Garmin | G1000: Beechcraft King Air C90A/C90GT/C90GTi | Garmin G1000: Beechcraft King Air C90A/C90GT/C90GTi G1000/GFC700 System Maintenance Manual/ICA, Beechcraft Model C90A/C90GT/C90GTi King Air

Garmin G1000: Beechcraft King Air C90A/C90GT/C90GTi G1000/GFC700 System Maintenance Manual/ICA, Beechcraft Model C90A/C90GT/C90GTi King Air
G1000 / GFC 700 System Maintenance Manual
Beechcraft Model C90A/C90GT/C90GTi King Air
Contains Instructions for Continued Airworthiness for STC
#SA01456WI-D
190-00682-01
February 2017
Revision L
© Copyright 2007-2017
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,
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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
RECORD OF REVISIONS
Revision Revision Date
Description
ECO #
J
9/17/2015
Updated Section 4.12 procedure
K
4/22/2016
Removed standby instrument P/Ns from AWL in 142292
Section 4.1 for standby instrument power checks
every 220 hours. Updated standby attitude
instrument P/N to 4200-1( ) in Section 2.2.18.
L
2/22/2017
Add GDL69A legacy and GDL69A SXM software loading
procedures. Add GTX 33D information. Delete Configurations
1, 11, 12, 13, 14, 15, 16 and 20
Page ii
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132916
141046
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
190-00682-01
DOCUMENT PAGINATION
Section
Pagination
Table of Contents
ii – xvi
Section 1
1-1 – 1-6
Section 2
2-1 – 2-14
Section 3
3-1 – 3-78
Section 4
4-1 – 4-40
Section 5
5-1 – 5-88
Section 6
6-1 – 6-16
Section 7
7-1 – 7-50
Section 8
8-1 – 8-6
Section 9
9-1 - 9-16
Section 10
10-1 - 10-2
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
190-00682-01
Page iii
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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 ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean,
lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective
coatings.
IMPORTANT
All G1000 screen shots used in this document are current at the time of publication. Screen
shots are intended to provide visual reference only. All information depicted in screen
shots, including software file names, versions and part numbers, is subject to change and
may not be up to date.
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190-00682-01
TABLE OF CONTENTS
PARAGRAPH
1
PAGE
INTRODUCTION ......................................................................................................... 1-1
1.1
CONTENT, SCOPE, PURPOSE ....................................................................................... 1-1
1.2
APPLICABILITY ............................................................................................................. 1-1
1.3
IDENTIFYING AN STC CONFIGURATION .......................................................................... 1-1
1.4
G1000 SYSTEM SOFTWARE VERSION AND AIRCRAFT CONFIGURATION CHECK................ 1-2
1.5
ORGANIZATION ............................................................................................................ 1-3
1.6
DEFINITIONS/ABBREVIATIONS ....................................................................................... 1-4
1.6.1
Units of Measure ......................................................................................................................... 1-4
1.7
PUBLICATIONS ............................................................................................................. 1-5
1.8
REVISION AND DISTRIBUTION ........................................................................................ 1-6
2
SYSTEM DESCRIPTION ............................................................................................ 2-1
2.1
EQUIPMENT DESCRIPTIONS .......................................................................................... 2-1
2.1.1
GDU 1040A PFD (2) & GDU 1500 MFD ..................................................................................... 2-1
2.1.2
GMA 1347D Audio Panel (2) ....................................................................................................... 2-2
2.1.3
GMC 710 AFCS Control Unit ...................................................................................................... 2-2
2.1.4
GCU 475 FMS Control Unit ......................................................................................................... 2-2
2.1.5
GIA 63W Integrated Avionics Unit (2) ......................................................................................... 2-3
2.1.6
GEA 71 Engine/Airframe Unit (2) ................................................................................................ 2-4
2.1.7
GTX 33 Mode S Transponder (2) ................................................................................................ 2-5
2.1.8
GDC 74B Digital Air Data Computer (2) ...................................................................................... 2-5
2.1.9
OAT Probe (2) ............................................................................................................................. 2-5
2.1.10
Attitude & Heading Reference System (2) .................................................................................. 2-6
2.1.11
GMU 44 Magnetometer (2) ......................................................................................................... 2-6
2.1.12
GDL 69A/69A SXM Datalink ....................................................................................................... 2-7
2.1.13
Weather Radar ............................................................................................................................ 2-7
2.1.14
GSA 80/81 Servo Motors and GSM 85A/86 Servo Mounts ........................................................ 2-8
2.1.15
Comant CI428-410 / CI428-200 GPS/WAAS Antennas.............................................................. 2-8
2.1.16
Thommen 5A58.22.26K.28.1.XX Airspeed Indicator .................................................................. 2-8
2.1.17
Thommen 3A43.22.35F.28.1.FU Altimeter ................................................................................. 2-8
2.1.18
Mid-Continent 4200-1( ) Attitude Indicator .................................................................................. 2-8
2.1.19
L-3 PS-835(C or D Model) Emergency Standby Battery............................................................. 2-9
2.1.20
Engine Signal Conditioning ......................................................................................................... 2-9
2.2
G1000 OPTIONAL INTERFACES ................................................................................... 2-10
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2.3
ELECTRICAL POWER DISTRIBUTION ............................................................................ 2-10
2.4
SHIELD BLOCK GROUNDS........................................................................................... 2-13
2.5
G1000 SYSTEM BLOCK DIAGRAM ............................................................................... 2-14
3
G1000 CONTROL, OPERATION, AND FULL SOFTWARE LOAD ............................ 3-1
3.1
G1000 CONTROL ........................................................................................................ 3-1
3.1.1
GDU 1040A and GDU 1500 Displays ......................................................................................... 3-1
3.1.2
GCU 475 - MFD Controller .......................................................................................................... 3-3
3.1.3
GMC 710 - AFCS Controls .......................................................................................................... 3-3
3.1.4
GMA 1347D Audio Panel ............................................................................................................ 3-4
3.2
G1000 OPERATION...................................................................................................... 3-6
3.2.1
G1000 Normal Mode ................................................................................................................... 3-6
3.2.2
Reversionary Mode ..................................................................................................................... 3-7
3.2.3
Configuration Mode ..................................................................................................................... 3-8
3.3
G1000 SYSTEM SOFTWARE INFORMATION .................................................................. 3-13
3.3.1
G1000 Software Image ............................................................................................................. 3-13
3.3.2
Loader Card Creation ................................................................................................................ 3-14
3.3.3
Software Files ............................................................................................................................ 3-18
3.3.4
Configuration File Descriptions ................................................................................................. 3-18
3.3.5
Airframe and Optional Configurations ....................................................................................... 3-19
3.3.6
Configuration File Storage ......................................................................................................... 3-27
3.3.7
G1000 Software Load Summary ............................................................................................... 3-30
3.4
G1000 SYSTEM SOFTWARE AND CONFIGURATION LOAD PROCEDURE .......................... 3-31
3.4.1
Third Party STC Documentation and Optional Equipment List ................................................. 3-31
3.4.2
System Power Up ...................................................................................................................... 3-31
3.4.3
MFD & PFD Software Load ....................................................................................................... 3-31
3.4.4
Initial G1000 System Software and Baseline Configuration Load ............................................ 3-32
3.4.5
GDL 69A Legacy Software/Configuration ................................................................................ 3-34
3.4.6
GDL 69A SXM Software/Configuration ..................................................................................... 3-34
3.4.7
GRS AHRS / GMU 44 Magnetometer Software and Configuration Load ................................. 3-35
3.4.8
GWX 68 / 70 Radar Software and Configuration Load ............................................................. 3-35
3.4.9
GSM 85A / 86 Servo Mount Configuration Load ....................................................................... 3-35
3.4.10
King Air C90 Airframe Configuration ......................................................................................... 3-36
3.4.11
Weight and Airspeed Configuration ........................................................................................... 3-37
3.4.12
Non-Garmin Traffic System Option Configuration ..................................................................... 3-39
3.4.13
GTS 8XX Traffic System Option Configuration ......................................................................... 3-40
3.4.14
Stormscope (WX-500) Option Configuration ............................................................................. 3-40
3.4.15
ADF – 60 Option Configuration ................................................................................................ 3-40
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3.4.16
Radar Altimeter Option Configuration ....................................................................................... 3-41
3.4.17
DME 42 Option Configuration ................................................................................................... 3-41
3.4.18
GTX 33 Extended Squitter (ES) Option Configuration .............................................................. 3-41
3.4.19
ESP Support Option Configuration............................................................................................ 3-42
3.4.20
GSR56 ....................................................................................................................................... 3-42
3.4.21
Update Config Module ............................................................................................................... 3-43
3.4.22
Jeppesen ChartView Enable ..................................................................................................... 3-43
3.4.23
FliteCharts Enable ..................................................................................................................... 3-44
3.4.24
TAWS B Enable......................................................................................................................... 3-44
3.4.25
TAWS A Option ......................................................................................................................... 3-45
3.4.26
SVS/Pathways Enable .............................................................................................................. 3-45
3.4.27
ESP Enable ............................................................................................................................... 3-46
3.4.28
Optional Search and Rescue Enable ........................................................................................ 3-46
3.4.29
Aircraft Registration Number Entry ............................................................................................ 3-47
3.4.30
GMA 1347 #1 and GMA 1347 #2 Configuration Settings Check .............................................. 3-48
3.4.31
Clearing Default User Settings and Splash Screen Loading .................................................... 3-48
3.5
SOFTWARE AND CONFIGURATION LOAD VERIFICATION ................................................. 3-50
3.5.1
Software Verification.................................................................................................................. 3-50
3.5.2
Airframe Configuration Verification ............................................................................................ 3-51
3.5.3
Stormscope (WX-500) Configuration Load Confirmation. ......................................................... 3-51
3.6
FINAL G1000 SYSTEM SETUP..................................................................................... 3-52
3.6.1
Navigation Database Loading ................................................................................................... 3-52
3.6.2
Terrain/Obstacle Database Card Loading ................................................................................. 3-53
3.6.3
Configuration of Navigation Map for Non-Garmin Traffic System ............................................. 3-54
3.7
G1000 SYSTEM TESTING ........................................................................................... 3-55
3.7.1
Display Testing .......................................................................................................................... 3-55
3.7.2
Cooling Fan Check .................................................................................................................... 3-58
3.7.3
Reversion Mode Check ............................................................................................................. 3-58
3.7.4
GPS Signal Acquisition ............................................................................................................. 3-59
3.7.5
VHF COMM Operational Check ................................................................................................ 3-60
3.7.6
Marker Beacon Test .................................................................................................................. 3-60
3.7.7
VOR/LOC/GS Test .................................................................................................................... 3-61
3.7.8
GTX 33 Testing ......................................................................................................................... 3-61
3.7.9
Airspeed Indicator Check .......................................................................................................... 3-61
3.7.10
TAWS B Functional Check ........................................................................................................ 3-62
3.7.11
FliteCharts Functional Check .................................................................................................... 3-63
3.7.12
ChartView Functional Check ..................................................................................................... 3-64
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3.7.13
SafeTaxi Functional Check ....................................................................................................... 3-65
3.7.14
Aircraft Weight Configuration Functional Check ....................................................................... 3-66
3.7.15
GWX Weather Radar Check ..................................................................................................... 3-70
3.7.16
Traffic System Functional Check (Optional Installation) ........................................................... 3-71
3.7.17
DME Functional Check (Optional Installation) .......................................................................... 3-72
3.7.18
ADF Functional Check (Optional Installation) ........................................................................... 3-73
3.7.19
Gen Purpose A429 Bus Check (Optional Installation) .............................................................. 3-73
3.7.20
Stormscope Functional Check (Optional Installation) ............................................................... 3-74
3.7.21
Non-Garmin Radio Altimeter Check (Optional Installation) ....................................................... 3-75
3.7.22
ESP Functional Check .............................................................................................................. 3-76
3.7.23
Search and Rescue Functional Check ...................................................................................... 3-78
3.8
FINAL TEST ............................................................................................................... 3-78
4
INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ............................................ 4-1
4.1
AIRWORTHINESS LIMITATIONS ...................................................................................... 4-1
4.2
SERVICING INFORMATION ............................................................................................. 4-3
4.2.1
On Condition Servicing ................................................................................................................ 4-3
4.2.2
Required Tools ............................................................................................................................ 4-4
4.2.3
Special Tools ............................................................................................................................... 4-4
4.3
MAINTENANCE INTERVALS ............................................................................................ 4-5
4.3.1
Discontinued Maintenance ........................................................................................................ 4-10
4.4
VISUAL INSPECTION ................................................................................................... 4-11
4.5
ELECTRICAL BONDING TEST ....................................................................................... 4-16
4.5.1
Requirements ............................................................................................................................ 4-16
4.5.2
Test Equipment ......................................................................................................................... 4-16
4.5.3
Phase 3 Electrical Bonding Procedure ...................................................................................... 4-17
4.5.4
Phase 4 Electrical Bonding Procedure ...................................................................................... 4-18
4.6
GRS 77 OR GRS 7800 EARTH MAGNETIC FIELD UPDATES .......................................... 4-18
4.7
GSA 8X GREASING PROCEDURE ................................................................................ 4-19
4.8
FLAPS-IN-MOTION DISCRETE INPUT CHECK ................................................................. 4-20
4.9
SLIP CLUTCH TORQUE AND SERVO CURRENT DISPLAY CHECK PROCEDURE ................. 4-21
4.9.1
Automatic Slip Clutch Test Procedure (SW Version 0636.03 and Subs) .................................. 4-21
4.9.2
Manual Slip Clutch Test Procedure (SW Version 0636.02 and earlier) .................................... 4-23
4.9.3
Servo Adjustment Fixture Procedure ........................................................................................ 4-26
4.9.4
Servo Current Display Check .................................................................................................... 4-27
4.10
G1000 REDUNDANT CONNECTION CHECK .................................................................. 4-29
4.11
ENGINE DATA CHECK ................................................................................................. 4-32
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4.11.1
Torque ....................................................................................................................................... 4-32
4.11.2
ITT ............................................................................................................................................. 4-32
4.11.3
Oil Pressure ............................................................................................................................... 4-33
4.12
TRIM ANNUNCIATOR CHECK ....................................................................................... 4-34
4.13
G1000 MISCOMPARE CHECKS.................................................................................... 4-35
4.14
NOSE AVIONICS COMPARTMENT FANS OPERATIONAL CHECK ....................................... 4-37
4.15
INSTRUMENT PANEL FANS OPERATIONAL CHECK ......................................................... 4-37
4.16
STANDBY BATTERY PERIODIC CHECKS ....................................................................... 4-37
4.16.1
Charge Check ............................................................................................................................ 4-37
4.16.2
Capacity Test............................................................................................................................. 4-39
4.16.3
Cell Isolation Test ...................................................................................................................... 4-40
4.16.4
Charging Procedure .................................................................................................................. 4-40
5
TROUBLESHOOTING ................................................................................................ 5-1
5.1
G1000 ALERTING SYSTEM ........................................................................................... 5-2
5.1.1
Aural & Audio Alerts .................................................................................................................... 5-3
5.2
SYSTEM ANNUNCIATIONS ............................................................................................. 5-4
5.2.1
Failed Path Messages ................................................................................................................. 5-4
5.2.2
System Failure Troubleshooting ................................................................................................ 5-20
5.2.3
Engine/Airframe Instrument Failures ......................................................................................... 5-25
5.2.4
ADF/DME Failure ...................................................................................................................... 5-25
5.3
C90 SERIES SPECIFIC ALERTS ................................................................................... 5-27
5.4
TAWS TROUBLESHOOTING ........................................................................................ 5-28
5.5
SYNTHETIC VISION AND PATHWAYS TROUBLESHOOTING .............................................. 5-29
5.6
GFC 700 AFCS TROUBLESHOOTING .......................................................................... 5-30
5.6.1
General Troubleshooting ........................................................................................................... 5-31
5.6.2
GFC Configuration Alerts (SW Version 0636.03 and Subs) ..................................................... 5-34
5.6.3
GFC Status Page ...................................................................................................................... 5-34
5.6.4
GIA Fault Log Descriptions ....................................................................................................... 5-35
5.6.5
GIA Pre-Flight Test Steps ......................................................................................................... 5-37
5.7
BACKUP COMMUNICATIONS PATH CHECKS .................................................................. 5-44
5.7.1
Overview .................................................................................................................................... 5-44
5.7.2
Data Path Failures ..................................................................................................................... 5-44
5.8
GDU 104X TROUBLESHOOTING ................................................................................. 5-45
5.8.1
GDU 104X Symptoms ............................................................................................................... 5-45
5.8.2
GDU 104X Alerts ....................................................................................................................... 5-46
5.9
GMA SYMPTOMS ....................................................................................................... 5-54
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5.9.1
GMA Alerts ................................................................................................................................ 5-55
5.10
GIA 63 TROUBLESHOOTING ....................................................................................... 5-56
5.10.1
COM Symptoms ........................................................................................................................ 5-56
5.10.2
NAV Symptoms ......................................................................................................................... 5-56
5.10.3
Glideslope Receiver Symptoms ................................................................................................ 5-56
5.10.4
GPS Symptoms ......................................................................................................................... 5-57
5.10.5
GIA Alert Messages................................................................................................................... 5-58
5.11
GEA TROUBLESHOOTING ........................................................................................... 5-65
5.11.1
GEA Alerts ................................................................................................................................. 5-65
5.12
GTX TROUBLESHOOTING ........................................................................................... 5-66
5.12.1
GTX Alerts ................................................................................................................................. 5-66
5.13
GDL 69A OR GDL 69A SXM TROUBLESHOOTING ....................................................... 5-67
5.13.1
GDL 69A or GDL 69A SXM Symptoms ..................................................................................... 5-67
5.13.2
GDL 69A/69A SXM Alerts ......................................................................................................... 5-68
5.14
GRS AND GMU TROUBLESHOOTING ........................................................................... 5-69
5.14.1
AHRS Symptoms....................................................................................................................... 5-69
5.14.2
GRS Alerts ................................................................................................................................. 5-70
5.14.3
GMU Alerts ................................................................................................................................ 5-72
5.14.4
Calibration Procedure E: Magnetometer Interference Test...................................................... 5-72
5.15
GDC 74B TROUBLESHOOTING ................................................................................... 5-76
5.15.1
Air Data Symptoms.................................................................................................................... 5-76
5.15.2
GDC 74B Alerts ......................................................................................................................... 5-76
5.16
GWX 68 OR GWX 70 TROUBLESHOOTING .................................................................. 5-77
5.16.1
GWX Alerts and Problems ........................................................................................................ 5-77
5.17
GMC 710 TROUBLESHOOTING ................................................................................... 5-78
5.17.1
GMC 710 Alerts and Problems .................................................................................................. 5-78
5.18
GCU 475 TROUBLESHOOTING .................................................................................... 5-79
5.18.1
GCU 475 Alerts and Problems .................................................................................................. 5-79
5.19
SOFTWARE/CONFIGURATION TROUBLESHOOTING ........................................................ 5-80
5.19.1
System Communication Hierarchy ............................................................................................ 5-81
5.20
BACKSHELL CONNECTORS ......................................................................................... 5-82
5.21
STANDBY ATTITUDE INDICATOR TROUBLESHOOTING .................................................... 5-86
5.21.1
Standby Attitude Indicator Symptoms ....................................................................................... 5-86
5.22
STANDBY AIRSPEED INDICATOR TROUBLESHOOTING.................................................... 5-86
5.22.1
Standby Airspeed Indicator Symptoms ..................................................................................... 5-86
5.23
STANDBY ALTIMETER TROUBLESHOOTING ................................................................... 5-87
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5.23.1
Standby Altimeter Symptoms .................................................................................................... 5-87
5.24
STANDBY BATTERY TROUBLESHOOTING ...................................................................... 5-87
6
EQUIPMENT REMOVAL & REPLACEMENT ............................................................. 6-1
6.1
GDU 1040A/1500 ....................................................................................................... 6-1
6.2
GMA 1347D AUDIO PANEL .......................................................................................... 6-2
6.3
GIA 63W INTEGRATED AVIONICS UNITS ........................................................................ 6-2
6.4
GEA 71 ENGINE/AIRFRAME UNIT .................................................................................. 6-2
6.5
GTX 33 TRANSPONDER ............................................................................................... 6-3
6.6
GDC 74B AIR DATA COMPUTER ................................................................................... 6-3
6.7
GTP 59 OAT PROBE ................................................................................................... 6-3
6.8
GRS 77 / GRS 7800 AHRS......................................................................................... 6-4
6.8.1
GRS 77 AHRS ............................................................................................................................. 6-4
6.8.2
GRS 7800 AHRS ......................................................................................................................... 6-4
6.9
GMU 44 MAGNETOMETER ........................................................................................... 6-4
6.10
GDL 69A/ OR GDL69A SXM ....................................................................................... 6-5
6.11
GSA 80/81 SERVOS .................................................................................................... 6-5
6.12
GSM 85A / GSM 86 SERVO MOUNTS ........................................................................... 6-6
6.13
GCU 475 .................................................................................................................... 6-6
6.14
GMC 710.................................................................................................................... 6-6
6.15
GWX 68 / GWX 70...................................................................................................... 6-7
6.16
CONFIGURATION MODULE ............................................................................................ 6-8
6.16.1
Configuration Module Removal & Replacement ......................................................................... 6-8
6.16.2
GRS 7800 Configuration Module Removal & Replacement ....................................................... 6-9
6.16.3
Configuration Module Checkout ................................................................................................ 6-10
6.17
GEA 71 BACKSHELL THERMOCOUPLE REMOVAL & REPLACEMENT ............................... 6-11
6.18
GPS/WAAS ANTENNAS ............................................................................................. 6-12
6.19
ENGINE SIGNAL CONDITIONERS .................................................................................. 6-12
6.20
SENIOR AEROSPACE PC920 SIGNAL CONDITIONING UNIT ............................................ 6-13
6.21
INSTRUMENT PANEL ANNUNCIATORS (PROP SYNCH AND STANDBY BATTERY) ............... 6-13
6.22
L-3 AVIONICS (BF GOODRICH) PS-835(C OR D MODEL) EMERGENCY BATTERY............ 6-14
6.23
STANDBY AIRSPEED INDICATOR .................................................................................. 6-14
6.24
STANDBY ALTIMETER ................................................................................................. 6-14
6.25
STANDBY ATTITUDE INDICATOR .................................................................................. 6-15
6.26
AVIONICS COOLING FANS ........................................................................................... 6-15
6.27
GDU COOLING FANS ................................................................................................. 6-16
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6.28
7
TRANSPONDER ANTENNA ........................................................................................... 6-16
G1000 HARDWARE REPLACEMENT - SOFTWARE LOADING AND TESTING ...... 7-1
7.1
GDU 1040/1500 MFD & PFD ...................................................................................... 7-1
7.1.1
GDU Display Software and Configuration Loading ..................................................................... 7-2
7.1.2
PFD/MFD Test............................................................................................................................. 7-5
7.2
GMA 1347D AUDIO PANEL .......................................................................................... 7-7
7.2.1
GMA Software and Configuration Loading .................................................................................. 7-7
7.2.2
GMA 1347D Test ......................................................................................................................... 7-8
7.3
GIA 63W INTEGRATED AVIONICS UNIT ........................................................................ 7-11
7.3.1
GIA 63W Software and Configuration Loading ......................................................................... 7-11
7.3.2
GIA 63W Test ............................................................................................................................ 7-12
7.4
GEA 71 ENGINE/AIRFRAME UNIT ................................................................................ 7-15
7.4.1
GEA 71 Software and Configuration Loading ........................................................................... 7-15
7.4.2
