matching etc.
Removal:
1. Gain access to the left forward avionics compartment in the nose of the aircraft.
2. Disconnect the eight coax QMA or TNC connectors.
3. Disconnect the three electrical connectors.
4. Unlock the unit from the rack by loosening the ratcheting latch mechanism.
5. Remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Insert the unit into the installation rack.
3. Lock the unit into the rack by using the ratcheting latch mechanism.
4. Reconnect the eight coax QMA or TNC connectors and the three electrical connectors.
5. Close access to the left forward avionics compartment.
6. Configure and test the GTS unit per Section 7.17.
6.32
GPA 65 PA/LNA Unit
Removal:
1. Remove cabin interior to access FS 158 at WL 119 on the left side of the fuselage.
Reference the Antenna Install drawing listed in Table 1-1 for more details.
2. Disconnect the eight coax “quick-lock” connectors.
3. Disconnect the electrical connector.
4. Remove the four mounting screws that hold the unit to the installation brackets.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Reattach the unit to the mounting brackets reusing existing hardware.
3. Connect the eight coax connectors. Note the color coded bands which match the mating
connectors on the unit.
4. Reconnect the electrical connector pigtail.
5. Ensure that all connectors (coax and electrical) are locked in place.
6. Reinstall cabin interior.
7. No configuration is required for the GPA 65. Test the GTS 820/850 per Section 8.14.
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GA 58 Traffic Antennas
Removal:
1. Gain access to the antenna coaxial cable connectors by removing the cabin interior
ceiling panel. Refer to the Antenna Install drawing listed in Table 1-1.
2. Disconnect the four coaxial cable connectors.
3. Remove the antenna mounting screws.
4. Remove antenna.
Reinstallation:
1. Install antenna using retained mounting screws.
2. Connect the four coaxial cable connectors. Note the color coded bands which match the
mating connectors.
3. Fillet seal around antenna. Refer to the Antenna Install drawing listed in Table 1-1.
4. Reinstall cabin interior ceiling panel.
5. Test the GTS 820/850 or GTS Processor per Section 8.14.
6.34
GDL 59 Wi-Fi Datalink
Removal:
1. Gain access to the unit based on location a. If the unit is installed under the cabin floor, remove the cabin center floor panel at the
main entry door. Remove the remote equipment shelf or detach the two rack mount
angles from the shelf. Retain all mounting hardware.
b. If the unit is installed in the tail, open the tailcone access door on the bottom of the
tailcone.
2. Unlock the GDL 59 handle by loosening the Phillips screw on the handle.
3. Pull the handle upward to unlock the GDL59. Gently remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Lift the handle and gently insert the GDL 59 into its rack. The handle should engage the
dogleg track.
3. Press down on the GDL 59 handle to lock the unit into the rack.
4. Lock the handle to the GDL 59 body using the Philips screw. Torque the handle screw
to 10-14 in-lbs.
5. If the unit is installed under the cabin floor, reinstall the remote equipment shelf or two
rack mount angles using the retained hardware and the cabin center floor panel.
6. If the unit is installed in the tail, close the tailcone access door.
7. Configure, activate, and test the GDL 59 per Section 7.18.
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6.35
GSR 56 Satellite Receiver
Removal:
1. Gain access to the unit based on location a. If the unit is installed under the cabin floor, remove the cabin center floor panel at the
main entry door. Remove the remote equipment shelf or detach the two rack mount
angles from the shelf. Retain all mounting hardware.
b. If the unit is installed in the tail, open the tailcone access door on the bottom of the
tailcone.
2. Unlock the unit from the rack by pulling out on the ratcheting latch mechanism and
turning counter-clockwise until the latch mechanism clears the tab on the unit.
3. Slide the unit out of the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Insert the unit into the installation rack.
CAUTION:
Do not use excessive force when inserting the GDL 56 into
the rack. This may cause damage to occur to the connectors,
unit, and/or unit rack. If heavy resistance is felt during
installation, stop! Remove the GDL 56 and identify the
source of resistance.
3. Lock the unit into the rack by using the ratcheting latch mechanism.
4. If the unit is installed under the cabin floor, reinstall the remote equipment shelf or two
rack mount angles using the retained hardware and the cabin center floor panel.
5. If the unit is installed in the tail, close the tailcone access door.
6. Register with Garmin Connext per Section 8.15.
7. No software or configuration loading is required for the GSR 56. Test the GSR 56
according to Section 8.17.
6.36
GRA 5500 Radar Altimeter
Removal:
1. Gain access to the avionics shelf in the tail area.
2. Disconnect the electrical connector.
3. Disconnect the two coaxial cable connectors, making note of which cable is Transmit
(Tx) and which cable is Receive (Rx).
4. Pull back on the lockdown mechanism and simultaneously turn counterclockwise until
free.
5. Disengage the lockdown mechanism collar from the GRA 5500 hook and slide the GRA
5500 forward to remove the unit from the rack.
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Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Place the unit on the mounting rack ensuring the GRA 5500 rear feet are aligned in the
mounting rack slots.
3. Slide the GRA 5500 back until the feet are fully engaged with the mounting rack.
4. Lift the lockdown mechanism collar in place on the GRA 5500 hook and hand turn the
lockdown mechanism knob clockwise until the GRA 5500 is secure and cannot
reasonably be ratcheted any tighter by hand.
5. Connect the electrical connector.
6. Connect the two coaxial cable connectors.
7. For integrated installations (using a RS-422 connection to GIA2), configure and test the
GRA 5500 according to Section 7.16. For non-integrated installations (using Arinc 429
connections), configure and test per Section 3.17.
6.37
GSD 41 Data Concentrator
Removal:
1. Gain access to the avionics shelf in the tail area.
2. Unlock the unit from the rack by loosening the ratcheting latch mechanism.
3. Remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair
any damage.
2. Insert the unit into the installation rack.
CAUTION:
Do not use excessive force when inserting the GSD 41 into
the rack. This may cause damage to occur to the connectors,
unit, and/or unit rack. If heavy resistance is felt during
installation, stop! Remove the GSD 41 and identify the
source of resistance.
3. Lock the unit into the rack by using the ratcheting latch mechanism.
4. Configure the GSD 41 according to Section 7.20.
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7. Garmin G1000 LRU Replacement/Configuration & Testing
This section provides procedures to be followed after a piece of G1000 equipment is replaced.
At the beginning of each LRU section, instructions are given to guide the technician for various
removal/replacement scenarios. These instructions define necessary procedures to be followed
for situations where original equipment was reinstalled as well as for situations where new
equipment (new serial number) is installed.
NOTE
Garmin recommends the use of SanDisk brand SD cards to load G1000 software
and configuration files. If another brand of card is used, and software loading
problems occur, replace the card with a SanDisk brand card and reattempt the
software load.
CAUTION
Connect a ground power unit to the aircraft for software loading. DO NOT
RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A
BATTERY CHARGER AS AN EXTERNAL POWER SOURCE DUE TO
ELECTRICAL NOISE IT MAY INJECT IN THE G1000 SYSTEM. DO NOT
ALLOW POWER TO BE REMOVED FROM THE SYSTEM WHEN LOADING
SOFTWARE! Remove power only when told to do so by the following
procedure. Power loss during a software upgrade may cause a LRU to become
corrupted and unresponsive requiring replacement. Remove power only when told
to do so in the procedure.
All displays should be in the same mode (configuration or normal), unless
instructed differently.
If an incorrect configuration file is loaded at any time in this section, STOP
and start the configuration load over using Section 3.8.
7.1
GDU 1050A/1550 PFD & MFD
Original Display Reinstalled
If the removed display(s) are re-installed in their original positions, no software or configuration
loading is required. This does not include units that were returned for repair as their software
and configuration files are deleted during the repair testing process. Continue to the PFD/MFD
Test procedure, Section 7.1.7.
Original PFD Displays Installed in Opposite Locations for Troubleshooting
If the PFD 1 and PFD 2 are installed in opposite positions, no software or configuration loading
is required. Continue to the PFD/MFD Test procedure, Section 7.1.7.
New Repair or Exchange Display(s) Installed
If a new, repaired or exchanged GDU is installed, the correct software and configuration files
must be loaded to the unit.
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7.1.1
LRU Replacement Procedure PFD1
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the MFD, scroll to the LRU replacement page.
6. Activate the curser and select PFD1 in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 3.8.
16. If there are no red-Xs or system alerts, continue to Section 7.1.7.
7.1.2
Legacy Replacement Procedure PFD1 (Alternate Method)
A full system configuration re-load is required when a new, repaired, or exchanged display is
installed using this method. This includes all options and feature enablements.
To complete this procedure, continue to Section 3.8.
7.1.3
LRU Replacement Procedure PFD2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Remove SD cards from top and bottom slots of PFD2, MFD, and PFD1 if present.
3. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
4. Turn on Avionics electrical busses.
5. Power on PFD2, MFD, and PFD1 in configuration mode.
6. Using the MFD, scroll to the LRU replacement page.
7. Activate the curser and select PFD2 in the LRU dropdown box.
8. Press the CHK All softkey.
9. Press the Load softkey.
10. Press ENT to acknowledge the process was complete.
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11. Deactivate the curser.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 3.8.
17. If there are no red-Xs or system alerts, continue to Section 7.1.7.
7.1.4
Legacy Replacement Procedure PFD2 (Alternate Method)
A full system configuration re-load is required when a new, repaired, or exchanged display is
installed using this method. This includes all options and feature enablements.
To complete this procedure, perform Section 3.8.
7.1.5
LRU Replacement Procedure MFD
NOTE
Anytime the MFD is replaced, all databases will have to be reloaded.
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Remove SD cards from top and bottom slots of PFD2, MFD, and PFD1 if present.
3. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
4. Turn on Avionics electrical busses.
5. Power on PFD2, MFD, and PFD1 in configuration mode.
6. Using the PFD1, scroll to the LRU replacement page.
7. Activate the curser and select MFD in the LRU dropdown box.
8. Press the CHK All softkey.
9. Press the Load softkey.
10. Press ENT to acknowledge the process was complete.
11. Deactivate the curser.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 3.8.
17. Install databases Section 3.14 to re-load databases.
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18. After databases are re-loaded, continue to Section 7.1.7.
7.1.6
Legacy Replacement Procedure MFD (Alternate Method)
A full system configuration re-load is required when a new, repaired, or exchanged display is
installed using this method. This includes all options and feature enablements. To complete this
procedure, perform Section 3.8.
7.1.7
PFD/MFD Test
1. Allow displays to initialize for ~1 minute.
2. Check that all COM/NAV display fields are valid in the top corners of both PFDs.
3. Check that attitude, heading, altitude, airspeed, vertical speed and OAT fields are valid
within 2 minutes of power up on both PFDs.
4. Press the Sensor softkey on each PFD and switch between ADC1 and ADC2. Verify
that data from both GDC air data computers is valid on both displays.
5. Press the Sensor softkey on each PFD and switch between AHRS1 and AHRS2. Verify
that data from both GSU 75 or GRS 77/7800 is valid on both displays.
6. Check that the engine instrument fields are valid on the MFD.
Figure 7-1, G1000 Normal Mode Check
7. Push the red DISPLAY BACKUP button on the pilot-side GMA 1347D. Verify that the
pilot-side PFD and MFD displays enter reversion mode. MFD should have valid altitude,
airspeed, vertical speed, COM1, COM2, NAV1, NAV2 and engine instruments.
8. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify
PFD 1 and MFD return to normal display modes.
9. Repeat Step 1 using GMA2. Ensure that PFD 2 and MFD enter reversion mode and
MFD displays valid altitude, airspeed, vertical speed, COM1, COM2, NAV1, NAV2 and
engine instruments.
10. De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button.
Verify PFD 2 and MFD return to normal display modes.
11. Select the Map – TAWS Map page on the MFD.
12. Verify that the title at the top of the page reads “Map – TAWS-B” or “Map-TAWS-A”. If
TAWS has not been enabled, the title will read “Map – Terrain Proximity” or “Map –
Terrain”.
13. Press the MENU button and select “Test TAWS” from the pop-up menu.
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14. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over
the cockpit speaker.
15. If no other service is to be performed, perform final return-to-service test as specified in
Section 9.
7.2
GMA 1347D Audio Panel
Original GMA 1347D Reinstalled
No software/configuration loading or testing is required if the removed GMA 1347D is reinstalled. This does not include units that were returned for repair as their software and
configuration files are deleted during the repair testing process. Continue to the final return-toservice checks in Section 9.
Original GMA 1347D Installed in Opposite Locations for Troubleshooting
If the original GMA #1 and GMA #2 are installed in opposite locations, configuration loading is
required. See Section 7.2.1.
New, Repaired or Exchange GMA 1347D Installed
If a new, repaired or exchanged GMA 1347D is installed, the correct software and configuration
files must be loaded to the unit. See Section 7.2.1.
7.2.1
LRU Replacement Procedure GMA 1 or GMA 2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GMA1 or GMA2, whichever was replaced in the LRU
dropdown box
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.2.2.
16. If there are no red-Xs or system alerts, continue to Section 7.2.3.
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7.2.2
Legacy Replacement Procedure GMA 1 or GMA 2 (Alternate Method)
To load the GMA complete the following subsections in order as they apply to the aircraft.
7.2.2.1
01) Baseline (For GMA 1 or GMA 2 replacement)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the small FMS knob to highlight “01) Baseline” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air 200-300-Series Baseline Load Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Use the large FMS knob to scroll to GMA1 or GMA2 whichever was replaced.
9. Highlight the software box and press the ENT key.
10. Highlight the Configuration box and press the ENT key.
11. Press “Load” softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
13. Green “PASS” in the Configuration and Software columns for each item loaded.
14. “Upload Complete………….”COMPLETE” in the summary box.
15. Acknowledge the prompt by pushing the ENT key.
7.2.2.2 07) Connext - SXM (For GMA 1 or GMA 2 replacement and aircraft
equipped with a GDL 59 and/or GSR 56 only)
1. Scroll the curser to the Group window and select “07) Connext - SXM
2. Press the ENT key.
3. In the ITEM window highlight the installed GDL 59 and/or GSR 56 configuration and
press the ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GMA1 or GMA 2 configuration box, whichever was replaced, and
press the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
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7.2.2.3 11) Non Garmin Options (For GMA 1 or GMA 2 replacement and aircraft
equipped with a ADF only)
1. Scroll the curser to the Group window and select 11) Non-Garmin options.
2. Press the ENT key.
3. In the ITEM window highlight King Air – ADF Option and press the ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GMA 1 or GMA 2 configuration box, whichever was replaced, and
press the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
7.2.2.4 11) Non Garmin Options (For GMA 1 or GMA 2 replacement and aircraft
equipped with a DME only)
1. Scroll the curser to the ITEM window highlight King Air – DME Option and press the ENT
key on PFD1.
2. Press the CLR ALL softkey.
3. Scroll the curser to GMA 1 or GMA 2 configuration box, whichever was replaced, and
press the ENT key to check the box.
4. Press “Load” softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
6. Acknowledge the prompt by pushing the ENT key.
7.2.2.5
Configuration Manager Update
1. With the system still in configuration mode, scroll to the Configuration Manager page on
PFD 1.
2. Press the CNFM CFG softkey.
3. Select ok when prompted to “Confirm configuration as expected configuration”
4. Power cycle the system. Verify there are no red-Xs or system alerts.
5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
6. If there are no red-Xs or system alerts, continue to Section 7.2.3.
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7.2.3
GMA 1347D Test
Except for marker beacon operation, an in-aircraft checkout may be performed in the aircraft
with known good microphone, headset, and speaker.
7.2.3.1
Intercom System (ICS) Check
1. Ensure that the MAN SQ key is off (no light).
2. Adjust GMA1 and GMA2 ICS volume to a comfortable level.
3. Plug in a headset at each COCKPIT ICS position. One at a time, plug a headset into
each left and right CABIN ICS jack location (if installed) (one headset on right, one
headset on left).
4. Verify the following:
•
Two-way communication between each CABIN ICS jack position.
•
CABIN ICS position cannot hear the pilot and copilot.
•
CABIN ICS positions cannot be heard by the pilot or copilot.
5. On GMA1 select COM1 MIC and AUDIO.
6. Ensure INTR COM is deselected on GMA1 or GMA2. Verify an active (green) COM1
frequency is displayed on both PFDs.
7. On GMA1 or 2 select PA and verify the PA select annunciator is illuminated on GMA1
and GMA2. Verify COM1 active frequency is displayed white.
8. Initiate passenger address using pilot’s headset boom mic by keying the pilot’s PTT.
Verify the following:
•
Clear PA audio can be heard over cabin speaker and CABIN ICS headsets
•
PA selected annunciator on GMA1 flashes ~ once per second during PA
address.
9. Repeat Step 8 using pilot hand mic.
10. Initiate passenger address using copilot’s headset boom mic by keying the copilot’s PTT.
Verify the following:
•
Clear PA audio can be heard over cabin speaker and CABIN ICS headsets
•
PA selected annunciator on GMA1 flashes ~ once per second during PA
address.
11. Repeat Step 10 using copilot hand mic.
7.2.3.2
Transceiver Operational Check
Perform a ramp test radio check by exercising the installed transceivers, microphone,
microphone key and audio over the headphones and speaker. Verify that communications are
clear and PTT operation is correct for each pilot position.
1. On the pilot’s audio panel, select the audio source corresponding to each installed
avionics unit (i.e. NAV1, NAV2, COM1, COM2, ADF and DME) and check for audio over
the pilot’s headset.
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2. Press the SPKR key on pilot’s audio panel and verify that the selected audio is heard
over the pilot’s speaker.
3. On the copilot’s audio panel, select the audio source corresponding to each installed
avionics unit (i.e. NAV1, NAV2, COM1, COM2, ADF and DME) and check for audio over
the copilot’s headset.
4. Press the SPKR key on copilot’s audio panel and verify that the selected audio is heard
over the copilot’s speaker.
7.2.3.3
Failsafe Operation Check – GMA 1347D #1
1. Turn the GMA 1347D #1 off by pulling the AUDIO NO 1 circuit breaker. This directs all
COM 1 phone audio, MIC audio and MIC key to the pilot’s position.
2. Check the failsafe operation by exercising the COM 1 boom mic, hand mic, microphone
key and audio over the headphones. All volume control for the COM audio should be
through the PFD volume control. Verify proper operation of COM 1 using the failsafe
operation.
3. Close the AUDIO NO 1 circuit breaker to continue testing.
7.2.3.4
Failsafe Operation Check – GMA 1347D #2
1. Turn the GMA 1347D #2 off by pulling the AUDIO NO 2 circuit breaker. This directs all
COM 2 phone audio, MIC audio and MIC key to the co-pilot’s position.
2. Check the failsafe operation by exercising the COM 2 boom mic, hand mic, microphone
key and audio over the headphones. All volume control for the COM audio should be
through the PFD volume control. Verify proper operation of COM 2 using the failsafe
operation.
3. Close the AUDIO NO 2 circuit breaker to continue testing.
7.2.3.5
Marker Beacon Test
1. Using a ramp tester, simulate the outer marker, middle marker, and inner marker signals
by following the test equipment manufacturer’s instructions. Verify that each marker
audio signal is present over the pilot and co-pilot headphones and speaker.
2. Verify that the outer, middle, and inner annunciations appear on PFD 1 and PFD 2 when
the corresponding signal is applied. Marker beacon annunciations ( , , and )
appear at the upper left corner of the altitude indicator on the PFD. Operate the MKR
MUTE key on the #1 and #2 GMA 1347D and ensure that the audio signal is muted.
3. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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7.2.4
Landing Gear Aural Alert Check
This check should be conducted in conjunction with the Phase 2 and Phase 4 Landing Gear
Retraction, Warning Horn check, in the existing King Air Maintenance Program.
NOTE
This procedure is applicable only to aircraft equipped with a tone generator as part
of the aircraft audio system. Refer to the appropriate aircraft wiring diagrams to
determine if a tone generator is installed.
This check can be accomplished in conjunction with the Weight on Wheels and
Low Speed Awareness Band Test in Section 8.11.
1. Conduct the Landing Gear Retraction, Warning Horn check as stated in the King Air 300
Series Maintenance Manual, listed in Table 1-1.
2. Verify that the aural tone is played through the G1000 audio system and through both
cockpit speakers.
7.2.5
SiriusXM Audio Suppression Check
This procedure is applicable only to aircraft that have Sirius XM radio subscriptions.
WARNING
The following steps require movement of the landing gear. Ensure
aircraft is safe for the operation of the landing gear before proceeding.
1. Jack aircraft to allow operation of landing gear (reference King Air 300 Series
Maintenance Manual Chapter 7-00-00).
2. Ensure both left and right throttles are at IDLE position.
3. While monitoring pilot and copilot Sirius XM audio, retract landing gear to the full up and
locked position and verify the following:
•
landing gear warning horn is active
•
XM audio is muted in the pilot and co-pilot stations
4. Increase both left and right throttles forward of IDLE position (towards takeoff position)
and verify the following:
•
landing gear warning horn is not active
•
XM audio can be heard (For aircraft not equipped with a tone generator, deselect
mute softkey or adjust Sirius XM volume to restore Sirius XM audio)
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5. Extend landing gear to the full down and locked position and return both throttles to idle
position.
6. Remove aircraft from jacks.
7. Ensure STALL WARN circuit breaker is closed.
8. While monitoring pilot and copilot Sirius XM audio, press the STALL WARN TEST switch
and verify the following:
•
Stall warning tone is active
•
XM audio is muted in the pilot and co-pilot stations
9. Release the STALL WARN TEST switch and verify the following:
•
Stall warning tone is not active.
•
XM audio can be heard (For aircraft not equipped with a tone generator, deselect
mute softkey or adjust Sirius XM volume to restore Sirius XM audio.)
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7.3
GIA 63W Integrated Avionics Unit
Original GIA 63W(s) Reinstalled
No software or configuration loading is required if the removed GIA is re-installed in its original
position (GIA1 and GIA2 in their original racks). This does not include units that were returned
for repair as their software and configuration files are deleted during the repair testing process.
Continue to the return-to-service checks in Section 9.
Original GIA 63Ws Swapped for Troubleshooting
No software loading is required if the originally installed GIA units are re-installed in opposite
positions (GIA1 and GIA2 in opposite unit racks). However, configuration loading is required.
See Section 7.3.1.
New, Repaired or Exchange GIA 63W(s) Installed
If a new, repaired or exchange GIA 63W is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.3.1.
7.3.1
LRU Replacement Procedure GIA1 or GIA2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GIA1 or GIA2, whichever was replaced in the LRU
dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Select Com1 or 2 in the LRU dropdown box.
11. Press the CHK All softkey.
12. Press the Load softkey.
13. Press ENT to acknowledge the process was complete.
14. Select GPS1 or 2 in the LRU dropdown box.
15. Press the CHK All softkey.
16. Press the Load softkey.
17. Press ENT to acknowledge the process was complete.
18. Select Nav1 or 2 in the LRU dropdown box.
19. Press the CHK All softkey.
20. Press the Load softkey.
21. Press ENT to acknowledge the process was complete.
22. Deactivate the curser.
23. Scroll to the Configuration Manager page.
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24. Press the CNFM CFG softkey.
25. Select ok when prompted to “Confirm configuration as expected configuration”
26. Power cycle the system. Verify there are no red-Xs or system alerts.
27. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.3.2.
28. If there are no red-Xs or system alerts, continue to Section 7.3.3.
7.3.2
Legacy Replacement Procedure GIA1 or GIA2 (Alternate Method)
To load the GIA complete the following subsections in order as they apply to the aircraft.
7.3.2.1
01) Baseline (For GIA 1 or GIA 2 replacement)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate the cursor and rotate the small FMS knob to display the drop down menu.
Rotate the large FMS knob to highlight “01) Baseline” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air 200-300 Series Baseline Load Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Use the large FMS knob to scroll to GIA 1 or GIA 2 whichever was replaced.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Scroll to GIA 1 or GIA 2 Region Config, whichever was replaced.
12. Highlight the Configuration box and press the ENT key to check the box.
13. Scroll to NAV 1 or NAV 2, whichever was replaced.
14. Highlight the Software box and press the ENT key to check the box.
15. Scroll to COM 1 or COM 2, whichever was replaced.
16. Highlight the Software box and press ENT key to check the box.
17. Highlight the Configuration box and press the ENT key to check the box.
18. Scroll to GPS/WAAS 1 or GPS/WAAS 2, whichever was replaced.
19. Highlight the Software box and press the ENT key to check the box.
20. Scroll to GIA 1 or GIA 2 AUDIO, whichever was replaced.
21. Highlight the Software box and press the ENT key to check the box.
22. Scroll to AUDIO CONFIG.
23. Highlight the Configuration box and press the ENT key to check the box.
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24. Press “Load” softkey.
25. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
26. Acknowledge the prompt by pushing the ENT key.
7.3.2.2
03) 300 Series Engine-Prop (For GIA 1 or GIA 2 replacement)
1. Scroll the curser to the Group window and select “03) 300 Series Engine-Prop”.
2. Press the ENT key.
3. In the ITEM window highlight the aircraft’s engine and prop combination and press the
ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA1 or GIA 2 configuration box, whichever was replaced, and press
the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
7.3.2.3
04) AHRS – Air Data (For GIA 1 or GIA 2 replacement)
NOTE
The aircraft will be equipped with dual GSU 75 ADAHRS or a combination
of GRS and GDC. If the aircraft is equipped with the combination GRS
and GDC, the installer will need to load the GRS file then load the GDC
file using the following procedure. If the aircraft is equipped with GSU 75s,
the GSU 75 is the only file that needs to be loaded.
1. Scroll the curser to the Group window and select “04) AHRS – Air Data.
2. Press the ENT key.
3. In the ITEM window highlight the installed GDC selection or GSU 75B and press the
ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA1 or GIA 2 configuration box, whichever was replaced, and press
the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
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•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key
9. Repeat steps 1-8 if there are GRS 77s or GRS 7800s installed. Select the
installed GRS unit in Step 3.
7.3.2.4
05) Autopilot (For GIA 1 or GIA 2 replacement)
1. Scroll the curser to the Group window and select “05) Autopilot.
2. Press the ENT key.
3. In the ITEM window highlight the installed autopilot configuration and press the ENT key
on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA CERT software box, and press the ENT key to check the box.
6. If King Air 300/B300 Series GFC700 – ESP Installation (No AOA) was selected in the
ITEM window, scroll the curser to select GIA 1 or GIA 2 configuration box, whichever
was replaced. Press the ENT to check the box.
7. Press “Load” softkey.
8. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
9. Acknowledge the prompt by pushing the ENT key.
7.3.2.5
06) Garmin Transponders (For GIA 1 or GIA 2 replacement)
1. Scroll the curser to the Group window and select 06) Garmin Transponders.
2. Press the ENT key.
3. In the ITEM window highlight the installed transponder configuration and press the ENT
key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA1 or GIA 2 configuration box, whichever was replaced, and press
the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
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7.3.2.6 07) Connext – SXM (For GIA 1 replacement and aircraft equipped with a
standalone GSR 56 only)
1. Scroll the curser to the Group window and select 07) Connext – SXM.
2. Press the ENT key.
3. In the ITEM window highlight the installed standalone GSR 56 configuration and press
the ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA1 configuration box and press the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
7.3.2.7 08) Radar (For GIA 2 replacement and aircraft equipped with a Garmin
GRA 5500 radar altimeter only)
1. Scroll the curser to the Group window and select 08) Radar.
2. Press the ENT key.
3. In the ITEM window highlight King Air - GRA 5500 Radar Altimeter and press the ENT
key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA 2 configuration box, and press the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
7.3.2.8 11) Non Garmin Options (For GIA 2 replacement and aircraft equipped
with a ADF only)
1. Scroll the curser to the Group window and select 11) Non-Garmin options.
2. Press the ENT key.
3. In the ITEM window highlight King Air – ADF Option and press the ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GIA 2 configuration box, and press the ENT key to check the box.
6. Press “Load” softkey.
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7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
7.3.2.9 11) Non Garmin Options (For GIA 1 replacement and aircraft equipped
with a DME only)
1. Scroll the curser to the ITEM window highlight King Air – DME Option and press the ENT
key on PFD1.
2. Press the CLR ALL softkey.
3. Scroll the curser to GIA 1 configuration box, and press the ENT key to check the box.
4. Press “Load” softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
6. Acknowledge the prompt by pushing the ENT key.
7.3.2.10 11) Non Garmin Options (For GIA 2 replacement and aircraft equipped
with a non-Garmin radar altimeter only)
1. Scroll the curser to the ITEM window highlight King Air – RAD ALT Option (429
Interface) and press the ENT key on PFD1.
2. Press the CHK ALL softkey.
3. Press “Load” softkey.
4. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
5. Acknowledge the prompt by pushing the ENT key.
7.3.2.11 11) Non Garmin Options (For GIA 1 or GIA 2 replacement and aircraft
equipped with a non-Garmin TCAS II system only)
1. Scroll the curser to the ITEM window highlight King Air – Non-Garmin TCAS II System
Option and press the ENT key on PFD1.
2. Press the CLR ALL softkey.
3. Scroll the curser to GIA 1 or GIA 2 configuration box, whichever was replaced, and press
the ENT key to check the box.
4. Press “Load” softkey.
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5. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
6. Acknowledge the prompt by pushing the ENT key.
7.3.2.12 Non Garmin Options (For GIA 2 replacement and aircraft equipped with
a non-Garmin traffic system only)
1. Scroll the curser to the ITEM window highlight King Air – Traffic System Option (429
Interface) and press the ENT key on PFD1.
2. Press the CHK ALL softkey.
3. Press “Load” softkey.
4. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
5. Acknowledge the prompt by pushing the ENT key.
7.3.2.13 Non Garmin Options (For GIA 2 replacement and aircraft equipped with
a lightning detection system only)
1. Scroll the curser to the ITEM window highlight King Air – Lightning System Option and
press the ENT key on PFD1.
2. Press the CHK ALL softkey.
3. Press “Load” softkey.
4. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
5. Acknowledge the prompt by pushing the ENT key.
7.3.2.14 Enhanced AFCS Feature Enablement (For GIA 1 or GIA 2 replacement
and aircraft equipped with Enhanced AFCS only)
1. Open PFD1 PRI and SEC circuit breakers.
2. Insert Enhanced AFCS feature enablement card (010-00330-55).
3. While holding in the #12 softkey or ENT key on PFD1, close PFD 1 PRI and SEC circuit
breakers.
4. Select the “SYSTEM UPLOAD” page.
5. Activate the cursor and select Enhanced AFCS in the group window and press ENT key
on PFD1.
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6. In the ITEM window highlight Enhanced AFCS Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Scroll the curser to GIA1 or GIA 2 configuration box, whichever was replaced, and press
the ENT key to check the box.
9. Press “Load” softkey.
10. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
11. Acknowledge the prompt by pushing the ENT key.
7.3.2.15 Configuration Manager Update
1. With the system still in configuration mode, scroll to the Configuration Manager page on
PFD 1.
2. Press the CNFM CFG softkey.
3. Select ok when prompted to “Confirm configuration as expected configuration”.
4. Power cycle the system. Verify there are no red-Xs or system alerts.
5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
6. If there are no red-Xs or system alerts, continue to Section 7.3.3.
7.3.3
7.3.3.1
GIA 63W Test
GPS Signal Acquisition
Figure 7-2, Aux – GPS Status Page (MFD)
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The GIA 63W units should normally acquire a GPS navigation solution within 5 to 10 minutes of
startup, provided the aircraft is outside (or indoors with a GPS repeater). Select the Aux – GPS
Status page on the MFD. Two softkeys on the bottom of the display allow the user to toggle
between GPS 1 and GPS 2. Verify that both receivers show 3D DIFF NAV on the MFD.
NOTE
It may be necessary to temporarily disable or move away from GPS repeaters
while testing, as repeaters may adversely affect GPS receiver performance.
7.3.3.2
VHF COM Interference Test
This test must be conducted outside. Use of a GPS repeater inside a hangar may result in a
failed test. This procedure assumes that the system is currently set to 25 kHz COM channel
spacing. Once the signal acquisition test has been completed successfully, perform the
following steps:
1. On the MFD, monitor GPS signal strength bars on the Aux – GPS Status page.
2. On the PFD, ensure that the CDI is set to GPS. If it is not, press the ‘CDI’ softkey until
GPS ENR is displayed.
3. Verify that the GPS “INTEG” flag is out of view.
4. Select 121.150 MHz on the No. 1 COM transceiver.
5. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels.
6. During the transmit period, verify that the GPS “INTEG” flag does not come into view on
the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD.
7. Repeat steps 5 and 6 and re-transmit while monitoring GPS 2 signal levels on the MFD.
8. Repeat steps 4 through 7 for each of the following frequencies:
•
121.175 MHz
•
121.200 MHz
•
131.250 MHz
•
131.275 MHz
•
131.300 MHz
9. Repeat steps 4 through 8 for the No. 2 COM transceiver (GIA2).
10. On the MFD, select the Aux – System Setup page.
11. Under the COM CONFIG field, change the COM channel spacing from 25 kHz to 8.33
kHz.
12. Go back to the Aux – GPS Status page.
13. Select 121.185 MHz on the No. 1 COM transceiver.
14. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels.
15. During the transmit period, verify that the GPS “INTEG” flag does not come into view on
the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD.
16. Repeat steps 14 and 15 and re-transmit while monitoring GPS 2 signal levels on the
MFD.
17. Repeat steps 14 through 16 for each of the following frequencies:
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•
121.190 MHz
•
130.285 MHz
•
131.290 MHz
18. Repeat steps 14 through 17 for the No. 2 COM transceiver (GIA2).
19. On the MFD, select the Aux – System Setup page and change the COM channel
spacing back to 25 kHz.
7.3.3.3
VOR/LOC/GS Test
Check the VOR, ILS, and Glideslope functions with ramp test equipment. Operate the
equipment according to the test equipment manufacturer’s instructions. Adjust the RF signal to
a level adequate to perform the test. Select the appropriate HSI source by using the CDI
softkey.
NOTE
The PFD HSI does not show a course deviation bar unless a valid VHF NAV
frequency is tuned.
7.3.3.4
GFC 700 VOR/LOC/GS Test
1. Ensure FD is coupled to PFD1 as indicated by a left pointing arrow next to the AFCS
mode controller XFR button.
2. Simulate a VOR signal on a radial equivalent to the aircraft heading. Tune the NAV 1
and NAV 2 receivers to the simulation frequency.
3. Set the HSI on PFD1 to VOR1 by pressing the CDI softkey until VOR1 is selected. Set
the HSI on PFD2 to VOR2 by pressing the CDI softkey until VOR2 is selected. Rotate
CRS1 and CRS2 knobs to set VOR1 and VOR2 course pointers to aircraft heading.
(CDI Synchronization must be set to OFF on the Aux – System Setup 1 page on the
MFD.)
4. Verify full scale deflection of VOR1 and VOR2 CDI by varying CRS1 and CRS2 selected
course at least 10° left and right. Reset course pointers to aircraft heading.
5. Engage the autopilot and press the NAV key on the AFCS mode controller. Using the
CRS1 knob alter course by 10° to the right. Verify the flight director and aircraft controls
respond by flying to the VOR course. Repeat to the left.
6. Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller. Verify FD
is coupled right as indicated by a right pointing arrow on the AFCS mode controller next
to the XFR button. Repeat step 5 using CRS2 knob while coupled to PFD2.
7. Set CRS1 and CRS2 course pointers to aircraft heading.
8. Simulate a Localizer/Glideslope signal. Tune this signal on NAV 1 and NAV 2 receiver.
Set the PFD1 HSI to LOC1 and PFD2 HSI to LOC2 by pressing CDI softkey until LOC1
and LOC2 is selected. Use the test equipment to center the deviation bars (localizer and
glideslope) on PFD1 and PFD2.
9. Press the APR key on the AFCS mode controller. Verify that the LOC and PIT
annunciations are green and ALTS and GS are white on PFD1 and PFD2. Apply
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right/left and up/down localizer/glideslope signals using the test equipment. Verify that
the Flight Director and flight controls respond appropriately.
10. Couple FD to PFD1 by pressing the XFR button on the AFCS mode controller. Verify FD
is coupled to PFD1 as indicated by a left pointing arrow on the AFCS mode controller
next to the XFR button.
11. Repeat step 9 while coupled to PFD1.
12. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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7.4
GEA 71 Engine/Airframe Unit
Original GEA 71 Reinstalled
No software or configuration loading is required if the removed GEA 71 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the return-to-service checks in Section 9.
Original GEA 71 Installed in Opposite Locations for Troubleshooting
No software loading is required if the original GEA units are installed in opposite locations (GEA
#1 and GEA #2 in opposite unit racks). Continue to the GEA 71 Test Section 7.4.3.
New, Repaired or Exchange GEA 71 Installed
If a new, repaired or exchange GEA 71 is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.4.1.
7.4.1
LRU Replacement Procedure GEA1 or GEA2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GEA1 or GEA2, whichever was replaced in the LRU
dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.4.2
16. If there are no red-Xs or system alerts, continue to Section 7.4.3.
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7.4.2
Legacy Replacement Procedure GEA1 or GEA2 (Alternate Method)
To load the GEA complete the following subsections in order as they apply to the aircraft.
7.4.2.1
01) Baseline (For GEA 1 or GEA 2 replacement)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate the cursor and rotate the small FMS knob to display the drop down menu.
Rotate the large FMS knob to highlight “01) Baseline” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air 200-300-Series Baseline Load Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Use the large FMS knob to scroll to GEA 1 or GEA 2 whichever was replaced.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press “Load” softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
13. Acknowledge the prompt by pushing the ENT key.
7.4.2.2
03) 300 Series Engine-Prop (For GEA 1 or GEA 2 replacement)
1. Scroll the curser to the Group window and select “03) 300 Series Engine-Prop”.
2. Press the ENT key.
3. In the ITEM window highlight the aircraft’s engine and prop combination and press the
ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GEA1 or GEA 2 configuration box, whichever was replaced, and
press the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
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7.4.2.3 11) Non Garmin Options (For GEA 2 replacement and aircraft equipped
with a FDR)
1. Scroll the curser to the Group window and select “11) Non Garmin Options”.
2. Press the ENT key.
3. In the ITEM window highlight the aircraft’s engine and prop combination and press the
ENT key on PFD1.
4. Press the CLR ALL softkey.
5. Scroll the curser to GEA 2 configuration box, and press the ENT key to check the box.
6. Press “Load” softkey.
7. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
8. Acknowledge the prompt by pushing the ENT key.
7.4.2.4
Configuration Manager Update
1. With the system still in configuration mode, scroll to the Configuration Manager page on
PFD 1.
2. Press the CNFM CFG softkey.
3. Select ok when prompted to “Confirm configuration as expected configuration”
4. Power cycle the system. Verify there are no red-Xs or system alerts.
5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
6. If there are no red-Xs or system alerts, test the GEA per Section 7.4.3.
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7.4.3
GEA 71 Test
On the MFD (normal mode), check the indication for each of the sensor or monitor inputs with
the aircraft engines off.
In general, verify all engine and system instruments show valid static normal values and
markings, with no red Xs or erratic indications. Reference Figure 7-3 for normal engine
instrument markings (figure may not reflect actual aircraft installation). If individual engine
readings do not appear normal or have a red-X over them, go to Section 7.4.4 for individual
instrument tests.
Figure 7-3, Normal Engine Instrument Markings (MFD)
If no other service is to be performed and individual GEA input testing is not required, continue
to the return-to-service checks in Section 9.
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7.4.4
GEA Engine Indication Checks
Perform engine indicating systems checks for the left and right engine indications in the
following Sections. To prepare the aircraft for the tests, perform the following:
1. Turn off the G1000 system and remove external power from the aircraft.
2. Open engine cowlings on the left and/or right engines to access firewall connectors and
the ITT thermocouple junction block as needed.
7.4.4.1
ITT Functional Check
Required test equipment:
Test Equipment
Calibrated DC Power Source
or ITT Tester
Make/Requirement
0-100 mVDC
or 200C-1200C
If the left engine gauge needs tested, perform the following:
1. Disconnect all thermocouple wires except for the Alumel-Green #10 and Chromel-White
#8 leads from the left hand engine thermocouple junction block mounted to the gas
generator case.
2. Connect the DC Power Source or ITT Tester across the Alumel-Green #10 (-) and
Chromel-White #8 (+) leads of the thermocouple junction block. Make sure the polarity of
the Alumel and Chromel leads are strictly observed when making connections.
3. Apply external power to aircraft and start the G1000 system in normal mode.
4. If the test input shows an incorrect ITT gauge reading outside the Indication tolerance in
Table 7-1, perform the following:
a. Troubleshoot the left engine ITT system per Beechcraft King Air 300 Series
Maintenance Manual, Chapter 77, Airframe ITT Wire Harness Continuity Check.
Note for this test, the GEA 1 unit replaces the previously installed analog ITT
indicator. Remove GEA 1 unit from its rack to conduct the continuity test from
the terminal block to the GEA 1 unit ITT input pins.
b. If the ITT Wire Harness Continuity Check passes, replace GEA 1.
5. If the test input shows a correct ITT reading within the Indication tolerance in Table 7-1,
troubleshoot the left engine ITT system per Beechcraft King Air 300 Series Maintenance
Manual, Chapter 77, using the following checks:
a. ITT Thermocouple Loop Resistance Check
b. ITT Thermocouple Insulation Resistance Check
6. After correcting the condition causing the incorrect ITT reading, turn off the G1000
system and remove external power from aircraft.
7. Reconnect all thermocouple wires to the junction blocks and torque nuts per Beechcraft
King Air 300 Series Maintenance Manual, Chapter 77.
8. If no other EIS gauge tests are needed, reinstall the engine cowling(s).
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If the right engine gauge needs to be tested, perform the following:
1. Disconnect all thermocouple wires except for the Alumel-Green #10 and Chromel-White
#8 leads from the right hand engine thermocouple junction block mounted to the gas
generator case.
2. Connect the DC Power Source or ITT Tester across the Alumel-Green #10 (-) and
Chromel-White #8 (+) leads of the thermocouple junction block. Make sure the polarity of
the Alumel and Chromel leads are strictly observed when making connections.
3. Apply external power to aircraft and start the G1000 system in normal mode.
4. If the test input shows an incorrect ITT gauge reading outside the Indication tolerance in
Table 7-1, perform the following:
a. Troubleshoot the right engine ITT system per Beechcraft King Air 300 Series
Maintenance Manual, Chapter 77, Airframe ITT Wire Harness Continuity Check.
Note for this test, the GEA 2 unit replaces the previously installed analog ITT
indicator. Remove GEA 2 unit from its rack to conduct the continuity test from
the terminal block to the GEA 2 unit ITT input pins.
b. If the ITT Wire Harness Continuity Check passes, replace GEA 2.
5. If the test input shows a correct ITT reading within the Indication tolerance in Table 7-1,
troubleshoot the right engine ITT system per Beechcraft King Air 300 Series
Maintenance Manual, Chapter 77, using the following checks:
a. ITT Thermocouple Loop Resistance Check
b. ITT Thermocouple Insulation Resistance Check
6. After correcting the condition causing the incorrect ITT reading, turn off the G1000
system and remove external power from aircraft.
7. Reconnect all thermocouple wires to the junction blocks and torque nuts per Beechcraft
King Air 300 Series Maintenance Manual, Chapter 77.
8. If no other EIS gauge tests are needed, reinstall the engine cowling(s).
NOTE
If the ITT Tester is not temperature compensated or if using the DC Signal
method, use the chart shown in Figure 7-4 to convert the ambient
temperature to millivolts and subtract from the DC Signal value in Table 7-1.
200
DC Signal
(mV, subtract
temp offset)
8.137
400
16.395
400 ± 17
600
24.902
600 ± 12
800
33.277
800 ± 7
1000
41.269
1000 ± 12
Test Point (°C)
1200
Indication (°C)
200 ± 17
48.828
1200 ± 17
Table 7-1, ITT Indication Test Points
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Figure 7-4, Ambient Temperature Conversion Chart
7.4.4.2
Torque Functional Check
Required test equipment:
Test Equipment
Make/Requirement
Calibrated DC Power Source
0-10 VDC
If the left engine gauge needs to be tested, perform the following:
1. Disconnect the J102 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a DC voltage into GEA 1 by connecting the DC power source to the left engine
firewall connector-pins J102-C (HI) and J102-R (LO).
4. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-2, troubleshoot the torque sensor per the Beechcraft King Air 300 Series Maintenance
Manual.
5. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-2 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace GEA 1.
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6. If no other EIS gauge tests are needed, reconnect and safety the J102 connector and
reinstall the engine cowling(s).
If the right engine gauge needs to be tested, perform the following:
1. Disconnect the J103 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a DC voltage into GEA 2 by connecting the DC power source to the left engine
firewall connector-pins J103-C (HI) and J103-R (LO).
4. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-2, troubleshoot the torque sensor per the Beechcraft King Air 300 Series Maintenance
Manual.
5. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-2 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace GEA 2.
6. If no other EIS gauge tests are needed, reconnect and safety the J103 connector and
reinstall the engine cowling(s).
Test Point (VDC)
Torque Indication (%)
0.000 ± 0.020
0±2
1.035 ± 0.020
45 ± 2
1.725 ± 0.020
75 ± 2
2.300 ± 0.020
100 ± 2
Table 7-2, Torque Indication Test Points
7.4.4.3
Turbine Tach N1 Functional Check
Required test equipment:
Test Equipment
Make/Requirement
Signal Generator
0-10Vdc / 0 – 1k Hz
If the left engine gauge needs to be tested, perform the following:
1. Disconnect the J104 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a 3Vrms sine wave signal into the No. 1 TACH-GEN Adapter by connecting the
Signal Generator to the left engine firewall connector-pins J104-J and J104-K.
4. Allow five seconds for the input signal to stabilize after changes before verifying the
indications.
5. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-3, troubleshoot the tach sensor per the Beechcraft King Air 300 Series Maintenance
Manual.
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6. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-3 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace the Signal Conditioner.
c. Replace GEA 1.
7. If no other EIS gauge tests are needed, reconnect and safety the J104 connector and
reinstall the engine cowling(s).
If the right engine gauge needs to be tested, perform the following:
1. Disconnect the J105 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a 3Vrms sine wave signal into the No. 2 TACH-GEN Adapter by connecting the
Signal Generator to the left engine firewall connector-pins J105-J and J105-K.
4. Allow five seconds for the input signal to stabilize after changes before verifying the
indications.
5. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-3, troubleshoot the tach sensor per the Beechcraft King Air 300 Series Maintenance
Manual.
6. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-3 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace the Signal Conditioner.
c. Replace GEA 2.
7. If no other EIS gauge tests are needed, reconnect and safety the J105 connector and
reinstall the engine cowling(s).
Test Point (Hz)
Indication (%)
0
0.0 ± 0.3
70 ± 1
100.0 ± 0.3
Table 7-3, N1 Indication Test Points
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7.4.4.4
Prop Tach N2 Functional Check
Required test equipment:
Test Equipment
Make/Requirement
Signal Generator
0-10Vdc / 0 – 1k Hz
If the left engine gauge needs to be tested, perform the following:
1. Ensure that Prop Sync switch indicator located on the instrument panel is not depressed.
2. Disconnect the J102 firewall connector.
3. Apply external power to aircraft and start the G1000 system in normal mode.
4. Inject a 2.5Vrms sine wave signal into the No. 1 TACH-GEN Adapter by connecting the
Signal Generator to the left engine firewall connector-pins J102-W (HI) and J102-X (LO).
5. Allow five seconds for the input signal to stabilize after changes before verifying the
indications.
6. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-4, troubleshoot the tach sensor per the Beechcraft King Air 300 Series Maintenance
Manual.
7. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-4 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace the Signal Conditioner.
c. Replace GEA 1.
8. If no other EIS gauge tests are needed, reconnect and safety the J102 connector and
reinstall the engine cowling(s).