GEA 71 Test .............................................................................................................................. 7-16
7.4.3
Additional GEA 71 Functional Tests .......................................................................................... 7-17
7.5
GTX 33 TRANSPONDER ............................................................................................. 7-24
7.5.1
GTX 33 Software and Configuration Loading ........................................................................... 7-24
7.5.2
Aircraft Registration Number Configuration .............................................................................. 7-25
7.5.3
GTX 33 Test .............................................................................................................................. 7-26
7.6
GDC 74B AIR DATA COMPUTER ................................................................................. 7-27
7.6.1
GDC Software and Configuration Loading ................................................................................ 7-27
7.6.2
Air Data Test (GDC 74B and STBY Instruments) ..................................................................... 7-28
7.6.3
Static Port Vertical Speed (Rate of Climb) Test ........................................................................ 7-31
7.6.4
OAT Probe Check ..................................................................................................................... 7-31
7.7
GRS AHRS / GMU 44 MAGNETOMETER ..................................................................... 7-32
7.7.1
GRS/GMU Software and Configuration Loading ....................................................................... 7-32
7.7.2
GRS/GMU Calibration Procedures ............................................................................................ 7-34
7.7.3
Procedure A1: GRS AHRS Pitch/Roll Offset Calibration ......................................................... 7-35
7.7.4
Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure
(Optional).................................................................................................................................................. 7-36
7.7.5
Procedure B: GRS AHRS/GMU 44 Magnetic Calibration ........................................................ 7-37
7.7.6
Procedure D: Engine Run-Up Vibration Procedure ................................................................... 7-39
7.7.7
GRS/GMU Test ......................................................................................................................... 7-40
7.8
GDL 69A OR GDL 69A SXM DATA LINK ..................................................................... 7-41
7.8.1
GDL 69A/69A SXM Software and Configuration Loading ......................................................... 7-41
7.8.2
GDL 69A/69A SXM Test ........................................................................................................... 7-42
7.9
GSA 80/81 SERVOS .................................................................................................. 7-42
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7.9.1
GSA Software and Configuration Loading ................................................................................ 7-42
7.10
GCU 475 FMS CONTROLLER ..................................................................................... 7-44
7.10.1
GCU Software and Configuration Loading ................................................................................ 7-44
7.10.2
GCU 475 Test............................................................................................................................ 7-44
7.11
GMC 710 AFCS CONTROLLER .................................................................................. 7-45
7.11.1
GMC Software and Configuration Loading ............................................................................... 7-45
7.11.2
GMC 710 Test ........................................................................................................................... 7-46
7.12
GWX 68/70 W EATHER RADAR ................................................................................... 7-47
7.12.1
GWX Software and Configuration Loading ............................................................................... 7-47
7.12.2
GWX Test .................................................................................................................................. 7-49
8
G1000 FUNCTION AND INTERFACE CHECKS ........................................................ 8-1
8.1
LANDING GEAR AURAL ALERT CHECK ........................................................................... 8-1
8.2
SIRIUSXM AUDIO SUPPRESSION CHECK FOR AIRCRAFT WITH A TONE GENERATOR ......... 8-1
8.3
SIRIUSXM AUDIO SUPPRESSION CHECK FOR AIRCRAFT W ITHOUT A TONE GENERATOR .. 8-2
8.3.1
Gear Warning Discrete ................................................................................................................ 8-2
8.3.2
Stall Warning Discrete ................................................................................................................. 8-3
8.4
TAWS B FUNCTIONAL CHECK ...................................................................................... 8-4
8.5
WEIGHT ON W HEELS AND LOW SPEED AWARENESS BAND TEST..................................... 8-5
9
SYSTEM RETURN TO SERVICE PROCEDURE ........................................................ 9-1
9.1
BACKUP PATH SYSTEM TESTING .................................................................................. 9-1
9.1.1
GPS Failure Test ......................................................................................................................... 9-1
9.1.2
GIA Failure Test .......................................................................................................................... 9-3
9.1.3
Display Failure Test ..................................................................................................................... 9-4
9.1.4
G1000 Backup Path Test ............................................................................................................ 9-5
9.2
MISCELLANEOUS SYSTEM TESTS .................................................................................. 9-7
9.2.1
G1000 Cooling Fan Fail Annunciation Check ............................................................................. 9-7
9.2.2
Standby Instrument Electrical Power Check ............................................................................... 9-8
9.3
GFC 700 GROUND TEST.............................................................................................. 9-9
9.3.1
Pre-Flight Test ............................................................................................................................. 9-9
9.3.2
AFCS Switch Check .................................................................................................................. 9-11
9.3.3
Autopilot Clutch Overpower Check ........................................................................................... 9-12
9.3.4
Manual Electric Pitch Trim Speed Check .................................................................................. 9-13
9.3.5
Autopilot Operation Check ........................................................................................................ 9-13
9.3.6
VOR/LOC/GS Test .................................................................................................................... 9-14
10
MAINTENANCE RECORDS ..................................................................................... 10-1
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LIST OF ILLUSTRATIONS
FIGURE ................................................................................................................................................. PAGE
FIGURE 2-1, C90 ELECTRICAL DISTRIBUTION .................................................................................. 2-11
FIGURE 2-2, AVIONICS MASTER POWER SCHEMATIC .................................................................... 2-12
FIGURE 2-3, G1000 COMPONENT POWER SOURCES ..................................................................... 2-13
FIGURE 2-4, G1000 SYSTEM BLOCK DIAGRAM ................................................................................ 2-14
FIGURE 3-1, GDU 1040A CONTROL INTERFACE ................................................................................. 3-1
FIGURE 3-2, GDU 1500 CONTROL INTERFACE ................................................................................... 3-2
FIGURE 3-3, G1000 SOFTKEYS ............................................................................................................. 3-2
FIGURE 3-4, MFD CONTROLS (GCU 475) ............................................................................................. 3-3
FIGURE 3-5, AFCS CONTROLS (GMC 710) ........................................................................................... 3-3
FIGURE 3-6, GMA 1347D PN 011-01257-00 CONTROLS ...................................................................... 3-4
FIGURE 3-7, GMA 1347D PN 011-01257-20 CONTROLS ...................................................................... 3-5
FIGURE 3-8, NORMAL MODE ................................................................................................................. 3-6
FIGURE 3-9, MANUAL REVERSION WITH MFD FAILURE .................................................................... 3-7
FIGURE 3-10, MANUAL REVERSION WITH PILOT PFD FAILURE ....................................................... 3-7
FIGURE 3-11, SET AND ACTV SOFTKEYS AND COLUMNS ................................................................ 3-9
FIGURE 3-12, LOSS OF COMMUNICATION ........................................................................................ 3-10
FIGURE 3-13, CONFIGURATION STATUS ........................................................................................... 3-10
FIGURE 3-14, DATA TRANSMISSION INDICATORS ........................................................................... 3-11
FIGURE 3-15, G1000 LRU CONFIGURATION FILE STORAGE........................................................... 3-28
FIGURE 3-16, GRS/GDC CONFIGURATION SETTINGS STORAGE .................................................. 3-29
FIGURE 3-17, SOFTWARE/CONFIGURATION OVERVIEW ................................................................ 3-30
FIGURE 3-18, AIRCRAFT REGISTRATION .......................................................................................... 3-47
FIGURE 3-19, SYSTEM STATUS .......................................................................................................... 3-50
FIGURE 3-20, STORMSCOPE CONFIGURATION PAGE (REFERENCE ONLY) ................................ 3-51
FIGURE 3-21, MFD POWER UP PAGE (FORMAT REFERENCE) ....................................................... 3-55
FIGURE 3-22, PFD POWER-UP SYSTEM ANNUNCIATIONS ............................................................. 3-56
FIGURE 3-23, PFD NORMAL OPERATION .......................................................................................... 3-57
FIGURE 3-24, GDU REVERSIONARY MODE ....................................................................................... 3-58
FIGURE 3-25, AUX – GPS STATUS PAGE ........................................................................................... 3-59
FIGURE 3-26, MARKER BEACON SYMBOLOGY ................................................................................ 3-60
FIGURE 4-1, SERVO GEAR................................................................................................................... 4-19
FIGURE 4-2, GIA I/O PAGE ................................................................................................................... 4-20
FIGURE 4-3, DISCRETE INDICATIONS ................................................................................................ 4-20
FIGURE 4-4, AIRFRAME CONFIGURATION PAGE ............................................................................. 4-21
FIGURE 4-5, GFC STATUS PAGE ........................................................................................................ 4-22
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FIGURE 4-6, GFC STATUS PAGE ........................................................................................................ 4-23
FIGURE 4-7, GFC STATUS PAGE ........................................................................................................ 4-28
FIGURE 4-8, STANDBY BATTERY ........................................................................................................ 4-38
FIGURE 4-9, POWER SUPPLY CONNECTION .................................................................................... 4-40
FIGURE 5-1, AUX – SYSTEM STATUS PAGE ........................................................................................ 5-1
FIGURE 5-2, ALERTS & ANNUNCIATIONS ............................................................................................ 5-2
FIGURE 5-3, ADVISORY SOFTKEY ANNUNCIATION ........................................................................... 5-2
FIGURE 5-4, SYSTEM ANNUNCIATIONS............................................................................................... 5-4
FIGURE 5-5, AFCS ANNUNCIATION FIELD ......................................................................................... 5-30
FIGURE 5-6, GFC STATUS PAGE ........................................................................................................ 5-34
FIGURE 5-7, MAGNETOMETER INTERFERENCE TEST .................................................................... 5-73
FIGURE 5-8, MAGNETOMETER INTERFERENCE TEST COMPLETE ............................................... 5-75
FIGURE 5-9, GIA 63W BACKSHELL CONNECTORS ........................................................................... 5-82
FIGURE 5-10, GEA 71 BACKSHELL CONNECTORS ........................................................................... 5-83
FIGURE 5-11, GMA 1347D BACKSHELL CONNECTORS ................................................................... 5-83
FIGURE 5-12, GTX 33/33D BACKSHELL CONNECTORS ................................................................... 5-83
FIGURE 5-13, GDU 1040A/1500 BACKSHELL CONNECTOR (P10401 OR P15001) ......................... 5-84
FIGURE 5-14, GRS 77 BACKSHELL CONNECTOR (P771) ................................................................. 5-84
FIGURE 5-15, GRS 7800 BACKSHELL CONNECTOR (P78001) ......................................................... 5-84
FIGURE 5-16, GDC 74B BACKSHELL CONNECTOR (P74B1) ............................................................ 5-84
FIGURE 5-17, GDL 69A/GDL 69A SXM BACKSHELL CONNECTOR (P69A1) .................................... 5-85
FIGURE 5-18, GCU 475 BACKSHELL CONNECTOR (P4751) ............................................................. 5-85
FIGURE 5-19, GMC 710 BACKSHELL CONNECTOR (P7101) ............................................................ 5-85
FIGURE 5-20, GWX 68 BACKSHELL CONNECTOR (P681) ................................................................ 5-85
FIGURE 5-21, GWX 70 BACKSHELL CONNECTOR (P751) ................................................................ 5-85
FIGURE 5-22, SIGNAL CONDITIONER MATING CONNECTOR (PVIB1) ............................................ 5-86
FIGURE 6-1, CONFIGURATION MODULE INSTALLATION ................................................................... 6-8
FIGURE 6-2, GRS 7800 CONFIGURATION MODULE INSTALLATION ................................................. 6-9
FIGURE 6-3, GEA BACKSHELL THERMOCOUPLE ............................................................................. 6-11
FIGURE 7-1, G1000 NORMAL MODE CHECK........................................................................................ 7-5
FIGURE 7-2, MARKER BEACON SYMBOLOGY .................................................................................. 7-10
FIGURE 7-3, AUX – GPS STATUS PAGE (MFD) .................................................................................. 7-12
FIGURE 7-4, NORMAL ENGINE INSTRUMENT MARKINGS (MFD) .................................................... 7-17
FIGURE 7-5, AIRCRAFT REGISTRATION ............................................................................................ 7-25
FIGURE 7-6, GRS PITCH/ROLL OFFSET CALIBRATION PAGE ......................................................... 7-35
FIGURE 7-7, ENGINE RUN-UP TEST PAGE ........................................................................................ 7-39
FIGURE 7-8, NORMAL MODE AHRS CHECK ...................................................................................... 7-40
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FIGURE 8-1, LOW SPEED AWARENESS BAND SYMBOLIZATION ..................................................... 8-5
FIGURE 9-1, GDU DATA VERIFICATION (ARINC 429) .......................................................................... 9-5
FIGURE 9-2, GIA DATA VERIFICATION (ARINC429/RS-232) ............................................................... 9-6
FIGURE 9-3, GIA DATA VERIFICATION (RS-485) ................................................................................. 9-7
FIGURE 9-4, PRE-FLIGHT TEST ........................................................................................................... 9-10
LIST OF TABLES
TABLE ................................................................................................................................................... PAGE
TABLE 1-1, MDL CONFIGURATIONS SUMMARY .................................................................................. 1-1
TABLE 1-2, REQUIRED DOCUMENTS ................................................................................................... 1-5
TABLE 1-3, REFERENCE PUBLICATIONS ............................................................................................. 1-6
TABLE 3-1, DATA INDICATOR SYMBOLS............................................................................................ 3-11
TABLE 3-2, LRU TO CONFIGURATION FILE RELATIONSHIP ............................................................ 3-23
TABLE 3-3, OPTIONAL AIRFRAME WEIGHT CONFIGURATIONS ..................................................... 3-37
TABLE 4-1, MAINTENANCE INTERVALS ............................................................................................... 4-5
TABLE 4-2, DISCONTINUED MAINTENANCE INTERVALS................................................................. 4-10
TABLE 4-3, NOSE SECTION VISUAL INSPECTION PROCEDURE .................................................... 4-11
TABLE 4-4, NOSE AVIONICS COMPARTMENT VISUAL INSPECTION PROCEDURE...................... 4-11
TABLE 4-5, PILOT’S COMPARTMENT VISUAL INSPECTION PROCEDURE .................................... 4-11
TABLE 4-6, INSTRUMENT PANEL G1000 EQUIPMENT VISUAL INSPECTION PROCEDURE ........ 4-13
TABLE 4-7, CABIN AREA VISUAL INSPECTION PROCEDURE.......................................................... 4-14
TABLE 4-8, REAR FUSELAGE AND EMPENNAGE VISUAL INSPECTION PROCEDURE ................ 4-15
TABLE 4-9, LIGHTNING STRIKE INSPECTION PROCEDURE............................................................ 4-15
TABLE 4-10, MEASURED TORQUE...................................................................................................... 4-25
TABLE 4-11, SLIP CLUTCH TORQUE SETTINGS ............................................................................... 4-27
TABLE 4-12, STANDBY BATTERY REQUIRED EQUIPMENT ............................................................. 4-38
TABLE 5-1, SVS TROUBLESHOOTING ................................................................................................ 5-29
TABLE 5-2, SVS-RELATED ALERT MESSAGES ................................................................................. 5-29
TABLE 5-3, AFCS ANNUNCIATION TROUBLESHOOTING ................................................................. 5-31
TABLE 5-4, AFCS GENERAL TROUBLESHOOTING ........................................................................... 5-33
TABLE 5-5, MAGNETOMETER INTERFERENCE TEST SEQUENCE (EXAMPLE) ............................ 5-74
TABLE 6-1, CONFIGURATION MODULE KIT – 011-00979-03............................................................... 6-8
TABLE 6-2, GRS 7800 CONFIGURATION MODULE PARTS ................................................................. 6-9
TABLE 7-1, AIRSPEED AND ALTITUDE TABLE ................................................................................... 7-29
TABLE 7-2, VERTICAL SPEED TABLE ................................................................................................. 7-31
TABLE 7-3, REQUIRED GRS/GMU CALIBRATIONS ............................................................................ 7-34
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1
INTRODUCTION
1.1
Content, Scope, Purpose
This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G1000 integrated
avionics and GFC700 Automatic Flight Control System (AFCS) as installed in the King Air C90 Series using
STC #SA01456WI-D. This document satisfies the requirements for continued airworthiness as defined by
14 CFR Part 23.1529 and Appendix G. Information in this document is required to maintain the continued
airworthiness of the G1000 and GFC700 system.
1.2
Applicability
This document applies to all Model C90A/C90GT/C90GTi King Air aircraft equipped with the G1000 and
GFC700 AFCS systems. References to “C90 Series” throughout this document include C90A, C90GT, and
C90GTi models. Items in this document that are aircraft model(s) specific will identify the model(s) instead
of “C90 Series”.
The GFC 700 AFCS system is an integral part of the G1000 system and is included in “G1000 system”
references throughout this document.
Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft operator to
include the maintenance information provided by this document in the operator’s Aircraft Maintenance
Manual and the operator’s Aircraft Scheduled Maintenance Program.
1.3
Identifying an STC Configuration
Table 1-1 lists the approved configurations for this STC as defined by the Master Drawing List (MDL) listed
in Table 1-2.
Software loads are governed primarily by the G1000 System Software Version number. The following table
identifies the System Software Version for this STC.
NOTE
G1000 System Software Version 0636.07 is added with STC MDL Rev. 17 and is the
recommended software version for new installations. G1000 System Software Versions
0636.01, 0636.02, 0636.03, 0636.05 and 0636.06 will remain to support fielded aircraft.
Software Version 0636.04 is not approved for installation.
Table 1-1, MDL Configurations Summary
MDL
Configuration
Aircraft
Model
G1000 System
Software Version
Notes
-1
C90A/C90GT King Air
0636.01
STC MDL Rev. 4 Approval
-1
C90A/C90GT King Air
0636.02
STC MDL Rev. 5 Approval
-1
C90A/C90GT/C90GTi King Air
0636.03
STC MDL Rev. 6 Approval
-1
C90A/C90GT/C90GTi King Air
0636.05
STC MDL Rev. 11 Approval
-1
C90A/C90GT/C90GTi King Air
0636.06
STC MDL Rev. 13 Approval
-1
C90A/C90GT/C90GTi King Air
0636.07
STC MDL Rev. 17 Approval
This STC addresses multiple C90 Series configurations. These configuration variants are added by loading
the applicable airframe configuration and related options. Refer the General Arrangement drawing listed
in Table 1-2 for additional information.
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1.4
G1000 System Software Version and Aircraft Configuration Check
Follow these steps before any G1000 System Software is loaded for unit replacement to assure the correct
software and configuration files are loaded.
1. Inspect the aircraft maintenance logs for records of non-Garmin STCs installed. Inspect aircraft
records for signs of other alterations, including field updates and Service Bulletins.
2. Power on the G1000 system by setting the BAT switch to ON, then the EXT PWR switch to ON
and finally the AVIONICS MASTER switch to ON.
3. On the MFD start-up screen, check the upper right section of MFD splash screen for G1000 system
software version and airframe configuration number.
4. Write these numbers down for reference when loading software and configuration files.
An alternate location to find the G1000 system software version and airframe configuration number is on
the MFD AUX – SYSTEM STATUS page. On this page, this information is displayed in the AIRFRAME
window in the upper right corner of the display. The display shows the current G1000 airframe configuration
and system software version number. The system software version number is shown in the following
format: ‘System Software Version XXXX.XX’. It correlates to the G1000 software used to load the software
to the system in the example below:
System Software Version ‘0636.07’ = G1000 Software P/N 006-B0636-07
The General Arrangement drawing defines the approved G1000 software versions for this STC.
Page 1-2
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1.5
Organization
The following outline briefly describes the organization of this manual:
Section 2: System Description
Provides a complete description of the type design change associated with installing the G1000 integrated
cockpit system in the King Air C90 Series. An overview of the G1000 system interface is also provided.
Section 3: G1000 Control & Operation
Presents basic control and operation information specifically tailored to maintenance practices. Basic
G1000 Configuration Mode operation is also described.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for continued airworthiness of the G1000 and GFC 700 systems.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000
system.
Section 6: G1000 Equipment Removal & Replacement
Gives instructions for the removal and replacement of G1000 equipment.
Section 7: G1000 Hardware Replacement - Software Loading and Testing
Gives instructions for loading software, configuring, and testing of individual G1000 hardware removed for
service.
Section 8: G1000 Function and Interface Checks
Gives instructions for checking G1000 functions and interfaces for proper operation.
Section 9: System Return to Service Procedure
Specifies return-to-service procedures to be performed upon completion of maintenance of the G1000
system.
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1.6
Definitions/Abbreviations
ADC:
Air Data Computer
ADF:
Automatic Direction Finder
ADTS:
Air Data Test Set
AFCS:
Automatic Flight Control System
AFM:
Aircraft Flight Manual
AFMS:
Aircraft Flight Manual Supplement
AHRS:
Attitude Heading Reference System
CFR:
Code of Federal Regulations
DME:
Distance Measuring Equipment
EAU:
Engine/Airframe Unit
ESP:
Electronic Stability and Protection
GPS:
Global Positioning System
HSDB:
High-Speed Data Bus (Ethernet)
IAU:
Integrated Avionics Unit
ICS:
Inter-Com System
ITT:
Interstage Turbine Temperature
LRU:
Line Replaceable Unit
MFD:
Multi-Function Flight Display
OAT:
Outside Air Temperature
PFD:
Primary Flight Display
STBY:
Standby
STBY ATT:
Standby Attitude Indicator
STBY ALT:
Standby Altimeter
STBY A/S:
Standby Airspeed Indicator
STC:
Supplemental Type Certificate
TAWS:
Terrain Awareness & Warning system
WAAS:
Wide Area Augmentation System
VHF:
Very High Frequency
1.6.1
Units of Measure
Unless otherwise stated, all units of measure are English units.
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1.7
Publications
The following documents are required by this maintenance manual to perform maintenance:
Table 1-2, Required Documents
Part Number
Garmin Documents
005-00375-30
STC Master Drawing List
005-W0022-00
Wiring Diagram, G1000/GFC 700 King C90
005-00375-22
General Arrangement, G1000/GFC700 AFCS, King Air C90
005-00375-19
GWX Radar Install, King Air C90A
005-00375-21
Antenna Install, King Air C90A
005-00375-28
Main Instrument Panel Installation, King Air C90
005-00375-34
Electrical Equipment Install, Nose Bay, King Air C90A
005-00375-41
Roll Servo Install, King Air C90A
005-00375-42
Yaw Servo Install, King Air C90A
005-00375-43
Pitch Servo Install, King Air C90A
005-00375-44
Pitch Trim Servo Install, King Air C90A
005-00375-53
Magnetometer Install, King Air C90A
005-00375-54
OAT Sensor Install, King Air C90A
005-00375-71
Standby Battery Install, King Air C90A
005-00375-78
Cabin Speaker Amplifier Installation, King Air C90
005-00375-79
Fwd Bulkhead Connector Plate Installation, King Air C90
320-00326-XX
Wire Harness Assembly, G1000/GFC 700
005-00375-55
Wire Harness Routing, Nose, King Air C90
005-00375-56
Wire Harness Routing, Cabin, King Air C90
005-00375-31
Wire Harness Routing, Tail, King Air C90
005-00375-23
Control Wheel Modification,G1000/GFC 700, King Air C90
005-00375-25
Overhead Control Panel Modification, G1000/GFC 700, King Air C90A
005-00375-26
Pedestal Re-Configuration, King Air C90A
005-00375-29
Circuit Breaker Panel Modification, King Air C90A
005-00375-70
Circuit Breaker Panel Modification, King Air C90A
005-00375-83
Glareshield Lighting Modification, King Air C90
005-00375-AA
GTX 33D Transponder Option, King Air C90
Part Number
Beechcraft Documents
90-590024-11
King Air C90 Series Wiring Diagram Manual
90-590012-13
King Air Model 90 Series Maintenance Manual
101-590097-13
King Air Series Component Maintenance Manual
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
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Part Number
Other Documents
523-0772458-00611A
Collins DME-42 Transceiver Repair Manual (If DME is installed)
9016182
Mid-Continent Instruments - Installation Manual and Operating
Instructions, 4200 Series Attitude Indicator
85-292-1-1033
TP-336
Signal Conditioner Installation Manual (Meggitt Sensing Systems)
L-3 Avionics Systems – Emergency Power Supply Installation Manual, PS835
The following publications are recommended to be on hand during the performance of maintenance
activities.
Table 1-3, Reference Publications
Part Number
Garmin Document
190-00682-02
G1000/GFC 700, King Air C90A/C90GT Airplane Flight Manual
Supplement
190-00664-XX
G1000 King Air C90 Cockpit Reference Guide
190-00355-04
GDL 69 Series SiriusXM Satellite Radio Activation Instructions
190-00907-00
G1000 System Maintenance Manual
190-00303-72
GSA8X/GSM85(A) Installation Manual
190-00303-83
GSM 86 Servo Gear Box Installation Manual
190-00313-12
Circular Connector (and Configuration Module) Installation Instructions
Beechcraft Document
Part Number
98-39006
Structural Inspection and Repair Manual
Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealer Resource
Center’ section of the Garmin web site; refer to Section 1.8 for details.
1.8
Revision and Distribution
This document is required for maintaining the continued airworthiness of the aircraft. When this document
is revised, every page will be revised to indicate current revision level.
Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center
website.
Owner/operators may obtain the latest revision of this document from the https://fly.garmin.com/ Support
page, or by contacting a Garmin dealer, contacting Garmin Product Support at 913-397-8200, toll free 866739-5687, or using around the world contact information on https://fly.garmin.com/.
A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the
revision is determined to be significant.
Page 1-6
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2
SYSTEM DESCRIPTION
2.1
Equipment Descriptions
2.1.1
GDU 1040A PFD (2) & GDU 1500 MFD
Two Garmin GDU 1040A displays and one GDU 1500 display are installed in the King Air instrument panel.
The GDU 1040A units, 10.4 inch LCD displays with 1024x768 resolution, are configured as PFD 1 and PFD
2; the GDU 1500 unit, a 15 inch LCD display with 1024x768 resolution, is configured as a MFD. All displays
provide control and display of nearly all functions of the G1000 integrated cockpit system. The PFD displays
are located on either side of the MFD, with the stand-by instruments located between the Pilot’s PFD (PFD 1)
and the MFD. GMA 1347 Audio Panels are located outboard of each PFD. Additionally, a GMC 710 AFCS
Controller is located in the upper instrument panel, above the MFD, and a GCU 475 is installed in the pedestal.
The GCU 475 provides the control interface for the MFD.
The GDU 1500 communicates with the GDU 1040A units and the GDL 69A through a high-speed data bus
(HSDB) Ethernet connection. The GDU 1500 communicated with the GCU 475 via RS-232 digital interface.
The GDU 1040A units communicate with each other and the GIA 63W units through a high-speed data bus
(HSDB) Ethernet connection.
Electrical power to PFD 1, MFD, and PFD 2 is provided by the triple-fed bus. The triple-fed bus is powered by
the battery and both generator buses. Additionally, a secondary power source is provided to PFD 1 by the
center bus, which is fed by both generator buses and the battery. Therefore, the displays power-up
immediately with external or aircraft power or battery operation.
All displays are installed in the King Air panel using ¼-turn fasteners. Three GDU cooling fans are also
installed behind the panel for PFD and MFD cooling.
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2.1.2
GMA 1347D Audio Panel (2)
The Garmin GMA 1347D Audio Panel integrates NAV/COM digital audio, intercom system and marker beacon
controls. The C90 installation includes two GMA 1347 panels. The GMA 1347D panels provide control of all
cockpit intercom/mic systems as well as NAV/COM/ILS audio. The units also provide display reversion mode
control through a large red button. Power to the audio panels is provided by the avionics bus. These units
only power up when the avionics master switch is turned on. The GMA 1347D units interface with the existing
marker beacon antenna, as well as existing mic and phone jacks and oxygen mask mic.
2.1.3
GMC 710 AFCS Control Unit
The dedicated AFCS controls on the GMC 710 allow crew control interface with the various GFC 700 autopilot
/ flight director functions. GMC 710 controls are discussed in detail in the G1000 Cockpit Reference Guide.
The GMC 710 is powered by the triple fed bus.
2.1.4
GCU 475 FMS Control Unit
The GCU 475 functions as the primary control interface to the GDU 1500 MFD. The GCU 475 provides
alphanumeric, softkey, and flight planning function keys used to interface with the G1000; the MFD does not
possess any knobs or controls other than softkeys. The GCU 475 is powered by the triple-fed bus. Detailed
instructions regarding the controls are discussed in the G1000 Cockpit Reference Guide.
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2.1.5
GIA 63W Integrated Avionics Unit (2)
Two Garmin GIA 63W Integrated Avionics Units (IAUs) contains the VHF COM/NAV receivers, WAAS GPS
receiver, Flight Director, and system integration microprocessors. The GIAs also serve as a communication
interface to all other G1000 LRUs in the system. Each GIA 63W communicates directly with the on-side GDU
1040A display using a HSDB Ethernet connection. Both GIAs are located remotely in the nose equipment
bay.
Power is provided to both GIAs by the triple-fed bus. The triple-fed bus is powered by the battery and both
generator buses. Additionally, a secondary power source is provided to GIA1 by the center bus, which is fed
by both generator buses and the battery. The GIA 1’s COMM power supply (COM 1) is provided by No.1
Avionics Bus. GIA 2’s COMM power supply (COM 2) is provided by No.2 Avionics Bus. Therefore, both
GIAs power-up immediately with external or aircraft power or battery operation, with the exception of both
COMs, which will become active after selection of Avionics Master on. Both GIA 63s interface to the following
equipment:
 Existing VOR/LOC/Glideslope Antenna System
 Existing VHF COM #1 & #2 Antennas
 GPS/WAAS Antennas
 GMA 1347D, #1 & #2
 GEA 71, #1 & #2
 GDU 1040A, #1 & #2
 GSA Servos
 GRS AHRS, #1 & #2
 Traffic System (if installed)
The GIA 63W #1 interfaces to the following additional equipment:
 GDC 74B #1
 GTX 33 #1
 DME 42 (if installed)
The GIA 63W #2 interfaces to the following additional equipment:
 GDC 74B #2
 GTX 33 #2
 ADF 60 (if installed)
 Stormscope (if installed)
 Radio Altimeter (if installed)
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2.1.6
GEA 71 Engine/Airframe Unit (2)
The Garmin GEA 71 Engine/Airframe Units provide engine/airframe data to the G1000 system. Data received
from transducers/sensors is processed and sent to GIA 63Ws (via RS-485 digital interface), and subsequently
to the GDU 1500 MFD. Engine parameters are normally displayed on the MFD. In the event of MFD failure,
the engine parameters can be displayed on PFD 1 and/or PFD 2 using display reversion. The GEAs are
located behind the instrument panel and are mounted in a vertical orientation. Power is received from the
triple-fed bus. Both GEA units will power-up immediately with external or aircraft power or battery operation.
Each GEA interfaces to the following sensors for its onside engine:

Oil Pressure Sensor

Oil Temperature Sensor

Fuel Flow Sensor (via onside Signal Conditioner)

Turbine Speed Sensor (via onside Signal Conditioner)

Propeller Speed Sensor(via onside Signal Conditioner)

Torque Sensor

Interstage Turbine Temperature (ITT) Sensor
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2.1.7
GTX 33 Mode S Transponder (2)
The GTX 33 Non-Extended Squitter or GTX 33 Extended Squitter (ES) (Optional) or GTX 33D Diversity
(Optional) transponders communicate with the on-side GIA 63W through RS-232 digital interface. The units
are mounted in the nose equipment bay. Power is provided by the No. 1 and No. 2 avionics bus for GTX 33
No. 1 and No. 2 respectively. The GTX 33 Non-Extended Squitter and Extended Squitter units interface with
the existing transponder antennas. The GTX 33D units interface with newly installed diversity transponder
antennas.
NOTE
A model designation of GTX 33 in this manual will imply either the GTX 33 Non-Extend
Squitter or GTX 33 Extended Squitter (ES) or GTX 33D Diversity transponder.
2.1.8
GDC 74B Digital Air Data Computer (2)
The Garmin GDC 74B computers compile information from the pitot/static system and various outside air
temperature (OAT) and awareness sensors and provide digital air data computations to the G1000 system.
The GDC 74B communicates with the GIA 63W, GDU 1040A, and GRS AHRS using ARINC 429 digital
interface. The unit is mounted behind the instrument panel. Power is provided to both GDC 74B units by the
triple-fed bus. Additionally, a secondary power source is provided to the No. 1 computer by the center bus.
The GDC 74B connects to existing pitot/static ports via existing tubing in C90A and C90GT airframes. For
C90GTi airframes new pitot/static tubing and hardware is purchased from Beechcraft Company. Reference
the Main Instrument Panel Installation drawing for details.
2.1.9
OAT Probe (2)
The Garmin GTP 59 OAT Probes provide the GDC 74B with air temperature data. The OAT probes are
mounted to the bottom of the King Air fuselage at F.S. 113.5. The probes receive power directly from the GDC
74B air data computers.
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2.1.10 Attitude & Heading Reference System (2)
The Garmin GRS 77 AHRS or GRS 7800 AHRS units provide attitude and heading information to the G1000
system. The units, mounted nose equipment bay, contain advanced tilt sensors, accelerometers, and rate
sensors. The unit interfaces with the GDC 74B and GMU44 Magnetometer and utilizes GPS signals from the
GIA 63Ws. Actual attitude and heading information is sent using ARINC 429 digital interface to both GDU
1040As and GIA 63Ws. Power is provided to both GRS 77 or GRS 7800 units by the triple-fed bus.
Additionally, a secondary power source is provided to the No. 1 GRS by the center bus. The GRS interfaces
with and provides power to the GMU 44 Magnetometer. The GRS supplies attitude and heading information
directly to the PFDs, MFD, and GIAs.
Additionally, the GRS 7800 AHRS provides heading with or without the aiding of the Garmin GMU 44
magnetometer. When operating without the aid of the magnetometer, the GRS 7800 is functionally similar to
that of a Directional Gyro.
NOTE
A model designation of GRS or GRS AHRS in this manual will imply either the GRS 77 or
GRS 7800 unit unless one model is specifically named.
GRS 77
GRS 7800
2.1.11 GMU 44 Magnetometer (2)
The GMU 44 provides horizontal and vertical magnetic field information to the GRS AHRS. This allows
heading to be calculated and provides assistance during AHRS alignment. The GMU 44 units are mounted in
the vertical tail. The units receive power directly from the GRS units and communicate with the GRS units via
RS-485 digital interface.
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2.1.12 GDL 69A/69A SXM Datalink
The GDL 69A/69A SXM provides the interface to the GWX 68 or GWX 70 weather radar by acting as a
communications hub between the MFD and GWX via HSDB. The GDL 69A/69A SXM also provides SiriusXM
Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A/69A
SXM is mounted behind the instrument panel. Power to the GDL 69A/69A SXM is received from the avionics
No. 3 bus. The GDL 69A/69A SXM sends weather data through the HSDB bus to the MFD, where the data
link interface is controlled. Digital audio is sent directly to the GMA 1347D Audio Panel.
2.1.13 Weather Radar
The GWX 68 or GWX 70 Airborne Weather Radar provides weather radar data output to the GDU 1500 MFD.
The GWX is mounted forward of the forward bulkhead at F.S. 30. Power to the GWX is received from the
avionics No. 2 bus. Data received from the GWX is routed through the GDL 69A data link unit to the MFD via
high-speed data bus (Ethernet).
NOTE
A model designation of GWX in this manual will imply either the GWX 68 or GWX 70 unit
unless one model is specifically named.
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2.1.14 GSA 80/81 Servo Motors and GSM 85A/86 Servo Mounts
The GSA 81 (low-torque) Servo Actuator is an electromechanical unit that will provide automatic control of
pitch trim. The Garmin GSA 80 (high-torque) Servo Actuator is an electromechanical unit that will provide
pitch, roll and yaw damp and turn coordination. The GSA 80/81 contains a motor-control and monitor circuit
board, as well as a solenoid and a brushless DC motor. The GSA 80/81 servo receives serial RS-485 data
packets from the GIA 63Ws. The roll servo is located in the lower fuselage at F.S. 185. The pitch, yaw, and
pitch trim servos are located in the tail. Power to the servos is received from the avionics No. 2 bus.
All servos mount to a Garmin GSM 85A or GSM 86 Servo Mount. The GSM 85A/86 is responsible for
transferring the output torque of the GSA 80/81 servo actuators to the mechanical flight control surface linkage.
The GSM 85A has a slip clutch that is field adjustable to the required torque value. The GSM 86 has a clutch
cartridge that is not field adjustable but can be replaced if the specified torque value is not within limits.
NOTES
A model designation of GSA in this manual will imply either the GSA 80 or GSA 81 unit
unless one model is specifically named.
A model designation of GSM in this manual will imply either the GSM 85A or GSM 86 unit
unless one model is specifically named
2.1.15 Comant CI428-410 / CI428-200 GPS/WAAS Antennas
The Comant CI428-410 GPS/WAAS/XM and CI428-200 GPS/WAAS antennas meet the GPS WAAS Gamma
3 specifications required for G1000. For procedural instructions on accessing the GPS antennas, refer to the
King Air Model 90 Series Maintenance Manual listed in Table 1-2.
2.1.16 Thommen 5A58.22.26K.28.1.XX Airspeed Indicator
A Thommen 5A58.22.26K.28.1.XX unit is installed as the standby airspeed indicator. The General
Arrangement drawing Table 4 shows available part numbers signified by the XX notation above and aircraft
effectivity. The standby airspeed indicator is self illuminated and is connected to the left generator bus. The
internal lights are also connected to the emergency standby battery.
2.1.17 Thommen 3A43.22.35F.28.1.FU Altimeter
The Thommen 3A43.22.35F.28.1.FU altimeter with internal vibrator is used as the standby altimeter. The
vibrator is powered by the No. 1 triple-fed bus. This unit is self illuminated and its internal lighting is connected
to the left generator bus. Both the vibrator and the internal lighting are also connected to the emergency
standby battery.
2.1.18 Mid-Continent 4200-1( ) Attitude Indicator
The Model 4200-1( ) Electric Attitude Indicator is used as the standby attitude indicator and is connected to
the No. 3 triple-fed bus. This unit is self illuminated and its internal lighting is connected to the left generator
bus. The unit along with its internal lighting is also connected to the emergency standby battery.
The Model 4200-11 Mod 2 is applicable only to installations using STC SA01456WI-D Master Drawing List
(MDL) 005-00375-30, Revision 16 and later approved revisions.
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2.1.19 L-3 PS-835(C or D Model) Emergency Standby Battery
In the event of loss of all normal electrical power, the battery is designed to provide 24 VDC (nominal)
emergency power source for the following items:

standby attitude indicator (operation and internal lighting)

standby altimeter (vibrator and internal lighting)

standby airspeed indicator (lighting only)
The aircraft power buss provides a trickle charge to the PS-835 under normal conditions. This battery is
existing in the rear fuselage of aircraft previously equipped with Collins EFIS and is installed in the nose
avionics bay by this STC, on aircraft that were not previously equipped with Collins EFIS.
2.1.20 Engine Signal Conditioning
Changes to the engine signal conditioning components were initiated with STC SA01456WI-D Master Drawing
List (MDL) 005-00375-30, Revision 5. The Sandia ST26 Tach Generator Unit (PN 305662-00), Senior
Aerospace PC920 Signal Conditioning Unit (PN PC920-6A00PH-2A1) and the Garmin 005-00375-93 TachGen Filter Assembly were replaced by the Vibro-Meter (Meggit) Signal Conditioner Signal Conditioner.
Reference the Main Instrument Panel Installation drawing listed in Table 1-2 for the locations of the Signal
Conditioner Components.
2.1.20.1 Sandia Aerospace ST26 Tach Generator Adapter Units (2)
The ST26 Tach Generator Adapter Units are used for converting the signal from the propeller speed and
turbine speed sensors into a signal that is usable by the GEAs. The output signal from this adapter unit will
be represented by a 5 VDC square wave signal at same frequency of input signal. The No. 1 ST26 (left side)
unit is connected to the No. 1 Triple-fed bus and the No. 2 ST26 (right side) unit is connected to the No. 2
triple-fed bus.
The Sandia Aerospace ST26 Tach Generator Adapter Unit is applicable only to installations using STC
SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions.
2.1.20.2 Senior Aerospace PC920 Signal Conditioning Unit
The PC920 unit was installed per this STC only for aircraft with Senior Aerospace Ketema fuel flow transducer,
part number 1/2-2-81-306. The PC920 unit is used for converting the signal from the fuel flow sensor into a
variable 0 to 5 VDC signal that is proportional to flow rate. The PC920 unit No. 1 channel is connected to the
No. 1 triple-fed bus and the No. 2 channel is connected to the No.2 triple-fed bus. The No. 1 channel
(connector P9201) converts the fuel flow signal for the left engine and the No. 2 channel (connector P9202)
converts the fuel flow signal for the right engine.
The Senior Aerospace PC920 Signal Conditioner Unit is applicable only to installations using STC
SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions.
2.1.20.3 Garmin 005-00375-93 Tach-Gen Filter Assembly (2)
The Tach-Gen Filter Assembly is used to filter out high frequency signal noise and is installed between the
Sandia ST26 Signal Conditioner and both the propeller speed and turbine speed sensors. There is one tachgen filter installed for each engine. The left engine tach-gen filter is installed on the underside of the floor
panel located forward of the pilots seat position. The right engine tach-gen filter is installed on the underside
of the floor panel located forward of the co-pilots seat position. There are no power requirements for the tachgen filter assembly.
The Garmin Tach-Gen Filter Assembly, Part Number 005-00375-93, is applicable only to installations using
STC SA01456WI-D Master Drawing List Revision 4 and previously approved revisions.
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2.1.20.4 Vibro-Meter (Meggit) Signal Conditioner (2)
Each GEA 71 receives signals from its on-side engine turbine speed sensor, propeller speed sensor and fuel
flow sensors via a Vibro-Meter (Meggit) Signal Conditioner. This unit converts the signals from the engine
sensors to a signal usable by the GEA 71. These units are installed behind the instrument panel. Electrical
power to the No. 1 Engine Signal Conditioner is provided from No. 1 Triple-fed bus and to the No. 2 Engine
Signal Conditioner from No. 2 triple-fed bus. Both signal conditioners will power-up immediately with external
or aircraft power or battery operation.
The Vibro-Meter (Meggit) Signal Conditioner is applicable only to installations using STC SA01456WI-D
Master Drawing List Revision 5 and subsequent approved revisions or fielded installations modified in
accordance with Garmin Document 190-00682-06.
2.2
G1000 Optional Interfaces
Optional equipment includes BF Goodrich WX-500 Stormscope, Rockwell Collins ADF-60A, and Rockwell
Collins DME-42. Additional interfaces (such as Garmin GTS 8XX Traffic Systems, GSR 56 Iridium
Communications, and TAWS-A) require separate installation approval other than this STC. Refer to wiring
diagram listed in Table 1-2, for connection information for optional interfaces.
2.3
Electrical Power Distribution
This airplane uses a multi-bus system, as detailed below and in Figures 2-1 and Figure 2-2. In normal
operation, all buses are automatically tied into a single-loop system where all sources supply power through
individual protective devices. The battery and generator switches on the pilot’s left subpanel are used to
control power from the ship battery and generators into the airplane electrical system. Switches in the cockpit
that receive power from the center and triple-fed buses are identified by a white ring on the panel around the
switch.
Left and Right Generator Buses: The left and right generator buses receive power from their respective left
and right generators (ref. Figure 2-1). The left and right generator buses also support the No. 2 and No. 3
avionics buses, respectively, via the avionics master switch (ref. Figure 2-2). The No. 2 avionics bus supplies
power to the following G1000 equipment: GMA 2, GTX 2, GWX, GSA servos. The No. 3 avionics bus supplies
power to the GDL 69(). The No. 2 and No. 3 avionics buses also supply power to optional interface equipment.
Center Bus: The center bus is fed by two generator buses and the hot battery bus, which automatically
connects those components whenever the bus ties are closed (ref. Figure 2-1). The center bus provides a
secondary power source for the following G1000 equipment: PFD 1, GIA 1, GDC 1, and GRS 1.
Triple-fed Bus: The triple-fed is powered from the hot battery bus and both generator buses (ref. Figure 2-1.)
The triple-fed bus also supports avionics no.1 bus via the avionics master switch (ref. Figure 2-2). The
following G1000 equipment is supported by the triple-fed bus: MFD, PFD 1, PFD 2, GCU 475, GMC 710, GIA
1, GIA 2, GEA 1, GEA 2, GDC 1, GDC 2, OAT, GRS 1, and GRS 2. The No. 1 avionics bus provides power
for the following G1000 equipment: GMA 1 and GTX 1. The No. 1 triple-fed bus provides power to the No.1
Sandia Aerospace ST26 tach generator adapter, No 1 channel of the Senior Aerospace PC 920 fuel flow
conditioner, No.1 Vibro-Meter (Meggit) Signal Conditioner (if installed), and Thommen standby altimeter
vibrator (under normal conditions.) The No 2 triple-fed bus provides power to the No. 2 Sandia Aerospace
ST26 tach generator adapter, the No. 2 channel of the Senior Aerospace PC 920 fuel flow conditioner, and
the No.2 Vibro-Meter (Meggit) Signal Conditioner (if installed). The No. 3 triple-fed bus provides power to the
Mid-Continent standby attitude indicator (under normal conditions) and provides power for charging the L-3
emergency standby battery.
Emergency Standby Battery Function: The Standby Emergency Battery (STBY BATT) system in the King Air
C90 is designed to provide uninterrupted DC power to the Standby Attitude indicator (gyro motor) and the
Standby Altimeter (vibrator) from the L-3 PS-835(C or D Model) Emergency Standby Battery. In addition, the
STBY BATT system supplies a fixed lighting voltage to the Standby Attitude Indicator, the Standby Altimeter,
and the Standby Airspeed Indicator in the event of a total loss of DC power (ref. Figure 2-1.) For aircraft
retrofitted using STC SA01456WI-D Master Drawing List Revision 6 or later, the STBY “whiskey” compass will
also receive lighting from the STBY BATT in the event of a total loss of DC power. The STBY BATT system
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is a redundant power source to the Standby Attitude indicator, Standby Altimeter, and the Standby Airspeed
Indicator.
The electrical system is protected from excessively high current flow by the bus tie system. A bus tie sensor
and relay is located between each generator bus and the center bus and also between the battery bus and
the center bus. When the battery switch is on, battery bus voltage energizes and closes the relay. Similarly,
when a generator or external power is brought on-line, the generator bus tie relays are energized and closed.
Figure 2-1, C90 Electrical Distribution
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Figure 2-2, Avionics Master Power Schematic
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Figure 2-3, G1000 Component Power Sources
2.4
Shield Block Grounds
The connectors on Garmin G1000 LRUs utilize the Shield Block grounding system to provide necessary
ground reference to wire shielding and/or transducers. The shield block termination method allows multiple
grounds to be terminated directly to a block mounted to the connector backshell assembly. Shielding and
grounding requirements for all other LRUs and connectors are shown in the respective install drawings.
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2.5
G1000 System Block Diagram
Figure 2-4, G1000 System Block Diagram
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3
G1000 Control, Operation, and Full Software Load
All control and operation of G1000 equipment as normally used in flight occurs through the PFDs, MFD,
GMC 710, GCU 475, and GMA 1347D audio panel. Figures 3-1 thru 3-7 identifies various interface buttons
for these units.
3.1
3.1.1
G1000 Control
GDU 1040A and GDU 1500 Displays
Figure 3-1 and Figure 3-2 provide identification of the GDU 1040A PFD and GDU 1500 MFD controls.
Figure 3-1, GDU 1040A Control Interface
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Figure 3-2, GDU 1500 Control Interface
3.1.1.1
Softkeys
Some pages have commands or selections that are activated by the GDU 1040 softkeys. If a softkey is
associated with a command, that command will be displayed directly above the key. A grayed-out softkey
shows a command that is unavailable. A softkey that is highlighted shows the current active selection.
Figure 3-3, G1000 Softkeys
3.1.1.2
FMS Knob
The FMS knobs shown in Figure 3-1 and Figure 3-4 are the primary controls for the G1000 system.

To cycle through different configuration screens:
o
To change page groups: Rotate the large FMS knob.
o
To change pages in a group: Rotate the small FMS knob.

To activate the cursor for a page, press the small FMS knob directly in, as one would push a regular
button.

To cycle the cursor through different data fields, rotate the large FMS knob.

To change the contents of a highlighted data field, rotate the small FMS knob. This action either
brings up an options menu for the particular field, or in some cases allows the operator to enter
data for the field.

To confirm a selection, press the ENT key.

To cancel a selection, press the small FMS knob in again, deactivating the cursor. The CLR key
may also be used to cancel a selection or deactivate the cursor.
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3.1.2
GCU 475 - MFD Controller
The MFD controls are located on the GCU 475 as show in Figure 3-4.
Figure 3-4, MFD Controls (GCU 475)
3.1.3
GMC 710 - AFCS Controls
The dedicated AFCS controls located on the GMC 710 are discussed in detail in the G1000 Cockpit
Reference Guide. The following figure is provided for reference:
Figure 3-5, AFCS Controls (GMC 710)
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3.1.4
GMA 1347D Audio Panel
Figure 3-6 provides the audio panel controls for GMA 1347D PN 011-01257-00. The GMA 1347D PN 01101257-00 is applicable only to installations using STC SA01456WI-D Master Drawing List Revision 4 and
previously approved revisions.
Figure 3-6, GMA 1347D PN 011-01257-00 Controls
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Figure 3-7 provides the audio panel controls for GMA 1347D PN 011-01257-20. The GMA 1347D PN 01101257-20 with the Cabin Intercom button is applicable only to installations using STC SA01456WI-D Master
Drawing List Revision 5 and subsequent approved revisions or fielded installations modified in accordance
with Garmin Document 190-00682-06.
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 3-7, GMA 1347D PN 011-01257-20 Controls
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3.2
G1000 Operation
NOTE
Various procedures herein may require operating the aircraft on the ground for extended
periods. Do not conduct extended ground operations (in excess of 15 minutes) with
cabin air temperatures above 40 degrees C (104ºF).
3.2.1
G1000 Normal Mode
To start the G1000 system in Normal Mode:


With a ground power unit connected to the external power receptacle, set the BAT and EXT PWR
switches to ‘ON’. The following G1000 equipment is powered:
o
PFD1, PFD2, and the MFD displays
o
GRS AHRS Units
o
GDC 74B Air Data Computers
o
GIA 63W Integrated Avionics Units
o
GEA 71 Engine/Airframe Units
o
GCU 475 FMS Control Unit
o
GMC 710 Autopilot Control Unit
o
GMA 1347D Audio Panel #1
o
GTX 33 Transponder #1
Set the AVIONICS MASTER PWR switch to ‘ON’. The following G1000 equipment is powered:
o
GTX 33 Transponder #2
o
GMA 1347D Audio Panel #2
o
GDL 69A or GDL 69A SXM Datalink Unit
o
GSA Servos
o
GWX Weather Radar Unit
The G1000 system is now powered in the normal mode. In the normal operating mode, data fields that are
invalid have large red X’s through them. A valid field does not display a red X. Allow the displays to initialize
for approximately one minute. The GDC 74Bs requires a longer initialization period than do the other LRUs.
During normal operation, this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid
during the first ~40-60 seconds of PFD power-up. The PFDs and MFD will function as specified in the
G1000 Cockpit Reference Guide, when the system has been correctly installed and configured.
Figure 3-8, Normal Mode
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3.2.2
Reversionary Mode
Reversionary mode allows for display of information related to safe flight in the event of a display
communication or hardware failure. On this 3-display system, only a manual reversionary mode is possible.
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 1347 audio panel.
NOTE
When the ‘DISPLAY BACKUP’ button is pushed to exit reversionary mode, there is a 5second debounce (or the GDU waits for 5 consecutive seconds) and then returns to normal
mode if no other input is received. If the ‘DISPLAY BACKUP’ button is pushed again during
this 5-second interval, the timer will repeat the count.
Figure 3-9, Manual Reversion with MFD failure
Figure 3-10, Manual Reversion with pilot PFD failure
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3.2.3
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 system in Configuration Mode:
1. Open the MFD, PFD1 (PRI), PFD1 (SEC) and PFD2 circuit breakers.
2. Apply external power, then set the BAT, EXT PWR and AVIONICS MASTER PWR switches to ON.
3. Press and hold the ENT key on the co-pilot’s PFD while closing the PFD 2 circuit breaker.
4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the PFD.
5. Repeat steps 3 through 4 on the MFD using the MFD circuit breaker and using the far right soft key
(#12) on the MFD.
6. Repeat steps 3 through 4 on the pilot’s PFD using the PFD 1 (PRI) or PFD 1 (SEC) circuit breaker.
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.
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3.2.3.1
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.
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.
SET Column
ACTIVE Column
SET>ACTV and ACTV>SET Softkeys
Figure 3-11, SET and ACTV Softkeys and Columns
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
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specific LRU from the PFD. (Note that this can also be accomplished by reloading the configuration files
for the LRU, using the software loader card. Section 7 describes this process for each LRU).
A blank active column, as shown in Figure 3-12, represents loss of communication between the display and
the particular unit. See Section 5 for more details on troubleshooting.
Figure 3-12, Loss of Communication
3.2.3.2
Configuration Prompts
When configuration settings are changed, the technician receives on-screen prompts and/or confirmations
such as those shown in Figure 3-13. Section 7 shows other prompts encountered during the configuration
process.
Figure 3-13, Configuration Status
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3.2.3.3
Data Transmission Indicators
Several configuration screens utilize an indicator light system to show discrete (ON/OFF) data and/or
hardware component status. A difference in the presentation of the data indicator exists between the
previously approved 0636.01 and 0636.02 versions of G1000 system software. Table 3-1 presents the data
indicator differences between those two versions of software. G1000 system software versions 0636.02
and later use the same data indicators.
G1000 System Software Data Indicator Symbol Differences
006-B0636-01, v 0636.01
Indicator
Meaning
006-B0636-02, v 0636.02
Indicator
Meaning
Valid
Valid
Invalid/Fail
Invalid/Fail
Unknown
Unknown
-
-
OFF
-
-
TRUE
-
-
FALSE
-
-
HIGH
-
-
LOW
Table 3-1, Data Indicator Symbols
This manual will depict the data indicator symbols used by the G1000 System Software Version 0636.03
and later. The following applies to all such status indicators:

Green Checkmark: Expected data is successfully received and is ON or VALID. 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 or FAIL.

Amber question mark (?): Data is unknown.