If the right engine gauge needs to be tested, perform the following:
1. Ensure that Prop Sync switch indicator located on the instrument panel is not depressed.
2. Disconnect the J103 firewall connector.
3. Apply external power to aircraft and start the G1000 system in normal mode.
4. Inject a 2.5Vrms sine wave signal into the No. 2 TACH-GEN Adapter by connecting the
Signal Generator to the left engine firewall connector-pins J103-W (HI) and J103-X (LO).
5. Allow five seconds for the input signal to stabilize after changes before verifying the
indications.
6. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-4, troubleshoot the tach sensor per the Beechcraft King Air 300 Series Maintenance
Manual.
7. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-4 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace the Signal Conditioner.
c. Replace GEA 2.
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8. If no other EIS gauge tests are needed, reconnect and safety the J103 connector and
reinstall the engine cowling(s).
Test Point (Hz)
Indication (RPM)
0.00
0 ± 30
66 ± 1
1600 ± 30
Table 7-4, N2 Indication Test Points
7.4.4.5
Fuel Flow Indication Functional Check
Required test equipment.
Name
Requirement
Decade Box or equivalent
device
0-1k ohms
Signal Generator
0-10Vdc / 0 – 1k Hz
If the left engine gauge needs to be tested, perform the following:
1. Disconnect the J104 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a 1000 ± 10Ω resistance into the Signal Conditioner by connecting the Decade
box to left engine firewall connector-pins J104-E and J104-F.
4. Inject a 25mV P-P sine wave signal into the Signal Conditioner by connecting the Signal
Generator to the left engine firewall connector-pins J104-Y (HI) and J104-Z (LO).
5. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-5, troubleshoot the fuel flow sensor per the Beechcraft King Air 300 Series
Maintenance Manual.
6. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-5 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace the Signal Conditioner.
c. Replace GEA 1.
7. If no other EIS gauge tests are needed, reconnect and safety the J104 connector and
reinstall the engine cowling(s).
If the right engine gauge needs to be tested, perform the following:
1. Disconnect the J105 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a 1000 ± 10Ω resistance into the Signal Conditioner by connecting the Decade
box to left engine firewall connector-pins J105-E and J105-F.
4. Inject a 25mV P-P sine wave signal into the Signal Conditioner by connecting the Signal
Generator to the left engine firewall connector-pins J105-Y (HI) and J105-Z (LO).
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5. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-5, troubleshoot the fuel flow sensor per the Beechcraft King Air 300 Series
Maintenance Manual.
6. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-5 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace the Signal Conditioner.
c. Replace GEA 2.
7. If no other EIS gauge tests are needed, reconnect and safety the J105 connector and
reinstall the engine cowling(s).
Test Point (Hz)
Indication (PPH)
0
0±2
140
100 ± 10
561
400 ± 10
841
600 ± 10
1122
800 ± 10
Table 7-5, Fuel Flow Indication Test Points
7.4.4.6
Oil Pressure Indication Functional Check
Required test equipment:
Name
Requirement
Calibrated DC Power Source
0-10 VDC
If the left engine gauge needs to be tested, perform the following:
1. Disconnect the J104 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a DC voltage into the GEA 1 by connecting the DC power source to the left engine
firewall connector-pins J104-A (LO) and J104-B (HI).
4. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-6, troubleshoot the oil pressure sensor per the Beechcraft King Air 300 Series
Maintenance Manual.
5. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-6 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace GEA 1.
6. Turn off the G1000 system and remove external power from the aircraft.
7. If no other EIS gauge tests are needed, reconnect and safety the J104 connector and
reinstall the engine cowling(s).
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If the right engine gauge needs to be tested, perform the following:
1. Disconnect the J105 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a DC voltage into the GEA 1 by connecting the DC power source to the left engine
firewall connector-pins J105-A (LO) and J105-B (HI).
4. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-6, troubleshoot the oil pressure sensor per the Beechcraft King Air 300 Series
Maintenance Manual.
5. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-6 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace GEA 2.
6. Turn off the G1000 system and remove external power from the aircraft.
7. If no other EIS gauge tests are needed, reconnect and safety the J105 connector and
reinstall the engine cowling(s).
Test Point (VDC)
Indication (PSI)
0.00 ± 0.10
0±4
1.75 ± 0.10
70 ± 4
2.50 ± 0.10
100 ± 4
3.75 ± 0.10
150 ± 4
5.00 ± 0.10
200 ± 4
Table 7-6, Oil Pressure Test Points
7.4.4.7
Oil Temperature Indication Functional Check
Required test equipment:
Name
Requirement
Decade box or equivalent
device
0-1k ohms
If the left engine gauge needs to be tested, perform the following:
1. Disconnect the J104 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a resistance into GEA 1 by connecting the Decade box to the left engine firewall
connector-pins J104-W and J104-X.
4. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-7, troubleshoot the oil temperature sensor per the Beechcraft King Air 300 Series
Maintenance Manual.
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5. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-7 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace GEA 1.
6. Turn off the G1000 system and remove external power from the aircraft.
7. If no other EIS gauge tests are needed, reconnect and safety the J104 connector and
reinstall the engine cowling(s).
If the right engine gauge needs to be tested, perform the following:
1. Disconnect the J105 firewall connector.
2. Apply external power to aircraft and start the G1000 system in normal mode.
3. Inject a resistance into GEA 2 by connecting the Decade box to the left engine firewall
connector-pins J105-W and J105-X.
4. If the test input shows a correct gauge reading within the Indication tolerance in Table
7-7, troubleshoot the oil temperature sensor per the Beechcraft King Air 300 Series
Maintenance Manual.
5. If the test input shows an incorrect gauge reading outside the Indication tolerance in
Table 7-7 perform the following:
a. Check gauge circuit wiring for faults.
b. Replace GEA 2.
6. Turn off the G1000 system and remove external power from the aircraft.
7. If no other EIS gauge tests are needed, reconnect and safety the J105 connector and
reinstall the engine cowling(s).
Test Point (Ohms)
Indication (C)
75
-46 ± 3
90
0±3
108
50 ± 3
Table 7-7, Oil Temperature Test Points
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7.5
GTX 335R, GTX 345R, GTX 33( ), or GTX 3000 Transponder
Original GTX is Reinstalled
No software or configuration loading is required if the removed GTX 335R, GTX 345R, GTX 33,
or GTX 3000 is re-installed. This does not include units that were returned for repair as their
software and configuration files are deleted during the repair testing process. Continue to GTX
335R, GTX 345R, GTX 33, or GTX 3000 Test Section 7.5.4.
Original GTX Installed in Opposite Locations for Troubleshooting
No software loading is required if the original GTX #1 and GTX #2 are installed in opposite
locations. Continue to Transponder Configuration Section 7.5.3.
New, Repaired or Exchange GTX is Installed
If a new, repaired or exchange GTX 335R, GTX 345R, GTX 33( ), or GTX 3000 is installed, the
correct software and configuration files must be loaded to the unit. See Section 7.5.1.
7.5.1
LRU Replacement Procedure GTX1 or GTX2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GTX1 or GTX2, whichever was replaced in the LRU
dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.5.2.
16. If there are no red-Xs or system alerts, continue to Section 7.5.3.
7.5.2
Legacy Replacement Procedure GTX1 or GTX2 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
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4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “06) Garmin Transponders” and press ENT key on
PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed transponder combination. Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Use the large FMS knob to scroll to GTX 1 or GTX 2 whichever was replaced.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press “Load” softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
13. Acknowledge the prompt by pushing the ENT key.
14. Deactivate the curser.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
20. If there are no red-Xs or system alerts, continue to Section 7.5.3.
7.5.3
Transponder Configuration
1. If not applied, apply power to the G1000 system and put all displays into config mode.
2. On PFD1, select the AIRCRAFT CONFIGURATION page.
3. For GTX 33 unit replacement only, press the Set GTX # softkey for the unit replaced and
acknowledge the PFD1 prompt by pressing the ENT key. For GTX 3000 units only,
press the SET GTX softkey and acknowledge the PFD1 prompt by pressing the ENT
key. GTX 335R and 345R units automatically save the registration number, no action is
needed for these units.
4. After completing transponder configuration, deactivate the cursor.
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Figure 7-5, Aircraft Registration
7.5.4
GTX 335R, GTX 345R, GTX 33( ), or GTX 3000 Test
Operation of the GTX 335R, GTX 345R, GTX 33() or GTX 3000 Mode-S transponder is
accomplished using PFD 1, PFD 2 or the MFD. Refer to G1000 King Air 300 Series Cockpit
Reference Guide, listed in Table 1-1, for basic operation.
The integrated transponder/altitude reporting system must be verified in accordance with Title
14 of the Code of Federal Regulations (14 CFR) §§ 91.411 and 91.413, every 24 calendar
months, or any time the transponder is removed. This test requires the use of a Mode S ramp
generator. Specific instructions for operating the ramp tester are contained in the applicable
operator's manual. Refer to 14 CFR Part 43 Appendices E and F for testing criteria.
Note that for GTX 33D or GTX 3000 units, the aircraft must be put on jacks to simulate an in-air
condition in order to test the Mode S diversity transmission channel isolation.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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7.6
GSU 75B ADAHRS
Original GSU unit is Reinstalled
No software or configuration loading is required if the removed GSU 75B is re-installed in the
same location. This does not include units that were returned for repair as their software and
configuration files are deleted during the repair testing process. Perform a pitot - static system
leak check and continue to Section 9.
Original GSU unit Installed in Opposite Locations for Troubleshooting
No software loading is required if the original GSU #1 and GSU #2 are installed in opposite
locations. Perform a pitot - static system leak check and continue to Section 9.
New, Repaired or Exchange GSU unit is Installed
If a new, repaired or exchange GSU unit is installed, the correct software and configuration files
must be loaded to the unit.
New GSU 75B Configuration Module is Installed
The correct configuration files must be loaded if the GSU75B configuration module has been
replaced.
7.6.1
LRU Replacement Procedure GSU1 or GSU2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GRS1 or GRS2 in the LRU dropdown box, whichever was
replaced.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Select GDC 1 or GDC 2 in the LRU dropdown box, whichever was replaced.
11. Press the CHK All softkey.
12. Press the Load softkey.
13. Press ENT to acknowledge the process was complete.
14. Deactivate the curser.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.6.2.
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20. If there are no red-Xs or system alerts, continue to Section 7.7.3 for the air data portion
of the GSU and Section 7.10.5 for the AHRS portion of the GSU.
7.6.2
Legacy Replacement Procedure GSU1 or GSU2 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “04) AHRS – Air Data” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air- GSU 75B ADAHRS and GMU 44 Magnetometer. Press ENT key
on PFD1.
7. Press the CLR ALL softkey.
8. Use the large FMS knob to scroll to GSU 1 or GSU 2 whichever was replaced.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press “Load” softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
13. Acknowledge the prompt by pushing the ENT key.
14. Deactivate the curser.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
21. If there are no red-Xs or system alerts, continue to Section 7.7.3 for the air data portion
of the GSU and Section 7.10.5 for the AHRS portion of the GSU.
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7.7
GDC 7400 Air Data
Original GDC unit is Reinstalled
No software or configuration loading is required if the removed GDC 7400 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Perform a pitot - static system leak check and
continue to Section 9 if no other service is performed.
Original GDC unit Installed in Opposite Locations for Troubleshooting
No software loading is required if the original GDC #1 and GDC #2 are installed in opposite
locations. Perform Section 7.7.3 if no other service is performed.
New, Repaired or Exchange GDC unit is Installed
If a new, repaired or exchange GDC unit is installed, the correct software and configuration files
must be loaded to the unit.
7.7.1
LRU Replacement Procedure GDC 1 or GDC 2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GDC1 or GDC 2, whichever was replaced in the LRU
dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.7.2.
16. If there are no red-Xs or system alerts, continue to Section 7.7.3.
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7.7.2
Legacy Replacement Procedure GDC 1 or GDC 2 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “04) AHRS – Air Data” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed GDC. Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Use the large FMS knob to scroll to GDC 1 or GDC 2 whichever was replaced.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press “Load” softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
13. Acknowledge the prompt by pushing the ENT key.
14. Deactivate the curser.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
20. If there are no red-Xs or system alerts, continue to Section 7.7.3.
7.7.3
Air Data Test (GSU 75B or GDC 7400)
The G1000 system must be maintained in accordance with the G1000 System Maintenance
Manual listed in Table 1-2 and appropriate regulations. When the GDC unit is tested in
accordance with 14 CFR Part 43, Appendix E, note the following exceptions:
•
For paragraph (b)(1)(i) Scale Error, use Table 7-8 of this section instead of Appendix E,
Table I
•
Do not perform paragraph (b)(1)(iv) Friction
•
Do not perform paragraph (b)(1)(vi) Barometric Scale Error
The following Air Data Test is to be performed in addition to or in conjunction with any other
regulated tests. This test must be performed on both pilot and copilot systems with a calibrated
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Air Data Test Set (ADTS) with a combined accuracy/repeatability specification of less than ±20
feet for the test altitude range.
1. Perform pitot static system leak check of each system as described in the King Air 300
Series Maintenance Manual, 34-00-00, with the following changes:
a. For the pitot leak check, set the air data test unit to an indicated airspeed of 200
knots with the static system vented to ambient pressure conditions (ground). Pitot
leak rate is not to exceed 1 knot in 1 minute.
b. For the static leak check, set the air data test set to 30,000 feet and an indicated
airspeed of 120 knots. Static leak rate is not to exceed 300 feet in 1 minute.
2. Connect the pitot/static tester to the aircraft left and right pitot and static ports. Note that
the standby altimeter and airspeed indicator are connected to the copilot side pitot and
static lines.
3. Verify that the PFD1 altimeter baro setting is set to 29.92 in Hg (1013.25 mb).
4. Start PFD1 in configuration mode and navigate to the GRS page. The values for altitude
and airspeed are shown on the AHRS/AIR DATA INPUT table as B ALT and IAS for
both AIR DATA 1 and AIR DATA 2.
5. Simulate the altitudes and airspeeds for each condition shown in Table 7-8. Wait for
ADTS to report that target values have been achieved.
6. On Table 7-8, record the altitude (B ALT) displayed on PFD1 for AIR DATA 1 and
AIR DATA 2 for each condition.
7. On Table 7-8, record the airspeed (IAS) displayed on PFD1 for AIR DATA 1 and
AIR DATA 2 for each condition.
8. Verify that the indicated altitudes and airspeeds are within allowable tolerances.
9. File the results with the aircraft maintenance records.
If either the pilot or copilot air data system does not meet the tolerances specified, have
maintenance checks performed on the air data system or the pitot/static system.
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Table 7-8, Air Data System Test
Test
Point
Altitude (FT)
Nominal
Altitude
ALT
AS
0
0
0
99
0
132
0
198
0
50
1000
50
2000
80
4000
80
8000
260
8000
10000
120
10000
11000
120
11000
13000
150
13000
14000
150
14000
16000
180
16000
18000
210
18000
19000
138
18983
19000
162
18971
19000
185
18958
19000
209
18947
19000
221
18947
19000
233
18947
0
0
0
1000
2000
4000
8000
8000
Airspeed (KIAS)
AIR DATA 1
AIR DATA 2
AIR DATA 1
AIR DATA 2
Tolerance
Tolerance
Tolerance
Tolerance
Actual
+/-20
Actual
+/-20
Actual
+/-2
Actual
+/-2
+/-20
+/-20
+/-2
+/-2
+/-20
+/-20
+/-2
+/-2
+/-20
+/-20
+/-2
+/-2
+/-20
+/-20
+/-2
+/-2
+/-25
+/-25
+/-2
+/-2
+/-25
+/-25
+/-2
+/-2
+/-30
+/-30
+/-2
+/-2
+/-30
+/-30
+/-2
+/-2
+/-30
+/-30
+/-2
+/-2
+/-35
+/-35
+/-2
+/-2
+/-40
+/-40
+/-2
+/-2
+/-40
+/-40
+/-2
+/-2
+/-45
+/-45
+/-2
+/-2
+/-45
+/-45
+/-2
+/-2
+/-47
+/-47
+/-2
+/-2
+/-47
+/-47
+/-2
+/-2
+/-47
+/-47
+/-2
+/-2
+/-47
+/-47
+/-2
+/-2
+/-47
+/-47
+/-2
+/-2
+/-47
+/-47
+/-2
+/-2
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Air Data System Test (Continued)
Test
Point
ALT
AS
Altitude (FT)
Nominal
Altitude
29000
111
28999
29000
130
28982
29000
150
28967
29000
169
28953
29000
178
28946
29000
188
28937
29000
196
28928
35000
97
35016
35000
114
34996
35000
130
34978
35000
147
34961
35000
156
34953
35000
164
34946
35000
171
34939
Airspeed (KTS)
AIR DATA 1
AIR DATA 2
AIR DATA 1
AIR DATA 2
Tolerance
Tolerance
Tolerance
Tolerance
Actual
+/-72
Actual
+/-72
Actual
+/-2
Actual
+/-2
+/-72
+/-72
+/-2
+/-2
+/-72
+/-72
+/-2
+/-2
+/-72
+/-72
+/-2
+/-2
+/-72
+/-72
+/-2
+/-2
+/-72
+/-72
+/-2
+/-2
+/-72
+/-72
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
+/-87
+/-87
+/-2
+/-2
Aircraft S/N: _____________________
Date: __________________
Operator: __________________
ADTS
ADAHRS1/ADC1
ADAHRS2/ADC2
Model: __________
Model: __________
Model: _______________________
P/N: ___________________
P/N: ____________________
S/N: _______________________
S/N: ___________________
S/N: ____________________
Cal. Date: _____________________
Cal. Date: ______________
Cal. Date: ________________
Make: _______________________
Leak Check Static System at 30,000 ft, 120 kts (pass if <300 ft in 1 min)
Pilot: _____________ Feet/Min
Copilot: ___________ Feet/Min
Leak Check Pitot System at 200 kts (pass if <1 KIAS in 1 min)
Pilot: _____________ KIAS/Min
Copilot: ___________ KIAS/Min
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7.7.4
Static Port Vertical Speed (Rate of Climb) Test
1. Command ADTS to change the altitude at the rates shown in the table below.
2. Wait for ADTS to report that target rates have been achieved.
3. Verify that the Rate of Climb reported by the Vertical Speed field on PFD1 and PFD2 are
within the tolerances specified in Table 7-9.
Table 7-9, Vertical Speed Table
Vertical Speed, feet/minute Allowed tolerance, ±feet/minute
2000
100
1000
50
500
45
200
45
0
N/A (No VS Display)
-200
45
-500
45
-1000
50
-2000
100
7.7.5
OAT Probe Check
1. Ensure on-side sensors for PFD1 and PFD2.
2. Ensure the outside air temperature (OAT) probes and a calibrated thermometer stabilize
at ambient temperature.
3. Verify that the OAT measurement shown on PFD1 and PFD2, in degrees Celsius,
indicate within 2 °C of the ambient temperature as measured by the calibrated
thermometer.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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7.8
GRS 77 or 7800 AHRS and GMU 44 Magnetometer
Original GRS is Reinstalled
If the original GRS is reinstalled, then no software loading is required. This does not include
units that were returned for repair as their software and configuration files are deleted during the
repair testing process.
If the GRS rack was not removed or loosened, continue to the GRS/GMU Test Section 7.10.5.
If the GRS rack was removed or loosened, continue to the GRS/GMU Calibration Procedures
Section 7.10.
Original GRS is installed in Opposite Location for Troubleshooting
If the original GRS #1 and GRS #2 are installed in opposite locations (GRS #1 and GRS #2 in
opposite unit racks), no software loading is required.
If the GRS rack(s) was not removed or loosened, continue to the GRS/GMU Test Section
7.10.5.
If the GRS rack(s) was removed or loosened, continue to the GRS/GMU Calibration Procedures
Section 7.10.
New, Repaired or Exchange GRS is Installed
If a new, repaired or exchange GRS is installed, then software must be loaded.
New GRS Configuration Module is Installed
If the GRS configuration module is replaced, no software loading is required. Continue to the
GRS/GMU Calibration Procedures Section 7.10.
7.8.1
LRU Replacement Procedure GRS1 or GRS2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GRS1 or GRS2, whichever was replaced in the LRU
dropdown box.
7. Verify all boxes are checked. If they are not checked, press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
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15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.8.2.
16. If there are no red-Xs or system alerts and the GRS rack(s) were not removed or
loosened, continue to the GRS/GMU Test Section 7.10.5.
17. If there are no red-Xs or system alerts and the GRS rack(s) was removed or loosened,
continue to the GRS/GMU Calibration Procedures Section 7.10.
7.8.2
Legacy Replacement Procedure GRS1 or GRS2 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
6. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
7. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “04) AHRS – Air Data” and press ENT key on PFD1.
8. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed GRS. Press ENT key on PFD1.
9. Press the CLR ALL softkey.
10. Press “Load” softkey.
11. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
12. Acknowledge the prompt by pushing the ENT key.
13. Deactivate the curser.
14. Scroll to the Configuration Manager page.
15. Press the CNFM CFG softkey.
16. Select ok when prompted to “Confirm configuration as expected configuration”
17. Power cycle the system. Verify there are no red-Xs or system alerts.
18. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
17. If there are no red-Xs or system alerts and the GRS rack(s) were not removed or
loosened, continue to the GRS/GMU Test Section 7.10.5.
18. If there are no red-Xs or system alerts and the GRS rack(s) was removed or loosened,
continue to the GRS/GMU Calibration Procedures Section 7.10.
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7.9
GMU 44 Magnetometer
Original GMU 44 is Reinstalled
If the original GMU 44 is reinstalled, then no software loading is required. This does not include
units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Continue to the GRS/GMU Test Section 7.10.5.
Original GMU 44 is Installed in Opposite Location for Troubleshooting
If the original GMU #1 and GMU #2 are installed in opposite locations (GMU #1 and GMU #2 in
opposite unit racks), no software loading is required. However, performing the Magnetometer
Calibration Procedure is required. Continue to the GRS/GMU Magnetic Calibration Section
7.10.3.
New, Repaired or Exchange GMU 44 is Installed
If a new, repaired or exchange GMU 44 is installed, then software must be loaded.
7.9.1
LRU Replacement Procedure GMU1 or GMU2
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GMU1 or GMU2, whichever was replaced in the LRU
dropdown box.
7. Verify all boxes are checked. If they are not checked, press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.9.2.
16. If there are no red-Xs or system alerts, continue to Section 7.10.
7.9.2
Legacy Replacement Procedure GMU1 or GMU2 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
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4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “04) AHRS – Air Data” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed GRS. Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Scroll to GMU1 or 2.
9. Highlight the Software box.
10. Press the ENT key.
11. Press “Load” softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….”COMPLETE” in the summary box.
13. Acknowledge the prompt by pushing the ENT key.
14. Deactivate the curser.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
20. If there are no red-Xs or system alerts, continue to Section 7.10.
7.10
GSU/GRS/GMU Calibration Procedures
GSU/GRS/GMU Recalibration Criteria
The following calibration procedures are provided for the GRS and GMU 44:
•
Pitch/Roll Offset: (Procedure A1, PROVIDED IN SECTION 7.10.1)
•
Magnetometer Calibration: (Procedure B, PROVIDED IN SECTION 7.10.3)
•
Engine Run-Up Vibration Test: (Procedure D, PROVIDED IN SECTION 7.10.4)
•
Magnetometer Interference Test: (Procedure E, PROVIDED IN SECTION 5.17.4)
Follow the steps given for each procedure on-screen at the GRS/GMU CALIBRATION page.
Note that the CALIBRATE command cannot be selected and activated until the installer
acknowledges all required steps have been carried out by pressing the ENT key on each step.
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Table 7-10, Required GRS/GMU Calibrations
Calibrations Required
Procedure A1:
GSU 75B,
Procedure B:
Procedure D:
GRS 77, or
GSU/GRS/GMU Engine Run-up
Condition
GRS 7800
Magnetic
Vibration
Pitch/Roll
Calibration
Test
Offset
Either GMU 44 was removed and
reinstalled. (no change in serial number)
GMU 44 was replaced with new unit.
(New serial number)
GRS AHRS or GSU ADAHRS was removed
and/or replaced. The mounting tray was
NOT removed and the mounting tray bolts
were NOT loosened.
GRS AHRS or GSU ADAHRS was removed
and/or replaced. The mounting tray WAS
removed and/or mounting tray bolts WERE
loosened.
GRS AHRS or GSU ADAHRS Configuration
Module was replaced.
None Required.
Continue to GSU/GRS/GMU Test Section.
X
None Required.
Continue to GSU/GRS/GMU Test Section.
X
X
X
X
X
X
7.10.1 Procedure A1: GSU 75B, GRS 77, or GRS 7800 Pitch/Roll Offset
Calibration
This procedure must be performed for both GSU/GRS units installed in the aircraft. This first
procedure must be carried out with the engine off.
1. Level the aircraft to within ±0.25° of zero pitch and zero roll using a digital level. (Follow
instructions in King Air 300 Series Maintenance Manual, listed in Table 1-1, for leveling)
2. Start PFD 1 in Configuration mode.
3. Go to the GRS Page Group and select the GRS/GMU Calibration page at the PFD. This
page is protected and the following softkey password must be entered at the PFD to
continue:
•
9
•
10
•
11
•
12 (Far Right softkey)
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Figure 7-6, GRS/GMU Calibration, Pitch/Roll Offset
NOTE
On the calibration pages, “GRS” includes GRS and GSU units.
4. Ensure that the GRS 1 is selected in the SELECT GRS UNIT window on the PFD.
5. Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH /
ROLL OFFSET.
6. Press the ENT key.
7. Use the cursor to highlight Step 1 in the BEFORE CALIBRATION window.
8. Follow the checklist items displayed on the PFD and press the ENT key as each step is
completed or confirmed.
9. When the CALIBRATE field is blinking, press the ENT button to begin the procedure.
10. After several seconds, a new checklist appears in the lower half of the PFD. Press the
ENT key as each step is confirmed. When the CONFIRM AIRCRAFT IS LEVEL field is
blinking, press the ENT key to continue.
11. The result of the pitch/roll offset compensation is displayed on the PFD. If successful,
the AHRS records the required pitch and roll offsets, informs the operator of a successful
conclusion and returns to normal operation.
12. Press the ENT key on the PFD to conclude this procedure for GRS 1.
13. Repeat steps 4 through 12 for GRS 2.
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7.10.2 Compass Rose Evaluation of Magnetic Disturbances for Magnetometer
Calibration Procedure (Optional)
NOTE
The Magnetometer Calibration Procedure that follows in Section 7.10.3
(Calibration Procedure B) must be carried out at a site that is
determined to be free of magnetic disturbances. If it is unsure whether
the site is ‘clean’, the technician should verify that the site is ‘clean’ by
following the guidance provided in Section 7.10.2. The technician may
skip Section 7.10.2 if the site condition is acceptable.
Typically, a compass rose is an acceptable location to perform the
magnetometer calibration procedure. However, because not all
compass roses are well maintained, even an existing compass rose
should be regularly evaluated using the method described here to
determine if it is free of magnetic disturbances. If evaluation of an
existing compass rose indicates that magnetic disturbances are
present, then an alternative location must be found to perform the
Magnetometer Calibration Procedure.
A G1000-equipped airplane that has completed the pitch/roll offset compensation procedure
(Procedure A-1, Section 7.10.1) can be used to evaluate a candidate site for magnetic
disturbances and determine whether it is a suitable location to perform the magnetometer
calibration procedure. The magnetometer calibration procedure itself contains the logic to
simultaneously survey the location for magnetic cleanliness while it is computing the
magnetometer calibration parameters.
In order to evaluate a candidate site, the Magnetometer Calibration Procedure must be
performed twice: once turning clockwise around the site, and once turning counter-clockwise.
Both times, the procedure should be conducted as described in Section 7.10.3 of this
document, with the exception of the direction of turns around the site.
NOTE
Although Section 7.10.3 indicates that the Magnetometer Calibration
Procedure should be performed by making a series of clockwise turns
around the site, the procedure can also be performed by making
counter-clockwise turns for the purpose of evaluating the site for
magnetic disturbances.
If the PFD displays the “CALIBRATION SUCCESSFUL / SITE IS CLEAN” message upon
completion of the Magnetometer Calibration Procedure in each clockwise and counterclockwise direction, then the candidate site is sufficiently free of magnetic disturbances and is
acceptable for performing the Magnetometer Calibration Procedure. It is important to obtain
successful result in both the clockwise and counter-clockwise directions to ensure that the
magnetometer sweeps over a large enough area at the candidate site.
If the PFD displays either the “MAG FIELD AT SITE NOT UNIFORM” or “MAG FIELD AT SITE
DIFFERS FROM IGRF MODEL” message upon completion of the Magnetometer Calibration
Procedure in either of the two directions, then the site contains magnetic disturbances that are
too large.
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7.10.3 Procedure B: GSU 75, GRS 77, or GRS 7800 and GMU 44 Magnetic
Calibration
NOTES
Procedure A-1 (Section 7.10.1) must first be successfully accomplished before
performing Procedure B, only for situations where the GSU/GRS was replaced
with a new unit.
On the calibration pages, “GRS” refers to whatever GRS or GSU unit is
installed.
1. Start the aircraft engine following the procedures referenced in the appropriate King Air
AFM or AFMS as shown in the General Arrangement drawing, listed in Table 1-1.
2. After aircraft engine startup, taxi the aircraft to a properly calibrated compass rose.
3. At the compass rose, align the aircraft to a heading of magnetic north (±5°).
CAUTION
Calibration Procedure B must be carried out on a compass rose in order to
guarantee measurements free of environmental magnetic disturbances.
Attempting to carry out this maneuver on a typical ramp area may not yield a
successful calibration. The accuracy of the AHRS/ADAHRS cannot be
guaranteed if this calibration is not performed on a magnetically clean compass
rose or equivalent. If the compass rose condition is not known, it is
recommended that the technician follow the guidance in Section 7.10.2.
NOTE
This procedure provides instructions for calibrating both GRS AHRS or both
GSU ADAHRS separately. It is acceptable to calibrate both GRS AHRS or
both GSU ADAHRS simultaneously by putting both PFD 1 and PFD 2 in
configuration mode and following the procedure below, using PFD 1 to
calibrate GSU/GRS 1 and PFD 2 to calibrate GSU/GRS 2.
4. Restart PFD 1 in configuration mode.
5. Go to the GRS Page Group on the PFD.
6. Select the GRS/GMU Calibration page and enter the following softkey password:
•
9
•
10
•
11
•
12 (far right softkey)
7. Use the FMS small knob to highlight GRS/GSU for calibration and press the ENT key.
8. Using the FMS small knob, select MAGNETOMETER. Press the ENT button.
9. Use the cursor to highlight the first step in the BEFORE CALIBRATION window.
10. Follow the checklist items displayed on the PFD and press the ENT key as each one is
completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to
begin the procedure.
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11. The PFD display advises the operator when to turn the aircraft, when to stop, and when
to turn again.
12. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 25° to 30° of
turn from the last heading, the PFD display advises the operator to stop the aircraft.
NOTE
Due to the difficulties in executing smooth, accurate turns the PFD may
incorrectly interpret a station and instruct to “HOLD POSITION” prior to full
completion of a 30° turn. If this scenario is encountered, it is best for the
operator to ignore the “HOLD POSITION” command and instead use outside
references to complete the approximate 30° turn. Instead of using the PFD
instruction to turn as a real-time indication of when to turn, simply judge the 30°
(±5°) turn increments of the aircraft by using the compass rose radials.
Dwelling at these 30° increments for the time recommended by the PFD should
result in successful calibration.
13. The PFD guides the operator to dwell at multiple headings around a complete circle.
NOTE
Due to high winds or excessive airframe vibration, the operator may encounter
a condition where the PFD restarts the 18-second countdown without full
completion of the previous countdown. If this is encountered more than once
for a given station, the operator should begin turning to the next station
(approximately 30°). A minimum of 2 successful stations per quadrant is
required, where a successful station is a full 18-second countdown followed by
instruction to move. Ensure that at least 2 stations per quadrant are completed.
Thus, it may sometimes be required to dwell at a station after a countdown
restart.
A maximum of 30 stations is allowed for the entire calibration
procedure. If too many countdown restarts are encountered, the calibration
will fail with the message, “TOO MANY STATIONS.”
14. Repeat the turn-and-stop process until the PFD advises that a successful calibration is
complete. The GRS AHRS/GSU ADAHRS then enters its normal operational mode.
Press the ENT button on the PFD to conclude this procedure.
15. Repeat steps 7 through 14 for GSU/GRS 2.
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7.10.4 Procedure D: Engine Run-Up Vibration Procedure
NOTES
On the calibration pages, “GRS” refers to whatever GRS or GSU unit is
installed.
Calibration Procedure D is performed in order to guarantee that the
ADAHRS/AHRS mounting is sufficiently rigid and insensitive to vibration. This
procedure must be performed for both GSU/GRS units installed in the aircraft.
Calibration Procedures A1 and B (Sections 7.10.1 and 7.10.3 respectively) are
not required prior to this procedure.
Figure 7-7, GRS/GMU Calibration, Engine Run-Up
1. Restart PFD 1 in configuration mode.
2. Use the FMS small knob to highlight GRS 1 for calibration and press the ENT key. The
SELECT PROCEDURE field is not blinking.
3. Initiate the AHRS engine run-up vibration test procedure by performing the following
steps:
a) Select the ENGINE RUN-UP TEST procedure and press the ENT key.
b) Follow the checklist items displayed on the PFD, and press the ENT key as each
one is completed or confirmed. When the CALIBRATE field is blinking, press the
ENT key to begin the procedure.
4. The PFD display instructs the operator to gradually increase power from idle to full
throttle and back to idle over a period of 2-4 minutes.
5. When the operator has completed the engine run-up and the engine is back to an idle
setting, press the ENT key to indicate that the process is complete. When this is done,
the TEST COMPLETE field stops blinking.
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6. The PFD informs the operator if the installation has passed or failed the vibration test. If
the test fails, the specific measurements causing the failure are identified and associated
numeric values are displayed on the PFD.
NOTE
Should a failure occur, the technician may perform the Engine Run-up test up
to 3 times successively before corrective action must be taken. If the test does
not pass after three attempts, then the installation should not be considered
reliable until the source of the vibration problem is identified and remedied. In
the event of repeated failure of the engine run-up test, record the values that
are reported to be out of range for future reference.
The following are potential causes for failure of the engine run-up test:
a) Vibration motion of GSU/GRS and/or GMU44 caused by neighboring
equipment and/or supports.
b) Mounting screws and other hardware for GSU/GRS and/or GMU44 not
firmly attached.
c) GSU/GRS connector not firmly attached to unit.
d) Cabling leading to GSU/GRS or GMU44 not firmly secured to supporting
structure.
e) An engine / propeller that is significantly out of balance.
7. Press the ENT key on the PFD to conclude this procedure
8. Repeats steps 2 through 7 for GSU/GRS 2 then the aircraft can be taxied back and the
engine can be shut down for final testing. Continue to Section 7.10.5.
7.10.5 GSU/GRS/GMU Test
Start the displays in normal mode. The ADAHRS/AHRS attitude and heading information
displayed should become valid within 1 minute of power-up as shown in Figure 7-8 if at least
one GPS receiver has a valid position. If GPS is unavailable, the ADAHRS/AHRS initialization
may take up to 2 minutes.
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Figure 7-8, Normal Mode AHRS Check
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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7.11
GDL 69A or GDL 69A SXM Data Link
Original GDL 69A/69A SXM is Reinstalled
No software or configuration loading is required if the removed GDL 69A is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GDL 69A/69A SXM Test Section
7.11.3.
New, Repaired or Exchange GDL 69A/69A SXM is Installed
If a new, repaired or exchange GDL 69A/69A SXM is installed, the correct software and
configuration files must be loaded to the unit, then the SiriusXM Satellite Radio subscription
must be reactivated. See the SiriusXM Activation Instructions listed in Table 1-2.
7.11.1 LRU Replacement Procedure
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GDL69 in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.11.2.
16. If there are no red-Xs or system alerts, continue to Section 7.11.3.
7.11.2 Legacy Replacement Procedure GDL69 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “Connext – SXM” and press ENT key on PFD1.
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6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed GDL69. Press ENT key on PFD1.
7. Press the CLR ALL softkey.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
NOTE
If the software load fails, cycle power to the GDL 69A only and confirm
that the software part number and version are updated in the DATA
window on the MFD. Then, press ENT button on the PFD to check the
GDL 69A SXM SOFTWARE and CONFIGURATION check boxes and
press LOAD softkey again to resume the software update.
10. Press ENT key on PFD1 to acknowledge upload complete.
11. Deactivate cursor.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
17. If there are no red-Xs or system alerts, continue to Section 7.11.3.
7.11.3 GDL 69A Test
If a SiriusXM Satellite Radio subscription has already been activated for the GDL 69A/69A
SXM, then power up the G1000 and go to the Aux – Information page and verify that the GDL
69A/69A SXM is working properly. Refer to the Cockpit Reference Guide, listed in Table 1-2,
for details on Sirius XM Radio weather and music operation.
If the GDL 69A/69A SXM is replaced (new unit), the owner must re-activate the subscription,
using the new GDL 69A/69A SXM’s Radio ID number(s). Refer to the GDL 69A/69A SXM
Satellite Radio Activation Instructions, listed in Table 1-2, for details on the activation process.
As a final operations check, make sure there are no MANIFEST errors shown on the PFD for
the GDL 69A/69A SXM.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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7.12
GSA 80 Servos
Original Servo(s) Reinstalled
No software loading is required if the removed servo(s) is re-installed. This does not include
units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Continue to the return-to-service checks in Section 9.
New, Repaired or Exchange Servo(s) Installed
If a new, repaired or exchange servo is installed, the correct software files and certification gains
must be loaded to the unit.
7.12.1 LRU Replacement Procedure GSA80 Servos
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select the installed GSA CTRL in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Select the installed GSA MON in the LRU dropdown box.
11. Press the CHK All softkey.
12. Press the Load softkey.
13. Press ENT to acknowledge the process was complete.
14. Deactivate the curser.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.12.2.
20. If there are no red-Xs or system alerts, continue to return to service checks in Section 9.
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7.12.2 Legacy Replacement Procedure GSA80 Servos (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “05) Autopilot” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
highlight the installed autopilot configuration. Press ENT key on PFD1.
7. Press the CLR ALL key.
8. Scroll to highlight the installed servo.
9. Highlight the software box and press the ENT key to check the box.
10. Scroll to highlight the installed servo cert line.
11. Highlight the software box and press the ENT key to check the box.
12. Press the Load softkey.
13. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
14. Press ENT key on PFD1 to acknowledge upload complete.
15. Deactivate cursor.
16. Scroll to the Configuration Manager page.
17. Press the CNFM CFG softkey.
18. Select ok when prompted to “Confirm configuration as expected configuration”
19. Power cycle the system. Verify there are no red-Xs or system alerts.
20. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
21. If there are no red-Xs or system alerts, continue to return to service checks in Section 9.
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7.13
GCU 477 FMS Controller
Original GCU 477 Reinstalled
No software or configuration loading is required if the removed GCU 477 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GCU 477 Test Section 7.13.3.
New, Repaired or Exchange GCU 477 Installed
If a new, repaired or exchange GCU 477 is installed, the correct software and configuration files
must be loaded to the unit. See Section 3.6 and then continue to the GCU 477 Test Section
7.13.3.
7.13.1 LRU Replacement Procedure GCU 477
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select the installed servo CTL in the LRU dropdown box.
7. Press the Load softkey.
8. Press ENT to acknowledge the process was complete.
9. Select the installed servo MON in the LRU dropdown box.
10. Press the Load softkey.
11. Press ENT to acknowledge the process was complete.
12. Deactivate the curser.
13. Scroll to the Configuration Manager page.
14. Press the CNFM CFG softkey.
15. Select ok when prompted to “Confirm configuration as expected configuration”
16. Power cycle the system. Verify there are no red-Xs or system alerts.
17. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.13.2.
18. If there are no red-Xs or system alerts, continue to Section 7.13.3.
7.13.2 Legacy Replacement Procedure GCU 477 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
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5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “01) Baseline” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air 200-300 Series Baseline Load. Press ENT key on PFD1.
7. Press the CLR ALL key.
8. Scroll to highlight GMC.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press the Load softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
13. Press ENT key on PFD1 to acknowledge upload complete.
14. Deactivate cursor.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
20. If there are no red-Xs or system alerts, continue to Section 7.13.3.
7.13.3 GCU 477 Test
Perform the following key and knob presses and knob rotations on the GCU 477, and verify the
actions on the MFD.
1. Rotate the large FMS knob and verify that the page groups change.
2. Rotate the small FMS knob and verify that the pages change within the page groups.
3. Use the large FMS knob to display the Map page group and the small FMS knob to
display the Map - Navigation Map page.
4. Rotate the RANGE knob to the right and verify the map display zooms out.
5. Rotate the RANGE knob to the left and verify the map display zooms in.
6. Press the RANGE knob to get the pointer on the map display.
7. Move the RANGE knob to the left and verify the pointer moves to the left.
8. Move the pointer up, right and down and verify that the pointer moves accordingly.
9. Press the RANGE knob to stop displaying the pointer.
10. Press the left and right arrowheads of the SOFTKEY SELECT keys. Verify softkeys
highlighting on the MFD changes.
11. Press the SEL key to select one of the softkeys.
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12. Press the
key to display the FPL – Direct To page.
13. Use the keypad to type KIXD and verify KIXD is displayed on the MFD.
14. Press the SPC key to add a space and then the BACK key to delete the space.
15. Press the CLR key to clear the field.
16. Type K34 and then press the ENTER key twice. Verify that the flight path to K34 is
displayed on the map.
17. Press the FPL key to open the FPL – Active Flight Plan page. Press the FPL key
again to close it.
18. Press the PROC key to open the Procedures page. Press the PROC key again to close
it.
19. Press the MENU key to open the Menu page. Press the MENU key again to close it.
20. Press the COM key until 1 is lit. Verify the tuning box is present around the COM 1
frequency on PFD1.
21. Using GCU477 keypad, enter in a frequency of 123.450. Verify COM1 frequency
changes as entered.
22. Press the COM key until 2 is lit. Verify the tuning box is present around the COM 2
frequency on PFD1.
23. Using GCU477 keypad, enter in a frequency of 123.450. Verify COM2 frequency
changes as entered.
24. Press the NAV key until 1 is lit. Verify the tuning box is present around the NAV 1
frequency on PFD1.
25. Using GCU477 keypad, enter in a frequency of 108.00. Verify NAV1 frequency changes
as entered.
26. Press the NAV key until 2 is lit. Verify the tuning box is present around the NAV 2
frequency on PFD1.
27. Using GCU477 keypad, enter in a frequency of 108.00. Verify NAV1 frequency changes
as entered.
28. Press the XPDR key. Verify a flashing box appears in the XPDR 1 code window.
29. Using GCU477 keypad, enter in a code of 1234. Verify XPDR1 shows a code of 1234 in
the window.
30. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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7.14
GMC 710 AFCS Controller
Original GMC 710 Reinstalled
No software or configuration loading is required if the removed GMC 710 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GMC 710 Test Section 7.14.3.
New, Repaired or Exchange GMC 710 Installed
If a new, repaired or exchange GMC 710 is installed, the correct software and configuration files
must be loaded to the unit. See Section 3.6 and then continue to the GMC 710 Test Section
7.14.3.
7.14.1 LRU Replacement Procedure GMC 710
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GMC1 in the LRU dropdown box.
7. Press the Load softkey.
8. Press ENT to acknowledge the process was complete.
9. Deactivate the curser.
10. Scroll to the Configuration Manager page.
11. Press the CNFM CFG softkey.
12. Select ok when prompted to “Confirm configuration as expected configuration”
13. Power cycle the system. Verify there are no red-Xs or system alerts.
14. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.14.2
15. If there are no red-Xs or system alerts, continue to Section 7.14.3.
7.14.2 Legacy Replacement Procedure GMC 710 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “01) Baseline” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air 200-300 Series Baseline Load. Press ENT key on PFD1.
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7. Press the CLR ALL key.
8. Scroll to highlight GMC.
9. Highlight the software box and press the ENT key to check the box.
10. Highlight the Configuration box and press the ENT key to check the box.
11. Press the Load softkey.
12. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
13. Press ENT key on PFD1 to acknowledge upload complete.
14. Deactivate cursor.
15. Scroll to the Configuration Manager page.
16. Press the CNFM CFG softkey.
17. Select ok when prompted to “Confirm configuration as expected configuration”
18. Power cycle the system. Verify there are no red-Xs or system alerts.
19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5
20. If there are no red-Xs or system alerts, continue to Section 7.14.3.
7.14.3 GMC 710 Functional check
Perform a basic operational check on the GMC 710. The following knob, wheel and key
presses and rotations are to be performed on the GMC 710.
1. Ensure the G1000 is operating in normal mode and the autopilot is operational.
2. Press the FD key a few times; verify the Flight Director display on PFD1 toggles on and
off. Leave the flight director displayed.
3. Press the XFR key and verify the white-illuminated arrowhead points in the opposite
direction. Verify the green arrow displayed at the top of PFD 1 also points in the same
direction.
4. Rotate the ALT SEL knob and verify the altitude bug, displayed on PFD 1 altitude tape,
moves.
5. Rotate the UP/DN wheel and verify the flight director moves in the vertical direction.
6. Press the HDG key and verify the white illumination appears next to the key. Rotate the
HDG knob and verify the heading bug, displayed on PFD 1 compass card, moves and
the flight director follows.
7. Press the HDG knob and verify the heading bug centers.
8. Press the YD key and verify the white illumination appears next to the key.
9. Press the VS key and verify the white illumination appears next to the key.
10. Press the FLC key and verify the white illumination appears next to the key.
11. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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GWX 68 or GWX 70 Weather Radar
Original GWX 68 or GWX 70 Reinstalled
No software or configuration loading is required if the removed GWX 68 or GWX 70 is reinstalled. This does not include units that were returned for repair as their software and
configuration files are deleted during the repair testing process. Continue to the GWX 68 or
GWX 70 Test Section 7.15.3.
New, Repaired or Exchange GWX 68 or GWX 70 Installed
If a new, repaired or exchange GWX 68 or GWX 70 is installed, the correct software and
configuration files must be loaded to the unit. See Section 3.6 and then continue to the GWX 68
or GWX 70 Test Section 7.15.3.
7.15.1 LRU Replacement Procedure GWX
LRU Replacement feature is not available for the GWX. Continue to Section 7.15.2.
7.15.2 Legacy Replacement Procedure GWX (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “08) Radar” and press ENT key on PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed radar. Press ENT key on PFD1.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press ENT key on PFD1 to acknowledge upload complete.
11. Deactivate cursor.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
17. If there are no red-Xs or system alerts, continue to Section 7.15.3.
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7.15.3 GWX 68 or GWX 70 Functional Check
Operation of the GWX 68 or GWX 70 Weather Radar is accomplished using the MFD/GCU 477.
Refer to G1000 King Air 300 Series Cockpit Reference Guide, listed in Table 1-2, for basic
operation.
NOTE
Before energizing the equipment, be sure microwave radiation safety
precautions including both fuel and personnel safety considerations have been
observed. These include clearing all personnel to an area beyond the
maximum permissible exposure level (MPEL) boundary. The MPEL for the
GWX 68 is 11 feet and the GWX 70 is 10 feet.
1. On the GCU, turn the large FMS knob to select the Map Page Group then turn the small
FMS knob to select the Map – Weather Radar page.
2. Select the Mode softkey.
3. Select the Standby softkey to initiate the one-minute warm-up period. Verify the radar
enters the standby mode after the warm-up is complete.
4. Select the Mode softkey.
5. Select the Weather softkey. After reading the CAUTION statement, turn the large FMS
knob to select YES. Press the GCU ENT key.