White N/A: Expected data is OFF, or no data is expected.
Figure 3-14, Data Transmission Indicators
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3.2.3.4
Configuration Mode Navigation
Using the FMS knob as described in Section 3.1.1.2, a user can navigate through different pages and page
groups in the Configuration Mode. For complete description and breakdown of each page, refer to the
G1000 System Maintenance Manual.
System Page Group
1. System Status
2. Date/Time
3. Main Lighting
4. Audio Alert Configuration
5. System Upload
GDU Page Group
1. RS-232/ARINC 429 Config
2. GDU Status
3. GDU Test
4. Diagnostics
GIA Page Group
1. RS-232/ARINC 429 Config
2. RS-485 Configuration
GEA Page Group
1. Engine Data
GTX Page Group
1. RS-232/ARINC 429 Config
6. Aircraft Configuration*
7. Diagnostics Terminal
8. OEM Diagnostics
9. System Configuration
10 System Data Paths
11. System Setup
12. Manifest Configuration
13. Maintenance Log
5.
6.
7.
8.
Serial/Ethernet I/O
Video
Alert Configuration
DAT Configuration*
9. Airframe Configuration
10. TAWS Configuration
3. GIA I/O Configuration
4. COM Setup
5. GIA Status
6. GIA CAN Configuration
2. GEA Status
3. GEA Configuration
2. Transponder Configuration
GRS Page Group
1. AHRS/ADC Input
2. GRS / GMU Calibration
ADC Page Group
1. ADC Configuration
2. GDC Configuration
GFC Page Group
1. GFC Configuration
2. GFC Status
GMA Page Group
1. GMA Configuration
GDL Page Group
1. GDL 69
RMT Page Group
1. Remote Controller Status
GWX Page Group
1. GWX Configuration
OTHER Page Group
1. Stormscope®
CAL Page Group
1. Fuel Tank Calibration
2. Flaps & Trim Calibration
3. HSCM Calibration
4. DAT Calibration*
*Appears only in aircraft with GDU Software v13.08 or later
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3.3
G1000 System Software Information
The following sections provide a detailed description of loading all G1000 software and configuration files.
This section is primarily used for G1000 Service Bulletin Software Updates. Loading of all software and
configuration files is usually not required for service removal and replacement of units. Refer to Section 7
of this manual for the necessary steps during service removal and replacement of G1000 units.
3.3.1
G1000 Software Image
All software and configuration files were certified by Garmin and are considered part of FAA-approved Type
Design data. Approved software and hardware definitions for each STC Configuration is defined on the
appropriate General Arrangement drawing listed in Table 1-2.
G1000 software and configuration files are controlled via the approved software image part number listed
on the General Arrangement drawing listed in Table 1-2. This software image is loaded into the G1000
using a software loader card. The installer shall create this software loader card by downloading the
approved software image in accordance with Section 3.3.2.
NOTE
Only SanDisk brand 8GB SD cards or smaller are recommended for use with the G1000
system.
IMPORTANT
To satisfy the G1000 STC requirements for the King Air C90 Series, it is critical that
the technician use the correct software loader card part number when servicing the
G1000 system.
Approved loader card part numbers are defined on the General Arrangement
drawing.
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 3, 5, 6, and 7, before attempting to use the software loader cards.
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3.3.2
Loader Card Creation
The software image is an executable self-extracting file which builds the correct file structure onto an SD
card for use loading software to the G1000 and GFC 700. To create a software loader card, follow the
procedures outlined below.
NOTE
In order to create a G1000 system loader card, the facility completing these procedures,
must be an authorized Garmin 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 username and password.
2. Click the I Agree button on the confidentiality agreement page.
3. Select Technical Tools then select Software Downloads.
4. In the Keyword(s) filter, enter “0636” and click on the Go button.
5. A screen similar to the one shown below will appear. The numbers shown are for example only.
Download
link
(example figure)
6. Click on the download symbol for the appropriate software version part number based upon the
information provided in General Arrangement drawing and save the file to the local hard drive.
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7. Double-click the .exe file that was downloaded. The following window will pop-up on the screen.
Ensure that there is an empty SD card in the card reader, and then click Setup.
(example figure)
(example figure)
NOTE
When the extraction begins, the program automatically deletes all current files on the SD
card and copies the selected files to it, regardless of the file format on the SD card. Ensure
files are not necessary, or card is empty before proceeding.
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Version of card
being created
Enter SD card
Click next once
card is inserted
(example figure)
8. Ensure the card and correct drive letter is used, and click next.
Select drive
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9. A window will pop-up onto the screen to indicate file progress.
Copy of files to
selected drive
10. Once successfully completed, the following message/window will pop-up. Click Finish to finalize
SD card.
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3.3.3
Software Files
Software files are defined by part number and version number on the General Arrangement drawing. See
Table 1-2 for the correct General Arrangement drawing part numbers. Each G1000 LRU reports the
software version it currently contains to the user in two places.
1. Normal System Mode: The MFD AUX – SYSTEM STATUS page lists each LRU and the reported
software version. It does not report the software part number.
2. Configuration Mode:
The SYSTEM STATUS page reports more detailed LRU information,
including software version, part number, and LRU status.
Software files for units removed for service are loaded from the SYSTEM UPLOAD page in configuration
mode. See Section 7 for these procedures.
3.3.4
Configuration File Descriptions
Configuration Files are divided into groups, and are only displayed at the System Upload page during the
software/configuration loading process. There are five categories of configuration files:
C90
C90-Options
C90-Configurations
C90-Weight and Airspeed
Configuration files contain preset selections for input/output channels, aircraft-specific settings, and LRUspecific settings. The following list describes each of the configuration files:
AIRFRAME
This file contains data such as airspeed parameters, engine/airframe sensor
limitations, fuel tank parameters and alerting system settings that tailor a G1000
PFD or MFD to the aircraft.
AIRFRAME
ALERTS
C90 Series specific alerts are set when this file is loaded.
SYSTEM
This file configures the G1000 high-speed data bus (HSDB) to expect two PFDs,
MFD, two GIAs, and a GDL69.
MANIFEST
This file loads a manifest checklist of all software part numbers and versions
associated with an approved system configuration. The G1000 performs a
software check between each LRU’s reported version and the version contained
on the manifest. If an inequality is detected for an LRU, this LRU is then
excluded from the G1000 and a manifest alert is triggered to the operator.
MFD1
This file configures MFD serial/discrete communication and alert system
settings.
PFD 1/PFD 2
These files configure PFD 1/PFD 2 serial/discrete communication and alert
system settings.
GCU
This file configures GCU 475 serial/discrete communication settings.
GMC
This file configures GMC 710 serial/discrete communication settings.
GIA1/GIA2
These files configure GIA1/GIA2 serial/discrete communication settings.
GMA1/GMA2
This file configures GMA 1347 audio and serial communication settings
for both audio panels.
GTX1/GTX2
These files configure GTX 1/GTX 2 transponder and serial communications
settings.
GEA1/GEA2
These files configure GEA 1/GEA 2 engine/airframe parameters.
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GDC1/GDC2
This file configures GDC 74B air data values for the C90 Series.
GDL
This file configures GDL 69 gains and cable loss for the C90 Series installation.
GWX
This file configures parameters as appropriate for the C90 Series radar
installation.
AUDIO
This file configures audio alerts for the C90 Series.
3.3.5
Airframe and Optional Configurations
Multiple Garmin and Third Party optional equipment configurations are available with the C90 Series.
These files are loaded after the factory default configuration is established. Each option modifies one or
more of the above configuration files, depending on what setting changes are required to activate the
optional equipment. It should be noted that any required supporting hardware for the option must be
installed before the option can function.
The following default configuration appears at the System Upload page within the ITEM window, when the
“C90” choice is selected from the GROUP window.
King Air C90 – Baseline
The following optional configurations appear at the System Upload page within the ITEM window, when the
“C90-Configurations” choice is selected from the GROUP window. These options are associated with
various Blackhawk, Silverhawk, Raisbeck, C90GT, or C90GTi configurations. If reloading configuration,
refer to Table 5 of the General Arrangement Drawing, listed in Table 1-2, to identify the appropriate
configuration for your aircraft. If the technician needs to determine the configuration of an existing
installation, refer to Section 1.4.
King Air C90A – Config 2
King Air C90A – Config 3
King Air C90A – Config 4
King Air C90A – Config 5
King Air C90A – Config 6
King Air C90A – Config 7
King Air C90A – Config 8
King Air C90A – Config 9
King Air C90A – Config 10
King Air C90GT/GTi – Config 17
King Air C90GT/GTi – Config 18
King Air C90A – Config 19
King Air C90A – Config 21
King Air C90A – Config 22
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The following options appear at the System Upload page within the ITEM window, when the “C90-Weight
and Airspeed” choice is selected from the GROUP window. These options are associated with various
Blackhawk/Raisbeck configurations or unique to aircraft serial numbers. If reloading configuration, refer to
Table 5 of the General Arrangement drawing to identify the appropriate configuration for your aircraft.
Software Ver 0636.01
Software Ver 0636.02
Software Ver 0636.03
King Air C90 –Weight LJ 10631137, 1146
King Air C90 – MTOW 9,650 lbs
King Air C90 – MTOW 9,650 lbs
King Air C90 – 90-206CGW
King Air C90 – MTOW 10,100 lbs
King Air C90 – MTOW 10,100 lbs
King Air C90 – 05-206CGW
King Air C90 – MTOW 10,350 lbs
King Air C90 – MTOW 10,350 lbs
King Air C90 – Airspeed LJ 10631137,1146
King Air C90 – MTOW 10,500 lbs
King Air C90 – MTOW 10,500 lbs
King Air C90 – Airspeed LJ 10631137, 1146
King Air C90 – Centex MTOW
10,353 lbs
King Air C90 – Centex MTOW
10,485 lbs
King Air C90 – Airspeed LJ 10631137, 1146
Software Ver 0636.05
Software Ver 0636.06 and
subs
King Air C90 – MTOW 9,650 lbs
King Air C90 – MTOW 9,650 lbs
King Air C90 – MTOW 10,100 lbs
King Air C90 – MTOW 10,100 lbs
King Air C90 – MTOW 10,350 lbs
King Air C90 – MTOW 10,350 lbs
King Air C90 – MTOW 10,500 lbs
King Air C90 – MTOW 10,500 lbs
King Air C90 – Centex MTOW
10,353 lbs
King Air C90 – Centex MTOW
10,353 lbs
King Air C90 – Centex MTOW
10,485 lbs
King Air C90 – Centex MTOW
10,485 lbs
King Air C90 – Airspeed LJ 10631137, 1146
King Air C90 – Airspeed Tape
Markings for LJ 1063-1137, 1146
King Air C90 – Airspeed LJ 11381299 Except 1146, 1288, and 1295
King Air C90 - 90kt Vmca Airspeed
Tape Marking
King Air C90 – 91kt Vmca Airspeed
Tape Marking
King Air C90 – 93kt Vmca Airspeed
Tape Marking
King Air C90 –208kt Vmo Airspeed
Tape Marking
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The following options appear at the System Upload page within the ITEM window, when the “C90-Options”
choice is selected from the GROUP window.
Software Ver 0636.01 &
0636.02
Software Ver 0636.03 & 0636.05
Software Ver 0636.06
King Air C90 – ADF-60 Option
King Air C90 – ADF-60 Option
King Air C90 – ADF-60 Option
King Air C90 – DME-42 Option
King Air C90 – DME-42 Option
King Air C90 – DME-42 Option
King Air C90 – Traffic System
Option
King Air C90 – Traffic System Option
King Air C90 – Traffic System
Option
King Air C90 - WX 500 Option
King Air C90 - WX 500 Option
King Air C90 - WX 500 Option
King Air C90 – GTX 33 ES Option
King Air C90 – GTX 33 ES Option
King Air C90 – GTX33 ES Option
King Air C90 – ESP Support (no AOA)
King Air C90 – ESP Support
King Air C90 – GSM 85A
King Air C90 – GSM 85A Servo
Mounts
King Air C90 – GSM 86
King Air C90 – GSM 86 Servo
Mounts
King Air C90 – Rad Alt*
King Air C90 – Non-Garmin Radar
Altimeter Option
King Air C90 –GSR 56 Stand-alone*
King Air C90 – Stand-alone GSR56
Option*
King Air C90 – GTS 8XX Traffic*
King Air C90 – GTS 8XX
TAS/TCAS1 Option*
King Air C90 - Non-Garmin Traffic
System Option
King Air C90 - FliteCharts Enable
King Air C90 - GRS77 AHRS
Option
King Air C90 - GRS7800 AHRS
Option
King Air C90 - GWX 68 Radar
Option
King Air C90 - GWX 70 Radar
Option
King Air C90 - TAWS-A Support*
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Software Ver 0636.07 & Subs
King Air C90 – ADF-60 Option
King Air C90 – DME-42 Option
King Air C90 – GDL 69A
King Air C90 – GDL 69A SXM
King Air C90 – Traffic System
Option
King Air C90 - WX 500 Option
King Air C90 – GTX33 ES Option
King Air C90 – ESP Support
King Air C90 – GSM 85A Servo
Mounts
King Air C90 – GSM 86 Servo
Mounts
King Air C90 – Non-Garmin Radar
Altimeter Option
King Air C90 – Stand-alone
GSR56 Option*
King Air C90 – GTS 8XX
TAS/TCAS1 Option*
King Air C90 - Non-Garmin Traffic
System Option
King Air C90 - FliteCharts Enable
King Air C90 - GRS77 AHRS
Option
King Air C90 - GRS7800 AHRS
Option
King Air C90 - GWX 68 Radar
Option
King Air C90 - GWX 70 Radar
Option
King Air C90 - TAWS-A Support*
*These options are not approved by this STC.
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CONFIGURATIONS
AUDIO
GMA_PIL
GMA_COPIL
GTX1
GTX2
GEA1
GEA2
GDC_PIL
GDC_COPIL
X
X
X
X
X
X
X
X
X
X
X
X
X
Configuration 3
X
Configuration 4
X
Configuration 5
X
Configuration 6
X
Configuration 7
X
Configuration 8
X
Configuration 9
X
Configuration 10
X
MFD
GWX
GIA2
X
X
GWX
GDC 74B
#2
AUDIO
X
GDL 69A
GDC 74B
#1
GIA1
X
GDL_69
GTX 33
#2
GMC
X
GEA 71
#2
GTX 33
#1
GCU
X
GEA 71
#1
GMA 1347
#2
MFD1
X
Configuration 2
GMA 1347
#1
PFD 2
X
GIA 63W
#2
PFD 1
Baseline Configuration
GIA 63W
#1
MANIFEST
FILE NAME
GMC 710
SYSTEM
X
LRU
GCU 475
A/F ALERTS
X
PFD
AIRFRAME
Table 3-2, LRU to Configuration File Relationship
X
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X
Configuration 18
X
Configuration 19
X
Configuration 21
X
Configuration 22
X
Airspeed Tape Markings for LJ
1063-1137,1146
X
90kt Vmca Airspeed Tape
Marking
X
91kt Vmca Airspeed Tape
Marking
X
93kt Vmca Airspeed Tape
Marking
X
208kt Vmo Airspeed Tape
Marking
X
GDL 69A
GWX
GWX
GDC 74B
#1
GDC_PIL
GDL_69
GEA 71
#2
GEA2
GDC 74B
#2
GEA 71
#1
GEA1
GDC_COPIL
GTX 33
#2
GTX 33
#1
GTX1
GTX2
GMA
1347 #2
GMA_COPIL
GMA
1347 #1
GMA_PIL
GIA 63W
#2
GIA2
AUDIO
GIA 63W
#1
GMC 710
GMC
AUDIO
GCU 475
GCU
GIA1
MFD
MFD1
PFD 2
PFD 1
SYSTEM
MANIFEST
PFD
Configuration 17
A/F ALERTS
FILE NAME
AIRFRAME
LRU
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X
X
GRS7800 AHRS Option
X
X
X
X
GWX
GWX
X
X
X
X
X
YAW GSM
SERVO
MOUNT
GDL 69A
GDL_69
X
ROLL GSM
SERVO
MOUNT
GDC 74B #2
GDC_COPIL
GRS 7800 #1
GDC 74B #1
YAW SERVO
X
ROLL SERVO
X
PITCH TRIM
SERVO
GRS77 AHRS Option
PITCH GSM
SERVO
MOUNT
PITCH TRIM
GSM SERVO
MOUNT
X
PITCH SERVO
FliteCharts Enable
GRS 7800 #2
X
X
GRS 7800 2
X
X
GRS 7800 1
ESP Option
GDC_PIL
GIA 63W #2
GIA2
X
DME-42 Option
AUDIO
GIA 63W #1
GMC
AUDIO
GMC 710
GCU
GIA1
MFD
GCU 475
MFD1
PFD 2
PFD 1
X
ADF-60 Option
GEA 71 #2
X
GEA2
*Centex MTOW 10,485 lbs
GEA 71 #1
X
GEA1
*Centex MTOW 10,353lbs
GTX 33 #2
X
GTX2
*MTOW 10,500 lbs
GTX 33 #1
X
GTX1
*MTOW 10,350 lbs
GMA 1347
#2
X
GMA_COPIL
*MTOW 10,100 lbs
GMA 1347
#1
X
SYSTEM
PFD
*MTOW 9,650 lbs
GMA_PIL
Optional Configuration Files
CONFIGURATIONS
FILE NAME
MANIFEST
AIRFRAME
ALERTS
LRU
X
X
X
X
X
X
X
X
X
GSM 85A Servo Mounts
GSM 86 Servo Mounts
X
X
X
X
GWX 68 Radar Option
X
X
X
X
* Airframe Weight Configurations shown for C90 System Software PN 006-B0636-02 and subsequent approved software revisions.
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Optional Configuration Files
CONFIGURATIONS
X
GDC 74B
#2
GDL 69A
GWX
GDC_COPIL
GDL_69
GWX
GTS 8XX
GDC 74B
#1
GDC_PIL
GEA 71
#2
GEA2
GEA 71
#1
GEA1
GTX 33
#1
GTX1
GTX 33
#2
GMA
1347 #2
GMA_COPIL
GTX2
GMA
1347 #1
GMA_PIL
GIA 63W
#2
GIA2
AUDIO
GIA 63W
#1
GMC 710
GMC
GIA1
GCU 475
GCU
AUDIO
MFD
MFD1
X
PFD 2
X
PFD 1
PFD
Non-Garmin Radar Altimeter
Option
MANIFEST
X
SYSTEM
GWX 70 Radar Option
ALERTS
FILE NAME
AIRFRAME
LRU
X
X
Non-Garmin Traffic System
Option
X
WX 500 Option
X
X
GTX 33 ES Option
TAWS-A Support Option
X
X
X
Standalone GSR56 Option
X
X
X
GTS 8XX TAS/TCAS1 Option
X
X
X
X
X
X
X
X
X
X
X
X
GDL 69A
X
X
GDL 69A SXM
X
X
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IMPORTANT
Certain software and configuration files are REQUIRED to be re-loaded during
maintenance that involves removal and replacement of G1000 equipment.
Refer to Section 7 for re-configuration requirements for each G1000 LRU. Pay special
attention to the configuration of options for the G1000.
NOTE
Some functions require a separate ENABLE SD card.
Arrangement drawing for card part number.
3.3.6
See the appropriate General
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 except the GRS 77 AHRS and GMU 44 units. Each file is also stored in the PFD internal memory.
The applicable PFD also sends a copy of certain aircraft specific configuration files to the ‘Master
Configuration module’ located in the No.1 PFD connector backshell (see Section 6.16). If PFD 1 is
replaced, the configuration module retains aircraft specific calibration files in the aircraft to restore into the
new PFD 1.
NOTE
The GRS 77 AHRS and GMU 44 Magnetometer do not have a configuration file on the
G1000 system loader card. However, these LRUs do store calibration data acquired during
the post installation checkout which are specific to the aircraft installation. While
performing maintenance on these units, recalibration may be required. See Section 7.7.2
for more information on recalibration criteria.
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G1000 Master Configuration Module
(located in PFD backshell connector)
GMC 710
Master configuration module contains aircraft specific
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 1040A PFD
Contains ‘ACTIVE’ PFD settings.
Represents ‘SET’ column for all
LRUs. Stores all configuration files in
internal memory. Uses master
configuration module for backup of
some aircraft specific data.
GDU 1500 MFD
Contains ‘ACTIVE’
MFD settings. The
MFD uses PFD
internal
configuration files
for backup.
No. 2 GDU 1040A PFD
Contains ‘ACTIVE’ PFD settings.
Represents ‘SET’ column for all
LRUs. Stores all configuration files in
internal memory.
No. 1 GIA 63W
No. 2 GIA 63W
RS-232
Contains ‘ACTIVE’
settings. Uses PFD
internal configuration
files for backup.
Contains ‘ACTIVE’
settings. Uses PFD
internal configuration
files for backup.
RS-485
RS-232
GMA 1347
Contains ‘ACTIVE’
GMA settings. Uses
PFD internal
configuration files for
backup.
RS-232
RS-232
RS-485
(ETHERNET)
RS-232
GMA 1347
Contains ‘ACTIVE’
GMA settings. Uses
PFD internal
configuration files for
backup.
RS-232
HIGH-SPEED DATABUS
No. 1 GEA 71
No. 1 GTX 33
No. 2 GTX 33
No. 2 GEA 71
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.
Contains
‘ACTIVE’
settings. Uses
PFD internal
configuration files
for backup.
GCU 475
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 3-15, G1000 LRU Configuration File Storage
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The GDC 74B configuration module stores a copy of the unit configuration file.
The GRS 77 configuration module does not store any configuration files. Instead, it stores only calibration
data recorded during installation calibration procedures.
The GRS 7800 configuration module stores unit configuration files in addition to calibration data recorded
during installation calibration procedures.
GRS 77/7800 Config Module
GDC 74B Config Module
(located in/on GRS backshell connector)
(located in GDC backshell connector)
Stores a copy of AHRS / magnetometer
calibration values that are recorded upon
completion of post-installation calibration
procedures. For GRS 7800 also stores
some configuration data.
Stores a copy of the GDC 74B configuration
file
GRS 77/7800 AHRS
GDC 74B
The GRS stores calibration data internally.
The GDC 74B stores GDC configuration file internally.
The GRS also stores factory calibration data internally.
Should internal memory or the configuration module fail, AHRS
output data flags invalid.
The GDC 74B also stores factory calibration data internally.
Should internal memory or the configuration module fail, loss
of some or all air data outputs will result.
GRS Internal Memory
GDC Internal Memory
Contains internal sensor calibration data
that is not installation-specific. Data is
stored from factory calibrations.
Contains internal sensor calibration data
that is not installation-specific. Data is
stored from factory calibrations.
Figure 3-16, GRS/GDC Configuration Settings Storage
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3.3.7
G1000 Software Load Summary
The following diagram is an overview of the full software and configuration load sequence for the G1000
system. Detailed instructions for performing the full system load begins in Section 3.4.
GDU 1040A PFDs / GDU 1500 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 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 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 Configuration Verification
After system configuration files are loaded, the technician verifies that the
correct configuration on the Airframe Configuration page.
Figure 3-17, Software/Configuration Overview
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3.4
G1000 System Software and Configuration Load Procedure
This section outlines the procedures required to load all software and configuration files to the G1000
system using System Software Version 0636.07. Earlier System Software Version load in the same manner
as v0636.07, but will not show as many file options (ref Section 3.3.5). Skip software load sections for
equipment not installed with earlier System Software Versions when noted in the procedure.
NOTE
This section is organized for a complete system load if installing a new version of system
software per a Service Bulletin. When replacing individual units for service, follow the
software and configuration loading instructions in Section 7 for that unit. They may instruct
you to return to this Section to only load specific items and not to perform a full system
software load.
3.4.1
Third Party STC Documentation and Optional Equipment List
Make a list of the following to determine what configuration software files to load in the following sections.

Third Party STCs such as Blackhawk, Silverhawk, or Raisbeck STC engine/prop combinations.
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 3.4.10.

Aircraft Weight limits for takeoff, landing, and zero fuel by checking the Beechcraft AFM and any
third party STC AFMS if applicable. This information is required for Section 3.4.11.

Garmin optional equipment (i.e. GRS 77 or 7800 AHRS, GWX 68 or 70 Radar, GSM85A or GSM86
Servo Mounts, etc.).

Third party avionics equipment interfaced to G1000 (ADF, DME, Traffic, etc.).

Record GMA1 and GMA2 Configuration settings for marker beacon settings. A system software
load will change these to default values, so they may need to be reentered at the end of the
procedure to restore previous marker beacon performance.

Check what G1000 Features are Unlocked such as SVT, TAWS-B, ChartView, etc. and find the
Unlock cards for these features.
3.4.2
System Power Up
Connect 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. 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.
3.4.3
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 G1000 software loader card into PFD2 top card slot.
4. Turn on the Avionics electrical busses.
5. On PFD2, press and hold the ENT key.
6. Close the PFD2 circuit breaker.
7. When the words “INITIALIZING SYSTEM” appear in the top left corner of the display, release the
ENT key.
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8. If the display prompts to load Boot Block files, press the YES softkey. This prompt only appears
for older displays and system software that requires this update, so it will not appear if not
needed. The display automatically determines if this update is needed for the installer.
9. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, press the YES
softkey.
10. 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.
11. When complete, the PFD2 may prompt that the load is complete and then it is verifying the
Basemap database file. Follow the onscreen prompts to continue.
12. After the messages, PFD2 starts in configuration mode displaying the SYSTEM STATUS page.
Open the PFD2 circuit breaker.
13. Remove the loader card from PFD2 and insert it into the MFD top card slot.
14. Repeat Steps 5 through 12 for the MFD. The MFD does not have an ENT key, so instead use
softkey #12 for ENT when stated above.
15. When MFD update is complete and unit off, remove the loader card from the MFD and insert it into
the PFD1 top card slot.
16. Repeat Steps 5 through 12 for PFD1. When complete, leave PFD1 on with the loader card
remaining in the top card slot.
17. Start the MFD and PFD2 in configuration mode by pressing and holding the ENT key or softkey
#12 when closing their circuit breakers and releasing the key when the words “INITIALIZING
SYSTEM” appear on the screen.
18. Continue to Section 3.4.4.
3.4.4
Initial G1000 System Software and Baseline Configuration Load
IMPORTANT
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 3 in this Section 3.4.4.
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1. Ensure all avionics circuit breakers are closed and the G1000 system is fully powered
2. On PFD 1, go to the SYSTEM UPLOAD page using the small FMS knob.
3. Activate the cursor and use the small FMS knob to highlight ”C90” in the GROUP window. Press
the ENT key to select.
4. Once C90 is selected the cursor moves to the ITEM window. Rotate the small FMS knob to activate
the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file and press the ENT
key.
NOTES
The PRODUCT window displays information regarding each G1000 LRU. The LRU VERS
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.
There should be a GSA line in the product window for each servo (pitch, pitch trim, roll,
and yaw). Any missing servo may not be reporting its serial number to the system and need
troubleshooting for power and communications. Serial number reporting can be verified on
the SYSTEM STATUS page.
5. Press the CHK ALL softkey.
6. Press the LOAD softkey.
7. Observe software loading progress and verify software load completes as indicated by the
following:
 Green “PASS” or N/A in SOFTWARE and CONFIGURATION columns for all items.
 “Upload Complete………….COMPLETE” in the summary box.
8. If a unit software or configuration load fails, the software load process stops. Verify the unit is
installed and has power, then you may restart the load process by pressing the LOAD softkey and
the load should resume at the failed point. If a unit continues to fail loading software or configuration
files, stop the load process and troubleshoot the unit and/or call Garmin Product Support for
assistance.
9. Press the ENT key to acknowledge the “Upload Complete” box.
10. Proceed to Section 3.4.5.
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3.4.5
GDL 69A Legacy Software/Configuration
This procedure is for G1000 System Software Version 0636.07 and subsequent. For version 0636.06 and
previous, skip and continue to Section 3.4.9 as these files are loaded previously in the baseline load.
Follow this procedure to configure the GDL69A Legacy (Part Number 011-00987-00) if installed.
1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM
UPLOAD” page using the small FMS knob on PFD1.
2. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the small
FMS knob to highlight “C90-Options” and press ENT key on PFD1.
3. Rotate the small FMS knob to highlight “King Air – GDL69A Legacy”. Press ENT key on PFD1.
4. Verify “King Air - GDL69A Legacy” is displayed in the “Item” window. 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. Press ENT key on PFD1 to acknowledge upload complete.
7. Deactivate cursor.
3.4.6
GDL 69A SXM Software/Configuration
This procedure is for G1000 System Software Version 0636.07 and subsequent.
Follow this procedure to configure the GDL69A SXM (Part Number 011-03177-10) if installed.
1. With the loader card in the top slot of PFD1 and PFD1 in configuration mode, select the “SYSTEM
UPLOAD” page using the small FMS knob on PFD1.
2. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the small
FMS knob to highlight “C90-Options” and press ENT key on PFD1.
3. Rotate the small FMS knob to highlight “King Air – GDL69A SXM”. Press ENT key on PFD1.
4. Verify “King Air – GDL69A SXM” is displayed in the “Item” window. 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.
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.
6. Press ENT key on PFD1 to acknowledge upload complete.
7. Deactivate cursor.
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3.4.7
GRS AHRS / GMU 44 Magnetometer Software and Configuration Load
This procedure is for G1000 System Software Version 0636.06 and subsequent. For version 0636.05 and
previous, skip and continue to Section 3.4.9 as these files are loaded previously in the baseline load.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight ‘C90-Options’ and press the ENT key to select.
2. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 - GRS77 AHRS
Option” or “King Air C90 - GRS7800 AHRS Option” file for the unit installed and press the ENT
key.
3. Press the CHK ALL softkey.
4. Press the LOAD softkey.
5. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.8.
3.4.8
GWX 68 / 70 Radar Software and Configuration Load
This procedure is for G1000 System Software Version 0636.06 and subsequent. For version 0636.05 and
previous, skip and continue to Section 3.4.9 as these files are loaded previously in the baseline load.
1. Move the cursor to the ITEM window. Rotate the small FMS knob to activate the drop-down menu.
Move the cursor to highlight “King Air C90 - GWX 68 Radar Option” or ”King Air C90 - GWX 70
Radar Option” file for the unit installed and press the ENT key.
2. Press the CHK ALL softkey.
3. Press the LOAD softkey.
4. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
5. Press the ENT key to acknowledge upload complete
6. Continue to Section 3.4.9.
3.4.9
GSM 85A / 86 Servo Mount Configuration Load
This procedure is for G1000 System Software Version 0636.03 and subsequent. For version 0636.02 and
previous, skip and continue to Section 3.4.10 as these files are loaded previously in the baseline load.
1. Move the cursor to the GROUP window. Highlight “C90-Options” file and press the ENT key.
2. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 - GSM 85A
Servo Mounts” or “King Air C90 - GSM 86 Servo Mounts” file for the units installed and press
the ENT key.
3. Press the CHK ALL softkey.
4. Press the LOAD softkey.
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5. Observe software loading progress and verify software load completes without errors as indicated
by the following:
 Green “PASS” in the Configuration column for all items.
 “Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.10
3.4.10 King Air C90 Airframe Configuration
3.4.10.1 Determining Airframe Configuration
Aircraft in the following serial number range that have not been modified by the STCs listed below do not
require additional airframe configuration. Proceed to Section 3.4.11.
Serial number range –

1361, 1363-1366, 1368-1372, 1374-1376, 1378-1383, 1385, 1387-1388, 1390-1393, 1395-1396,
1398-1402, 1404-1410, 1412-1424,1426-1430, 1432-1497, 1499-1537, 1539, 1540-1726, 17281753,1755
STCs 
Blackhawk SA10341SC Opt. 2- Installation of Pratt & Whitney Canada PT6A-135A engines and
Hartzell HC-D4N-3C/D9290(S)(K) or HC-E4N-3N/D8990S(K) propellers.

Blackhawk SA10364SC - Installation of Pratt & Whitney Canada PT6A-135A engines and
McCauley 4HFR34C762/94LMA-4 or 4HFR34C768/94LMA-4 propellers.

Silverhawk SA10741SC - Installation of Pratt & Whitney Canada PT6A-135A engines and Hartzell
HC-E4N-3N/D8990S(K) or HC-B3TN-3( ,B,M)/T10173(E,B,NB,K,NK)-8 or McCauley
4HFR34C768/94LMA-4 propellers.

Raisbeck SA3593NM - Installation of Hartzell/Raisbeck quiet or swept blade turbofan propellers.
For aircraft modified by the Blackhawk, Silverhawk, and/or Raisbeck STCs above, refer to Table 5 of the
General Arrangement drawing to determine the applicable configuration file to load.
Example
A/C serial number - 1362

A/C modified by - Raisbeck STC SA3593NM with AFMS 86-206C

Configuration to be loaded – King Air C90A – Config 7
Once the correct configuration is determined, load the appropriate King Air C90 configuration per Section
3.4.10.2 below.
IMPORTANT
If the aircraft being modified has incorporated any modifications beyond Beechcraft factory
configuration or the Third Party STCs listed above 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. Contact Garmin Product Support if
assistance is needed to determine compatibility with modifications not listed in Garmin STC
documentation.
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3.4.10.2 Loading Airframe Configuration.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Configurations” and press the ENT key to select it.
2. In the ITEM window, rotate the inner FMS knob to view the list of available C90 configurations and
highlight the correct configuration file as determined in Section 3.4.10.1. Press the ENT key to
select the file required.
3. Verify the correct configuration file is displayed in the ITEM window (for example “King Air C90A –
Configuration 7”).
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.11.
3.4.11 Weight and Airspeed Configuration
In addition to the airframe configuration loaded above, certain installations will require additional steps to
configure the G1000 for airframe weight and airspeed markings. The information gathered in Section 3.4.1
is required to choose the correct files in the following Sections. If you do not have the information from
Section 3.4.1, -STOP- and find the aircraft information from that Section before continuing.
3.4.11.1 Weight Configuration Options
One of the following files will need to be loaded to configure the G1000 system with the correct aircraft
weight limitations. Use the aircraft weight information obtained from Section 3.4.1 to find the correct file in
the table below, then continue to Section 3.4.11.2, Loading Airframe Weight Configurations.
OPTIONAL AIRFRAME WEIGHT CONFIGURATIONS
MTOW
9,650 lbs
10,100 lbs
MZFW
No Limitation
9,000 lbs
MLDW
9,168 lbs
9,700 lbs
10,100 lbs
No Limitation
9,600 lbs
10,350 lbs
10,500 lbs
10,353 lbs
10,485 lbs
9,000 lbs
9,000 lbs
9,378 lbs
9,378 lbs
9,700 lbs
9,700 lbs
9,700 lbs
9,832 lbs
Optional Weight Configuration
King Air C90 – MTOW 9,650 lbs
King Air C90 – MTOW 10,100 lbs,
MZFW 9000 lbs, MLW 9700 lbs.
King Air C90 – MTOW/MZFW 10,100
lbs, MLW 9600 lbs.
King Air C90 – MTOW 10,350 lbs
King Air C90 – MTOW 10,500 lbs
King Air C90 – Centex MTOW 10,353 lbs
King Air C90 – Centex MTOW 10,485 lbs
Table 3-3, Optional Airframe Weight Configurations
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3.4.11.2 Loading Airframe Weight Configurations
Follow this procedure to enable the airframe weight configuration.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Weight and Airspeed” and press ENT key.
2. In the ITEM window, rotate the inner FMS knob to view the list of available C90 option files. Highlight
the correct airframe weight option file as determined in Section 3.4.11.1 above and press the ENT
to select.
3. Verify the correct configuration file is displayed in the ITEM window and the AIRFRAME
configuration box is checked.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.11.3.
3.4.11.3 Determining the Correct Airspeed Indication Markings
Additional Airspeed option files will need to be loaded for certain aircraft serial numbers to position airspeed
tape markings correctly. Check the following conditions for your serial number aircraft to see if an airspeed
option file will need to be loaded.
If an airspeed option file needs to be loaded, follow the procedure in Section 3.4.11.4 for each file. If none
of the conditions below apply to your serial number aircraft, continue to Section 3.4.12.

For aircraft serial numbers LJ-1063 through LJ-1137 and LJ-1146:
o
Load the following airspeed configuration file:
“King Air C90 – Airspeed Tape Markings for LJ 1063 – 1137, 1146“.
o
If you have Raisbeck AFMS Part Number 13-C90-135A-1900, 13-C90-135A-1900SH,
90-206CGW, 05-206CGW, 13-206CGW, or C90-135A-1900, load the following airspeed
configuration file:
“King Air C90 - 208kt Vmo Airspeed Tape Marking”

All aircraft serial numbers:
o
If you have Raisbeck AFMS Part Number 86-206C, 90-206CGW, 05-206CGW, C90-135A1900, C90GT-1900, or 09-135-206, load the following airspeed configuration file:
“King Air C90 - 90kt Vmca Airspeed Tape Marking”.
o
If you have Raisbeck AFMS Part Number 13-135-206, 13-C90GT-1900, 13-C90-135A-1900,
13-C90-135A-1900SH, 14-C90GTx, or 14-C90GTRx, load the following airspeed configuration
file:
“King Air C90 - 91kt Vmca Airspeed Tape Marking”.
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o
If you have Raisbeck AFMS Part Number 13-206C or 13-206CGW, load the following airspeed
configuration file:
“King Air C90 - 93kt Vmca Airspeed Tape Marking”
3.4.11.4 Loading Airspeed Marking Option Files
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Weight and Airspeed” and press the ENT key.
2. In the ITEM window, rotate the inner FMS knob to view the list of available C90 configurations.
Highlight the correct airspeed indicator marking configuration file as determined in Section 3.4.11.3
above and press the ENT key.
3. Verify the correct configuration file is displayed in the ITEM window and the configuration box is
checked.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Load the next airspeed file if needed following steps 2 through 6.
8. Proceed to Section 3.4.12.
3.4.12 Non-Garmin Traffic System Option Configuration
This section loads the necessary configuration files for those aircraft equipped with a traffic system. If this
option is not needed, skip and continue to Section 3.4.13.
NOTE
The G1000 can only be configured for TIS or TAS but not both. Performing this procedure
will automatically disable the TIS function. Coordinate this configuration with Section
Traffic System Functional Check (Optional).
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the inner FMS knob to view the list of available C90 options. Highlight
the “King Air C90 – Non-Garmin Traffic System Option” file and press the ENT key.
3. Verify the “King Air C90 – Non-Garmin Traffic System Option” configuration file is displayed in
the ITEM window and the GIA 2 configuration box is checked.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.13.
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3.4.13 GTS 8XX Traffic System Option Configuration
This STC does not approve the installation or configuration of the GTS 8XX traffic system. A separate
installation approval is required to interface the GTS 8XX traffic system to G1000. This file is provided to
assist the installer to obtain a separate installation approval for the GTS 8XX system if desired. Continue
to Section 3.4.14.
3.4.14 Stormscope (WX-500) Option Configuration
This section loads the necessary configuration files for those aircraft equipped with a Stormscope WX500.
If this option is not needed, skip and continue to Section 3.4.15.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu..
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the inner FMS knob to view the list of available C90 Options. Highlight
the “King Air C90 – WX 500 Option” file and press the ENT key.
3. Verify the “King Air C90 – WX 500 Option” configuration file is displayed in the ITEM window.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.15.
3.4.15 ADF – 60 Option Configuration
This section loads the necessary configuration files for those aircraft equipped with a ADF 60. If this option
is not needed, skip and continue to Section 3.4.16.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the FMS inner knob to view the list of available C90 Options. Highlight
the “King Air C90 – ADF-60 Option” file and press the ENT key.
3. Verify the “King Air C90 – ADF-60 Option” configuration file is displayed in the ITEM window.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.16.
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3.4.16 Radar Altimeter Option Configuration
This section loads the necessary configuration files for the display of radar altimeter altitude on the G1000.
This STC does not approve the installation of the radio altimeter system. If a radar altimeter is not installed,
skip and continue to Section 3.4.17
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the FMS inner knob to view the list of available C90 Options. Highlight
the “King Air C90 - Non-Garmin Radar Altimeter Option” and press the ENT key.
3. Verify the “King Air C90 - Non-Garmin Radar Altimeter Option” is displayed in the ITEM window.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.17.
3.4.17 DME 42 Option Configuration
This section loads the necessary configuration files for those aircraft equipped with a DME 42. If a DME
42 is not installed, skip and continue to Section 3.4.18.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the FMS inner knob to view the list of available C90 Options. Highlight
the “King Air C90 – DME-42 Option” file and press ENT key.
3. Verify the “King Air C90 – DME-42 Option” configuration file is displayed in the ITEM window.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.18.
3.4.18 GTX 33 Extended Squitter (ES) Option Configuration
This section loads the necessary configuration files for those aircraft equipped with GTX 33ES
transponders. If these transponders are not installed, skip and continue to Section 3.4.19.
NOTE
The GTX 33 Transponder Part Number 011-00779-10 will require an upgrade to support
ES functionality prior to enabling the GTX 33 ES Option and must be routed to the Garmin
Service Center for this upgrade. If GTX 33 ES Transponder Part Number 011-00779-30
is installed in the aircraft, then the GTX 33 ES Option can be enabled. Reference the C90
General Arrangement Drawing for GTX 33 Transponder LRU software and version part
numbers compatible with extended squitter functionality.
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1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the FMS inner knob to view the list of available C90 Options. Highlight
the “King Air C90 – GTX33 ES Option” file and press the ENT key.
3. Verify the “King Air C90 – GTX33 ES Option” configuration file is displayed in the ITEM window.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.19.
3.4.19 ESP Support Option Configuration
This section loads the necessary configuration files for those aircraft that will enable the ESP and USP
features. If these features are not to be installed, skip and continue to Section 3.4.20.
An Enhanced AFCS unlock card is also required to enable this option (see Section 3.4.27.) and is loaded
later in this procedure.
1. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Options” and press the ENT key.
2. In the ITEM window, rotate the FMS inner knob to view the list of available C90 Options. Highlight
the “King Air C90 - ESP Support” file and press the ENT key.
3. Verify the “King Air C90 - ESP Support” configuration file is displayed in the ITEM window.
4. Press the LOAD softkey.
5. Monitor load progress. Verify software load completes without errors as indicated by the
following:

Green “PASS” in Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
6. Press the ENT key to acknowledge upload complete.
7. Continue to Section 3.4.20.
3.4.20 GSR56
This STC does not approve the installation or configuration of the GSR 56 satellite receiver. A separate
installation approval is required to interface the GSR56 Iridium system to G1000. This file is provided to
assist the installer to obtain a separate installation approval for the GSR 56 system if desired. Continue to
Section 3.4.21.
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3.4.21 Update Config Module
1. On PFD1, press the UPDT CFG softkey.
2. When the “Update Config Module?” prompt appears, verify YES is highlighted and press the ENT
key.
3. When the “Update Config Module” window says it is complete, press the ENT key.
4. Wait ten minutes before continuing for the displays to have sufficient time to crossfill data.
5. Open PFD1 circuit breaker and remove the G1000 system loader card.
6. Continue to Section 3.4.22.
3.4.22 Jeppesen ChartView Enable
Follow this procedure to enable the ChartView option. A ChartView Enable Card as specified in the General
Arrangement drawing will be required for this procedure. If ChartView is not desired, skip and continue to
Section 3.4.23.
NOTES
The required ChartView databases are subscription-based and are to be procured by the
installing agency directly from Jeppesen.
The G1000 can only be configured for FliteCharts or ChartView but not both. Performing
this procedure will automatically disable the FliteChart option. Coordinate this configuration
with Section 3.7.12 “ChartView Functional Check”.
1. Insert the ChartView Enable card in the top slot of PFD1.
2. Start PFD1 in configuration mode.
3. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
4. Go to the SYSTEM UPLOAD page.
5. Turn on the cursor and rotate the small FMS knob to activate the drop-down menu in the GROUP
window. Highlight “Configuration Files” and press the ENT key.
6. In the ITEM window, select the “Enable ChartView” file and press the ENT key.
7. Verify the AIRFRAME configuration box is checked. If it is not, 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 column for all items.

“Upload Complete………….COMPLETE” in the summary box.
10. Press the ENT key to acknowledge upload complete.
11. Open PFD1 circuit breaker and remove the ChartView Enable card.
12. Continue to Section 3.4.24.
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3.4.23 FliteCharts Enable
If ChartView has previously been enabled and is no longer desired, follow the procedures outlined in this
section to return the G1000 system to the basic FliteChart functions. If ChartView has not been enabled,
skip and continue to Section 3.4.24.
NOTE
The G1000 can only be configured for FliteCharts or ChartView but not both. Performing
this procedure will automatically disable the ChartView function if it was previously enabled.
Coordinate this configuration with Section “FliteChart Functional Checks”.
1. Insert the G1000 system loader card in the top slot of PFD1.
2. Start PFD1 in configuration mode.
3. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, press the NO softkey.
4. If a “DO YOU WANT TO UPDATE THE SPLASH SCREEN?” prompt appears, press the NO
softkey. The splash screen will be loaded later in this procedure.
5. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
6. Go to the SYSTEM UPLOAD page.
7. Turn on the cursor and rotate the small FMS knob to activate the drop-down menu in the GROUP
window. Highlight “C90-Options” file and press the ENT key.
8. In the ITEM window, highlight “King Air C90 - FliteCharts Enable” file and press the ENT key.
9. Verify the AIRFRAME configuration box is checked. If it is not, press the CHK ALL softkey.
10. Press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete.
13. Open PFD1 circuit breaker and remove the system loader card.
14. Continue to Section 3.4.24.
3.4.24 TAWS B Enable
Follow this procedure to enable the TAWS Class B function. A TAWS B Enable Card as specified on
General Arrangement drawing will be required for this procedure. If TAWS B is not desired, skip and
continue to Section 3.4.25.
1. Insert the TAWS B Enable card in the top slot of PFD1.
2. Start PFD1 in configuration mode.
3. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
4. Go to the SYSTEM UPLOAD page.
5. Turn on the cursor and rotate the small FMS knob to activate the drop-down menu in the GROUP
window. Highlight “Configuration Files” file and press the ENT key.
6. In the ITEM window, highlight ‘Enable TAWS’ option and press the ENT key.
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7. Press the LOAD softkey.
8. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
9. Press the ENT key to acknowledge upload complete.
10. Open PFD1 circuit breaker and remove the TAWS B Enable card.
11. Continue to Section 3.4.25.
3.4.25 TAWS A Option
This STC does not approve the installation or configuration of TAWS-A. A separate installation approval is
required to enable the TAWS-A function. This file is provided to assist the installer to obtain a separate
installation approval for TAWS-A if desired. Continue to Section 3.4.26.
3.4.26 SVS/Pathways Enable
Follow this procedure to enable the Synthetic Vision option. A GDU1XXX SVS Unlock 2 PFDs Card as
specified on General Arrangement Drawing will be required for this procedure. If this feature is not desired,
skip and continue to Section 3.4.27.
NOTES
The Garmin Synthetic Vision and Pathways feature requires 9 arc-second high resolution
terrain databases to function. Each G1000 display must be equipped with the 010-0033043 Terrain/Obstacle/SafeTaxi database card installed in the lower slot.
When the SVS/Pathways option is enabled for the first time the G1000 writes its unique
system ID to the Unlock card and locks the files to this unique ID. This prevents the
SVS/Pathways unlock card from use in other G1000 systems.
The unlock card is tied to the specific aircraft in which it was used for the first time. This
card MUST be kept with the aircraft for situations where SVS/Pathways must be reactivated.
1. Insert the SVS Enable card in the top slot of PFD1.
2. Start PFD1 in configuration mode.
3. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
4. Go to the SYSTEM UPLOAD page.
5. Turn on the cursor and rotate the small FMS knob to activate the drop-down menu in the GROUP
window. Highlight “Configuration Files” file and press the ENT key.
6. In the ITEM window, highlight “Enable SVS Dual PFD” file and press the ENT key.
7. Press the LOAD softkey.
8. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
9. Press the ENT key to acknowledge upload complete.
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10. Open PFD1 circuit breaker and remove the SVS Enable card.
11. Continue to Section 3.4.27.
3.4.27 ESP Enable
Follow this procedure to enable the Electronic Stability and Protection (ESP) function. An Enhanced AFCS
Unlock Card as specified on General Arrangement drawing will be required for this procedure. If this feature
is not desired, skip and continue to Section 3.4.28.
NOTE
Ensure that the “ESP Support” option file has been loaded previously from the G1000
system loader card per Section ESP Enable 3.4.19.
1. Insert the Enhanced AFCS Unlock card in the top slot of PFD1.
2. Start PFD1 in configuration mode.
3. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
4. Go to the SYSTEM UPLOAD page.
5. Turn on the cursor and rotate the small FMS knob to activate the drop-down menu in the GROUP
window. Highlight “Enhanced AFCS” file and press the ENT key.
6. In the ITEM window, highlight “Enable Enhanced AFCS” file and press the ENT key.
7. Verify the AIRFRAME configuration box is checked. If it is not, 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 column for all items.

“Upload Complete………….COMPLETE” in the summary box.
10. Press the ENT key to acknowledge upload complete.
11. Open PFD1 circuit breaker and remove the ESP Enable card.
12. Continue to Section 3.4.28.
3.4.28 Optional Search and Rescue Enable
Follow this procedure to enable the Search and Rescue (SAR) function. A SAR Enable Card as specified
on the General Arrangement drawing will be required for this procedure. If this feature is not desired, skip
and continue to Section 3.4.29.
1. Insert the Search and Rescue Enable card in the top slot of PFD1.
2. Start PFD1 in configuration mode.
3. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
4. Go to the SYSTEM UPLOAD page.
5. Turn on the cursor and rotate the small FMS knob to activate the drop-down menu in the GROUP
window. Highlight “Enhanced SAR” file and press the ENT key.
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6. In the ITEM window, highlight “Enhanced Search and Rescue” file and press the ENT key.
7. Verify the AIRFRAME configuration box is checked. If it is not, 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 column for all items.

“Upload Complete………….COMPLETE” in the summary box.
10. Press the ENT key to acknowledge upload complete.
11. Open PFD1 circuit breaker and remove the Search and Rescue Enable card.
12. Continue to Section 3.4.29.
3.4.29 Aircraft Registration Number Entry
NOTE
There are two different procedures in this section, one for G1000 System Software Version
0636.05 and previous and one for G1000 System Software Version 0636.06 and
subsequent. Follow the procedure for your system software version.
3.4.29.1 System Software Version 0636.05 and Previous
1. Start PFD1 in configuration mode.
2. On PFD1, go to the GTX page group then select the TRANSPONDER CONFIGURATION page.
3. Select or verify selected, XPDR1 is in the SELECT TRANSPONDER window.
4. Ensure that the ‘ADDRESS TYPE’ is ‘US TAIL’ under the ‘SET’ and ‘ACTIVE’ columns.
5. Activate the cursor and highlight the ‘ADDRESS’ field. Use the small/large FMS knobs to enter the
aircraft registration number.
Figure 3-18, Aircraft Registration
6. Once the correct registration number is entered, press the ENT key. The transponders are
configured.
7. Press the ENT key on PFD1 to acknowledge prompt.
8. Verify FLIGHT ID TYPE = SAME AS TAIL under SET and ACTIVE columns.
9. After completing transponder configuration, deactivate the cursor.
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10. Continue to Section 3.4.30.
3.4.29.2 System Software Version 0636.06 and Subsequent
1. Start PFD1 in configuration mode.
2. Messages may appear on the display about a missing “ARFRM_IMGS.ZIP” file and/or verifying
databases. These are resolved later in this procedure. Follow the onscreen prompts to continue.
3. On PFD1, go to the AIRCRAFT CONFIGURATION page.
4. Turn on the cursor and enter the aircraft’s tail number in the AIRCRAFT REGISTRATION field.
Press the ENT key after entering the number to save.
5. Move the cursor to the ICAO ADDRESS field and enter the aircraft’s 24 bit ICAO address. This
field populates automatically with the entry of a “N” registration number. Press the ENT key after
entering the number to save.
6. If applicable, move the cursor to the IATA AIRLINE DESIGNATOR field and enter the airline’s
designator code. Press the ENT key after entering the number to save.
7. Move the cursor to the VFR CODE field and enter the desired code that will become active when
the VFR key on the GDU is pressed. Press the ENT key after entering the number to save.
8. Press the “SET GTX1” softkey and acknowledge the GTX #1 save prompt by pressing the ”ENT
key.
9. Press the ENT key to acknowledge upload complete.
10. Press the “SET GTX2” softkey and acknowledge the GTX #2 save prompt by pressing the ENT
key.
11. Press the ENT key to acknowledge upload complete.
12. After completing transponder configuration, turn off the cursor.
13. Continue to Section 3.4.30.
3.4.30 GMA 1347 #1 and GMA 1347 #2 Configuration Settings Check
1. On PFD1, go to the GMA CONFIGURATION page.
2. Compare the marker beacon values to the original values before the software update.
3. If there are differences on some items, turn on the cursor and enter the original value then press
the ENT key to save the new values.
4. Move the cursor to the SELECT GMA UNIT window and choose GMA1347 #2.
5. Repeat steps 2-3 for GMA1347 #2.
6. Turn off the cursor when done.
7. Continue to Section 3.4.31.
3.4.31 Clearing Default User Settings and Splash Screen Loading
1. Open the PFD1, PFD2, and MFD circuit breakers.
2. Place the software loader card in the top slot of PFD2.
3. Hold the CLR and ENT keys on PFD2 and close PFD2 circuit breaker.
4. Release the CLR and ENT keys when the words “Initializing System” appear on the screen.
5. When prompted to clear user settings select the YES softkey.
6. When prompted to update system files, press the NO softkey.
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7. When prompted to update splash screen files, press the YES softkey.
8. When the load is complete, follow the onscreen prompt to continue.
9. When the display shows the SYSTEM STATUS config page, open PFD2 circuit breaker.
10. Remove the loader card from PFD2 and insert it into the upper slot of the MFD.
11. Hold the #12 softkey on the MFD and close the MFD circuit breaker.
12. Let go of the #12 softkey key when the words “Initializing System” appear on the screen.
13. When prompted to update system files, press the NO softkey.
14. When prompted to update splash screen files, press the YES softkey.
15. When the load is complete, follow the onscreen prompt to continue.
16. When the display shows the SYSTEM STATUS config page, open MFD circuit breaker.
17. Remove the loader card from the MFD.
18. Hold the #11 softkey on the MFD and close the MFD circuit breaker.
19. Let go of the #11 softkey key when the words “Initializing System” appear on the screen.
20. When prompted to clear user settings select the YES softkey.
21. When the clear user setting function is complete, follow the onscreen prompt to continue.
22. When the display shows the Garmin splashscreen page, open MFD circuit breaker.
23. Insert the loader card into the upper slot of PFD1.
24. Repeat steps 3 through 9 for PFD1.
25. Remove the loader card from PFD1.
26. Turn off the G1000 system.
27. Continue to Section 3.5.
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3.5
Software and Configuration Load Verification
This section is performed after a full G1000 system software load to check that the correct software version
and airframe configuration were loaded.
3.5.1
Software Verification
Figure 3-19, System Status
1. Open the PFD1, PFD2, and MFD circuit breakers.
2. Turn on the G1000 system.
3. Start PFD1, PFD2, and the MFD in configuration mode.
4. On PFD1, turn on the cursor and highlight each of the items in the LRU window. Verify that the
software part number and version reported in the DATA window matches the software part
number and version listed in the General Arrangement drawing for the system software version
loaded.
5. Turn off the cursor when complete.
6. Continue to Section 3.5.2.
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3.5.2
Airframe Configuration Verification
1. On PFD1, go to the GDU page group.
2. Go to the AIRFRAME CONFIGURATION page.
3. Verify the correct airframe configuration is displayed in the IDENTIFICATION window.
IMPORTANT
If any software part numbers/versions and/or airframe configuration do not match those
specified by the General Arrangement drawing, reload the software and/or configuration
files to correct. If the installer cannot determine which files to reload or suspects loading
steps were skipped, the software load procedure should be restarted at Section 3.4.4.
4. Continue to Section 3.5.3.
3.5.3
Stormscope (WX-500) Configuration Load Confirmation.
If this option is not installed, skip and continue to Section 3.6.
1. On PFD1, go to the OTHER page group.
2. Go to the STORMSCOPE© page.
Figure 3-20, Stormscope Configuration Page (Reference Only)
3. Turn on the cursor and highlight the DATA field. Use the small FMS knob to open the drop down
menu then highlight “Config” and press the ENT key.
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4. Verify that the DATA window shows the following:
Hdg: None:
J3-1
J3-2
Hdg Valid Flag
Flag Sense
Hdg Value
Inhibit Line
Antenna Mount
J3-4
<aircraft heading>
Off
Bottom
J3-3
Jumper
Jumper
No Flag
+invld
Open
Open
5. Turn off the cursor.
NOTE
The DATA window is updated once every five seconds. Changes may not be visible until
the window has refreshed.
3.6
Final G1000 System Setup
3.6.1
Navigation Database Loading
This section shows how to load the Navigation database into the MFD and allow the G1000 system to
crossfill the database to PFD1 and PFD2. The installer may optionally load the Navigation database into
each display individually. If a current Navigation database is loaded, skip and continue to Section 3.6.2.
1. Turn off the G1000 system.
2. Use a blank SD card to obtain a current Navigation database from Jeppesen or Garmin. Do NOT
use the G1000 system loader card or a Garmin database card.
3. Insert the SD card containing the current Navigation database into the top slot of the MFD.
4. Turn on the G1000 system. A prompt similar to the following will be displayed on the MFD:
5. Select the YES softkey to confirm the standby navigation database update. After the database is
updated, a prompt similar to the following will be displayed on the MFD:
6. Select the NO softkey.
7. After the MFD starts in normal mode, the system will synchronize and automatically update the
other display’s Nav standby databases. Go to the MFD AUX - SYSTEM STATUS page and monitor
the synchronization process in the SYNC STATUS sub-section in the DATABASE window This
sub-section is only present when a sync is occurring or has occurred on the current power cycle.
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8. If an error occurs during synchronization, one of the following messages will be displayed followed
by the affected GDU:

Err No Space - SD card does not contain sufficient memory

Timeout – system timed-out prior to the database transfer completing

Canceled - an active synchronization has been cancelled due to the SYNC DBS softkey being
unselected

Err – displayed for all other errors
NOTE
A power cycle is required to restart synchronization when ‘Err No Space’ or ‘Err’
is shown.
9. When the synchronization is complete, the status is shown as ‘Complete’.
10. Cycle power to PFD1, PFD2, and MFD.
11. After the displays have started in normal mode, go to the MFD AUX – SYSTEM STATUS page and
press the MFD1 DB softkey. Scroll through the database list and confirm that the current NAV
database is loaded.
12. Press the MFD1 DB softkey again to toggle to PFD1 DB. Scroll through the database list for PFD1
and confirm that the correct NAV database is loaded.
13. Press the PFD1 DB softkey again to toggle to PFD2 DB. Scroll through the database list for PFD2
and confirm that the correct NAV database is loaded.
14. Continue to Section 3.6.2.
3.6.2
Terrain/Obstacle Database Card Loading
1. Open the PFD1, PFD2 and MFD circuit breakers.
2. Insert a SD card containing current Terrain/Obstacle database cards into each of the bottom slots
of the PFDs and MFD. Refer to the General Arrangement drawing for the correct card part
numbers.
3. Close the PFD1, PFD2 and MFD circuit breakers.
4. At power-on, several messages may appear on each display to verify the databases on the card.
This is normal. Follow the onscreen prompts to continue past these messages.
5. On the MFD, go to the AUX – SYSTEM STATUS page.
6. Press the MFD1 DB softkey. Scroll through all of the databases contained in the MFD and
confirm that the Garmin databases are listed. Some databases like the Terrain database may
need a few minutes to verify and show the version number. If this occurs, wait for all the
databases to complete verification before continuing.
7. Press the MFD1 DB softkey again to toggle to PFD1 DB. Scroll through all of the databases
contained in the PFD1 and confirm that the Garmin databases are listed.
8. Press the PFD1 DB softkey again to toggle to PFD2 DB. Scroll through all of the databases
contained in the PFD2 and confirm that the Garmin databases are listed.
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NOTE
If Garmin databases contained on the Terrain/Obstacle cards are out of date, updated
databases can be obtained at Fly.garmin.com.
9. Continue to Section 3.6.3.
3.6.3
Configuration of Navigation Map for Non-Garmin Traffic System
This section applies if a non-Garmin traffic system is installed and configured. If a non-Garmin traffic system
is not installed, proceed to Section 3.7.
1. Use the GCU FMS knob to select the MFD NAVIGATION MAP page.
2. Press the GCU MENU key to display the PAGE MENU.
3. Highlight the “MAP SETUP” option and press the ENT key
4. In the GROUP window, highlight “Traffic” and press the ENT key.
5. Use the GCU FMS knobs and ENT key to modify the following selections to match below:

TRAFFIC is selected ON

TRAFFIC MODE – ALL TRAFFIC

TRAFFIC SMBL – 300NM

TRAFFIC LBL – 300NM
6. Return to the Map Page by pressing the GCU FMS knob or momentarily pressing and holding the
CLR key.
7. Turn off cursor.
8. Continue to Section 3.7.
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3.7
G1000 System Testing
This section outlines instructions for testing the various aircraft systems that were affected by the G1000
system software installation. No test set forth in this section should be used in lieu of the maintenance
procedures contained within the Beechcraft King Air C90 Series Maintenance Manual or any specific
procedures or standards that are in place by way of an FAA Certified Repair Station or other similar facility,
and are to be used in a supplemental manner only.
3.7.1
Display Testing
The G1000 system is tested while operating in the normal mode unless otherwise specified. If the system
is in configuration mode, restart the displays by cycling the PFD1, PFD2 and MFD circuit breakers to start
the display in the normal mode.
In the normal operating mode, data fields that are invalid have large red X’s through them (examples shown
in Figure 3-22). A valid field does not display a red X as shown. Allow the displays to initialize for
approximately one minute before checking for issues. The GDC 74Bs requires a longer initialization period
than the other LRUs. This may cause the airspeed, altitude, vertical speed, and OAT fields to be invalid
during the first ~40-60 seconds of PFD power-up
1. Turn off the G1000 system.
2. Verify all circuit breakers are closed.
3. Start G1000 system in normal mode.
4. Observe the MFD power-up screen. When the display appears as shown below in Figure 3-21,
verify the correct splash screen appears on the left side of the display. A “Garmin King Air” or
“Garmin King Air with Electronic Stability and Protection, ESP™” splash screen will be shown. The
“ESP” splash screen should only be present if the ESP feature is enabled.
Figure 3-21, MFD Power Up Page (format reference)
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5. Verify that the System Software Version shown in the upper right corner is correct per the General
Arrangement drawing.
6. Press the GCU ENT key or MFD #12 softkey to continue to the MAP page.
7. Check that all COM/NAV fields are valid in the top corners of PFD1 and PFD2.
8. Check that altitude, airspeed, vertical speed, TAS, and OAT fields are valid on PFD1 and PFD2.
9. Press the SENSOR softkey on each PFD and switch between ADC1 and ADC2. Verify that data
from both air data computers is valid on both displays.
10. Press the SENSOR softkey on each PFD and switch between AHRS1 and AHRS2. Verify that
data from both AHRS units is valid on both displays.
11. Check that engine instrument fields are valid on the MFD.
12. 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 (refer to Section 7 for target loading units).
13. Continue to Section 3.7.2.
Figure 3-22, PFD Power-up System Annunciations
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(without SVS enabled)
(with SVS enabled)
Figure 3-23, PFD Normal Operation
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3.7.2
Cooling Fan Check
1. Confirm equipment fan operation by verifying the absence of the following alert messages:

PFD 1 FAN FAIL

PFD 2 FAN FAIL

MFD FAN FAIL

AVN 1 FAN FAIL

AVN 2 FAN FAIL
2. Continue to Section 3.7.3.
3.7.3
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. MFD should have valid altitude, airspeed, vertical
speed, COMM1, COMM2, NAV1, NAV2 and engine instruments.
Figure 3-24, 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.
3. Repeat Step 1 using GMA2. Ensure that PFD2 and MFD enter reversion mode and MFD displays
valid altitude, airspeed, vertical speed, COMM1, COMM2, NAV1, NAV2 and engine instruments.
4. De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD2
and MFD return to normal display modes.
5. Open PFD1 (PRI) and PFD1 (SEC) circuit breakers. Verify the PFD1 goes blank and MFD display
remains in normal mode.
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6. Push the red DISPLAY BACKUP button on the pilot-side GMA 1347D. Verify that the MFD display
enters reversion mode. MFD should have valid altitude, airspeed, vertical speed, COMM2, NAV2
and engine instruments.
7. Close PFD1 (PRI) and PFD1 (SEC) circuit breakers and de-activate pilot-side reversion mode by
pushing the DISPLAY BACKUP button. Verify PFD1 and MFD return to normal display modes.
8. Continue to Section 3.7.4.
3.7.4
GPS Signal Acquisition
1. Go to the MFD AUX - GPS STATUS page.
2. Toggle between GPS 1 and GPS 2 using the two softkeys on the bottom of the display and verify
that both receivers show 3D DIFF NAV on the MFD. The GIA 63W units should normally acquire
a 3D GPS navigation solution within 2 minutes of startup, provided the aircraft is outside or
indoors with a GPS repeater.
3. Continue to Section 3.7.5.
Figure 3-25, AUX – GPS Status Page
NOTE
If the aircraft is located where it is under multiple GPS repeaters in a hanger, or if the
aircraft is by an open hanger door plus there is a GPS repeater inside, the GPS may not
obtain a position lock. Move the aircraft, close hanger doors, or turn off multiple GPS
repeaters to correct.
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3.7.5
VHF COMM Operational Check
Perform a ramp test radio check by exercising the installed transceivers, boom mic, hand mic, microphone
key and audio over the headphones and speaker. Verify that communications are clear and PTT operation
is correct for each pilot position.
1. 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 headsets.
2. Press the SPKR key and verify that the selected audio is heard over the speaker.
3. Continue to Section 3.7.5.1.
3.7.5.1
Failsafe Operation Check
1. Open AUDIO No 1 CB.
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 PFD1
and PFD2 volume control. Verify proper operation of COM 1 using the failsafe operation.
3. Close AUDIO No 1 CB.
4. Continue to Section 3.7.6.
3.7.6
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.
2. Verify that each marker audio signal is present over the pilot and co-pilot headphones and cockpit
speaker.
3. Verify that the outer, middle, and inner annunciations appear on PFD1 and PFD2 when the
corresponding signal is applied. Marker beacon annunciations appear at the upper left corner of
the altitude indicator on the PFD (Figure 3-26).
4. Operate the MKR MUTE key on GMA1 and GMA2 and ensure that the audio signal is muted.
5. Continue to Section 3.7.7.
Figure 3-26, Marker Beacon Symbology
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3.7.7
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. 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.
1. Simulate a VOR signal on radial 360°.
2. Verify full scale deflection of the CDI while applying a 10° deviation signal.
3. Exercise the CDI with both right and left deviations for both VOR 1 and VOR 2 receivers.
4. Repeat using a simulated localizer signal.
5. Exercise the Glideslope deviation indicator with up and down deviation indications and verify proper
direction of deviation.
6. Continue to Section 3.7.8.
3.7.8
GTX 33 Testing
Operation of the GTX 33 transponder is accomplished using PFD1, PFD2, or MFD. Refer to the G1000
King Air C90 Cockpit Reference Guide 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. These tests require 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. Continue to Section
3.7.9.
3.7.9
Airspeed Indicator Check
This test is performed with and air data test box or alternatively during a flight test below 16,000’.
1. Connect an Air Data Test box to the aircraft.
2. Set airspeed to zero knots and altitude to zero feet.
3. Increase airspeed and verify the airspeed tape transitions on PFD1 correspond to the information
below. Keep altitude at zero feet.