6. Select the STAB softkey to activate or deactivate antenna stabilization. Verify the current
stabilization condition is shown in the upper right of the weather radar display.
7. Select the Back softkey.
8. Select the Vertical softkey.
9. Select the Tilt softkey to activate the cursor in the Tilt field.
10. On the GCU, turn the small FMS knob to select the desired antenna tilt angle. Press the
GCU ENT key. Press the GCU FMS knob to remove the cursor.
11. Select the Gain softkey to activate the cursor in the Gain field.
12. On the GCU, turn the small FMS knob to adjust the gain for the desirable level. Verify
the gain setting is visible in the gain field as a movable horizontal bar in a flashing box
and the line pointer is a reference depicting the calibrated position. Press the FMS knob
to remove the cursor.
13. On the GCU, select the Gain softkey again to recalibrate the gain. Verify ‘Calibrated’ is
displayed in the Gain field.
14. Select the Mode softkey.
15. Select the Off softkey.
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7.16
GRA 5500 Radar Altimeter
Original GRA 5500 Reinstalled
No software or configuration loading is required if the removed GRA 5500 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GRA 5500 Test Section 7.16.3.
New, Repaired or Exchange GRA 5500 Installed
If a new, repaired or exchange GRA 5500 is installed, the correct software and configuration
files must be loaded to the unit. Section 7.16.1 is for integrated GRA 5500 units. For nonintegrated GRA 5500 units using ARINC 429 connections to GIA 63W instead of RS-422, go to
Section 3.17 to load software and configure the unit.
7.16.1 LRU Replacement Procedure, Integrated GRA 5500
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GRA in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.16.2.
16. If there are no red-Xs or system alerts, continue to Section 7.16.3.
7.16.2 Legacy Replacement Procedure, Integrated GRA 5500 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “05) Radar” and press ENT key on PFD1.
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6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight King Air GRA 5500 Radar Altimeter. Press ENT key on PFD1.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press ENT key on PFD1 to acknowledge upload complete.
11. Deactivate cursor.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
17. If there are no red-Xs or system alerts, continue to Section 7.16.3.
7.16.3 GRA 5500 Functional Check
This check verifies that the G1000/radar altimeter interface operates correctly.
1. Navigate to the AUX – SYSTEM STATUS page on the MFD.
2. Press the RA TEST softkey and verify that the “RA TEST” annunciation is displayed on
both PFDs.
3. Verify 40 feet is displayed in the RA display window on both PFDs.
4. Press the RA TEST softkey again. Verify the RA readout window decreases to 0 feet on
PFD1 and PFD2.
5. Open the RADIO ALTM circuit breaker. Verify on PFD 1 and PFD 2 that an RA FAIL
message is displayed.
6. Close the RADIO ALTM circuit breaker.
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7.17
Garmin Traffic Systems (GTS 8XX/GTS 8XXX)
Original GTS Reinstalled
No software or configuration loading is required if the removed GTS is re-installed. This does
not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GTS Test Section 7.17.3.
New, Repaired or Exchange GTS Installed
If a new, repaired or exchange GTS is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.17.1 and then continue to the GTS Test Section
7.17.3.
7.17.1 LRU Replacement Procedure GTS
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GTS in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.17.2.
16. If there are no red-Xs or system alerts, continue to Section 7.17.3.
7.17.2 Legacy Replacement Procedure GTS (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “09) Garmin Traffic Systems” and press ENT key on
PFD1.
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6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed GTS configuration. Press ENT key on PFD1.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press ENT key on PFD1 to acknowledge upload complete.
11. Deactivate cursor.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
17. If there are no red-Xs or system alerts, continue to Section 7.17.3.
7.17.3 Antenna Test
The following test assures the traffic antennas and coaxial cables are properly connected.
1. On the MAP-TRAFFIC MAP page of the MFD, perform the following:
a. Press the OPERATE softkey (for TAS/TCAS I) or press TA ONLY softkey (for
TCAS II). A self-test of the antenna circuit is initialized. If the MFD displays
FAILURE at the upper left corner of the traffic display area, it will be necessary to
recheck the coaxial connections. If MFD displays OPERATING (for TAS/TCAS I)
or TA ONLY (for TCAS II) without indicating a fault, proceed to the next step of
antenna verification.
b. If an “ADS-B” softkey is displayed, press the softkey to turn it off.
2. Ensure that the transmitter or receiver (RX/TX) that you are testing is significantly closer
to the ramp tester than another operating RX/TX, or erroneous and inaccurate results
may occur. All four quadrants (0, 90, 180 and 270 degrees) relative to the aircraft will be
similarly tested to verify bearing of simulated intruder supplied via the ramp tester are
correctly displayed on the MAP-TRAFFIC MAP page of the MFD.
3. Set up a stationary intruder by selecting the following on the ramp tester:
•
Intruder type: ATCRBS
•
Intruder Start Distance: 2 nm
•
Intruder Start Altitude: 500 feet above field elevation
•
Vertical Speed: 0 fpm
•
Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and
a stationary intruder is created by not starting the scenario.)
4. Position ramp tester at 0 degrees (i.e. off the nose of the aircraft).
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5. Initiate the intruder scenario and verify a target is annunciated on the MAP-TRAFFIC
MAP page of the MFD at the correct bearing of approximately 0-degree azimuth at 2 NM
(read as +05 above a filled diamond indicating proximate traffic).
6. On the ramp tester, toggle intruder traffic to standby or off.
7. Reposition ramp tester and reengage the same intruder scenario for 90, 180 and 270
degrees relative to the aircraft.
8. Verify a target is annunciated on the MAP-TRAFFIC MAP page of the MFD at the same
bearing as the ramp tester.
9. If the bearing is not as anticipated or multiple targets are displayed during tests (not
including possible local targets), verify the following:
•
Coax cable connectors are properly secured at the bulkhead adapter fittings, GA
58 antennas, and GTS unit.
•
Connections are made to the proper channels and color-coded heat shrink is the
same color on both ends of coax cables.
•
Connectors are correctly installed on coax cables.
7.17.4 System Test
The following test provides a scenario that will converge and intercept the GTS to assure proper
operational and surveillance functions.
NOTE
Prior to simulating the ‘in-air’ condition, please contact your local Air Traffic
Control (Center and Approach) and inform them of your intention to perform
aircraft testing that may transmit ADS-B Out signals of an aircraft in the ‘in-air’
condition. Closed hangar doors may not provide adequate isolation from ATC.
1. Disconnect the radar altimeter receive coaxial cable or cover the receive antenna so the
radar altimeter reads over 2000 feet.
2. For GTS 8000 TCAS II test only, perform the following:
a. Change BARO setting to 29.92 in-Hg on PFD1 and PFD2.
b. Set the main landing gear WOW actuators in the air position.
3. On the MAP-TRAFFIC MAP page of the MFD, perform the following:
a. Press the OPERATE softkey (for TAS/TCAS I) or TA/RA softkey (for TCAS II).
b. If an “ADS-B” softkey is displayed, press the softkey to turn it off.
4. Position ramp tester at 90 degrees (i.e. off the right wing).
5. Select the following on the ramp tester:
•
Intruder type: ATCRBS.
•
Intruder Start Distance: 10 nm
•
Intruder Start Altitude: 300 ft above PFD1 displayed altitude
•
Vertical Speed: 0 fpm
•
Velocity: 360 kts
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6. Initiate the intruder scenario and observe the following:
•
The simulated intruder should be acquired at approximately 6-10 NM at 90 degree
bearing. Observe intruder closes on own aircraft at a rate of 0.1 NM/sec. Verify
that only a single simulated target is displayed in the expected quadrant (exclude
possible local traffic).
•
The simulated intruder should transition from Other Traffic (displayed as an open
diamond with +03 displayed above), to proximate traffic (displayed as a filled
white diamond with +03 displayed above), to a Traffic Advisory (TA) alarm (yellow
filled circle with +03 displayed above.)
•
For GTS 8000 TCAS II installations, the following applies:
The simulated intruder should transition from a Traffic Advisory (displayed as a
solid yellow circle with +03 displayed above), to a Resolution Advisory (RA) alarm
(red filled square with +03 displayed above). Additionally, a Resolution Advisory
is displayed on the vertical speed tape of PFD1 and PFD2 and an audible
Resolution Advisory is heard over cockpit speakers and headphones.
NOTE
The aural TA annunciations are muted if the gear is extended and the
Radar Altimeter indicates below 400 feet.
For GTS 8000 TCAS II, to generate a DESCEND resolution advisory, the
WOW actuators must be set to the in-air position and the Radar Altimeter
must read greater than 2,000 feet.
At the end of these tests, put the aircraft back ‘on-ground’ and restore radar altimeter operation.
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7.18
GDL 59
Original GDL 59 Reinstalled
No software or configuration loading is required if the removed GDL 59 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GDL 59 Test Section 7.18.4.
New, Repaired or Exchange GDL 59 Installed
If a new, repaired or exchange GDL 59 is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.18.1 and then continue to the GDL 59 Test Section
7.18.4.
7.18.1 LRU Replacement Procedure GDL 59
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GDL 59 in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.18.2.
16. If there are no red-Xs or system alerts, continue to Section 7.18.3.
7.18.2 Legacy Replacement Procedure GDL 59 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “07) Connext - SXM” and press ENT key on PFD1.
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6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight the installed GDL 59 configuration. Press ENT key on PFD1.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press ENT key on PFD1 to acknowledge upload complete.
11. Deactivate cursor.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system. Verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
17. If there are no red-Xs or system alerts, continue to Section 7.18.3.
7.18.3 Activation of Garmin Connext
In order to activate the optional GDL 59 and optional GSR 56 for Garmin Connext, contact
Garmin Product Support at one of the following numbers (M-F, 7:00 a.m. to 7:00 p.m. Central
Standard Time, - Central USA):
•
1.866.739.5687 (toll free in USA)
•
+1.913.440.1135 (worldwide)
Have the following information ready prior to calling:
•
If activating services for a GDL 59 installation
o
Aircraft tail number, serial number, manufacturer, and model
o
GDL 59 serial number
o
G1000 system ID number
Garmin Product Support will provide additional information for activation of data services.
To obtain the G1000 system ID number and unit serial numbers, accomplish the following:
1. Turn the large FMS knob on the MFD to select the AUX page group.
2. Turn the small FMS knob to select the SYSTEM STATUS page. Record the SYSTEM ID
number shown in the AIRFRAME field. This number is unique for each G1000 system.
3. Press the LRU softkey to activate the cursor in the LRU INFO field. Use the large FMS
knob to scroll the cursor to GDL 59. Record the GDL 59 serial number shown in the LRU
INFO field.
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7.18.4 GDL 59 Wi-Fi Data Link Functional Check
This check verifies GDL 59 Wi-Fi Data Link interface is configured and is functional. This check
requires an operating and available wireless network to be within range of the aircraft.
NOTE
This check only verifies the data output from the G1000 equipment. Any
equipment/wiring added that is not part of the installation data will need
separate testing and verification not covered as part of this document.
1. Start the G1000 System in Normal Mode.
2. Using the large FMS knob, select the AUX page group on the MFD. Using the small FMS
knob, select the AUX-REPORT STATUS page.
3. Press the WI-FI softkey on the MFD to select the AUX – WI-FI SETUP page.
4. Press the AVAIL softkey on the MFD to display the available WI-FI networks.
5. Press the FMS knob on the GCU to activate the cursor and rotate the small FMS knob to
highlight the desired network in the AVAILABLE NETWORKS field.
6. Press the CONNECT softkey on the MFD to connect to the network. (Skip to step 12 if the
selected network is a non-secure network.)
7. If the selected network is a secure network, enter the pass code in the ENTER
PASSPHRASE field in the WPA SECURITY SETTINGS pop-up window.
8. Press the ENT key on the GCU to accept the pass code, then press the ENT key on the
GCU again.
9. When the SAVE SETTINGS pop-up window is displayed, press the ENT key on the
GCU keypad to select SAVE CONNECTION.
10. Enter the appropriate airport identifier in the SELECT AN AIRPORT TO ASSOCIATE
WITH THE CONNECTION field, then press the ENT key on the GCU to accept the
identifier.
11. With the CONNECT button highlighted, press the ENT key on the GCU to connect to the
network.
12. Press the ENT key on the GCU if the verification window “Are you sure you want to
connect?” is displayed.
13. Verify that the CONNECTION STATUS field on the AUX – WI-FI SETUP page on the MFD
indicates CONNECTED.
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7.19
GSR 56
Original GSR 56 Reinstalled
No software or configuration loading is required if the removed GSR 56 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process. Continue to the GSR 56 Test Section 7.14.3.
New, Repaired or Exchange GSR 56 Installed
If a new, repaired or exchange GSR 56 is installed, the correct software and configuration files
must be loaded to the unit. See Section 3.6 and then continue to the GSR 56 Test Section
7.14.3.
7.19.1 LRU Replacement Procedure GSR 56
LRU Replacement feature is not available for the GSR56, continue to Section 7.19.2.
7.19.2 Legacy Replacement Procedure GSR 56 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the small FMS knob to highlight “07) Connext - SXM” and press ENT key on PFD1.
6. Rotate the small FMS knob to highlight the installed GSR 56 configuration. Press ENT
key on PFD1.
7. Verify the installed GSR 56 configuration is displayed in the “Item” window.
8. Press the CHK ALL key.
9. Press the Load softkey.
10. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
11. Press ENT key on PFD1 to acknowledge upload complete.
12. Deactivate cursor.
13. Scroll to the Configuration Manager page.
14. Press the CNFM CFG softkey.
15. Select ok when prompted to “Confirm configuration as expected configuration”
16. Power cycle the system. Verify there are no red-Xs or system alerts.
17. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
18. If there are no red-Xs or system alerts, continue to Section 7.19.3.
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7.19.3 Activation of Garmin Connext
In order to activate the optional GSR 56 for Garmin Connext, contact Garmin Product Support
at one of the following numbers (M-F, 7:00 a.m. to 7:00 p.m. Central Standard Time, - Central
USA):
•
1.866.739.5687 (toll free in USA)
•
+1.913.440.1135 (worldwide)
•
Have the following information ready prior to calling:
o
Aircraft tail number, serial number, manufacturer, and model
o
GSR 56 serial number
o
G1000 system ID number
o
Name of aircraft owner and contact information
o
Credit card information
Garmin Product Support will provide additional information for activation of data services.
To obtain the G1000 system ID number and unit serial numbers, accomplish the following:
1. Turn the large FMS knob on the MFD to select the AUX page group.
2. Turn the small FMS knob to select the SYSTEM STATUS page. Record the SYSTEM ID
number shown in the AIRFRAME field. This number is unique for each G1000 system.
3. Press the LRU softkey to activate the cursor in the LRU INFO field. Use the large FMS
knob to scroll the cursor to GSR1 (if GSR 56 is installed). Record the GSR 56 serial
number shown in the LRU INFO field.
7.19.4 GSR 56 Functional Check
1. Power up the aircraft.
2. Using the large FMS knob, select the AUX page group on the MFD. Using the small
FMS knob, select the AUX-TELEPHONE page.
3. Ensure the system is showing Iridium signal strength (best if aircraft is outside).
4. Press TEL button on the pilot’s GMA.
5. Press the DIAL softkey on the MFD.
6. Enter the test phone number in the ENTER PHONE NUMBER field using the GCU
keypad.
7. Press the ENT key on the GCU keypad to accept the phone number.
8. Press the ENT key on the GCU keypad to initiate the dialing sequence.
9. When call is complete, press the HANGUP softkey on the AUX – TELEPHONE page on
the MFD to end the call.
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7.20
GSD 41
Original GSD 41 Reinstalled
No software or configuration loading is required if the removed GSD 41 is re-installed. This
does not include units that were returned for repair as their software and configuration files are
deleted during the repair testing process.
New, Repaired or Exchange GDS 41 Installed
If a new, repaired or exchange GSD 41 is installed, the correct software and configuration files
must be loaded to the unit. See Section 7.20.1.
7.20.1 LRU Replacement Procedure GSD 41
1. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
2. Apply power to the G1000 system by connecting external power to the aircraft to
energize the aircraft and avionics electrical busses.
3. Turn on Avionics electrical busses.
4. Power on PFD2, MFD, and PFD1 in configuration mode.
5. Using the PFD1, scroll to the LRU replacement page.
6. Activate the curser and select GSD 1 in the LRU dropdown box.
7. Press the CHK All softkey.
8. Press the Load softkey.
9. Press ENT to acknowledge the process was complete.
10. Deactivate the curser.
11. Scroll to the Configuration Manager page.
12. Press the CNFM CFG softkey.
13. Select ok when prompted to “Confirm configuration as expected configuration”
14. Power cycle the system. Verify there are no red-Xs or system alerts.
15. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.20.2.
7.20.2 Legacy Replacement Procedure GSD 41 (Alternate Method)
1. Insert the software loader card in the top slot of PFD1.
2. Power on PFD2, MFD, and PFD1 in configuration mode.
3. Select NO when “Do you want to update system files” is displayed on the screen of
PFD1.
4. Select the “SYSTEM UPLOAD” page using the small FMS knob on PFD1.
5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate
the large FMS knob to highlight “11) Non Garmin Options” and press ENT key on
PFD1.
6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob
to highlight “King Air – FDR Option”. Press ENT key on PFD1.
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7. Press the CHK All softkey.
8. Press the Load softkey.
9. Monitor load progress. Verify software load completes without errors as indicated by the
following:
•
Green “PASS” in the Configuration and Software columns for each item loaded.
•
“Upload Complete………….COMPLETE” in the summary box.
10. Press ENT key on PFD1 to acknowledge upload complete.
11. Deactivate cursor.
12. Scroll to the Configuration Manager page.
13. Press the CNFM CFG softkey.
14. Select ok when prompted to “Confirm configuration as expected configuration”
15. Power cycle the system verify there are no red-Xs or system alerts.
16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.
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8. Subsystem Functional Checks
8.1
Non-Garmin Traffic System Functional Check
1. Select the Map – Traffic Map page on the MFD.
2. Verify that the TAS STBY, TAS OPER, Test, and ALT Mode softkeys are available on
the bottom of the MFD. Verify that an operating mode; STANDBY, OPERATE, or TEST
(not TAS FAIL) is displayed in the upper left corner of the traffic map. Verify that NO
DATA is not displayed in yellow in the center of the display over the aircraft symbol.
NOTE
If the ALT Mode softkey is not displayed, the G1000 has not been properly
configured for the traffic system. Reference Section 3.8.12, to enable the traffic
system.
3. Press the TAS OPER softkey and verify that TAS: OPERATING is displayed in the
upper left corner of the traffic map.
4. Press the TAS STBY softkey and verify that TAS: STANDBY is displayed in the upper
left corner of the traffic map.
5. Press the Test softkey and verify that TAS: TEST is displayed in the upper left corner of
the traffic map and a traffic test pattern is displayed. Upon completion of the test, verify
that “TAS SYSTEM TEST OK” is heard over the cockpit speaker.
NOTE
This annunciated traffic system test message may be different from the traffic
system installed on subject aircraft.
6. Open the TRFC circuit breaker on the avionics circuit breaker panel. On the MFD, verify
that NO DATA is displayed in yellow after several seconds.
7. Close the TRFC circuit breaker on the avionics circuit breaker panel and verify that NO
DATA is removed after several seconds.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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8.2
Stormscope Functional Check
Reference Section 3.18.1, for Stormscope configuration. This procedure assumes familiarity
with the set-up and operation of the WX-PA portable analyzer kit if required.
1. Apply power to the WX-500 and verify that no failed test messages appear. If fault
messages do appear, refer to the WX-500 Installation Manual for troubleshooting.
2. Following successful power up, verify the following modes:
•
All available ranges can be displayed.
•
Access to the cell mode and strike mode.
•
Strike counter is displayed in all weather modes and ranges.
3. Key COM1 and COM2 several times on different frequencies representing the lower, mid
and upper portion of the VHF COM frequency band. Verify keying of COM1 or COM2
does not cause strike data to appear on the MFD.
4. Operate DME, XPDR 1, XPDR 2 and weather radar. Verify these systems do not cause
strike data to appear on the MFD.
5. Connect the WX-PA cable to the WX-PA antenna.
6. Position the WX-PA antenna on the WX-500 antenna. Ensure the connection is tight. If
necessary, use tape to secure the WX-PA antenna. Ensure the “FORWARD” arrows are
aligned and the WX-PA antenna suction cups are positioned forward of center along the
longitudinal axis.
7. Secure the WX-PA cable to the aircraft with the attached suction cup and route the cable
to the cockpit.
8. Connect the remaining cable end to the WX-PA.
9. Power up the WX-PA and verify the WX-500 is in the weather mapping mode.
10. Set the WX-500 to STRIKE mode; 100 NM range (or next highest available range).
11. Select the Continuous Out mode displayed on the WX-PA menu and press
MENU/ENTER.
12. Select the bottom mount antenna configuration on the WX-PA keyboard (“A” key).
13. Select a cardinal bearing and a range of 120 NM.
14. Use the F1 and F2 keys to adjust range and F3 and F4 keys to adjust heading.
NOTE
The WX-500 will plot data at one-half the range selected on the WX-PA.
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15. Press MENU/ENTER to start the test.
16. Observe the MFD to ensure the proper positioning of the strikes, based on range and
azimuth settings on the WX-PA. Change the cardinal bearings and verify correct test
strikes. Verify the strikes are within 10 degrees of the selected azimuth and plot at 60NM
(1/2 120 NM).
17. Verify after 20 seconds of operation the strike counter reads 580 +/-40.
18. After testing for all ranges and bearings indicated, press 2ND then MENU/ENTER to
return to the main menu.
19. Select Circular Pattern mode on the WX-PA mode menu and press MENU/ENTER.
20. Select bottom mount antenna configuration on the WX-PA keyboard (“A” key).
NOTE
The MFD should be set at 100 NM (or next highest available range) on the 360degree weather screen and in strike mode.
21. Use the F1 and F2 keys to select 120 NM range and press MENU/ENTER to start the
test. Verify the WX-500 plots discharge points at approximately 60 NM.
22. Observe the MFD to ensure the proper positioning of the test strikes. Verify the strikes
are within 10 degrees of the 30-degree azimuth increment and within 12 NM of 60 NM,
23. When complete, set WX-PA for 55 NM, set the MFD for 50 NM (or the next highest
available range) and repeat test.
24. On the MFD, verify the sensor plots points just outside of 25 NM and the strikes are
within 10 degrees of the 30-degree azimuth and within 5 NM of 27.5 NM.
25. Repeat above setting the MFD for 25 NM (or the next highest available range) and the
WX-PA for 15 NM.
26. On the MFD, verify the positioning of test strikes are within 10 degrees of azimuth and
within 2 NM of 7.5 NM.
27. Restart the G1000 in configuration mode by opening the PFD and MFD circuit breakers.
While holding the ENT keys on the PFDs and MFD, restore power by closing the PFDs
and MFD circuit breakers.
28. Select the OTHER page group on the MFD. The Map - Stormscope Map page is
shown by default.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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8.3
TAWS Functional Check
8.3.1
Functional Check for TAWS-B
1. With the G1000 in Normal Mode, use the GCU FMS knob to select the Map group and
TAWS page on the MFD.
2. Verify that the title at the top of the page reads “Map – TAWS-B Map”.
NOTE
If TAWS has not been enabled, the title will read “Map – Terrain Proximity” or
“Map – Terrain”. Refer to Section 3.9.6 for TAWS B Configuration for enabling this
feature.
3. Press the GCU MENU button and select “Test TAWS System” from the pop-up menu.
Verify TAWS test annunciation is displayed on the MFD and both PFDs.
4. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over
the cockpit speaker (if selected) and the headsets.
5. Press the GCU MENU button again and select “Inhibit TAWS” from the pop-up menu
and press ENT on the GCU. Verify “TAWS INH” is displayed on PFD 1 and PFD 2.
6. Press the GCU MENU button again and select “Enable TAWS” from the pop-up menu
and press ENT on the GCU. Verify the “TAWS INH” annunciation on the PFDs has
extinguished.
7. With a GPS position acquired, shield or disconnect the GPS antennas to remove the
GPS signal. Verify “LOI” shows on the MFD and the “TAWS N/A” and “LOI”
annunciations show on the PFDs.
8. Reconnect or remove the shield from the GPS antennas, and verify the MFD “LOI”
indication and PFD “TAWS N/A” and “LOI” annunciations are removed once the GPS
satellites are acquired.
9. Pull PFD1 PRI and PFD1 SEC circuit breakers. Re-power PFD1 in configuration mode,
and use the PFD1 FMS knob to select the System Audio - Audio Alert Configuration
page.
10. Ensure cockpit speaker is selected ON. Use the PFD1 FMS knob to highlight each of the
following messages then select PLAY. Verify each of the following audio messages are
played:
•
Too Low Terrain
•
Sink Rate
•
Pull Up
•
Don’t Sink
•
Five Hundred
•
Caution, Terrain (2X)
•
Terrain (2X), Pull Up (2X)
•
Caution, Obstacle (2X)
•
Obstacle (2X), Pull Up (2X)
•
Terrain Ahead (2X)
•
Terrain Ahead, Pull Up (2X)
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•
Obstacle Ahead (2X)
•
Obstacle Ahead, Pull Up (2X)
11. Pull the PFD1 PRI and PFD1 SEC circuit breakers, and re-power PFD1 in normal
operating mode.
12. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.3.2
Functional Check for TAWS-A
1. With the G1000 in Normal Mode, use the GCU FMS knob to select the Map group and
TAWS page on the MFD.
2. Verify that the title at the top of the page reads “Map – TAWS-A Map”.
NOTE
If TAWS has not been enabled, the title will read “Map – Terrain Proximity”
or “Map – Terrain”. Refer to Section 3.9.7 for enabling TAWS-A.
3. Press the GCU MENU button and select “Test TAWS System” from the pop-up menu.
Verify TAWS test annunciation is displayed on the MFD and both PFDs.
4. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over
the cockpit speaker (if selected) and the headsets.
5. Press the GCU MENU button again and select “Inhibit TAWS” from the pop-up menu
and press ENT on the GCU. Verify “TAWS INH” is displayed on PFD 1 and PFD 2.
6. Press the GCU MENU button again and select “Enable TAWS” from the pop-up menu
and press ENT on the GCU. Verify the “TAWS INH” annunciation on the PFDs has
extinguished.
7. Press the GCU MENU button again and select “Inhibit GPWS” from the pop-up menu
and press ENT on the GCU. Verify “GPWS INH” is displayed on PFD 1 and PFD 2.
8. Press the GCU MENU button again and select “Enable GPWS” from the pop-up menu
and press ENT on the GCU. Verify the “GPWS INH” annunciation on the PFDs has
extinguished.
9. Press the GCU MENU button again and select “Flap Override” from the pop-up menu
and press ENT on the GCU. Verify “FLAP OVR” is displayed on PFD 1 and PFD 2.
10. Press the GCU MENU button again and select “Disable Flap Override” from the pop-up
menu and press ENT on the GCU. Verify the “FLAP OVR” annunciation on the PFDs
has extinguished.
11. With a GPS position acquired, shield or disconnect the GPS antennas to remove the
GPS signal. Verify “LOI” shows on the MFD and the “TAWS N/A” and “LOI”
annunciations show on the PFDs.
12. Reconnect or remove the shield from the GPS antennas and verify the MFD “LOI”
indication and PFD “TAWS N/A” and “LOI” annunciations are removed once the GPS
satellites are acquired.
13. Pull the RADIO ALTM circuit breaker. Verify “GPWS FAIL” is displayed on PFD1 and
PFD2.
14. Reset the RADIO ALTM circuit breaker. Verify “GPWS FAIL” annunciations are
removed.
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15. Pull PFD1 PRI and PFD1 SEC circuit breakers. Re-power PFD1 in configuration mode,
and use the PFD1 FMS knob to select the System Audio - Audio Alert Configuration
page.
16. Ensure cockpit speaker is selected ON. Use the PFD1 FMS knob to highlight each of the
following messages then select PLAY. Verify each of the following audio messages are
played:
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
•
Too Low, Terrain
Too Low, Flaps
Too Low, Gear
Sink Rate
Pull Up
Don’t Sink
Caution, Terrain (2X)
Terrain (2X), Pull Up (2X)
Terrain (2X)
Caution, Obstacle (2X)
Obstacle (2X), Pull Up (2X)
Terrain Ahead (2X)
Terrain Ahead, Pull Up (2X)
Obstacle Ahead (2X)
Obstacle Ahead, Pull Up (2X)
Five Hundred
Four Hundred
Three Hundred
Two Hundred
One Hundred
Glide Slope
Glide Path
17. Pull the PFD1 PRI and PFD1 SEC circuit breakers, and re-power PFD1 in normal
operating mode.
NOTE
The following steps require the movement of the flaps and landing gear.
This portion of the check can be accomplished in conjunction with the Landing
Gear Aural Alert and Sirius XM Audio Suppression Test in Section 7.2.4.
18. Place the airplane on jacks (Ref. King Air 300 Series Maintenance Manual Chapter 7-0000) with the wheels clear of the ground.
19. Ensure all equipment and personnel are clear of the flaps and landing gear. Place the
flaps and landing gear in the full down positions.
20. Using an air data test set connected to the pilot side pitot/static system, set an airspeed
of at least 190 kts as displayed on PFD1.
21. After the Alerts softkey flashes, press the Alerts softkey.
22. Verify the “TAWS FLAP FAULT – Flaps detected in the LDG position” and “TAWS
GEAR FAULT – Landing Gear detected in the DOWN position” messages are present.
23. Press the Alerts softkey to close the alerts window.
24. Place the flaps and landing gear in the full up positions.
25. Press the Alerts softkey again to open the alerts window.
26. Verify the “TAWS FLAP FAULT – Flaps detected in the LDG position” and “TAWS
GEAR FAULT – Landing Gear detected in the DOWN position” messages not present.
27. Return air data test set to GROUND.
28. Place the landing gear in the down position and remove the aircraft from the jacks.
29. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.4
FliteCharts Functional Check
FliteCharts is enabled by default and only turned off if the ChartView Only option file has been
loaded. Reference Section 3.8.11 (FliteCharts) or Section 3.9.2 (Dual Charts) for configuring
FliteCharts.
NOTE
This test is required only if FliteCharts or Dual Charts is enabled.
1. If Dual Charts are installed, ensure FliteCharts are set as the preferred charts.
2. With the G1000 in Normal Mode, use the GCU FMS knob to select Aux – System
Status page, then select MFD1 DB softkey.
3. Use the small FMS knob to scroll to CHART.
4. Verify “FliteCharts” is displayed in blue text adjacent to “CHART”.
5. Verify the FliteCharts database cycle number is displayed in blue text and the
FliteCharts database is current.
6. Deactivate the cursor and use the GCU large FMS knob to select the Map - Navigation
Map page then press the Charts softkey.
7. Verify the airport chart is displayed and the following softkeys are displayed (some
softkeys may be grayed out):
•
CHRT OPT
•
Show Map
•
INFO 1
•
DP
•
STAR
•
APR
•
WX
•
NOTAM
•
Go Back
8. Press the CHRT OPT softkey and verify the following softkeys are displayed (some
softkeys may be grayed out):
•
All
•
Header
•
Plan
•
Profile
•
Minimums
•
Fit WDTH
•
Full SCN
•
Back
9. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.5
ChartView Functional Check
ChartView must be enabled using a ChartView or Dual Charts Enable Card. Reference Section
3.9.1 (ChartView only) or 3.9.2 (Dual Charts) for enabling procedures.
NOTE
The required ChartView databases are subscription-based and are to be
procured by the aircraft owner directly from Jeppesen.
1. If Dual Charts are installed, ensure ChartView are set as the preferred charts.
2. With the G1000 in Normal Mode, use the GCU FMS knob to select ‘Aux – System
Status’ page, then select MFD1 DB softkey.
3. Use the small FMS knob to scroll to CHART.
4. Verify “ChartView” is displayed in blue text adjacent to CHART.
5. Verify the ChartView database cycle number is displayed in blue text and the ChartView
database is current.
6. Deactivate the cursor and use the large GCU FMS knob to select the Navigation Map
Page then press the Charts softkey.
7. Verify the airport chart is displayed and the following softkeys are displayed (some
softkeys may be grayed out):
•
CHRT OPT
• APR
•
Show Map
• WX
•
INFO-1
• NOTAM
•
DP
• Go Back
•
STAR
8. Press CHRT OPT softkey and verify the following softkeys are displayed (some softkeys
may be grayed out):
•
All
•
Header
•
Plan
•
Profile
•
Minimums
•
Fit WDTH
•
Full SCN
•
Back
9. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.6
SafeTaxi Functional Check
The maximum map ranges for enhanced detail are configurable by the flight crew. When
zoomed in close enough to show the airport detail, the map reveals runways with numbers,
taxiways with identifying letters/numbers, and airport landmarks including ramps, buildings,
control towers, and other prominent features. Resolution is greater at lower map ranges. When
the aircraft location is within the screen boundary, including within SafeTaxi ranges, an airplane
symbol is shown on any of the navigation map views for enhanced position awareness.
Any map page that displays the navigation view can also show the SafeTaxi airport layout,
within the maximum configured range. The following is a list of pages where the SafeTaxi
feature can be seen:
•
Navigation Map Page
•
Inset map
•
Weather Datalink Page
•
Airport Information Page
•
Intersection Information Page
•
NDB Information Page
•
VOR Information Page
•
User Waypoint Information Page
•
Trip Planning Page
•
Nearest Pages
1. Use the FMS knob on the GCU to select the Aux – System Status page and select
MFD1 DB softkey. Use the small FMS knob to scroll to CHART category and verify
“FliteCharts” is displayed in blue text adjacent to “CHART”.
2. Verify the FliteCharts database ‘Region’, ‘Cycle’ number, ‘Effective’, ‘Expires’, and
‘Disables’ dates of the subscription appear in cyan text.
3. Use the FMS knob on the GCU to select Map - Navigation Map page.
4. On the GCU, press MENU. With Map Setup highlighted, press ENT on the GCU. Rotate
the small GCU FMS knob to select the Aviation group and press the ENT key on GCU.
5. Turn the GCU large FMS Knob to scroll through the Aviation Group options to ‘SafeTaxi’.
6. Turn the GCU small FMS Knob to display the range of distances.
7. Turn the GCU FMS Knob to select 5000ft as the distance for maximum SafeTaxi display
range, and then press the GCU ENT key to complete the selection.
8. Using the GCU range knob, select a range of 5000ft or less. Verify SafeTaxi display
represents the current aircraft location and the airport layout.
9. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.7
DME Functional Check
This check verifies that the DME-to-G1000 interface operates correctly.
NOTE
Support for a single Collins DME-42 system is provided as an option in the
G1000. If the DME option is selected, the DME channel one audio level must
be adjusted by the procedure contained within Collins DME-42 Transceiver
Repair Manual 523-0772458, Maintenance Section 523-0772460-006118, to
adjust DME channel one audio level. Recommended nominal DME audio
output level is 4.46 Vpp + 0.10 Vpp. Procedure must be accomplished by an
approved repair station.
1. If DME is not displayed, press the PFD softkeys on PFD1 and PFD2, then press the
DME softkey. Verify the DME window is displayed next to the PFD1 and PFD2 HSI.
2. On PFD1 and PFD2, press the Back softkey then select DME softkeys. Verify the DME
TUNING screen is displayed.
3. On PFD1 and PFD2, use the large FMS knob to select the NAV1, NAV2 and HOLD
modes in the DME field. Verify that the NAV1, NAV2 and HOLD modes can be selected
by turning the small FMS knob.
4. Set NAV1 and NAV2 frequencies to 108.00 and 117.00 respectively.
5. On PFD1 and PFD2, select the DME NAV1 mode. Verify that the DME window display
is set to the NAV1 frequency of 108.00.
6. On PFD1 and PFD2, select the DME NAV2 mode by pressing the ENT softkey. Verify
that the DME window display is set to the NAV2 frequency of 117.00.
7. On PFD1 and PFD2, select the DME HOLD mode by using the FMS knob. Verify that
the last selected NAV frequency of 117.00 remains the same when the NAV2 frequency
is changed. Deselect DME HOLD.
8. On the NAV Test Set, set up a DME test and note the NAV frequency. Tune NAV 1 to
the test set frequency and set PFD1 and PFD2 DME MODE to NAV1. Set NAV 2 to a
frequency other than the test set frequency.
9. Verify that the DME distance on PFD1 and PFD2 match the test set.
10. Select, or verify selected, DME and SPKR buttons on GMA1 and GMA2 audio panels to
select the DME audio and select speaker to ON. Verify that the DME audio can be
heard over the cockpit speakers.
11. On PFD1 and PFD2, set the DME mode to NAV2 and verify that the DME distance is
dashed out.
12. Tune NAV 2 to the test set frequency. Set NAV 1 to a frequency other than the test set
frequency.
13. Verify that the DME distance on PFD1 and PFD2 match the test set.
14. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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ADF Functional Check
8.8
This check verifies that the ADF / G1000 interface operates correctly.
1. Press the PFD softkey on PFD1 and PFD2. Toggle the BRG1 and BRG2 softkey until
the ADF bearing is shown on PFD1 and PFD2.
2. Verify that the ADF window is not invalid (no red ‘X’).
3. Using the ADF control head select a known valid local ADF. Verify that the ADF bearing
pointer moves towards a bearing and stabilizes.
4. Select ADF and SPKR on GMA1 and GMA2. Using the ADF control head, select, ANT
mode. Verify that the audio from the station tuned can be heard on the pilot and copilot
headset and cockpit speaker.
5. Increment the ADF volume control from full low to full high. Verify the volume increases
and decreases appropriately over pilot and copilot headset and cockpit speaker.
6. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.9
GRA 5500 Radar Altimeter Functional Check
This check verifies that the G1000/radar altimeter interface is operates correctly.
1.
Navigate to the Aux – System Status page on the MFD.
2. Press the RA Test softkey and verify that the “RA TEST” annunciation is displayed on
both PFDs.
3. Verify 40 feet is displayed in the RA display window on both PFDs.
4. Press the RA Test softkey again. Verify the RA readout window decreases to 0 feet on
PFD1 and PFD2.
5. Pull the RADIO ALTM circuit breaker. Verify on PFD 1 and PFD 2 that an RA FAIL
message is displayed.
6. Reset the RADIO ALTM circuit breaker.
7. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.10
Non-Garmin Radar Altimeter Check (Optional)
This check verifies that the G1000 / radar altimeter interface is operates correctly.
NOTE
This check only verifies the data output from the G1000 equipment. Any
equipment/wiring added that is not part of the installation data will need
separate testing and verification not covered as part of this document.
1. Navigate to the Aux – System Status page on the MFD.
2. Press the RA Test softkey and verify that “RA TEST” annunciation is displayed on both
PFDs.
3. Verify 50 feet is displayed in the RA display window on both PFDs.
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4. Press the RA Test softkey again. Verify the RA readout window displays 2500 feet and
decreases to 0 feet on PFD1 and PFD 2.
5. Pull the RADIO ALTM circuit breaker. Verify on PFD 1 and PFD 2 that an RA FAIL
message is displayed.
6. Reset the RADIO ALTM circuit breaker.
7. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.11
Weight on Wheels and Low Speed Awareness Band Check
This procedure will verify that the GDU air ground status uses valid Weight on Wheels (WOW)
inputs.
1. Ensure aircraft is positioned with weight on wheels.
2. Apply external power to the aircraft. Set BATT and AVIONICS MASTER switches to ON
and wait for all aircraft and avionics systems to complete their initialization and begin
operating normally.
3. Verify there are no WOW INVALID or WOW FAULT messages. Refer to Section 5.2 to
troubleshoot messages.
4. Verify the Low Speed Awareness band (red band) is NOT displayed on the PFD1 and
PFD2 airspeed tapes (see Figure 8-1.)
NOTE
This portion of the check can be accomplished in conjunction with the Landing
Gear Aural Alert and Sirius XM Audio Suppression Test in Section 7.2.4.
5. Place the airplane on jacks (Ref. King Air 300 Series Maintenance Manual Chapter 7-0000) with the wheels clear of the ground.
6. Verify there are no WOW INVALID or WOW FAULT messages. Refer to Section 5.4 to
troubleshoot messages.
7. Verify the Low Speed Awareness band (red band) appears at the low end of the Air
Speed Tape on the PFD1 and PFD2 (see Figure 8-1.)
8. Remove airplane from jacks.
9. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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Figure 8-1, Low Speed Awareness Band Symbolization
8.12
RVSM Checks
The following are required initial and continued airworthiness checks to verify proper
configuration for operation in RVSM airspace. RVSM operations are prohibited until the all of
the RVSM checks are completed successfully. Any changes to the aircraft external
configuration, such as the installation of additional antennas, probes, fairings or radomes along
the sides of the airplane, that may impact the air data system or aircraft performance may also
invalidate the RVSM certification for this aircraft.
8.12.1 RVSM Required Avionics Check
With the PFD in configuration mode, select the Aux – System Status page using the small
FMS knob. Press the small FMS knob to activate the cursor. Highlight each of the following
items in the LRU window and verify that the required software part number and version matches
the information in the General Arrangement drawing listed in Table 1-1. Verify hardware part
number by visual inspection of the units. Record the results in Table 8-1 (next page).
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Table 8-1, RVSM Required Avionics
HARDWARE
DESCRIPTION
ITEM
PART
NUMBER
SOFTWARE
OK
DESCRIPTION
PART
NUMBER
OK
VER
SYSTEM
STATUS
REPORT
MAIN SUB-SYSTEM
GIA1
AUDIO
GIA1
AUDIO
GPS/WAAS ENGINE
GPS1
CERTIFICATION
GAINS
GFC
CERT GIA
1
MAIN SUB-SYSTEM
GIA2
AUDIO
GIA2
AUDIO
GPS/WAAS ENGINE
GPS2
CERTIFICATION
GAINS
GFC
CERT GIA
2
SYSTEM
PFD1
FPGA
PFD1
FPGA
SYSTEM
PFD2
FPGA
PFD2
FPGA
SYSTEM
MFD1
FPGA
MFD
FPGA
GSU 75B
GDC 7400
ADC #1
SYSTEM
GDC1
FPGA
GDC1
FPGA
GSU 75B
GDC 7400
ADC #2
SYSTEM
GDC2
FPGA
GDC2
FPGA
8*
GTX 33(D)
GTX 3000
GTX 335R
GTX 345R
XPDR #1
GTX
33/3000/335/345
SYSTEM
GTX1
9*
GTX 33(D)
GTX 3000
GTX 335R
XPDR #2
GTX
33/3000/335
SYSTEM
GTX2
1
2
3
4
5
6
7
GIA 63W IAU #1
GIA 63W IAU #2
GDU 1050A
PFD#1
GDU 1050A
PFD#2
GDU 1550 MFD
* Any other transponder that meets or exceeds the requirements of TSO-C74c (Mode C) or
TSO-C112 (Class 2a; Mode S) may be installed.
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8.12.2 RVSM Critical Region Visual Inspection
The RVSM critical region is a 24 x 24 inch area around the static ports on both sides of the
airplane. The corners of the RVSM critical region are to be marked on the aircraft with placards
or paint of a contrasting color (see Figure 8-2.) The RVSM critical region must meet the
following visual inspection criteria:
1. The fuselage skin must be free from damage. All skin repairs within the RVSM critical
region must be flush (no external doublers). If any damage is found, the area must be
repaired. Locations of existing protruding head rivets in frames and skin laps are
acceptable.
2. The paint (including stripes) must be uniform and smooth. Remove any paint blisters or
flaking and sand smooth. Any decals or placards must be flush with no peeling edges.
3. The static ports must be free from any corrosion, elongation of holes, deformation or
obstructions. If any damage is found, replace the static port.
4. The oxygen servicing door on the right hand side must close approximately flush with
the fuselage skin and be free from damage or deformation. For the model 300 only, the
ELT access hole cover on the right hand side must be in place.
AFT
CORNER MARKING - TYPICAL
(USE CONTRASTING COLOR)
12 INCHES
STATIC PORTS
ELT ACCESS HOLE
(RH SIDE ONLY)
OXYGEN SERVICING DOOR
(RH SIDE ONLY)
12 INCHES
10 INCHES
14 INCHES
AFT
Figure 8-2, RVSM Critical Region
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Note that Model B300/B300C aircraft with installation of the Sierra Nevada Corporation (SNC)
Aircraft Survivability System (ASE) include a large external doubler and cover plate which are
within the RVSM critical region as shown in Figure 8-3. These items are installed by SNC
drawing number 01211012, B300 Aft ASE Provisions Installation. For these aircraft, the RVSM
critical region must meet the following additional visual inspection criteria:
The fillet seal around the perimeter of the external doubler must be smooth and uniform.
The protruding head screws must be installed tightly against the cover plate.
The cover plate must fit smoothly against the external doubler.
AFT
EXTERNAL DOUBLER
COVER PLATE
STATIC PORTS
OXYGEN SERVICING DOOR
(RH SIDE ONLY)
AFT
Figure 8-3, RVSM Critical Region (modified)
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8.12.3 RVSM Static Port Height Inspection
The Gauging Assembly p/n SPF-4 (A1M-BCH-GE) is available from Beechcraft. Any alternate
tool authorized in the King Air 300 Series Maintenance Manual for RVSM static port
measurements may be substituted for this tool. Initialize the tool as follows:
1. Make sure the dial indicator reads negative when the plunger is pressed and positive
when the plunger is free.
2. Place the gauging assembly on a flat surface (gauge block or equivalent.)
3. Ensure the smaller needle is at approximately (.1).
4. Rotate the dial indicator to set the large needle at (0) as shown in Figure 8-4.
DIAL INDICATOR
Figure 8-4, Dial Indicator
The static port measurements are obtained at four locations on each static port as shown in
Figure 8-6. These measurements are used to find an AVERAGE and ANGLE for each of the
four static ports. The AVERAGE is calculated by adding the four measurements and dividing
the total by 4. The ANGLE is calculated by subtracting the minimum measurement from the
maximum measurement. The calculated AVERAGE and ANGLE for each static port must fall
within the ranges shown in Figure 8-7.
Perform the static port measurement as follows:
1. Wipe the surface of static ports clean with isopropyl alcohol.
2. Place the gauging assembly onto the static port surface as shown in Figure 8-5.
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DIAL INDICATOR
GAGING ASSEMBLY
STATIC PORT
FUSELAGE SKIN
Figure 8-5, Static Port Measurement
NOTE
The dial indicator shows 0.100 inch when completely flush. Therefore, subtract
the readings from 0.100 inch to determine the actual static port height. This
should be completed before making any calculations.
3. For each static port, measure the static port height at the A, B, C and D locations as
shown in Figure 8-6. Record the measurements in the measurement log, Figure 8-7.
4. Calculate the AVERAGE for each static port using the measurements by adding the four
measurements and dividing the total by 4. Record the AVERAGE in the measurement
log, Figure 8-7.
5. Ensure the AVERAGE for each static port is within tolerance (+0.045 to +0.085 inch.) If it
is not, remove and reinstall the static ports as necessary to meet the tolerance.
6. Calculate the ANGLE for each static port by subtracting the smallest of the A, B, C or D
measurements from the largest of the A, B, C or D measurements. Record the ANGLE
in the measurement log, Figure 8-7.
7. Ensure the ANGLE for each static port is within tolerance (0.000 to +0.026 inch.) If it is
not, remove and reinstall the static ports as necessary to meet the tolerance.
A
B
D
C
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Figure 8-6, Static Port Measurement locations
A
B
C
D
AVERAGE
ANGLE
(A+B+C+D)/4
Largest - Smallest
UPPER LEFT
LOWER LEFT
UPPER RIGHT
LOWER RIGHT
Aircraft s/n:
Date:
Figure 8-7, Static Port Measurement Log
8.12.4 RVSM Air Data System Check
Perform the Air Data Test per Section 7.7.3.