Aircraft LJ-1063 through LJ-1137, and LJ-1146 markings must be shown as follows o
Without Raisbeck AFMS Part Numbers 13-C90-135A-1900, 13-C90-135A-1900SH,
90-206CGW, 05-206CGW, C90-135A-1750, and C90-135A-1900:
-
Red Band 20 to 76kts (appears only if Weight on Wheels is not active)
-
Wide White Band 76-89kts
-
Narrow White Band 89-148kts
-
Red Bar Vmca = See NOTE below
-
Blue Bar Vyse = 107 kts
-
Solid White Triangle 184kts
-
Red/White Vne “Barber Pole” >226kts
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o

With Raisbeck AFMS Part Numbers 13-C90-135A-1900, 13-C90-135A-1900SH, 90206CGW, 05-206CGW, C90-135A-1750, and C90-135A-1900:
- Red Band 20 to 76kts (appears only if Weight on Wheels is not active)
-
Wide White Band 76-89kts
-
Narrow White Band 89-148kts
-
Red Bar Vmca = See NOTE below
-
Blue Bar Vyse = 107 kts
-
Solid White Triangle 184kts
-
Red/White Vne “Barber Pole >208 kts
All Aircraft LJ-1138 and on except 1146 must be shown as follows -
Red Band 20 to 78kts (appears only if Weight on Wheels is not active)
-
Wide White Band 78-88kts
-
Narrow White Band 88-148kts
-
Red Bar Vmca = See NOTE below
-
Blue Bar Vyse = 108 kts
-
Solid White Triangle 184kts
-
Red/White “Barber Pole” >226kts
NOTE
Red Bar Vmca value changes based on Blackhawk, Silverhawk, and/or Raisbeck STCs
installed. If any of those STCs are installed, check the AFMS for them to determine if the
Beechcraft Vmca value is revised by the STC and to find the correct Vmca value (80, 85,
90, 91, or 93kts). For aircraft without Blackhawk, Silverhawk, or Raisbeck STCs installed,
check Beechcraft AFM for correct Vmca value (80, 85, or 90kts)
4. Reduce airspeed to 0 and disconnect the test box.
5. Continue to Section 3.7.10.
3.7.10 TAWS B Functional Check
1. From the MAP group, select the TAWS page on the MFD.
2. Verify that the title at the top of the page reads “MAP – TAWS-B”.
NOTE
If TAWS has not been enabled, the title will read “MAP – TERRAIN PROXIMITY” or “MAP
– TERRAIN”. Refer to Section 3.4.23 for TAWS enabling procedures.
3. Press the GCU MENU button and select “Test TAWS System” from the pop-up menu.
4. Verify TAWS test annunciation is displayed on the MFD and both PFDs.
5. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over the cockpit
speaker (if selected) and the cockpit headsets.
6. Continue to Section 3.7.11.
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3.7.11 FliteCharts Functional Check
This test is not required if Jeppesen ChartView is enabled. If ChartView is enabled, skip and continue to
Section 3.7.12.
1. On the MFD, go to the AUX – SYSTEM STATUS page.
2. Press the MFD1 DB softkey. If the MFD1 DB key is not present, but a PFD1 DB or PFD2 DB
softkey is visible, press the PFD DB softkey until the softkey title changes to MFD1 DB.
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 ‘REGION’, ‘CYCLE’ number, ‘EFFECTIVE’, ‘EXPIRES’, and
‘DISABLES’ dates of the subscription appear in blue text. If EXPIRES or DISABLES fields are
yellow, update the FliteCharts database on the MFD database card.
6. Deactivate the cursor and use the GCU large FMS knob to select the Navigation Map Page then
press the SHW CHRT softkey. If the SHW CHRT softkey is grayed out, press the joystick to turn
on the cursor and move the arrow to highlight a major airport and press the ENT key.
7. Verify Airport Chart is displayed and the following softkeys are displayed (some softkeys may be
grayed out):

CHRT OPT

CHRT

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. Continue to Section 3.7.13.
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3.7.12 ChartView Functional Check
ChartView must be enabled using a ChartView Enable Card as specified in the General Arrangement
drawing and a current ChartView database. Reference Section “ChartView Configuration” for enabling
procedures. If ChartView is not enabled, skip and continue to Section 3.7.13.
NOTE
The required ChartView databases are subscription-based and are to be procured by the
aircraft owner directly from Jeppesen.
1. On the MFD, go to the AUX - SYSTEM STATUS page.
2. Press the MFD1 DB softkey. If the MFD1 DB key is not present, but a PFD1 DB or PFD2 DB
softkey is visible, press the PFD DB softkey until the softkey title changes to MFD1 DB.
3. Use the small FMS knob to scroll to CHART.
4. Verify the ChartView database cycle number is displayed in blue text and ChartView database is
current.
5. Go to the MFD NAVIGATION MAP page and press the SHW CHRT softkey.
6. Verify the airport chart is displayed and the following softkeys are displayed (some softkeys may
be grayed out):

CHRT OPT

CHRT

INFO-1

DP

STAR

APR

WX

NOTAM

GO BACK
7. 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
8. Return to the Navigation Map Page.
9. Press the GCU MENU key to display the PAGE MENU.
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10. Turn the GCU large FMS knob to scroll through the OPTIONS Menu to ‘Show Chart’. Press the
GCU ENT key.
11. Verify airport diagram is being displayed.
12. Press the GCU FMS knob to activate the cursor. Turn the GCU large FMS Knob to select the Airport
Identifier Box.
13. Turn the GCU small and large FMS knob to enter the airport identifier for New Century airport
(KIXD) then press the GCU ENT key to complete the airport selection.
14. Select the APR softkey.
15. Press the GCU FMS knob to activate the cursor. Turn the GCU large FMS Knob to select the
Approach Box then turn the small FMS Knob to show the approach chart selection choices.
16. Turn either GCU FMS knob to scroll through the available charts and select a chart for viewing by
pressing the GCU ENT key.
17. Verify the appropriate ChartView chart is displayed.
18. Continue to Section 3.7.13.
3.7.13 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. Go to the MFD AUX – SYSTEM STATUS page.
2. Press the MFD1 DB softkey.
3. Use the small FMS knob to scroll to SAFETAXI.
4. Verify current revision levels are displayed for the following:

REGION

VERSION
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
CYCLE

EFFECTIVE

EXPIRES
5. Go to the MFD NAVIGATION MAP page.
6. On the GCU, press MENU.
7. Highlight “Map Setup” and press the ENT key.
8. In the GROUP window, highlight “Aviation” and press the ENT key.
9. Turn the GCU large FMS Knob to scroll through the Aviation Group options and highlight
“SAFETAXI”.
10. Turn the GCU small FMS Knob to display the range of distances.
11. Highlight “5000ft” and press the ENT key.
12. Close the Map Setup window.
13. Select a map range of 5000ft or less. Verify SafeTaxi display represents the current aircraft location
and the airport layout.
14. Continue to Section 3.7.14.
3.7.14 Aircraft Weight Configuration Functional Check
The following functional check will verify that the Maximum Takeoff Weight (MTOW) and Maximum Zero
Fuel Weight (MZFW) configurations were correctly loaded.
Reference the operating AFM or AFMS Limitation Section for subject aircraft. Note aircraft MTOW and
MZFW weight limits and determine the appropriate Weight Configuration Functional Check.
3.7.14.1 Aircraft Weight Limitation (MTOW = 10,100 lbs., MZFW = No Limitation)
1. On the MFD, go to the AUX - WEIGHT PLANNING page.
2. Select the EMPTY WT softkey.
3. Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4. Turn the large FMS knob to highlight the “CARGO” field.
5. Using the GCU keypad enter a CARGO weight of 1200. Press the ENT key to confirm the entry.
6. Verify the ZERO FUEL WEIGHT value is 10100 and displayed in cyan.
7. Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 1210.
8. Verify the ZERO FUEL WEIGHT value is 10110 and displayed in amber.
9. Turn the small FMS knob CCW to decrease the CARGO weight to 1200.
10. Verify the ZERO FUEL WEIGHT value is 10100 and displayed in cyan.
11. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Turn the small FMS knob
CW to increase the FUEL ON BOARD weight value to 10.
12. Verify that AIRCRAFT WEIGHT value is 10110 and displayed in amber.
13. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight value to zero (0).
14. Verify that AIRCRAFT WEIGHT value is 10100 and displayed in cyan.
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15. Continue to Section 3.7.15.
3.7.14.2 Aircraft Weight Limitation (MTOW = 10,350 lbs., MZFW = 9,000 lbs.)
1. On the MFD, go to the AUX - WEIGHT PLANNING page.
2. Select the EMPTY WT softkey.
3. Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4. Turn the large FMS knob to highlight the “CARGO” field. Using the GCU keypad enter a CARGO
weight of 100. Press the ENT key to confirm the entry.
5. Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan.
6. Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 110.
7. Verify the ZERO FUEL WEIGHT value is 9010 and displayed in amber.
8. Turn the small FMS knob CCW to decrease the CARGO weight to 100.
9. Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan.
10. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Using the GCU keypad
enter a FUEL ON BOARD weight of 1350. Press the ENT key to confirm the entry.
11. Verify that AIRCRAFT WEIGHT value is 10350 and displayed in cyan.
12. Turn the large FMS knob CCW to highlight the “FUEL ON BOARD” field. Turn the small FMS knob
CW to increase the FUEL ON BOARD weight to 1360.
13. Verify that AIRCRAFT WEIGHT value is 10360 and displayed in amber.
14. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight to 1350.
15. Verify that AIRCRAFT WEIGHT value is 10350 and displayed in cyan.
16. Continue to Section 3.7.15.
3.7.14.3 Aircraft Weight Limitation (MTOW = 10,100 lbs., MZFW = 9,000 lbs.)
1. On the MFD, go to the AUX - WEIGHT PLANNING page.
2. Select the EMPTY WT softkey.
3. Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4. Turn the large FMS knob to highlight the “CARGO” field. Using the GCU keypad enter a CARGO
weight of 100. Press the ENT key to confirm the entry.
5. Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan.
6. Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 110.
7. Verify the ZERO FUEL WEIGHT value is 9010 and displayed in amber.
8. Turn the small FMS knob CCW to decrease the CARGO weight to 100.
9. Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan.
10. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Using the GCU keypad
enter a FUEL ON BOARD weight of 1100. Press the ENT key to confirm the entry.
11. Verify that AIRCRAFT WEIGHT value is 10100 and displayed in cyan.
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12. Turn the large FMS knob CCW to highlight the “FUEL ON BOARD” field. Turn the small FMS knob
CW to increase the FUEL ON BOARD weight to 1110.
13. Verify that AIRCRAFT WEIGHT value is 10110 and displayed in amber.
14. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight to 1100.
15. Verify that AIRCRAFT WEIGHT value is 10100 and displayed in cyan.
16. Continue to Section 3.7.15.
3.7.14.4 Aircraft Weight Limitation (MTOW = 9,650 lbs., MZFW = No Limitation)
1.
On the MFD, go to the AUX - WEIGHT PLANNING page.
2.
Select the EMPTY WT softkey.
3.
Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4.
Turn the large FMS knob to highlight the “CARGO” field. Using the GCU keypad enter a CARGO
weight of 750. Press the ENT key to confirm the entry.
5.
Verify the ZERO FUEL WEIGHT value is 9650 and displayed in cyan.
6.
Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 760.
7.
Verify the ZERO FUEL WEIGHT value is 9660 and displayed in amber.
8.
Turn the small FMS knob CCW to decrease the CARGO weight to 750.
9.
Verify the ZERO FUEL WEIGHT value is 9650 and displayed in cyan.
10. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Turn the small FMS knob
CW to increase the FUEL ON BOARD weight to 10.
11. Verify that AIRCRAFT WEIGHT value is 9660 and displayed in amber.
12. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight value to zero (0).
13. Verify that AIRCRAFT WEIGHT value is 9650 and displayed in cyan.
14. Continue to Section 3.7.15.
3.7.14.5 Aircraft Weight Limitation (MTOW = 10,500 lbs., MZFW = 9,000 lbs.)
1.
On the MFD, go to the AUX - WEIGHT PLANNING page.
2.
Select the EMPTY WT softkey.
3.
Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4.
Turn the large FMS knob to highlight the “CARGO” field. Using the GCU keypad enter a CARGO
weight of 100. Press the ENT key to confirm the entry.
5.
Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan.
6.
Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 110.
7.
Verify the ZERO FUEL WEIGHT value is 9010 and displayed in amber.
8.
Turn the small FMS knob CCW to decrease the CARGO weight to 100.
9.
Verify the ZERO FUEL WEIGHT value is 9000 and displayed in cyan.
10. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Using the GCU keypad
enter a FUEL ON BOARD weight of 1500. Press the ENT key to confirm the entry.
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11. Verify that AIRCRAFT WEIGHT value is 10500 and displayed in cyan.
12. Turn the large FMS knob CCW to highlight the “FUEL ON BOARD” field. Turn the small FMS
knob CW to increase the FUEL ON BOARD weight to 1510.
13. Verify that AIRCRAFT WEIGHT value is 10510 and displayed in amber.
14. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight to 1500.
15. Verify that AIRCRAFT WEIGHT value is 10500 and displayed in cyan.
16. Continue to Section 3.7.15.
3.7.14.6 Aircraft Weight Limitation (MTOW = 10,353 lbs., MZFW = 9,378 lbs.)
NOTE
This weight configuration is for CENTEX STC # SA10747SC aircraft.
1.
On the MFD, go to the AUX - WEIGHT PLANNING page.
2.
Select the EMPTY WT softkey.
3.
Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4.
Turn the large FMS knob to highlight the “CARGO” field. Using the GCU keypad enter a CARGO
weight of 470. Press the ENT key to confirm the entry.
5.
Verify the ZERO FUEL WEIGHT value is 9370 and displayed in cyan.
6.
Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 480.
7.
Verify the ZERO FUEL WEIGHT value is 9380 and displayed in amber.
8.
Turn the small FMS knob CCW to decrease the CARGO weight to 470.
9.
Verify the ZERO FUEL WEIGHT value is 9370 and displayed in cyan.
10. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Using the GCU keypad
enter a FUEL ON BOARD weight of 980. Press the ENT key to confirm the entry.
11. Verify that AIRCRAFT WEIGHT value is 10350 and displayed in cyan.
12. Turn the large FMS knob CCW to highlight the “FUEL ON BOARD” field. Turn the small FMS
knob CW to increase the FUEL ON BOARD weight to 990.
13. Verify that AIRCRAFT WEIGHT value is 10360 and displayed in amber.
14. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight to 975.
15. Verify that AIRCRAFT WEIGHT value is 10350 and displayed in cyan.
16. Continue to Section 3.7.15.
3.7.14.7 Aircraft Weight Limitation (MTOW = 10,485 lbs., MZFW = 9,378 lbs.)
NOTE
This weight configuration is for CENTEX STC # SA10747SC aircraft.
1.
On the MFD, go to the AUX - WEIGHT PLANNING page.
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2.
Select the EMPTY WT softkey.
3.
Using the GCU keypad enter a basic empty weight of 8900. Press the ENT key to confirm the
entry.
4.
Turn the large FMS knob to highlight the “CARGO” field. Using the GCU keypad enter a CARGO
weight of 470. Press the ENT key to confirm the entry.
5.
Verify the ZERO FUEL WEIGHT value is 9370 and displayed in cyan.
6.
Turn the large FMS knob CCW to highlight the “CARGO” field. Turn the small FMS knob CW to
increase the CARGO weight to 480.
7.
Verify the ZERO FUEL WEIGHT value is 9380 and displayed in amber.
8.
Turn the small FMS knob CCW to decrease the CARGO weight to 470.
9.
Verify the ZERO FUEL WEIGHT value is 9370 and displayed in cyan.
10. Turn the large FMS knob CW to highlight the “FUEL ON BOARD” field. Using the GCU keypad
enter a FUEL ON BOARD weight of 1110. Press the ENT key to confirm the entry.
11. Verify that AIRCRAFT WEIGHT value is 10480 and displayed in cyan.
12. Turn the large FMS knob CCW to highlight the “FUEL ON BOARD” field. Turn the small FMS
knob CW to increase the FUEL ON BOARD weight to 1120.
13. Verify that AIRCRAFT WEIGHT value is 10490 and displayed in amber.
14. Turn the small FMS knob CCW to decrease the FUEL ON BOARD weight to 1110.
15. Verify that AIRCRAFT WEIGHT value is 10480 and displayed in cyan.
16. Continue to Section 3.7.15.
3.7.15 GWX Weather Radar Check
CAUTION
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 MFD, go to the 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. Verify no one is in the MPEL boundary.
5. Pre the MODE softkey.
6. Select the WEATHER softkey. After reading the CAUTION statement, turn the large FMS knob to
highlight YES and press the ENT key.
7. Select the STAB ON softkey to activate antenna stabilization and select the STAB OFF softkey to
deactivate.
8. Verify the current stabilization condition is shown in the upper right of the weather radar display.
9. Press the BACK softkey.
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10. Press the VERTICAL softkey.
11. Press the TILT softkey to activate the cursor in the TILT field.
12. On the GCU, turn the small FMS knob to change the antenna tilt angle. Verify the tilt indicator is
present on the radar display.
13. Press the GAIN softkey to activate the cursor in the GAIN field.
14. 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.
15. On the GCU, press the GAIN softkey again to recalibrate the gain.
16. Verify ‘CALIBRATED’ is displayed in the GAIN field.
17. Select the MODE softkey.
18. Select the OFF softkey.
19. Continue to Section 3.7.16.
3.7.16 Traffic System Functional Check (Optional Installation)
This Section tests the traffic system. If traffic is not installed, skip and continue to Section 3.7.17.
1. Select the TRAFFIC MAP page on the MFD.
2. Verify that the STANDBY, OPERATE, TEST and ALT MODE softkeys are available on the bottom
of the display.
3. Verify that an operating mode; STANDBY, OPERATE, or TEST (not FAIL) is displayed in the upper
left corner of the traffic map.
4. 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 3.4.12 or Traffic System Configuration Option to
enable the traffic system.
5. Press the OPERATE softkey and verify that OPERATING is displayed in the upper left corner of
the traffic map.
6. Press the STANDBY softkey and verify that STANDBY is displayed in the upper left corner of the
traffic map.
7. Press the TEST softkey and verify that TEST is displayed in the upper left corner of the traffic map
and a traffic test pattern is displayed. Upon completion of the test, verify that “TAS SYSTEM TEST
OK” is heard over the cockpit speaker.
NOTE
This annunciated traffic system test message may be different from the traffic system
installed on subject aircraft.
8. Open the TRAFFIC circuit breaker on the avionics circuit breaker panel.
NOTE
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The TRAFFIC circuit breaker may be labelled TFRC or SKYWATCH.
9. On the MFD, verify that NO DATA is displayed in yellow after several seconds.
10. Close the TRAFFIC circuit breaker on the avionics circuit breaker panel.
11. Verify that NO DATA is removed after several seconds.
12. Continue to Section 3.7.17.
3.7.17 DME Functional Check (Optional Installation)
This check verifies that the DME to G1000 interface operates correctly. If a DME is not installed, skip and
continue to Section 3.7.18.
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 523-077245800611A, Maintenance Section 523-0772460-006118 to adjust DME channel one audio
level. Recommended nominal DME audio output level is 1.32 Vpp + 0.10 Vpp for aircraft
with C90 G1000 System Software Version 0636.01 and 4.46 Vpp +0.10 Vpp for aircraft
with C90 G1000 System Software Version 0636.02 and subsequent approved versions.
This 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.
2. Verify the DME window is displayed next to the PFD1 and PFD2 HSI.
3. On PFD1 and PFD2, press the BACK softkey then select DME softkeys.
4. Verify the DME TUNING screen is displayed.
5. On PFD1 and PFD2, use the large FMS knob to select the NAV1, NAV2 and HOLD modes in the
DME field.
6. Verify that the NAV1, NAV2 and HOLD modes can be selected by turning the small FMS knob.
7. Set NAV1 and NAV2 frequencies to 108.00 and 117.00 respectively.
8. On PFD1 and PFD2, select the DME NAV1 mode.
9. Verify that the DME window display is set to the NAV1 frequency of 108.00.
10. On PFD1 and PFD2, select the DME NAV2 mode by pressing the ENT softkey.
11. Verify that the DME window display is set to the NAV2 frequency of 117.00.
12. On PFD1 and PFD2, select the DME HOLD mode by using the FMS knob.
13. Verify that the last selected NAV frequency of 117.00 remains the same when the NAV2 frequency
is changed.
14. Deselect DME HOLD.
15. On the NAV Test Set, set up a DME test and note the nav frequency.
16. Tune NAV 1 to the test set frequency and set PFD1 and PFD2 DME MODE to NAV1.
17. Set NAV 2 to a frequency other than the test set frequency.
18. Verify that the DME distance on PFD1 and PFD2 match the test set.
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19. Select, or verify selected, DME and SPKR buttons on GMA1 and GMA2 audio panels to select the
DME audio and select speaker to ON.
20. Verify that the DME audio can be heard over the cockpit speakers.
21. On PFD1 and PFD2, set the DME mode to NAV2 and verify that the DME distance is dashed out.
22. Tune NAV 2 to the test set frequency.
23. Set NAV 1 to a frequency other than the test set frequency.
24. Verify that the DME distance on PFD1 and PFD2 match the test set.
25. Continue to Section 3.7.18.
3.7.18 ADF Functional Check (Optional Installation)
This check verifies that the ADF to G1000 interface operates correctly. If the ADF is not installed, skip and
continue to Section 3.7.19.
1. Press the PFD softkey on PFD1 and PFD2.
2. Toggle the BRG1 and BRG2 softkey until the ADF bearing is shown on PFD1 and PFD2.
3. Verify that the ADF window is not invalid (no red ‘X’).
4. Using the ADF control head select a known valid local ADF.
5. Verify that the ADF bearing pointer moves towards a bearing and stabilizes.
6. Select ADF and SPKR on GMA1 and GMA2.
7. Using the ADF control head, select, ANT mode.
8. Verify that the audio from the station tuned can be heard on the pilots and copilots headset and
cockpit speaker.
9. Increment the ADF volume control from full low to full high.
10. Verify the volume increases and decreases appropriately over pilots and copilots headset and
cockpit speaker.
11. Continue to Section 3.7.19.
3.7.19 Gen Purpose A429 Bus Check (Optional Installation)
This check verifies that the Gen Purpose A429 Bus is transmitting. This check is only required if the Gen
Purpose data bus is to be used (i.e. ELT, Airshow, etc.). If this is not used, skip and continue to Section
3.7.20.
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. Operate the device that receives 429 data from GIA2 to verify it is receiving data. Labels present
on the General Purpose output are 117G, 121, 125, 171, 203, 204, 210, 213, 235, 260, 310, 311,
312, 314, 320, 351, and 352.
2. Continue to Section 3.7.20.
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3.7.20 Stormscope Functional Check (Optional Installation)
This check verifies that the G1000 / Stormscope interface operates correctly if installed. If it is not installed,
skip and continue to Section 3.7.21.
1. On the MFD, go to the Stormscope page.
2. Verify that no failed test messages appear. If fault messages do appear, refer to the WX-500
Installation Manual for troubleshooting.
3. Verify the following modes:

Access to both 360° and ARC weather view 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.
4. 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.
5. Operate DME, XPDR 1, XPDR 2 and weather radar. Verify these systems do not cause strike data
to appear on the MFD.
6. Connect the WX-PA cable to the WX-PA antenna.
7. 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 WXPA antenna suction cups are positioned forward of center along the longitudinal axis.
8. Secure the WX-PA cable to the aircraft with the attached suction cup and route the cable to the
cockpit.
9. Connect the remaining cable end to the WX-PA.
10. Power up the WX-PA and verify the WX-500 is in the weather mapping mode (i.e. 360° weather
view at the 200 NM range.
11. Set the WX-500 to STRIKE mode; 100 NM range (or next highest available range).
12. Select the Continuous Out mode displayed on the WX-PA menu and press MENU/ENTER.
13. Select the bottom mount antenna configuration on the WX-PA keyboard (“A” key).
14. Select a cardinal bearing and a range of 120 NM.
15. 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
16. Press MENU/ENTER to start the test.
17. Observe the MFD to ensure the proper positioning of the strikes, based on range and azimuth
settings on the WX-PA.
18. 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).
19. Verify after 20 seconds of operation the strike counter reads 580 +/-40.
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20. After testing for all ranges and bearings indicated, press 2 ND then MENU/ENTER to return to the
main menu.
21. Select Circular Pattern mode on the WX-PA mode menu and press MENU/ENTER.
22. Select bottom mount antenna configuration on the WX-PA keyboard (“A” key).
NOTE
The MFD should be set at 100 NM (or next highest available range) on the 360
degree weather screen and in strike mode.
23. 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.
24. 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,
25. When complete, set WX-PA for 55 NM, set the MFD for 50 NM (or the next highest available range)
and repeat test.
26. 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.
27. Repeat above setting the MFD for 25 NM (or the next highest available range) and the WX-PA for
15 NM.
28. On the MFD, verify the positioning of test strikes within are within 10 degrees of azimuth and within
2 NM of 7.5 NM.
29. Continue to Section 3.7.21.
3.7.21 Non-Garmin Radio Altimeter Check (Optional Installation)
This check verifies that the G1000 / radio altimeter interface is operates correctly. If it is not installed, skip
and continue to Section 3.7.22.
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. On the MFD, go to the AUX – SYSTEM STATUS page.
2. Press the RA TEST softkey and verify that “RA TEST” annunciation is displayed on both PFDs.
3. Verify 50 feet is displayed in the RA display window on both PFDs.
4. Press the RA TEST softkey again. Verify the RA readout window displays 2500 feet and decreases
to 0 feet on PFD1 and PFD 2.
5. Open the RAD ALT circuit breaker.
6. Verify on PFD 1 and PFD 2 that an RA FAIL message is displayed.
7. Close RAD ALT circuit breaker.
8. Continue to Section 3.7.22.
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3.7.22 ESP Functional Check
This procedure is required only for aircraft with the optional Electronic Stability and Protection (ESP) feature.
If it is not installed, skip and continue to Section 3.7.23.
1. Verify the DISPLAY BACKUP button on the audio panel is pushed in so that the GDUs will not
operate in reversionary mode.
2. Verify no AHRS, ADC, Autopilot, PFD, AFCS Mode Controller, GCU alert messages or monitor
flags (HDG MISCOMP etc.) are present on PFD1 or PFD2.
3. On the GMC, 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.
4. On the MFD, go to the AUX – SYSTEM SETUP 1 page.
5. On the MFD AUX – SYSTEM SETUP 1 page, press the SETUP 2 softkey.
6. Verify that on the SYSTEM SETUP 2 page there is a window for Stability & Protection and the
status is “ENABLED”.
7. Verify on PFD 1 and PFD 2 that there are no “ESP FAIL”, “ESP OFF”, or “ESP DEGRADE” alert
messages.
8. Cover both GPS1 and GPS2 antennas.
9. Verify on PFD 1 and PFD 2 the ESP Roll Indices are displayed at 45° on the roll indicator on the
Attitude Display.
10. On the MFD AUX - SYSTEM STATUS 2 page, change the Stability & Protection status to
“DISABLED”.
11. Verify on PFD 1 and PFD 2 the ESP Roll Indices are not displayed at 45° on the roll indicator on
the Attitude Display.
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12. Verify on PFD 1 and PFD 2 that there is an “ESP OFF” alert message.
13. Remove the cover from both GPS1 and GPS2 antennas.
14. Remove power to the aircraft and avionics systems by placing the aircraft AVIONICS MASTER
PWR and EXP PWR switches to OFF.
15. Wait ~ 1 minute before re-applying aircraft power.
16. Apply power to the aircraft and avionics systems by setting the BAT, EXT PWR and AVIONICS
MASTER PWR switches to ON.
17. 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.
18. 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.
19. On the MFD, go to the AUX – SYSTEM SETUP 2 page.
20. Verify that on the MFD SETUP 2 page the Stability & Protection status is “ENABLED”.
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21. Verify on PFD 1 and PFD 2 that there are no “ESP FAIL” or “ESP OFF” alert messages.
22. On the GMC, 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
23. Repeat steps 4 thru 21 while coupled to right side.
24. Continue to Section 3.7.23.
3.7.23 Search and Rescue Functional Check
This check verifies that the Search and Rescue feature operates correctly. If it is not installed, skip and
continue to Section 3.8.
1. On the GCU keypad, press the “FPL” key to display the Active Flight Plan Menu.
2. Press the “MENU” key to display the PAGE MENU Options.
3. Highlight “Search and Rescue” and press the ENT key.
4. In the Search and Rescue Menu, enter a start waypoint in the WAYPOINT field using the FMS
knobs and ENT key.
5. In the PATTERN field select “PARALLEL”.
6. With the FMS knob scroll through the options and change the fields as desired, or leave the default
entries.
7. When complete, highlight the “ACTIVATE SAR?” window and press the ENT key to activate the
flight plan.
8. On the MFD NAVIGATION MAP page, verify the parallel track search pattern is shown.
9. Continue to Section 3.8.
3.8
Final Test
1. On PFD1, check the ALERTS window for any alert messages. If any messages are present,
troubleshoot per Section 5 and resolve before continuing.
2. On PFD1, PFD2, and the MFD check for any failure annunciations or fields with a Red-X present.
If any are found, troubleshoot per Section 5 and resolve before continuing.
3. Continue to Section 9 and complete the Return to Service procedure.
Page 3-78
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4
Instructions for Continued Airworthiness
4.1
Airworthiness Limitations
The G1000 Integrated Flight Deck including the GFC 700 AFCS is airworthy when installed, configured,
and maintained in accordance with this section.
The G1000 and GFC 700 systems possess the following maintenance airworthiness limitations: The
intervals for the airworthiness limitations are shown in maximum number of hours between checks, as
required for certification. Table 4-1 aligns these requirements with the King Air Phase Inspection Program.
These limitations were derived from the certification data.
GFC 700 Limitations:

Every 220 hours, perform a check to verify that flaps-in-motion discrete inputs function
correctly. Refer to Table 4-1.

Every 420 hours, perform a GSM 85A slip clutch check (if GSM 85A is applicable) to verify
proper operation. Refer to Table 4-1.

Every 3000 hours, perform a GSM 86 clutch check (if GSM 86 is applicable) to verify proper
operation. Refer to Table 4-1.

Every 1000 hours, perform a servo current display check of the pitch, roll, and yaw servo.
Refer to Table 4-1.

Every 220 hours, perform a trim annunciator check to verify proper operation. Refer to
Table 4-1.
G1000 Limitations:

Every 220 hours, perform a G1000 redundant connections check. Refer to Table 4-1.

Every 220 hours, perform a G1000 cooling system electrical check. Refer to Table 4-1.

Every 220 hours, perform a nose avionics compartment fans operational check. Refer to
Table 4-1.

Every 220 hours, perform an instrument panel fans operational check. Refer to Table 4-1.

Every 820 hours, perform an engine data check. Refer to Table 4-1.

Every 820 hours, perform a G1000 miscompare check. Refer to Table 4-1.
Other Limitations:

Every 220 hours, check for proper function of the internal lighting of the standby attitude
indicator, standby altimeter and standby airspeed indicator as well as the proper power
availability to the standby attitude indicator and standby altimeter vibrator by performing
the Standby Instrument Electrical Power Checks. Refer to Table 4-1.

Every 200 hours or 6 Calendar Months (whichever occurs first), perform an Emergency
Battery Check of the L-3 PS-835(C or D Model) Emergency Battery. Refer to Table 4-1.
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
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Page 4-1
Revision L
4.2
Servicing Information
G1000 LRU maintenance is ‘on condition’ only. No component-level overhaul is required for this type
design change.
4.2.1
On Condition Servicing
‘On Condition’ replacement and/or servicing should occur when an item exhibits conditions, symptoms,
and/or abnormalities defined in Section 5 of this manual. Replacement and/or servicing should be made
only after the technician troubleshoots the system to the extent determined necessary by using the
guidance in this manual along with common avionics maintenance practices.
IMPORTANT
It is impossible to provide guidance for every conceivable failure scenario within the
scope of this manual. Every effort has been made to provide comprehensive
guidance for possible failures. The information in this document should always be
combined with 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 8 gives testing instructions to be accomplished for G1000 functions and aircraft
interfaces.
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 Hawker Beechcraft Structural Inspection and Repair Manual
listed in Table 1-3.
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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Page 4-3
Revision L
4.2.2
Required Tools
The following tools are needed to perform maintenance tasks on G1000 equipment:

Calibrated milliohm meter, OR

Agilent 34410A Ammeter or equivalent

Fluke 187 Voltmeter or equivalent

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 VDC 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

A 0.060” 6-Spline wrench
4.2.3
Special Tools
The following tools are needed to perform maintenance tasks on G1000 equipment and/or installation:

GSM 85A 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)
Page 4-4
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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 are aligned with the existing maintenance phase intervals used in the
current King Air Model 90 Series Maintenance Manual. A complete inspection cycle for the King Air C90 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 Model 90 Series Maintenance Manual, a tolerance of +/20 hours for all phase inspections. For tolerances on calendar months, refer to the
King Air Model 90 Series Maintenance Manual listed in Table 1-2.
The intention of Garmin is to align this maintenance program as best possible with the existing King Air C90
inspection program. For a complete description of the King Air inspection program, refer to the King Air
Model 90 Series Maintenance Manual listed in Table 1-2.
Table 4-1, Maintenance Intervals
Item
Description/Procedure
Manual Section
No.
Interval
G1000/GFC700 Equipment
Complete Visual Inspection of GWX 68 or
GWX 70 Equipment and Wiring located in
Nose Section
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Nose Avionics Compartment
G1000/GFC700
System Visual
Inspections
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Pilot’s Compartment
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located on and behind Instrument Panel
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Cabin
Complete Visual Inspection of
G1000/GFC700 Equipment and Wiring
located in Rear Fuselage and Empennage
4.4
(Table 4-3)
4.4
(Table 4-4)
Phase 4
4.4
(Table 4-5)
Phase 3
4.4
(Table 4-6)
Phase 3
4.4
(Table 4-7)
Phase 3
4.4
(Table 4-8)
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
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Phase 4
Phase 4
Page 4-5
Revision L
Item
Description/Procedure
Manual Section
No.
Interval
9.3.1,
9.3.2,
9.3.5
Phase 2 and 4
GFC700 Periodic
Check
Verify proper operation of the GFC700 by
performing the following:
Pre-Flight Test
AFCS Switch Checks
Autopilot Operation Checks
TAWS Functional
Check
Periodic TAWS function check
8.4
Phase 4
GDU 1040A PFD
(Qty 2)
Removal & Replacement
6.1
On Condition
GDU 1500 MFD
Removal & Replacement
6.1
On Condition
Removal & Replacement
6.2
On Condition
7.2.2
Phase 2 and 4
8.1
Phase 2 and 4
8.2 or 8.3
Phase 2 and 4
GMA 1347D Test
GMA 1347D (Qty 2)
Landing Gear Aural Alert and XM Audio
Suppression Test
XM Audio Suppression Check
GIA 63W IAU (Qty 2)
6.3
Removal & Replacement
GEA 71 EAU (Qty 2)
GTX 33 Transponder
(Qty 2)
GDC 74B (Qty 2)
GRS 77 or GRS 7800
AHRS (Qty 2)
On Condition
6.4
Removal & Replacement
6.5
On Condition
Test according to Title 14 CFR §§ 91.411
and 91.413 as well as Part 43 Appendix F.
7.5
24 Calendar Months
Removal & Replacement
6.6
On Condition
Test according to Title 14 CFR § 91.411 and
Part 43 Appendix E.
7.6
24 Calendar Months
Removal & Replacement
6.8
Magnetic variation database update.
4.6
GMU 44
Magnetometer (Qty 2)
6.9
GDL 69A or GDL 69A
SXM
6.10
On Condition
Removal & Replacement
GWX 68 or GWX 70
6.15
GMC 710
6.14
GCU 475
6.13
G1000 Cooling
System Electrical
Check*
Verify the operation of the fan power and
fan speed monitoring circuits for GIA1
Fan, GIA2 fan, PFD1 fan, MFD fan and
PFD2 fan and fan fail messages
9.2.1
220 hours max
Nose Avionics
Compartment Fans
Operational Check*
Functional test of the GIA1 and GIA2
ported fans. Verify airflow from all fan
ports
4.14
220 hours max
* Denotes Airworthiness Limitation Maintenance Requirement (See Section 4.1)
Page 4-6
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Instrument Panel
Fans Operational
Check*
Functional test of the PFD1, MFD and
PFD2 cooling fans. Verify airflow from
each fan
4.15
220 hours max
G1000 Redundant
Connection Check*
Verify PRI and SEC power sources for
PFD 1, GIA 1, GRS 1, GDC 1
Verify secondary paths for AHRS, ADC,
engine parameters and GPS data
Verify the operation of PFD and MFD
Ethernet connections
Verify ARINC connection between ADC1
and MFD and between GRS1 and MFD
Verify DISPLAY BACKUP button function
4.10
220 hours max
Engine Data Check*
Verify engine data is available and
accurate
4.11
820 hours max
Trim Annunciator
Check*
Verify trim annunciators function
properly
4.12
220 hours max
G1000 Miscompare
Check*
Verify AHRS, 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
Removal & Replacement
Refer to Master Drawing List, listed in Table
1-2, for installation drawings.
6.18
On Condition
Test the Flaps-in-motion discrete inputs
to the G1000 to verify proper operation.
4.8
220 hours max
Removal & Replacement.
Refer to the servo install drawings listed in
Master Drawing List, listed in Table 1-2.
6.11
On Condition
Clean and apply grease to output gears.
4.7
Phase 4
GSM 85A/86 Servo
Mounts (all)
Removal & Replacement.
Refer to the servo install drawings listed in
Master Drawing List, listed in Table 1-2.
6.12
On Condition
GSM 86 Clutch
Torque Check*
Verify that the pitch, roll and pitch trim
GSM 86 clutch torque values are within
acceptable limits.
4.9
3,000 hours max
Servo Current
Display Check*
Verify servo load cell integrity by
monitoring servo current at each axis
4.9
1,000 hours max
GSM 85A Servo
Mount Slip Clutch
Torque Check*
Verify that the pitch, roll, yaw and pitch
trim GSM 85A slip clutches are within
acceptable limits.
4.9
420 hours max
GPS/WAAS
Antennas
Diversity Transponder
Antenna
Flaps-in-motion
Discrete Input
Check*
GSA 81 and GSA 80
Servos (all)
* Denotes Airworthiness Limitation Maintenance Requirement (See Section 4.1)
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Revision L
G1000 Accessories
Configuration Module
Replacement (Qty 7)
Removal & Replacement.
6.16
GEA 71 Backshell
Thermocouple (Qty 2)
Removal & Replacement.
6.17
GTP 59 OAT Probe
(Qty 2)
Removal & Replacement.
6.7
PFD, MFD, and GIA
Cooling Fans (Qty 5)
Removal & Replacement
Refer to Master Drawing List, listed in Table
1-2, for installation drawings.
N/A
On Condition
G1000 Lightning Protection
Electrical Bonding
Test
Lightning Strike to
GTP 59 OAT Probe
or Antenna
Actual or Suspected
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
Removal & Replacement:
Refer to King Air Model 90 Series
Maintenance Manual listed in Table 1-2.
N/A
On Condition
Removal & Replacement:
Refer to King Air Model 90 Series
Maintenance Manual listed in Table 1-2.
N/A
Inspect the antenna/probe and surrounding
installation per 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)
Fuel Flow Transmitter
(Qty 2)
Prop Tachometer
(Qty 2)
Engine Speed
Tachometer (Qty 2)
On Condition
Engine Signal
Conditioners (Qty 2)
Aerospace Optics
Annunciator – Prop
Sync
PC920 Conditioner (if
added by this STC)
Page 4-8
Revision L
6.19
Removal & Replacement
6.21
6.20
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
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Other Equipment
Thommen Airspeed
Indicator - Standby
Removal & Replacement
6.23
On Condition
Removal & Replacement
6.24
On Condition
Test according to 14 CFR 91.411 and
Part 43 Appendix E.
N/A
24 Calendar Months
Removal & Replacement
6.25
On Condition
L-3 PS-835(C or D
Emergency Battery
Removal & Replacement
6.22
On Condition
Capacity test of standby battery
4.16.2
12 Calendar Months
Emergency Battery
Check*
Verify the emergency battery is being
charged
4.16.1
6 Calendar Months
(whichever first)
Standby Instrument
Electrical Power
Checks*
Verify STBY ATT & STBY ALT vibrator
operate and STBY ATT, STBY ALT &
STBY A/S illumination function on either
aircraft power or standby battery power
(standby compass checked during
existing maintenance)
9.2.2
220 hours max
Aerospace Optics
Annunciator –
Standby Battery
Removal & Replacement
6.21
Northern Airborne
Speaker Amplifier (if
added by this STC)
Removal & Replacement:
Refer to King Air Model 90 Series
Maintenance Manual listed in Table 1-2.
Thommen Altimeter –
Standby
Mid-Continent
Attitude Indicator –
Standby
200 hours max or
On Condition
N/A
* Denotes Airworthiness Limitation Maintenance Requirement (See Section 4.1)
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Revision L
4.3.1
Discontinued Maintenance
Table 4-2 shows a list of inspections and tests that are listed in the King Air Model 90 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
Description/Procedure
AC Inverter
Operational Check
Engine Torque
Indicating System**
Torque Indicator Re-calibration
Manual
Interval
Phase Inspections
Phases 1 - 4
CenTex STC
SA10339SC
5,000 hours
** Engine Torque Indicating System as installed by CenTex STC SA10339SC includes both an
indicator and a transducer. The indicator is removed per this STC (SA01456WI-D); the transducer
remains in the aircraft and the existing maintenance requirements for the transducer are still
applicable.
IMPORTANT
For installed equipment not listed in this maintenance manual, use the inspection
procedures set forth in Chapter 05 of the King Air Model 90 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 Model 90 Series Maintenance
Manual, or other appropriate maintenance manual, in cases where the requirements
conflict.
Page 4-10
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Revision L
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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 Model 90
Series Maintenance Manual listed in Table 1-2 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:
GWX 68 or GWX 70
a) Inspect the GWX 68 or GWX 70 unit, mount, and connectors for corrosion or other
defects. Check the integrity of the SHIELD BLOCK ground attachments to the harness
connector assembly as well as 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 1-2.
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)
a) 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.
GTX 33 (Qty 2)
a) Inspect the GTX 33 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.
GIA 63W (Qty 2)
a) Inspect the GIA 63W units, racks, and connectors for corrosion or other defects. Check
the integrity of the SHIELD BLOCK ground attachments to the harness connector
assembly as well as the integrity of the individual shields and their attachment.
GIA Avionics Fan
(Qty 2)
a) Inspect remote avionics fans and hoses for dirt accumulation and other damage.
Remove excess dirt as required.
LMD Rack and
Modules
a) Inspect the LMD rack, modules, and termination for corrosion or other defects.
a) Inspect bulkhead connectors for security of attachment, corrosion or other defects.
Nose Wiring
Harness
b) Inspect wire and coax for chafing, damage, proper routing of wire bundles and security
of attachment in accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph 11-96
and the Nose Wire Harness Routing drawing, listed in Table 1-2. . Pay particular
attention to possible areas of chaffing such as the middle shelf feed-through hole, wheel
well protrusion etc.
c) Inspect Ground blocks for security of attachment, corrosion or other defects.
d) Ensure all connectors are securely fastened.
Table 4-5, Pilot’s Compartment Visual Inspection Procedure
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Page 4-11
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Revision L
Item
Description/Procedure
Initials
Locate equipment in the aft pedestal for the following inspection:
GCU 475
a) Inspect the GCU 475 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 CTL-62
(relocated by STC)
a) Inspect the CTL-62 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. Refer also to the King Air Model
90 Series Maintenance Manual, listed in Table 1-2.
To gain access for the following Inspections, remove pilot and co-pilot seats and cockpit floor panels.
NOTE
The tach-gen filter assemblies, GPN 005-00375-93, are installed underneath the pilot and co-pilot cockpit floor panels. Caution
must be observed when removing floor panels so as not to damage tach-gen filter harnesses. A connector is installed in each
tach-gen filter harness to allow the filter to be disconnected when removing the floor panel. (The Tach-gen filter assembly is
applicable to installations with Sandia ST-26 Tach-Gen Adapter unit installed by STC SA01456WI-D MDL 005-00375-30, Revision
4 and previously approved revisions.)
Pedestal Wiring
GTP 59 (Qty 2)
a) 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 1-2.
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 1-2
Page 4-12
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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. Gain access to circuit breaker panels by removing
the screws which fasten the edge-lit placards to the panels
a) Remove the MFD and PFDs as described in Section 6.
GDU 1040A PFD
(Qty 2) & GDU 1500
MFD
b) 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.
c) Inspect the CTL-62 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. Refer also to the King Air Model
90 Series Maintenance Manual, listed in Table 1-2.
d) Do not reinstall GDUs at this time. GDU cutouts provide access for visual inspections
below.
a) Inspect all instrument panel 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 1-2.
G1000 Wiring
harness
b) Inspect all other exposed G1000 wiring 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 1-2.
c) Inspect all fwd bulkhead connectors for security of attachment
GDC 74B Air Data
Computer (Qty 2)
a) Visually inspect each GDC 74B 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.
GEA 71 Engine/
Airframe Unit (Qty 2)
a) 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)
a) Inspect the GMA 1347D 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)
a) Inspect fans for accumulation of dirt and other damage. Remove excess dirt as required.
GDL 69A or GDL
69A SXM
a) 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
a) Inspect the GMC 710 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.
a) Inspect the PC920 unit, mount, and connectors for corrosion or other defects.
Senior Aerospace
PC920 Signal Cond.
Sandia Aerospace
ST26 Adapter(Qty 2)
NOTE
Applicable only to STC SA01456WI-D, MDL 005-00375-30, Revision 4 and
previously approved revisions.
a) Inspect the ST26 unit, mount, and connectors for corrosion or other defects
NOTE: Applicable only to STC SA01456WI-D, MDL Revision 4 and previously approved
revisions.
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a) Inspect the signal conditioner unit, mount, and connectors for corrosion or other defects.
NOTE
VMI Signal
Conditioner (Qty 2)
Mid-Continent
Standby Attitude Ind.
Thommen Standby
Airspeed Ind.
Thommen Standby
Altimeter
Circuit Breaker
Panels
Applicable only to STC SA01456WI-D, MDL 005-00375-30,
subsequent approved revisions.
Revision 5 and
a) Inspect the standby attitude indicator unit and connector for corrosion or other defects.
a) Inspect the standby airspeed indicator 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 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 1-2, and the Cabin Wire Harness Routing
drawing, listed in Table 1-2. Pay particular attention to possible areas of chaffing.
b) Inspect edge-lit overlay panels for damage or defect.
c) Reinstall the circuit breaker edge-lit overlays to the circuit breaker panels.
Placards
a) 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 12.
b) Reinstall the circuit breaker edge-lit placards to the circuit breaker panels.
Reinstall the MFD and PFDs as described in Section 6.
Table 4-7, Cabin Area Visual Inspection Procedure
Item
Description/Procedure
Initials
To gain access for the following Inspections, remove floorboard in cabin at FS 185.00
Cabin Wiring
Harness
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 Cabin Wire Harness Routing drawing, listed in Table 1-2.
a) Using a flashlight, inspect the servo, servo mount, connectors, support structures, and
control cables to ensure that no corrosion, chaffing, cracks, or other defects exist.
b) Have an assistant manually move the control surfaces from stop to stop and visually
observe the servo, and control cabling/chain. Ensure there is no binding in the control
cabling or chain, and that the capstan/sprocket rotates freely.
GFC 700 Equipment
c) 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.
d) Check the tension on the control cables. Refer to the Roll Servo Install drawing, listed
in Table 1-2, for cable tension specifications:
e) Ensure that each cable is correctly attached to the clamps.
f)
Follow recommended checks for checking main control cables, following the
instructions in Chapter 27, Flight Controls, of the King Air Model 90 Series
Maintenance Manual.
g) Replace the access panels if no other maintenance is to be performed.
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Table 4-8, Rear Fuselage and Empennage Visual Inspection Procedure
Item
Description/Procedure
Initials
To gain access for the following Inspections, refer to the servo installation drawings and the King Air Model 90 Series
Maintenance Manual, listed in Table 1-2.
Tail Wiring Harness
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 1-2.
b) Verify security of aft bulkhead connectors
a) Using a flashlight, inspect the servos, servo mounts, connectors, support structures, and
control cables to ensure that no corrosion, chaffing, cracks, or other defects exist.
b) 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/chain. Ensure
there is no binding in the control cabling or chain, and that the capstan/sprocket rotates
freely.
c) For GSM 86 servo gearboxes (if installed), check that the retaining bolt for the slip clutch
cartridge is not damaged or loose.
GFC 700 Equipment
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 the cable is questionable, replace it with a new one.
e) Check the tension on the control cables. Refer to the respective servo installation
drawing listed in Table 1-2 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 Model 90 Series
Maintenance Manual, listed in Table 1-2.
h) Replace the access panels if no other maintenance is to be performed.
The GMU 44 units are mounted in the vertical tail. To gain access, remove service panel in tail. Refer to King Air
Model 90 Series Maintenance Manual, listed in Table 1-2, for removal instructions.
a) For each GMU 44, do the following:
b) Remove the three Phillips screws holding the GMU access plate to the mounting bracket.
Be sure to use a non-magnetic screwdriver to avoid harming the GMU.
c) Carefully lower the assembly and inspect the GMU 44 and mounting plate.
GMU 44 (Qty 2)
d) Inspect the mounting hardware and GMU 44 for corrosion or other damage.
e) Inspect the GMU wiring and ensure no chaffing, wear, or other damage exists in
accordance with AC 43.13-1B, Chapter 11, Section 8, Paragraph 11-96 and the Tail Wire
Harness Routing drawing, listed in Table 1-2. Pay particular attention to possible areas
of chaffing.
f) Reinstall the GMU 44.
Table 4-9, Lightning Strike Inspection Procedure
Item
Description/Procedure
GTP 59 OAT Probe
or Antenna
a) 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 6.7. Refer to the Hawker Beechcraft Structural Inspection and
Repair Manual listed in Table 1-3 for any aircraft structural repairs.
Nose Avionics
Compartment Fans
a) A post lightning strike operational check of the GIA1 and GIA2 ported fans must be
done. Verify airflow from all fan ports per Section 4.14. Verify fan power and the speed
monitoring circuit of the GIA1 and GIA2 fans per Section 8.1.4. If replacement of the
fan(s) is required, refer to Section 6.26.
Initials
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IMPORTANT
For installed equipment not listed in this maintenance manual, use the inspection
procedures set forth in Chapter 05 of the King Air Model 90 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 Model 90 Series Maintenance
Manual, or other appropriate maintenance manual, in cases where the requirements
conflict.
4.5
Electrical Bonding Test
The following bonding test is provided for G1000-equipped C90A/C90GT/C90GTi King Air aircraft as a
requirement beyond what is given in the aircraft maintenance manual. The electrical bonding checks are
split into two tests, Phase 3 Electrical Bonding Test and Phase 4 Electrical bonding test. This places the
bonding test requirement for each G1000 LRU in the same phase as the visual inspection of that zone to
minimize access requirements.
4.5.1
Requirements
All G1000 equipment must be installed. Gain access for the procedure listed below in Section 4.5.3 as
required and in accordance with the King Air Model 90 Series 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, a standard voltmeter, power
supply with adjustable current limit, and ammeter may be substituted as alternative method. The following
procedure is written using the voltmeter, power supply and ammeter. All test equipment must have valid
calibration records. The set up for this is described below.
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.
2.
3.
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 milli-amp at each point). Do not
allow the reference current to exceed 1.5 amps for safety.
With the current set to 1A voltage reading will be value of the bonding resistance. Set the voltmeter
to measure milli-volts 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 milli-amp is present when measuring the voltage.)
TIP: When a 1A current is used all the milli-volt readings are the same as milli-Ohms, 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 milli-volts, then the value recorded will be 3 milli-volts
reduced by 20% which is 2.5 milli-volts which is the same as 2.5 milli-Ohms.
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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.
Ensure that at each PFD, MFD and GMC test point, no more than 30 milli-volts (30 mΩ) are present. Ensure
that at each other test point, no more than 5 milli-volts (5 mΩ) are present. In this case, voltage is equivalent
to resistance (Ω), given that precisely 1 amp reference current is present or the voltage is reduced by the
percentage increase in current used.
Pilot Compartment

Top metal case of PFD 1: __________ milli-Ohms

Top metal case of PFD 2: __________ milli-Ohms

Top metal case of MFD: __________ milli-Ohms

Top metal case of GMA 1347D #1: __________ milli-Ohms

Top metal case of GMA 1347D #2: __________ milli-Ohms

Top metal case of GCU 475: __________ milli-Ohms

Top metal case of GMC 710: __________ mill-Ohms

GEA 71 #1 body: __________ milli-Ohms

GEA 71 #2 body: __________ milli-Ohms

GDC 74B #1 body: __________ milli-Ohms

GDC 74B #2 body: __________ milli-Ohms

SAT 1 Probe base nut (inside fuselage): __________ milli-Ohms

OAT 2 Probe base nut (inside fuselage): __________ milli-Ohms

GDL 69A body: __________ milli-Ohms

Engine Signal Conditioner #1 near mounting holes of case: __________ milli-Ohms

Engine Signal Conditioner #2 near mounting holes of case: __________ milli-Ohms

PC920 Fuel Flow Signal Conditioner (if installed) near mounting holes of case: _______ milli-Ohms