If either the pilot or copilot air data system does not meet the tolerances specified, have
maintenance checks performed on the air data system or the pitot/static system.
IMPORTANT!
RVSM operations are prohibited until the air data system meets all test conditions.
8.12.5 RVSM In-Flight Altitude Hold Check
RVSM operation requires that the autopilot system accurately maintain the acquired altitude
during non-turbulent, non-gust cruise conditions. The autopilot must be maintained in
accordance with the G1000 System Maintenance Manual listed in Table 1-2. The autopilot must
be shown to meet the performance specification of the following in-flight altitude hold test.
1. Verify the following conditions (normal RVSM cruise flight):
• Altitude FL290 to FL350
• Altimeter setting 29.92 in Hg (1013 HPA)
• Autopilot altitude hold engaged
• Non-turbulent, non-gust conditions
2. Record the data from the primary cockpit displays as specified by Table 8-2 every 5
minutes for a minimum flight segment of 30 minutes in length. The maximum altitude
deviation shown on the display throughout the test should not exceed ±65 feet.
If the aircraft fails to hold altitude to this tolerance, repeat the test ensuring that the airspeed
remains constant and the air remains stable during the entire test. If the test still fails, have
maintenance checks performed on the GFC 700 system, then repeat the test. RVSM
operations are prohibited until the autopilot is capable of maintaining altitude within ±65 feet of
the selected cruise altitude.
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Aircraft s/n:
Date:
Enroute To:
Pilot:
Time
(hr:min)
Pilot
Altitude
(ft)
Copilot
Airspeed
(kt)
Altitude
(ft)
Airspeed
(kt)
0:00
0:05
0:10
0:15
0:20
0:25
0:30
0:35
0:40
0:45
0:50
0:55
1:00
Table 8-2, In-Flight Altitude Hold Performance Test
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8.13
ESP Functional Check
NOTE
This procedure is required only for aircraft with the optional Electronic
Stability and Protection (ESP) feature.
1. Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS
MASTER PWR and BATT switches to ON. Ensure G1000 system and components are
powered and operating normally.
2. Verify the DISPLAY BACKUP button on the audio panel is pushed in so that the GDUs
will not operate in reversionary mode.
3. Verify no AHRS, ADC, Autopilot, PFD, AFCS Mode Controller, GCU alert messages or
monitor flags (amber HDG, etc.) are present on PFD1 or PFD2.
4. On initial power up verify that the MFD splash screen includes a graphic similar to the
following:
5. On the GMC 710 couple the Flight Director to the left side by pressing the XFR button.
The arrow that is illuminated indicates which side is coupled. No flight director modes
should be active at this time.
6. On the GCU, rotate the inner FMS knob to activate the Aux – System Setup page on the
MFD.
7. On the MFD Aux – System Setup page press the Setup 2 softkey.
8. Verify that on the MFD SETUP 2 page there is a window for Stability & Protection and the
status is “ENABLED”.
9. Verify on PFD 1 and PFD 2 that there are no “ESP FAIL”, “ESP OFF”, or “ESP DEGRADE”
alert messages.
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10. Cover both GPS1 and GPS2 antennas.
11. Verify on PFD 1 and PFD 2 the ESP Roll Indices are displayed at 45° on the roll indicator
on the Attitude Display.
12. On the GCU, press the inner FMS knob to activate the cursor then rotate the outer FMS
knob to select the Stability & Protection window on the MFD.
13. Rotate the inner FMS knob to change the status to “DISABLED”.
14. Verify that on the MFD Aux – System Setup 2 page Stability & Protection window that
the status is “DISABLED”.
15. Verify on PFD 1 and PFD 2 the ESP Roll Indices are not displayed at 45° on the roll
indicator on the Attitude Display.
16. Verify on PFD 1 and PFD 2 that there is an “ESP OFF” alert message.
17. Remove the cover from both GPS1 and GPS2 antennas.
18. Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS
MASTER PWR, EXT PWR, and BATT switches to OFF.
19. Wait ~ 1 minute before re-applying aircraft power.
20. Apply power to the aircraft and avionics systems by placing the aircraft AVIONICS
MASTER PWR and BATT switches to ON.
21. During power up and GPS satellite acquisition, verify on PFD1 and PFD2 the ESP Roll
Indices are displayed at 45° on the roll indicator on the Attitude Display.
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22. Once AFCS PFT is complete and GPS has acquired satellites, verify on PFD1 and PFD2
the ESP Roll Indices are not displayed at 45° on the roll indicator on the Attitude Display.
23. On the GCU, rotate the inner FMS knob to activate the Aux – System Setup page.
24. On the MFD Aux – System Setup page press the Setup 2 softkey.
25. Verify that on the Aux – System Setup 2 page there is a window for Stability & Protection
and the status is “ENABLED”.
26. Verify on PFD 1 and PFD 2 that there are no “ESP FAIL” or “ESP OFF” alert messages.
27. On the GMC 710, couple the Flight Director to the right side by pressing the XFR button.
The arrow that is illuminated indicates which side is coupled. No flight director modes
should be active at this time.
NOTE
On power up the coupled side will default to the left side. Each time power
is reapplied couple back to the right side and continue test steps.
28. Repeat step 1 thru 27 while coupled to right side.
29. Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS
MASTER PWR, EXT PWR, and BATT switches to OFF.
30. Wait ~ 1 minute before re-applying power for further testing as required.
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8.14
GTS Traffic System Functional Check
This section is applicable to the GTS 820/825 (TAS), GTS 850/855 (TCAS I), and GTS 8000
(TCAS II) traffic systems. Perform the following tests to verify GTS 820/850 or GTS Processor
operational and surveillance functions. Use a ramp tester such as a TIC TR220 or equivalent to
perform the tests.
These tests are performed at field elevation. Note that local traffic targets may appear during the
test and are not an indication of improper system operation.
For these tests, the radar altimeter must read over 2000 feet to play the aural alerts. To make
the radar altimeter read over 2000 feet, disconnect the receive coaxial cable or cover the receive
antenna from the radar altimeter.
To perform these tests for the GTS 8000 TCAS II traffic system, the aircraft must be in a
simulated ‘in-air’ condition. To put the aircraft ‘in-air’, place the aircraft on jacks or actuate the
weight on wheels switches on both L/H and R/H main landing gear.
NOTE
Prior to simulating the ‘in-air’ condition, please contact your local Air Traffic
Control (Center and Approach) and inform them of your intention to perform
aircraft testing that may transmit ADS-B Out signals of an aircraft in the ‘in-air’
condition. Closed hangar doors may not provide adequate isolation from ATC.
Figure 8-8, Traffic Map
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8.14.1 Antenna Test
The following test assures the antennas and coaxial cables are properly connected.
1. On the Map – Traffic Map page of the MFD, perform the following:
a. Press the TAS OPER softkey (for TAS/TCAS I) or press TA Only softkey (for
TCAS II). A self-test of the antenna circuit is initialized. If the MFD displays
FAILURE at the upper left corner of the traffic display area, it will be necessary to
recheck the coaxial connections. If MFD displays OPERATE (for TAS/TCAS I) or
TA ONLY (for TCAS II) without indicating a fault, proceed to the next step of
antenna verification.
b. If an “ADS-B” softkey is displayed, press the softkey to turn it off.
2. Ensure that the transmitter or receiver (TX/RX) that you are testing is significantly closer
to the ramp tester than another operating RX/TX, or erroneous and inaccurate results
may occur. All four quadrants (0, 90, 180 and 270 degrees) relative to the aircraft will be
similarly tested to verify bearing of simulated intruder supplied via the ramp tester are
correctly displayed on the Map – Traffic Map page of the MFD.
3. Set up a stationary intruder by selecting the following on the ramp tester:
•
Intruder type: ATCRBS
•
Intruder Start Distance: 2 nm
•
Intruder Start Altitude: 500 feet above field elevation
•
Vertical Speed: 0 fpm
•
Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and
a stationary intruder is created by not starting the scenario.)
4. Position ramp tester at 0 degrees (i.e. off the nose of the aircraft).
5. Initiate the intruder scenario and verify a target is annunciated on the Map – Traffic Map
page of the MFD at the correct bearing of approximately 0 degree at 2 NM (read as +05
above a filled diamond indicating proximate traffic).
6. On the ramp tester, toggle intruder traffic to standby or off.
7. Reposition ramp tester and reengage the same intruder scenario for 90, 180 and 270
degrees relative to the aircraft.
8. Verify a target is annunciated on the Map – Traffic Map page of the MFD at the same
bearing as the ramp tester.
9. If the bearing is not as anticipated or multiple targets (not including possible local traffic)
are displayed during tests, verify the following:
•
Coax cable connectors are properly secured at the bulkhead adapter fittings,
GA58 antennas, GTS unit and GPA 65 unit (if installed).
•
Connections are made to the proper channels and color-coded heat shrink is the
same color on both ends of coax cables.
•
Connectors are correctly installed on coax cables.
10. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.14.2 Ramp Test
The following test provides a scenario that will converge and intercept the GTS unit to assure
proper operational and surveillance functions.
NOTE
Prior to simulating the ‘in-air’ condition, please contact your local Air Traffic
Control (Center and Approach) and inform them of your intention to perform
aircraft testing that may transmit ADS-B Out signals of an aircraft in the ‘in-air’
condition. Closed hangar doors may not provide adequate isolation from ATC.
1. Disconnect the radar altimeter receive coaxial cable or cover the receive antenna so the
radar altimeter reads over 2000 feet.
2. For GTS 8000 TCAS II test only, perform the following:
a. Change BARO setting to 29.92 in-Hg on PFD1 and PFD2.
b. Set the main landing gear WOW actuators in the air position.
3. On the Map – Traffic Map page of the MFD, perform the following:
a. Press the TAS OPER softkey (for TAS/TCAS I) or TA/RA softkey (for TCAS II).
b. If an “ADS-B” softkey is displayed, press the softkey to turn it off.
4. Position ramp tester at 90 degrees (i.e. off the right wing).
5. Select the following on the ramp tester:
•
Intruder type: ATCRBS
•
Intruder Start Distance: 10 nm
•
Intruder Start Altitude: 300 ft above PFD1 displayed altitude
•
Vertical Speed: 0 fpm
•
Velocity: 360 kts
6. Initiate the intruder scenario and observe the following:
•
The simulated intruder should be acquired at approximately 6-10 NM at 90
degree bearing. Observe intruder closes on own aircraft at a rate of 0.1 NM/sec.
Verify that only a single simulated target is displayed in the expected quadrant
(exclude possible local traffic).
•
The simulated intruder should transition from Other Traffic (displayed as an open
diamond with +03 displayed above), to proximate traffic (displayed as a filled
white diamond with +03 displayed above), to a Traffic Advisory (TA) alarm
(yellow filled circle with +03 displayed above.)
•
For GTS 8000 TCAS II installations, the following applies:
The simulated intruder should transition from a Traffic Advisory (displayed as a
solid yellow circle with +03 displayed above), to a Resolution Advisory (RA)
alarm (red filled square with +03 displayed above). Additionally, a Resolution
Advisory is displayed on the vertical speed tape of PFD1 and PFD2 and an
audible Resolution Advisory is heard over cockpit speakers and headphones.
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NOTE
The aural TA annunciations are muted if the gear is extended (and the
Radar Altimeter indicates below 400 feet).
For GTS 8000 TCAS II, to generate a DESCEND resolution advisory, the
WOW actuators must be set to the in-air position and the Radar Altimeter
must read greater than 2,000 ft.
At the end of these tests, put the aircraft back ‘on-ground’ and restore radar altimeter operation.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
8.15
Activation of Garmin Connext
In order to activate the optional GDL 59 Wi-Fi datalink and optional GSR 56 satellite receiver for
Garmin Connext, contact Garmin Product Support at one of the following numbers (M-F, 7:00
a.m. to 7:00 p.m. USA Central Standard Time):
•
1.866.739.5687 (toll free in USA)
•
+1.913.440.1135 (worldwide)
Have the following information ready prior to calling:
•
•
If activating services for a GDL 59-only installation
o
Aircraft tail number, serial number, manufacturer, and model
o
G1000 system ID number
If activating services for a GDL 59 and GSR 56 installation
o
Aircraft tail number, serial number, manufacturer, and model
o
GSR 56 unit serial number
o
G1000 system ID number
o
Name of aircraft owner and contact information
o
Credit card information
Garmin Connext will provide additional information for activation of data services.
To obtain the G1000 system ID number and GSR 56 unit serial number, accomplish the
following:
1. Turn the large FMS knob on the MFD to select the Aux page group.
2. Turn the small FMS knob to select the Aux – System Status page. Record the SYSTEM
ID number shown in the AIRFRAME field. This number is unique for each G1000 system.
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SYSTEM ID Number Location
3. Use the large FMS knob to scroll the cursor to GSR1 (if GSR 56 is installed). Record the
GSR 56 serial number shown in the LRU INFO field.
For previously activated systems, if the GSR 56 satellite receiver unit is replaced, the new unit
serial number must be registered with Garmin Connext. Contact Garmin Product Support and
follow the activation procedure as described previously in this section.
For previously activated systems, if the GDL 59 Wi-Fi datalink unit is replaced, the system must
be registered again. This can be accomplished by entering the same passcode received during
the initial activation process as described in the following steps:
1. Connect to an available network (reference Section 8.16 for details.)
2. Using the large FMS knob, select the Aux page group on the MFD. Using the small
FMS knob, select the Map – Weather Data Link page.
3. Press the MENU key on the GCU to display the PAGE MENU window.
4. Select “Register With Connext”.
5. With the “Connext Registration” window open, enter the access code (provided by
Garmin Product Support during the initial activation of the system) in the Access Code
field, using the keypad on the GCU, and press the ENT key on the GCU.
NOTE
The replacement GDL 59 unit must be registered again, even if the MFD
already shows Registered in the Status window.
6. With the Register field highlighted, press the ENT key on the GCU.
7. Verify that the Status field indicates Registered and that the data displayed in the Current
Registration field matches the aircraft information.
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8.16
GDL 59 Wi-Fi Data Link Functional Check
This check verifies GDL 59 Wi-Fi Data Link interface is configured and is functional. This check
requires an operating and available wireless network to be within range of the aircraft.
NOTE
This check only verifies the data output from the G1000 equipment. Any
equipment/wiring added that is not part of the installation data will need
separate testing and verification not covered as part of this document.
1. Start the G1000 System in Normal Mode.
2. Using the large FMS knob, select the Aux page group on the MFD. Using the small FMS
knob, select the Aux-Maintenance Wi-Fi Setup page.
3. Press the AVAIL softkey on the MFD to display the available Wi-Fi networks.
4. Press the FMS knob on the GCU to activate the cursor and rotate the small FMS knob to
highlight the desired network in the Available Networks field.
5. Press the Connect softkey on the MFD to connect to the network. (Skip to step 11 if the
selected network is a non-secure network.)
6. If the selected network is a secure network, enter the pass code in the Enter Passphrase
field in the WPA Security Settings pop-up window.
7. Press the ENT key on the GCU to accept the pass code, then press the ENT key on the
GCU again.
8. When the Save Settings pop-up window is displayed, press the ENT key on the GCU
keypad to select Save Connection.
9. Enter the airport identifier in the Airport field, then press the ENT key on the GCU to
accept the identifier.
10. With the Connect button highlighted, press the ENT key on the GCU to connect to the
network.
11. Press the ENT key on the GCU if the verification window “Are you sure you want to
connect?” is displayed.
12. Verify that the Connection Status field on the Aux – Maintenance Wi-Fi Setup page on
the MFD indicates Connected.
13. If no other service is to be performed, continue to the return-to-service checks in Section
9.
8.17
GSR 56 Satellite Receiver Functional Check
1. Power up the PFD1 in configuration mode.
2. On the PFD1, select GDL page group using the large FMS knob.
3. Using the small FMS knob select the GSR56 Configuration page. Verify the page can be
displayed and information is available.
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Figure 8-9, GSR56 Configuration Page
4. Restart the G1000 System in Normal Mode.
5. Using the large FMS knob, select the Aux page group on the MFD. Using the small FMS
knob, select the Aux-Telephone page.
6. Ensure the system is showing Iridium signal strength (best if aircraft is outside).
7. Press TEL button on the pilot’s GMA.
8. Press the Dial softkey on the MFD.
9. Enter the test phone number in the ENTER PHONE NUMBER field using the GCU
keypad.
10. Press the ENT key on the GCU keypad to accept the phone number.
11. Press the ENT key on the GCU keypad to initiate the dialing sequence.
12. When call is complete, press the Hangup softkey on the Aux-Telephone page on the
MFD to end the call.
Figure 8-10, Aux-Telephone page
13. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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8.18
Search and Rescue Functional Check
1. On the MFD, press the “FPL” key to display the Active Flight Plan Menu.
2. Press the “MENU” key to display the PAGE MENU Options.
3. Scroll through the choices with the FMS knob and select “Search and Rescue”.
4. Press “ENT” key to complete the selection and view the SAR flight plan menus.
5. From the Search and Rescue Menu, turn the large and small FMS knobs to enter the
starting waypoint.
6. Press ENT key to complete the selection and move to the next option, “PATTERN” type.
7. Use the FMS knob to move to the PATTERN type and select “PARALLEL”.
8. With the FMS knob scroll through the options and change the fields as desired, or leave
the default entries.
9. Press ENT key with the “ACTIVATE SAR?” field highlighted, to complete and activate
the flight plan.
10. Verify the parallel track search pattern is on the Map – Navigation Map page.
11. If no other service is to be performed, continue to the return-to-service checks in Section
9.
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9. G1000 System Return to Service Procedure
If a G1000 LRU was replaced, verify the correct LRU software part numbers and versions
against the numbers listed on the General Arrangement drawing listed in Table 1-1.
Perform the following subsection tests to confirm the G1000 system is operating correctly.
9.1
Display Test
1. Apply aircraft power. On the MFD power-up screen in the upper right corner, find the
‘King Air B300 Series System XXXX.XX’ number. This number is the G1000 System
Software Loader Image version number that was used to install the software to the
system.
Figure 9-1, MFD Power Up Page
2. Verify that the System Software Version is the same as listed in Table 1 of the 00500629-N2 General Arrangement Drawing.
3. Press the GCU ENT key to acknowledge the ‘DEFAULT PROFILE’ Crew Profile option
on the MFD (NOTE: The rightmost softkey on the MFD may also be used).
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Figure 9-2, PFD Power-up System Annunciations
4. Allow the displays to initialize for approximately one minute. During normal operation,
this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid during the
first ~40-60 seconds of PFD power-up. After two minutes, verify no Red-X’s are present
on both PFDs and the MFD. Examples of potential Red-Xs are shown in Figure 9-2. If
any Red-X’s are present, stop and troubleshoot per Section 5. Examples of PFDs with
no Red-X failure indications are shown in Figure 9-3.
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(Without SVS enabled)
(With SVS enabled)
Figure 9-3, PFD Normal Operation
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NOTE
Outputs from the GRS 77/7800 or GSU 75B (AHRS portion) and GMU
44 are not valid until the units have been calibrated.
5. Check that all COM/NAV fields are valid in the top corners of PFD1 and PFD2.
6. Check that altitude, airspeed, vertical speed, GS, TAS, and OAT fields are valid on
PFD1 and PFD2.
7. Press the PFD Opt softkey on each PFD.
8. Press the SENSOR softkey on each PFD and switch between ADC1 and ADC2. Verify
that data from both GDC air data computers are valid on both displays.
9. Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2.
Verify that data from both GRSs are valid on both displays.
10. Check that engine instrument fields are valid on the MFD.
11. Verify that no MANIFEST alert messages appear in the lower right corner (press the
flashing ALERTS softkey to view alert messages). If any MANIFEST errors appear, the
correct software to the related LRU must be loaded before proceeding.
9.2
Display Failure Test
Step
Desired Result
MFD Failure Condition:
1. Open MFD CB.
2. Verify desired results.
3. Close MFD CB.
For an MFD failure condition, the following shall occur:
PFD2 Display Failure Condition:
1. Open PFD 2 CB.
2. Verify desired results.
3. Close PFD 2 CB.
•
•
MFD goes blank.
•
The COM 1/2 and NAV 1/2 tuning fields remain valid
and can be tuned by rotating the tuning knobs on
PFD1 and PFD2.
•
XPDR 1/2 fields remain valid and XPDRs can adjusted
via PFD softkeys.
All PFD1 and PFD2 primary flight information is
retained.
For a PFD2 failure condition, the following shall occur:
•
•
PFD2 goes blank.
PFD1 and MFD remain in normal display formats. The
following illuminate on PFD1:
o
o
o
o
o
•
•
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A white HDG box adjacent to the heading window
A white ROL box adjacent to the roll scale
A white PIT box adjacent to the pitch ladder
A white IAS box in the airspeed tape
A white ALT box in the altitude tape
GMA2 Fail – GMA2 is inoperative.
XPDR2 Fail – XPDR2 is Inoperative.
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Step
Desired Result
PFD1 Display Failure Condition:
1. Open PFD 1 PRI and PFD1 SEC circuit
breakers.
2. Verify desired results.
3. Close PFD 1 PRI and PFD1 SEC circuit
breakers.
For a PFD1 failure condition, the following shall occur:
•
•
PFD2 and MFD remain in normal display formats. The
following illuminate on PFD2:
o
o
o
o
o
•
•
9.3
PFD1 goes blank.
A white HDG box adjacent to the heading window
A white ROL box adjacent to the roll scale.
A white PIT box adjacent to the pitch ladder
A white IAS box in the airspeed tape
A white ALT box in the altitude tape
GMA1 Fail – GMA1 is inoperative.
XPDR1 Fail – XPDR1 is Inoperative.
Reversion Mode Check
1. Push the red DISPLAY BACKUP button on the pilot-side GMA 1347D. Verify that the
pilot-side PFD and MFD displays enter reversion mode (See Figure 9-4). MFD should
have valid altitude, airspeed, vertical speed, COM 1, COM 2, NAV 1, NAV 2 and engine
instruments.
Figure 9-4, GDU Reversionary Mode
2. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify
PFD1 and MFD return to normal display modes.
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3. Repeat Step 1 using GMA 2. Ensure that PFD 2 and MFD enter reversion mode and
MFD displays valid altitude, airspeed, vertical speed, COM 1, COM 2, NAV 1, NAV 2
and engine instruments.
4. De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button.
Verify PFD 2 and MFD return to normal display modes.
9.4
Cooling Fan Fail Annunciation Check
Do the following to verify the cooling fans and annunciations are functioning properly
Step
Desired Result
Cooling Fan Failure Conditions:
1. Ensure the G1000 is in normal mode and verify
that there are no fan related alert messages
displayed in the PFD1 or PFD2 Alerts Window.
2. Pull the following cooling fan circuit breakers:
a) PFD/GIA FANS LEFT
b) PFD/GIA FANS RIGHT
c) MFD FAN
For the cooling fan failure conditions, after a 30-second
delay verify that the following alert messages are
displayed:
Fan Failure reset and acknowledgement:
1. Reset all cooling fan circuit breakers.
2. Acknowledge alerts by pressing the Alerts
softkey on PFD1.
9.5
•
AVN FAN 1 FAIL – Avionics cooling fan #1 is
inoperative
•
AVN FAN 2 FAIL – Avionics cooling fan #2 is
inoperative
•
PFD 1 FAN FAIL – PFD #1 cooling fan is inoperative
•
PFD 2 FAN FAIL – PFD #2 cooling fan is inoperative
•
MFD FAN FAIL – MFD cooling fan is inoperative
Verify the above alerts extinguish.
GPS Signal Acquisition
This test requires the aircraft to be outside to see the GPS satellites or indoors with a GPS
repeater.
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Figure 9-5, AUX-GPS Status Page
Select the AUX - GPS Status page on the MFD. After the G1000 system has been on for a
minimum of two minutes, toggle between GPS 1 and GPS 2 using the two softkeys on the
bottom of the display. Verify that both receivers show a 3D GPS Solution in the GPS Status
field.
9.6
GPS Failure Test
Before starting this test, create a simple Direct-To flight plan to an airport or other waypoint that
is greater than 31 NM from the present aircraft position. Verify that the phase of flight displayed
on the GPS CDI is ENR.
Step
Desired Result
Single GPS Failure Condition:
1. Ensure GPS satellites are acquired.
2. Place a shroud over the GPS antenna for GIA 1
to prevent signal reception. Verify loss of signal
on MFD Aux – GPS Status page.
3. Check for desired results.
4. Remove shroud from the GIA 1 GPS antenna
and allow system to re-acquire satellites.
5. Place a shroud over the GPS antenna for GIA 2
to prevent signal reception. Verify loss of signal
on MFD Aux – GPS Status page.
6. Check for desired results.
7. Remove shroud from the GIA 2 GPS antenna.
For each of the single GPS failure conditions, the following
shall remain valid on the PFD throughout the procedure:
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• Attitude and Heading from AHRS.
• Airspeed, Altitude, Vertical Speed, and OAT from Air
Data Computer.
• GPS Course Deviation Indicator
For a GIA1 GPS Failure, an amber BOTH ON GPS2 is
displayed on PFD 1 and PFD 2.
For a GIA2 GPS Failure, an amber BOTH ON GPS1 is
displayed on PFD 1 and PFD 2.
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Step
Desired Result
Dual GPS Failure Condition:
1. Ensure GPS satellites are acquired.
2. Cover both GPS antennas. Verify loss of signal
on Aux – GPS Status page.
3. Check for desired results.
4. Remove shrouds from GPS antennas.
5. Allow both receivers to re-acquire satellite
signals before continuing.
For a dual GPS failure condition, the following shall occur:
• GPS CDI flags LOI on both PFDs.
• Attitude and Heading remain valid from both AHRS
on both PFDs.
• Airspeed, Altitude, Vertical Speed and OAT remain
valid from both Air Data Computers on both PFDs.
• LOI appears on MFD Map.
• TAWS N/A aural alert & annunciation given.
When GPS satellites are re-acquired, verify that the INTEG
OK annunciation is given on the HSI in white for a brief
period of time then disappears.
After ~10 seconds of stable GPS position reacquisition,
verify the TAWS AVAILABLE aural alert is given.
Verify that the system returns to normal navigation mode
(GPS CDI restored, LOI annunciation removed, & GPS
data magenta).
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9.7
GIA Failure Test
Step
GIA 1 Failure Condition:
1. Ensure GPS satellites are acquired.
2. Open GIA1 primary and secondary CBs.
3. Verify desired results.
4. Close GIA1 primary and secondary CBs. Allow
system to re-acquire satellites and return to
normal display modes.
GIA 2 Failure Condition:
1. Open GIA 2 CB.
2. Verify desired results.
3. Close GIA 2 CB. Allow system to re-acquire
satellites and return to normal display modes.
Dual GIA Failure Condition:
1. Open GIA 1 primary and secondary CBs and
GIA 2 CB.
2. Check for desired results.
3. Restore power to both GIA units.
Desired Result
For a GIA 1 failure condition, the following shall occur:
•
NAV 1 and COM 1 tuning fields on PFD1 and PFD2
are invalid (red X).
•
•
•
•
•
•
L/R engine data remains valid
•
AHRS and ADC data remain valid on PFD 1 and PFD
2.
XPDR 1 is Inoperative.
GMA 1 Is Inoperative.
AHRS 1 is using backup GPS source.
AHRS 2 not receiving backup GPS Information.
An amber BOTH ON GPS2 is displayed on PFD 1
and PFD2.
For a GIA 2 failure condition, the following shall occur:
•
NAV 2 and COM 2 tuning fields on PFD 1 and PFD 2
are invalid (red X).
•
•
•
•
•
•
L/R engine data remains valid.
•
AHRS and ADC data remain valid on PFD 1 and PFD
2.
XPDR 2 is Inoperative.
GMA 2 Is Inoperative.
AHRS 2 is using backup GPS source.
AHRS 1 not receiving backup GPS Information.
An amber BOTH ON GPS1 is displayed on PFD 1
and PFD 2.
For a dual GIA failure, the following shall occur:
•
•
•
•
•
•
•
•
•
COM 1/NAV 1 & COM 2/NAV 2 fields flag invalid.
GPS CDI flags LOI on PFD
NAV 1 & NAV 2 CDI loses deviation bar.
XPDR field flags invalid on PFD.
Engine Instrument field flags invalid on MFD.
All AHRS & ADC fields remain valid.
Red AFCS status annunciation given.
TAWS FAIL annunciation given.
ADF/DME windows flag invalid.*
*If equipped.
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9.8
GEA Functional Check
1. Verify the MFD engine instruments are displayed and indicate valid readings. Reference
figure below for normal EIS Display.
2. On GMA1, select DISPLAY BACKUP button. Observe MFD in reversion mode and
verify all engine instruments are displayed and indicate valid readings. Reference figure
below for reversion mode EIS display.
Normal EIS Display
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Reversionary EIS Display
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9.9
Standby Instrument Electrical Power Checks
This section tests the standby electrical power for the standby MD 302 instrument or standby
analog attitude indicator, standby altimeter, and the standby airspeed indicators. (The magnetic
compass is tested in each Phase inspection during the cockpit lights check in the Beechcraft
King Air 300 Series Maintenance Manual, listed in Table 1-1.)
Step
Desired Result
1.
Verify the STANDBY BATTERY annunciator/switch is not
illuminated.
2.
3.
4.
Remove or ensure external aircraft power is
removed. Set main battery switch to OFF.
Ensure the STBY INSTR (or STBY ATT and
STBY ALTM) circuit breaker(s) are closed.
Ensure the MASTER PANEL LIGHTS rocker
switch in the overhead panel is in the ON
position.
Ensure the STBY INSTR knob is turned to full
bright.
Select (depress) the STANDBY BATTERY switch.
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Verify the following:
•
For airplanes with MD 302 standby instrument installed.
o The MD 302 is activated, initializes, and
displays an attitude indication of the top
display and airspeed and altitude tapes on
the bottom display.
o The MD 302 brightness has limited
adjustment by rotating the knob on the bezel.
•
For airplanes with analog standby instruments installed.
o STBY Attitude indicator motor is energized as
indicated by the indicator motor and the
absence of OFF flag.
o STBY altimeter vibrator is active as indicated
by vibrator noise and absence of flag.
o STBY attitude, STBY Altimeter, STBY
Airspeed indicators are illuminated full bright.
•
Amber “ON” is annunciated full bright on the STANDBY
BATTERY switch.
•
White STANDBY BATTERY legend on the standby
battery switch is illuminated full bright.
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Step
Desired Result
Activate aircraft power by selecting the “on” position
of the BATTERY switch.
•
“ON” annunciation should extinguish on the STANDBY
BATTERY switch.
•
“ARM” should be fully illuminated (green) on the
STANDBY BATTERY switch.
•
White STANDBY BATTERY legend on the standby
battery switch remains illuminated.
•
For airplanes with MD 302 standby instrument installed.
o The MD 302 remains activated and displays
an attitude indication of the top display and
airspeed and altitude tapes on the bottom
display.
o The MD 302 brightness may be fully adjusted
by rotating the knob on the overhead panel.
•
For airplanes with analog standby instruments installed.
o The STBY attitude, STBY altimeter and STBY
airspeed instrument lighting reverts to the
aircraft settings.
o The STBY attitude OFF flag not present and
STBY altimeter vibrator remains active.
Deselect the STANDBY BATTERY switch
Remove aircraft power by selecting the battery
switch to “OFF” position.
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Verify the following:
Verify the following:
•
“ARM” annunciation extinguishes on the STANDBY
BATTERY switch.
•
White STANDBY BATTERY legend on the standby
battery switch remains illuminated.
•
For airplanes with MD 302 standby instrument installed.
o The MD 302 remains activated and displays
an attitude indication of the top display and
airspeed and altitude tapes on the bottom
display.
o The MD 302 brightness may be adjusted by
rotating the knob on the overhead panel.
•
For airplanes with analog standby instruments installed.
o STBY attitude OFF flag not present and
STBY altimeter vibrator remains active.
Verify the following:
•
White STANDBY BATTERY legend on the standby
battery switch extinguishes.
•
The magnetic compass is no longer illuminated.
•
For airplanes with MD 302 standby instrument installed.
o Both displays on the MD 302 are blank.
•
For airplanes with analog standby instruments installed.
o The STBY Attitude OFF flag is in view is
deactivated (the sound of the motor may be
present as the gyro spools down).
o The STBY altimeter vibrator is deactivated.
o The STBY attitude, STBY altimeter, STBY
airspeed are no longer illuminated.
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9.10
G1000 Backup Path Test
With all three displays in normal mode and the entire avionics system turned on, verify on PFD1
there is not a system alert message stating “Failed Data Path". If this message is present,
troubleshoot per Section 5.1.1 and resolve the issue before continuing.
9.11
GFC 700 Ground Checkout
The following procedures verify the proper operation of the GFC 700 AFCS, after maintenance
has been performed. The technician performing these checks should be thoroughly familiar
with the G1000 and GFC 700. Information on the installation and operation of the GFC 700 can
be found by referring to Sections 6.12 and the G1000 King Air 300 Series Cockpit Reference
Guide, listed in Table 1-2.
NOTE
In the sections that follow, an Autopilot disconnect should be accompanied by an
aural alert (two-second tone) unless otherwise specified.
9.11.1 Pre-Flight Test
1. Turn off the AVIONICS MASTER PWR, EXT PWR, and BATT switches and ground
power unit. After 30 seconds select the ground power unit, BATT, and EXT PWR
switches to ON. Verify the GFC 700 begins an automatic pre-flight test after AHRS and
ADC parameters become valid.
2. Verify that a white PFT annunciation is displayed on PFD1 and PFD2.
NOTE
A momentarily red
acceptable.
annunciation displayed before PFT starts is
3. Upon successful completion of the test, an aural alert will sound and the annunciation
will clear. The aural alert is generated by either GIA 63W #1 or GIA 63W #2, alternately,
with each system power-up. Thus, the PFT sequence must be run twice to verify both
GIA units are providing the correct aural alert.
NOTE
If the ‘PFT’ annunciation turns red, the test has failed. Return to Section 5 for
troubleshooting.
4. Repeat Steps 1 - 3 to test the PFT aural alert for the other GIA 63W.
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9.11.2 AFCS Switch Checks
Verify that the AFCS system buttons and switches are operating correctly by performing the
following:
1. Actuate both sections of the PITCH TRIM (NOSE UP/NOSE DN) switch to activate
Manual Electric Pitch Trim (MEPT). Verify the trim clutch engages and the trim wheel
drives in the requested direction. Check operation in both the up and down direction.
2. Press the AP/YD DISC TRIM INTRPT switch and hold while actuating the manual
electric trim switch. Verify trim does not run and the trim wheel rotates freely when
moved manually. Release the AP/YD DISC TRIM INTRPT button and PITCH TRIM
switch.
3. Engage the autopilot by pressing the AP key on AFCS mode controller. Press and hold
the left section of the manual electric trim switch. Verify the Autopilot disengages
normally with an aural alert and the trim wheel rotates freely when moved manually.
4. Engage the autopilot again by pressing the AP key on the AFCS mode controller. Verify
the pitch and roll clutches engage and resist movement of the control wheel. Press and
hold the CWS switch and verify the control wheel moves freely when moved manually.
Verify the green ‘AP’ at the top of PFD 1 and PFD 2 is replaced by a white ‘CWS’.
5. Release the CWS switch and press the ‘XFR’ key on the AFCS mode controller. Verify
the clutches are engaged and resist movement of the control wheel. Press and hold the
CWS switch and verify the control wheel moves freely when moved manually. Verify the
green ‘AP’ at the top of PFD 1 and PFD 2 is replaced by a white ‘CWS’.
6. Release the CWS switch and press the AP/YD DISC TRIM INTRPT switch on the pilots
control wheel. Verify the autopilot disengages with a flashing amber ‘AP’ annunciation
on PFD 1 and PFD 2, accompanied by an aural alert. Verify that the control wheel is
free in pitch and roll axes.
7. Engage the autopilot again by pressing the ‘AP’ key on the AFCS mode controller.
Open AFCS SERVOS circuit breaker. Verify the autopilot disconnects and the abnormal
disconnect is provided, consisting of a continuous aural alert and a flashing red/white
‘AP’ annunciation. Verify no AFCS annunciations (e.g. AFCS, PFT, Mistrim) remain on
PFD 1 or PFD 2. Press the AP/YD DISC TRIM INTRPT switch to cancel the abnormal
alert. Close the AFCS SERVOS circuit breaker to restore power to the system and wait
for completion of the pre-flight test sequence.
8. Engage the autopilot again by pressing the ‘AP’ key on the AFCS mode controller.
Ensure the autopilot is coupled to GIA 1 by verifying the arrowhead next to the ‘XFR’ key
on the AFCS mode controller is pointing to the pilot’s side. If the arrowhead points to the
copilot’s side, press the ‘XFR’ key. Open GIA 1 primary and secondary circuit breakers.
Verify the autopilot disconnects with a continuous aural alert and a flashing red/white
‘AP’ annunciation. Press the AP/YD DISC TRIM INTRPT switch to cancel the alert and
annunciation. Close the GIA1 primary and secondary circuit breakers and wait for
completion of the pre-flight test sequence.
9. Press the ‘XFR’ key on the AFCS mode controller and engage the autopilot by pressing
the ‘AP’ key on the AFCS Mode Controller. Press the AP/YD DISC TRIM INTRPT
switch on the pilot side to disconnect the autopilot; verify the flashing amber ‘AP’ alert is
displayed on PFD 1 and PFD 2.
10. Press the GO AROUND button on the left throttle. Verify ‘TO’ is annunciated on PFD 1
and PFD 2 for both PITCH and ROLL modes and the command bars should be at 10
degrees nose up and wings-level.
G1000 NXi System Maintenance Manual
King Air 300 Series
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Revision 2
11. Press the Flight Director (FD) key on the AFCS mode controller to deactivate the GA
mode. Press the AP key to engage the autopilot. Press the CWS button for a minimum
of 5 seconds and release; verifying there is no residual force on the control stick for the
pitch axis.
12. Disengage the autopilot by pressing the AP/YD DISC TRIM INTRPT switch on the copilot’s control wheel. Engage VS mode by pressing the VS key on the AFCS mode
controller. Verify PFD 1 and PFD 2 display ‘VS’ in green and indicates a pitch reference
of ‘0 FPM’.
13. Select an altitude using the ALT SEL knob on the AFCS mode controller. Press the FLC
key on the AFCS mode controller and verify that ‘FLC’ is annunciated on PFD 1 and
PFD 2 in green with a reference of 100 KTS.
14. Press the ALT key on the AFCS mode controller and verify that the ‘ALT’ annunciation is
displayed in green on PFD 1 and PFD 2 with an altitude reference equal to the aircraft
altitude (within the nearest 20 feet).
15. Press the FD key and verify that the mode annunciations and command bars are
removed from the display.
9.11.3 Autopilot Clutch Overpower Check
NOTE
The GFC 700 uses electronic torque limiting as well as mechanical slip
clutches to limit the maximum servo effort. When the system is on the ground,
the electronic torque limiting is removed, allowing manual checks of the slipclutch settings.
1. Engage the Autopilot by pressing the AP key on the AFCS mode controller.
2. Manually overpower the autopilot clutches in pitch, roll and yaw. If the Autopilot clutches
cannot be overpowered, check the GSM 86 clutch cartridge. Refer to the servo
installation drawing (listed in Table 1-1) as applicable.
3. Actuate and hold PITCH TRIM switch in either the NOSE UP or NOSE DOWN direction
to disconnect the autopilot. While the trim is running, restrain the aircraft pitch trim
wheel and verify that the trim clutch can be overpowered. If it cannot be overpowered,
check the GSM 86 clutch cartridge. Refer to the pitch trim servo installation drawing
listed in Table 1-1.
4. Engage the autopilot by pressing the AP key on the AFCS mode controller. Actuate and
hold the manual electric trim switch in either the up or down direction to disconnect the
autopilot. Verify that the trim wheel moves smoothly in both directions throughout the
entire trim range during manual electric trim operation. If the trim wheel hesitates, this
may indicate that the pitch trim clutch is slipping and proper clutch setting or clutch
cartridge and cable tension should be verified. Refer to the King Air 300 Series
Maintenance Manual and Pitch Trim Servo Install drawing, listed in Table 1-1, for clutch
settings and cable tensions. If both clutch setting and cable tension are within tolerance,
check the aircraft pitch trim system for excessive friction. Refer to the Beechcraft King
Air 300 Series Maintenance Manual listed in Table 1-2.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 386
Revision 2
9.11.4 Manual Electric Pitch Trim Speed Check
1. Run MANUAL ELECTRIC PITCH TRIM in one direction until it runs against the
mechanical stop.
2. Run the trim in the opposite direction, and using a stop watch or equivalent device, time
the trim speed to the opposite mechanical stop. Verify the elapsed time for full travel
measures 13 ± 3 seconds.
9.11.5 Autopilot Operation Checks
1. Engage the Autopilot by pressing the AP key on the AFCS mode controller. Push the
HDG knob to synchronize the heading bug to the current aircraft heading. Select HDG
mode by pressing the HDG key on the AFCS mode controller. Verify the command bars
are level and the control wheel is stationary. (There may be some roll motion in the yoke
if the aircraft not perfectly level.)
2. Turn the HDG knob to the left and right and check that the command bars move in the
correct direction and the control wheel follows the command bars.
3. Push and hold the CWS button and pull the control wheel to the center of the pitch
control range. Release the CWS button. Verify the autopilot clutches re-engage and
hold the wheel stationary.
4. Holding the control wheel lightly, rotate the NOSE UP/DN wheel on the AFCS mode
controller two clicks UP to increase the pitch reference. Verify the command bars move
up 1 degree and the control wheel begins moving aft. (In some aircraft, the down spring
may require manual assistance to get aft control stick movement).
5. While holding the control wheel firmly, press and hold the CWS button to re-synchronize
the pitch reference. Re-center the control wheel to wings level and mid-range elevator
travel. Release the CWS button and check that servo clutches re-engage before
releasing the control wheel.
6. Rotate the NOSE UP/DN wheel on the AFCS mode controller two clicks DOWN to
decrease the pitch reference. Verify the command bars move down 1 degree and the
control wheel begins moving forward. Hold the controls and press CWS to re-center the
command bars and stop control wheel movement.
7. With the Autopilot still engaged and the CWS button pressed, move the control wheel to
its aft limit. Release the CWS button and apply continuous forward pressure, slowly
moving the control wheel. After a brief delay, verify the trim wheel begins moving in a
trim up direction.
8. Grip the control wheel and press the CWS button. Verify trim motion stops. Move the
control wheel to the forward limit and release the CWS button. Slowly move the control
wheel aft. After a brief delay, verify the trim wheel begins to trim down. Relieve
pressure on the wheel and verify the trim motion stops. Check that the trim wheel is free
to turn. Hold the control wheel and press the AP/YD DISC TRIM INTRPT switch to
disconnect the autopilot.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
9.11.6 VOR/LOC/GS Test
Perform the following test using ramp test equipment. Operate the equipment according to the
test equipment manufacturer’s instructions.
NOTE
The PFD HSI does not show a course deviation bar unless a valid VHF NAV
frequency is tuned.
1. Ensure FD is coupled to PFD 1 as indicated by a left pointing arrow next to the XFR
button.
2. Simulate a VOR signal on a radial equivalent to the aircraft heading. Tune the NAV 1
and NAV 2 receivers to the simulation frequency.
3. Set the HSI on PFD 1 to VOR1 by pressing the CDI softkey until VOR1 is selected. Set
the HSI on PFD 2 to VOR2 by pressing the CDI softkey until VOR2 is selected. Rotate
CRS1 and CRS2 knobs to set VOR1 and VOR2 course pointers to aircraft heading.
(CDI Synchronization must be set to OFF on the Aux – System Setup 1 page on the
MFD.)
4. Verify full scale deflection of VOR1 and VOR2 CDI by varying the selected course at
least 10° left and right. Reset course pointers to aircraft heading.
5. Engage the autopilot and press the NAV key on the AFCS mode controller. Using the
CRS1 knob alter course by 10° to the right. Verify the flight director and aircraft controls
respond by flying to the VOR course. Repeat to the left.
6. Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller. Verify FD
is coupled right as indicated by a right pointing arrow on the AFCS mode controller next
to the XFR button. Repeat step 5 using CRS2 knob while coupled to PFD2.
7. Set CRS1 and CRS2 course pointers to aircraft heading.
8. Simulate a Localizer/Glideslope signal. Tune this signal on NAV 1 and NAV 2 receiver.
Set the PFD 1 HSI to LOC1 and PFD 2 HSI to LOC2 by pressing CDI softkey until LOC1
and LOC2 is selected. Use the test equipment to center the deviation bars (localizer and
glideslope) on PFD1 and PFD2.
9. Press the APR key on the AFCS mode controller. Verify that the LOC and GS
annunciations are green on PFD 1 and PFD 2. Apply right/left and up/down
localizer/glideslope signals using the test equipment. Verify that the Flight Director and
flight controls respond appropriately.
10. Couple FD to PFD 1 by pressing the XFR button on the AFCS mode controller. Verify
FD is coupled to PFD 1 as indicated by a left pointing arrow on the AFCS mode
controller next to the XFR button.
11. Repeat step 9 while coupled to PFD 1.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
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Revision 2
9.12
Maintenance Records
The Configuration Checklist in Section 3.6 should be completed when a Service Bulletin
software update has been performed and maintained with the aircraft permanent records.
Record the following information:
•
Part number of the G1000 software loader card used to perform software loading or
software updates.
•
Record part and serial numbers of any LRU which was replaced.
•
Record any database updates which were performed during maintenance.
•
Any other applicable information related to the maintenance work performed on the
aircraft.
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
Page 389
Revision 2
APPENDIX A - Garmin Unit Part and Serial Number Cross Reference
This table allows shows the unit part number and serial number prefix combinations.
LRU
GIA 63W
GDU 1050A (PFD 1 & PFD 2)
GDU 1550 (MFD)
GMA 1347D
GEA 71
GDC 7400 (OPTIONAL)
GRS 77 (LEGACY)
GRS 7800 (OPTIONAL)
GMU 44
GSU 75B
GTX 33 (LEGACY)
GTX 33D (OPTIONAL)
GTX 3000 (OPTIONAL)
GTX 335R (OPTIONAL)
GTX 345R (OPTIONAL)
GCU 477
GMC 710
GDL 59
GDL 69A (LEGACY)
GDL 69 SXM
GSD 41
GWX 68
GWX 70
GSA 80 PITCH SERVO
GSA 80 ROLL SERVO
GSA 9000 YAW SERVO
GSA 80 PITCH TRIM SERVO
GTS PROCESSOR (OPTIONAL)
GTS 820 TAS (OPTIONAL)
GTS 850 TCAS I (OPTIONAL)
GRA 5500
FLIGHT STREAM 510 (OPTIONAL)
G1000 NXi System Maintenance Manual
King Air 300 Series
190-00716-N1
PART NUMBER
SERIAL NUMBER FIRST
THREE DIGITS
011-01105-20
011-03470-10
011-03472-00
011-01257-20
011-00831-00
011-02337-00
011-02337-01
011-00868-10
011-02278-00
011-02278-01
011-00870-10
011-00870-20
011-03094-40
011-00779-30
011-00779-21
011-01997-00
011-03301-00
011-03303-00
011-01428-00
011-01428-20
011-01020-10
011-01746-00
011-00987-00
011-03177-10
011-01457-00
011-00883-20
011-01768-00
011-00877-20
011-00877-20
011-02213-00
011-02213-10
011-00877-21
011-02571-00
011-01446-00
011-01553-00
011-02537-00
011-03595-00
1HQ
494
496
171
467
1U60
1U61
420
25M
4DK
1CM
39Z
4E4
891
848
20S
3EF
3EH
194
48Y
220
1EJ
477
3NV
169
472
1DP
19Z
19Z
1R9
2JL
1A0
28P
1EA
1EB
2F8
402
Page A-1
Revision 2
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