PFD1 Cooling fan metal base: __________ milli-Ohms

PFD2 Cooling fan metal base: __________ milli-Ohms

MFD Cooling fan metal base: __________ milli-Ohms
Cabin Compartment

GSA 80 (Roll) Servo body: __________ milli-Ohms
4.5.4
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4.5.4
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.
Ensure at each test point no more than 5 milli-volts (5 mΩ) is present. In this case, voltage is equivalent to
resistance (Ω), given that precisely 1 amp reference current is present or the voltage is reduced by the
percentage increase in current used.
Nose Section

GWX 68 or GWX 70 body: __________ milli-Ohms
Nose Avionics Compartment

GIA 1 top: __________ milli-Ohms

GIA 2 top: __________ milli-Ohms

GTX 33 #1 top: __________ milli-Ohms

GTX 33 #2 top: __________ milli-Ohms

GRS 77 or GRS 7800 #1 metal base: __________ milli-Ohms

GRS 77 or GRS 7800 #2 metal base: __________ milli-Ohms

Standby battery: __________ milli-Ohms (may be installed in rear fuselage)
Rear Fuselage and Empennage
4.6

GMU 44 #1 metal base: __________ milli-Ohms

GMU 44 #2 metal base: __________ milli-Ohms

GSA 80 (Pitch) Servo body: __________ milli-Ohms

GSA 81 (Pitch Trim) Servo body: __________ milli-Ohms

GSA 80 (Yaw) Servo body: __________ milli-Ohms
GRS 77 or GRS 7800 Earth Magnetic Field Updates
The GRS utilizes an Earth magnetic field model which is updated once every five years. The update is
expected to be available from Garmin in each of the following years: 2015, 2020, and every five years
thereafter, as long as the GRS remains a Garmin-supported product.
The G1000 system alerts the operator that the magnetic field database is out of date by issuing the message
“AHRS SERVICE – AHRS Magnetic-field model needs update” (Ref. Section 5.14). Garmin will distribute
update instructions when updates are available. As of this writing, Garmin Service Bulletin No. 0533 Rev
B addresses the most recent update to the 2010 database. Service Bulletins may be obtained from
www.garmin.com at the ‘Dealer Resource Center ’ portion of the web site.
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4.7
GSA 8X Greasing Procedure
NOTE
The GSA 80 servo greasing procedure is required only when the GSA 80 is removed and
reinstalled . Re-grease each servo output gear following this procedure.
1. Remove each servo as per Section 6.
2. Using a lint-free cloth, remove excess grease build-up from the single servo output gear (see Figure
4-1.)
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!
3. Using a brush or other applicator, apply a thin coat of Aeroshell 33MS (Lithium-complex based)
grease to the servo output gear.
4. Reinstall each servo as per Section 6.
Figure 4-1, Servo Gear
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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 the
G1000 system 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 4-2, GIA I/O Page
TRUE/VALID
FALSE/INVALID
or
or
Figure 4-3, Discrete Indications
NOTE
Reference Table 3-1 for interpretation of data indicator symbols
1. Verify the DATA indicators of the discrete inputs labeled ‘FLAP EXTEND’ and ‘FLAP RETRACT’
show a FALSE/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 TRUE/VALID condition.
3. When the flap motion is completed, verify the DATA indicators of the discrete inputs labeled ‘FLAP
EXTEND’ and ‘FLAP RETRACT’ show a FALSE/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 TRUE/VALID condition.
5. When the flap motion is completed, verify the DATA indicators of the discrete inputs labeled ‘FLAP
EXTEND’ and ‘FLAP RETRACT’ show a FALSE/INVALID condition.
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6.
Repeat steps 1 through 5 for GIA2.
7.
The flap discrete input check is complete.
4.9
Slip Clutch Torque and Servo Current Display Check Procedure
Sections 4.9.1 thru 4.9.4 are applicable as follows:

Section 4.9.1: Automatic test for GSM 85A or GSM 86 with SW version 0636.03 and subs
o

Includes servo current check
Section 4.9.2: Manual test for GSM 85A with SW version 0636.02 and earlier
o
Includes servo current check

Section 4.9.3: Fixture procedure for GSM 85A or GSM 86

Section 4.9.4: Servo current check
o
4.9.1
The servo current check can be accomplished as part of Section 4.9.1 or Section 4.9.2. If
neither of those sections is being performed, this section is required.
Automatic Slip Clutch Test Procedure (SW Version 0636.03 and Subs)
To ensure proper operation during this test, it is necessary to remove power from the aircraft prior to starting.
1. Press and hold the enter button on PFD1, and restore power to the aircraft.
2. With PFD1 in Configuration Mode, verify the correct type of servo gearbox is configured for each
servo by going to the GDU - AIRFRAME CONFIGURATION page and check which servo mount is
reported in the AIRFRAME window.
Figure 4-4, Airframe Configuration Page
3. Go to the GFC Page Group and select the GFC STATUS page using the FMS knobs.
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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.
Figure 4-5, GFC Status Page
NOTE
The displayed test results on the PFD are not stored in G1000 memory. If power is cycled,
these values will be lost. However, these test values are not lost by changing configuration
mode pages.
IMPORTANT
It is highly recommended that the following test be performed at temperatures
between 50° F and 120° F.
5. Use the FMS knob to select the desired servo (PITCH, ROLL, YAW or PITCH TRIM).
6. Verify that the PFT status field shows PASSED.
7. Verify that the aircraft control surface to be checked is free to travel throughout its range of motion.
8. 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, cycle the AFCS SERVO circuit breaker and repeat the test.
9. During operation of the servo, observe the CURRENT field and verify that the current displayed
varies during operation
10. When test is completed, verify the CLUTCH TEST PASS message is displayed on the MFD.
11. Repeat steps 4 through 8 for each servo axis (Pitch, Roll, Yaw and Pitch Trim).
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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 test does not pass, the servo gearbox must be removed from the aircraft and
tested/adjusted per the Servo Adjustment Fixture Procedure in Section 4.9.3.
4.9.2
Manual Slip Clutch Test Procedure (SW Version 0636.02 and earlier)
1. With PFD1 in Configuration Mode, go to the GFC Page Group and select the GFC STATUS page
using the FMS knobs.
Figure 4-6, GFC Status Page
NOTE
The displayed test results on the PFD are not stored in G1000 memory. If power is cycled,
these values will be lost. However, these test values are not lost by changing configuration
mode pages.
IMPORTANT
It is highly recommended that the following test be performed at temperatures
between 50° F and 120° F.
2. Use the FMS knob to select the desired servo (PITCH, ROLL, YAW or PITCH TRIM).
3. Verify that the PFT status field shows PASSED.
4. Verify that the aircraft control surface to be checked is free to travel throughout its range of motion.
5. Press the ENG CLCH softkey on the PFD.
6. With the clutch engaged, take hold of the aircraft controls and manually overcome the clutch. Move
the control surface to be tested from stop to stop a minimum of two times each direction.
7. Position the control surface in the neutral position (full aft position if the PITCH SERVO is selected).
Press the DIS CLCH softkey.
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IMPORTANT
If the test must be stopped, firmly grasp the aircraft control being moved and press
the red AP DISC switch on the aircraft control stick. If an abnormal disconnect of a
servo occurs, cycle AFCS SERVO circuit breaker and repeat the step.
8. Manually select +2.50 rpm for the Drive Servo and press ENT.
9. Press the ENG CLCH softkey.
10. Press the DRV SRVO softkey.
11. Allow the selected servo to drive the control surface to either the NOSE DOWN stop (Pitch and
Pitch Trim) or the LEFT stop (Roll and Yaw).
12. During operation of the servo, observe the CURRENT field and verify that the current displayed
varies during operation
13. Allow the servo to continue driving against the control stop for at least 50 seconds. Observe the
TORQUE values displayed in the Servo Data field and record the maximum and minimum values
in Table 4-10 or in the appropriate aircraft maintenance records.
14. Manually select 0.00 rpm for the Drive Servo and press ENT. Allow the servo to stop.
15. Manually select -2.50 for the Drive Servo and press ENT. Allow the selected servo to drive the
control surface to either the NOSE UP stop (Pitch and Pitch Trim) or the RIGHT stop (Roll and
Yaw). If the PITCH SERVO is selected, firmly hold the control yoke in the full aft position until the
NOSE UP portion of the test is completed.
16. Allow the servo to continue driving against the control stop for at least 50 seconds. Observe the
TORQUE values displayed in the Servo Data field and record the maximum and minimum values
in Table 4-10 or in the appropriate aircraft maintenance records.
17. Manually select 0.00 rpm for the Drive Servo and press ENT. Allow the servo to stop.
18. Firmly grasp the aircraft control under test and press the DIS CLCH softkey.
19. Press the STP SRVO softkey.
20. Repeat steps 2 through 19 for each servo axis shown.
21. Verify that the minimum and maximum torque values measured are within the Minimum and
Maximum torque values allowed, for the given axis, listed in Table 4-10.
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Axis
Pitch
Roll
Yaw
Pitch
Trim
Direction
Min Measured
Torque (in-lbs)
Max Measured
Torque (in-lbs)
Min Allowed
Torque (in-lbs)
Max Allowed
Torque (in-lbs)
76
105
63
87
56
99
39
53
Up
Down
Left
Right
Left
Right
Up
Down
Table 4-10, Measured Torque
NOTE
If the measured values exceed the limits in Table 4-10, the servo must be removed from
the aircraft and tested/adjusted per the Servo Adjustment Fixture Procedure in Section
4.9.3.
4.9.2.1
Abnormal Test Prompts
During the testing, the following prompts may be displayed indicating an abnormality encountered during
the test. Use the following guidelines to troubleshoot.
Message Prompt
Probable Cause
STOP NOT REACHED
The servo did not detect a torque
value which exceeded 70% of the
established mechanical torque limit
within 1 minute of starting the test. A
low slip clutch setting is the likely
cause.
SERVO TORQUE TOO HIGH
The servo detected an average
torque value which exceeded 130%
of the established mechanical torque
limit. Likely causes include a high
slip clutch setting, or excess friction
encountered during the control
surface travel.
Action
Repeat test.
If the same result is received,
remove servo mount and check/set
clutch on stand.
Engage the autopilot for the axis
which reported torque to high.
Manually operate the controls and
verify that the clutch can be
overridden. If the clutch can slip,
repeat the test again. Otherwise
remove the servo mount and reset
the clutch.
Check control friction against aircraft
maintenance specifications.
If the same result is received on
retest, remove servo mount and
check/set clutch on stand.
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Message Prompt
Probable Cause
SERVO TORQUE TOO LOW
The servo detected an average
torque value which fell below 70% of
the established mechanical torque
limit after detecting that the stop was
reached.
Action
Repeat test again. If the same result
is received, remove servo mount and
check/set clutch on stand.
Likely causes include a low slip
clutch setting or a disturbance in the
controls before reaching the stop.
Repeat test again.
INVALID SERVO SPEED
TEST SPEED FAIL
SERVO TEST TIMED OUT
The servo is unable to maintain the
required ~2.5 RPM during the test
(Speed drops below 2 RPM or
exceeds 3 RPM)
Servo has not responded to the test
initialization command.
Servo not responding for over 60
seconds during testing.
If the same result is received,
remove servo mount and check/set
clutch on stand.
If resetting clutch does not clear
message, replace servo motor.
Repeat test again.
If message does not clear,
troubleshoot the servo and it’s wiring
for the source of the failure.
SERVO DATA TIMED OUT
The servo has failed to transmit load
cell sensor status.
Repeat test when the source of the
servo failure has been corrected.
LOAD CELL INVALID
A special test monitor has detected
an inequality between motor torque
and load cell torque greater than the
specified threshold.
An out-ofcalibration load cell may be the
cause.
Replace servo motor and repeat
test.
AIRBORNE STATUS
The G1000 system has detected
airborne status, (determined by true
airspeed) and has cancelled the test.
Verify the ADC is online.
Check pitot/static system is free of
obstructions and plumbing kinks.
Repeat test.
4.9.3
Servo Adjustment Fixture Procedure
Remove the GSM 85A (or GSM 86 if installed) Servo Mount as per Section 6.12.
The slip clutch torque values must be checked, and adjusted if necessary, to the values listed in Table 4-11.
IMPORTANT
This adjustment requires the use of the Garmin servo adjustment fixture, P/N T1000110-01. For detailed operating instructions for the fixture, refer to GSA8X /
GSM85(A) Installation Manual, listed in Table 1-3.
1. Perform this procedure within a temperature range of 50 °F to 120 °F.
2. If a protective cover is installed on the servo mount, remove the protective cover.
3. Place the servo mount 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 wing nuts on bottom of fixture while
holding the top thumbscrews.
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4. 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.
5. Connect a 2 Amp, 24 V, DC power supply to the fixture.
6. Place the solenoid switch to "on" and move the direction switch to the clockwise or counterclockwise position. Allow the clutch to rotate at least one revolution in each direction (note: the
capstan itself is fixed.)
7. 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.
8. If the minimum and maximum torque values are within the specified range in Table 4-11, the GSM
slip clutch is acceptable. Reinstall the GSM 85A or GSM 86 servo gearbox per Section 6.12.
9. If the minimum and maximum torque values are not within the specified range in Table 4-11, the
GSM 86 slip clutch cartridge must be replaced or the GSM 85A must be adjusted.
10. For GSM 85A only: If adjustment is required, remove cotter pin and adjust the nut on the capstan
as needed to obtain the torque value listed in Table 4-11, as shown on the torque wrench. Position
the nut to align with holes in the capstan shaft and install a new cotter pin.
11. When finished, remove the fixture cable, and then remove the servo gearbox from the fixture.
12. Install the GSM 85A or GSM 86 servo gearbox per Section 6.12.
Table 4-11, Slip Clutch Torque Settings
Servo
Pitch Trim*
Pitch
Yaw
Roll
GSM 85A Setting
49 +/-6 in-lbs*
88 +/-10 in-lbs
83 +/-10 in-lbs
73 +/-9 in-lbs
GSM 86 Setting
45 +/-13 in-lbs*
90+/-24 in-lbs
90 +/-18 in-lbs
72+/-21 in-lbs
*Valid with continuous travel servo gearbox only
4.9.4
Servo Current Display Check
To ensure proper operation during this test, it is necessary to remove power from the aircraft prior to starting.
1. Press and hold the enter button on PFD1, and restore power to the aircraft.
2. With PFD1 in Configuration Mode, go to the GFC Page Group and select the GFC STATUS page
using the FMS knobs.
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Figure 4-7, GFC Status Page
IMPORTANT
It is highly recommended that the following test be performed at temperatures
between 50° F and 120° F.
3. Use the FMS knob to select the desired servo (PITCH, ROLL, or YAW).
4. Verify that the aircraft control surface to be checked is free to travel throughout its range of motion.
5. Manually select +2.50 rpm for the Drive Servo and press ENT.
6. Press the ENG CLCH softkey.
7. Press the DRV SRVO softkey. During operation of the servo, observe the CURRENT field and
verify that the current displayed varies during operation.
IMPORTANT
Once the test starts the servo will begin to move the aircraft controls. If the test
must be stopped, firmly grasp the aircraft control being moved and press the red
AP DISC switch on the aircraft control stick.
8. Allow the selected servo to drive the control surface to either the NOSE DOWN stop (Pitch) or the
LEFT stop (Roll and Yaw). If the Pitch servo is selected, firmly hold the control yoke in the full
forward position until the NOSE DN test is completed.
9. Manually select 0.00 rpm for the Drive Servo and press ENT. Allow the servo to stop.
10. Firmly grasp the aircraft control under test and press the DIS CLCH softkey.
11. Press the STP SRVO softkey.
12. Repeat steps 2 through 11 for each servo axis shown.
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4.10 G1000 Redundant Connection Check
Perform the following steps to verify the following connections are intact:
(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
(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:
NOTE
Reference Table 3-1 for interpretation of data indicator symbols
(A) PRI and SEC power sources for PFD 1, GIA 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, open the following circuit breakers on the right hand circuit
breaker panel:

PFD 1 (PRI)

AHRS 1 (PRI)

ADC 1 (PRI)

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. Open the following circuit breakers on the right hand circuit breaker panel:

PFD 1 (SEC)

AHRS 1 (SEC)

ADC 1 (SEC)

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
NOTE
References to GRS in this section can imply either Garmin AHRS Model GRS 77 or GRS
7800. Differences to a specific GRS model will be identified with the applicable GRS model
number.
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 RS232 Channel 1 (GDC74 #1) and
RS232 Channel 6 (GRS #1) show valid indicators. Ref. Section 5.2.1.2.
5. With GIA1 selected in the SELECT UNIT window, verify the ARINC 429 IN5 (GDC74 #1) and
ARINC 429 IN6 (GRS #1) show valid indicators. Ref. Section 5.2.1.2.
6. With GIA2 selected in the SELECT UNIT window, verify the RS232 Channel 1 (GDC74 #2) and
RS232 Channel 6 (GRS #2) show valid indicators. Ref. Section 5.2.1.2.
7. With GIA2 selected in the SELECT UNIT window, verify the ARINC 429 IN5 (GDC74 #2) and
ARINC 429 IN6 (GRS #2) show valid indicators. Ref. Section 5.2.1.2.
8. In the PFD page group, go to the GIA RS-232/ARINC 429 CONFIG page.
9. With PFD1 selected in the SELECT UNIT window, verify the ARINC 429 IN1 (GRS #1) and ARINC
429 IN2 (GDC74 #1) show valid indicators. Ref. Section 5.2.1.1.
10. With PFD2 selected in the SELECT UNIT window, verify the ARINC 429 IN1 (GRS #2) and ARINC
429 IN2 (GDC74 #2) show valid indicators. Ref. Section 5.2.1.1.
(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. Re-start PFD 2, PFD 1 and MFD in normal mode.
2. On the right hand circuit breaker panel, open the MFD circuit breaker:
3. Verify NAV 1, COM 1, NAV 2 and COM 2 remain valid on both PFD 1 and PFD 2.
4. Close the MFD circuit breaker and wait for MFD to initialize:
5. Open the PFD 2 circuit breaker:
6. Press the DISPLAY BACK UP button on the Pilot’s GMA 1347D audio panel.
7. 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.
8. Press the DISPLAY BACK UP button on the Pilot’s GMA 1347D audio panel to return to normal
mode.
9. Close the PFD 2 circuit breaker and wait for PFD 2 to initialize:
10. Open the PFD 1 (PRI) and PFD 1 (SEC) circuit breakers:
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11. Press the DISPLAY BACK UP button on the Co-pilot’s GMA 1347D audio panel.
12. 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.
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:
a. NAV 1 and COMM1 tuning fields on PFD 1 and PFD 2 are invalid (red X).
b. L/R engine data remains valid.
c.
XPDR1 is Inoperative.
d. GMA1 Is Inoperative.
e. AHRS1 is using backup GPS source.
f.
AHRS2 not receiving backup GPS Information.
g. An amber BOTH ON GPS2 is displayed on PFD 1 and PFD 2.
h. 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:
a. NAV2 and COMM2 tuning fields on PFD 1 and PFD 2 are invalid (red X).
b. L/R engine data remains valid.
c.
XPDR2 is Inoperative.
d. GMA2 Is Inoperative.
e. AHRS2 is using backup GPS source.
f.
AHRS1 not receiving backup GPS Information.
g. An amber BOTH ON GPS1 is displayed on PFD 1 and PFD 2.
h. 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:
a. COM1/NAV1 & COM2/NAV2 fields flag invalid.
b. GPS CDI flags DR on PFD.
c.
NAV1 & NAV2 CDI loses deviation bar.
d. XPDR field flags invalid on PFD.
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e. Engine Instrument field flags invalid on MFD.
f.
All AHRS & ADC fields remain valid.
g. Red AFCS status annunciation given.
h. If equipped with TAWS, TAWS FAIL annunciation given.
i.
If equipped with ADF and/or DME, ADF/DME windows flag invalid.
9. Restore power to both GIA units.
4.11 Engine Data Check
Do the following to verify the engine data availability and validity for torque, ITT, and oil pressure. Required
test equipment is provided in the table below.
Test Equipment
Decade Box
Signal Generator
Make/Requirement
Model/Part Nbr
0-1k ohms
As appropriate
0-10Vdc / 0 – 1k Hz
As appropriate
4.11.1 Torque
1. Using a signal generator, inject a DC signal into the No. 1 GEA via left engine firewall connectorspins J102-C (HI) and J102-R (LO).
2. Simulate the following voltages, and verify the indication and status:
Test Point (Vdc)
Indication (ft-lbs)
0.00 +/- .02
0
2.53 +/- .02
1320
Status
bottom of green band
Green digital
Configurations
all
red digital*
NOTE: red radial
1315
4-10, 21-22
red digital*
2.90 +/- .02
1525
NOTE: red radial
1520
2-3, 17-19
(*) steady after 5 seconds
3. 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.
4. Close the GIA1 (PRI) and GIA1 (SEC) circuit breakers, and wait until the COM1 and NAV1 fields
are valid.
5. Repeat steps 1 and 2 using the No. 2 GEA via right engine firewall connectors-pins J103-C (HI)
and J103-R (LO).
6. Open GIA 2 circuit breaker, and verify the last observed torque indication remains unchanged.
7. Close the GIA 2 circuit breaker, and wait until the COM2 and NAV2 field are valid.
4.11.2 ITT
1. Remove left engine ITT thermocouple terminals from sensor. Using a signal generator, inject a DC
signal into the No. 1 GEA via left engine firewall connectors-pins, as follows:
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
S/N LJ-1063 thru LJ-1360, LJ-1362: J104-T* (LO) and J104-W* (HI)

S/N LJ-1361, LJ-1363 and after: J104-P* (LO) and J104-S* (HI)
2. Simulate the following voltages, and verify the indication and status:
Test Point (mV)
Indication (degC)
16.40 +/- .28
400*
44.3 +/- .28
1090*
Status
Configurations
bottom of green band
green digital
red triangle, start
mode
all
all
red digital**
(*) verify value displayed is within test point tolerances
(**) steady after 5 seconds
3. 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.
4. Close the GIA1 (PRI) and GIA1 (SEC) circuit breakers, and wait until the COM1 and NAV1 fields
are valid.
5. Repeat steps 8 and 9 using the No. 2 GEA via right engine firewall connectors-pins specified below
and right engine ITT thermocouple.

S/N LJ-1063 thru LJ-1360, LJ-1362: J105-T* (LO) and J105-W* (HI)

S/N LJ-1361, LJ-1363 and after: J105-P* (LO) and J105-S* (HI)
6. Open GIA 2 circuit breaker, and verify the last observed ITT indication remains unchanged.
7. Close the GIA 2 circuit breaker, and wait until the COM2 and NAV2 field are valid.
4.11.3 Oil Pressure
1. Using a signal generator, inject a DC signal into the No. 1 GEA via left engine firewall connectorspins J104-A (LO) and J104-B (HI).
2. Simulate the following voltages, and verify the indication and status:
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Test Point (Vdc)
Indication (PSI)
.98 +/- .1
39 +/- 1
2.0 +/- .1
80 +/- 1
2.1 +/- .1
85 +/- 1
Status
Configurations
red digital
NOTE: low red radial
40
bottom of green band
Green digital
bottom of green band
Green digital
all
4-10, 21-22
2-3, 17-19
3. On the right hand circuit breaker panel, open the GIA1 (PRI) and GIA1 (SEC) circuit breakers, and
verify the last observed oil pressure indication remains unchanged.
4. Close the GIA1 (PRI) and GIA1 (SEC) circuit breakers, and wait until the COM1 and NAV1 fields
are valid.
5. Repeat steps 15 and 16 using the No. 2 GEA via right engine firewall connectors-pins J105-A (LO)
and J105-B (HI).
6. Open GIA 2 circuit breaker, and verify the last observed oil pressure indication remains unchanged.
7. Close the GIA 2 circuit breaker, and wait until the COM2 and NAV2 field are valid.
8. Disconnect test equipment.
9. Reconnect the following firewall connectors, and verify all engine parameters are displayed valid
on the MFD with no Red X’s: J102, J103, J104, J105
4.12 Trim Annunciator Check
This procedure will check the trim annunciation from both GIA 1 and GIA 2.
1. Ensure the G1000 is in normal mode, the autopilot is not engaged, and the GMC 710 XFR key is
selected to the pilot’s 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. Release the switch and
wait for the PTRM annunciation to clear.
3. 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. Release the switch
and wait for the PTRM annunciation to clear.
4. Repeat Steps 2 and 3 for the right part of the pilot’s pitch-trim switch.
5. Repeat Steps 2 through 4 for the copilot’s pitch-trim switch.
6. Select copilot side by pressing the XFR key on the GMC 710 (changes active GIA to GIA 2).
7. Repeat Steps 2 through 5 and verify annunciations are displayed on both PFD 1 and PFD 2.
8. Re-select pilot side by pressing XFR key on the GMC 710 (changes active GIA back to GIA 1).
9. Hold the control yoke with the 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 0º
degrees.
10. Press the Go Around switch on the throttle, then engage the autopilot and apply a forward load on
the control yoke. Verify that the pitch trim wheel rotates in the nose up direction.
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11. Disengage the autopilot and flight director. Use the pitch-trim switch (or the pitch-trim wheel) to trim
full up.
12. Move the control yoke to the full forward position and hold.
13. Engage the autopilot, apply firm aft pressure on the control yoke for approximately 15 seconds,
allowing the pitch-trim wheel to move freely. Verify that the amber ELE ↓ annunciator is displayed
on both PFD 1 and PFD 2.
14. Disengage the autopilot and flight director. Use the pitch-trim switch (or the pitch-trim wheel) to trim
full down.
15. Move the control yoke to the full aft position and hold.
16. Engage the autopilot, apply firm forward pressure on the control yoke for approximately 15
seconds, allowing the pitch-trim wheel to move freely. Verify that the amber ELE ↑ annunciator is
displayed on both PFD 1 and PFD 2.
17. Disengage the autopilot and flight director. Rotate the control yoke to the full left position and hold.
18. Engage the autopilot, apply firm right load on the control yoke for approximately 10 seconds. Verify
that the amber ← AIL annunciator is displayed on both PFD 1 and PFD 2.
19. Disengage the autopilot and flight director. Rotate the control yoke to the full right position and hold.
20. Engage the autopilot, apply firm left load on the control yoke for approximately 10 seconds. Verify
that the amber AIL → annunciator is displayed on both PFD 1 and PFD 2.
21. Disengage the autopilot and flight director modes.
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..
22. Engage the yaw damper.
23. 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.
24. Verify that the amber ← RUD annunciator is displayed on both PFD 1 and PFD 2.
25. Reposition the rudder pedals to the neutral position.
26. 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.
27. Verify that the amber RUD → annunciator is displayed on both PFD 1 and PFD 2.
28. Reposition the rudder pedals to the neutral position.
29. Disengage yaw damper.
30. The Trim Annunciator Check is complete.
4.13 G1000 Miscompare Checks
This procedure will check the AHRS, airspeed and altitude miscompare monitors. Accomplish the following
checks with the aircraft positioned where it can receive GPS signals and magnetic heading. Access to
AHRS1 and AHRS2 will be required during this test.
1. Ensure the G1000 is operating in normal mode.
2. Connect a pitot/static test set to the aircraft ADC1 pitot and static ports (Pilot’s side). (Do not
connect the pitot/static tester to ADC2 ports at this time)
3. Set the baro-correction on PFD1 and PFD2 to 29.92in/hg.
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4. On the AFCS mode controller, press the AP button and verify autopilot engages.
5. Slowly increase the pitot/static test set to simulate an ADC1 / ADC2 altitude miscompare of greater
than 200 ft., verify ADC2 altitude does not increase, autopilot does not disconnect and amber
comparator window text “ALT MISCOMP” is displayed on PFD1 and PFD2.
6. Reduce ADC1 altitude to ambient pressure.
7. Repeat Step 5 with the pitot/static test set connected to the aircraft ADC2 pitot and static ports.
8. Use the pitot/static test set to simulate an airspeed of 40 kts for ADC1 and 55 kts for ADC2. Verify
the autopilot does not disconnect and amber comparator window text “IAS MISCOMP” is displayed
on PFD 1 and PFD2.
9. Use the pitot/static test set to simulate an airspeed of 55 kts for ADC1 and 40 kts for ADC2. Verify
the autopilot does not disconnect and amber comparator window text “IAS MISCOMP” is displayed
on PFD 1 and PFD2.
10. Use the pitot/static test set to simulate an airspeed of 85 kts for ADC1 and 95 kts for ADC2. Verify
the autopilot does not disconnect and amber comparator window text “IAS MISCOMP” is displayed
on PFD 1 and PFD2.
11. Use the pitot/static test set to simulate an airspeed of 95 kts for ADC1 and 85 kts for ADC2. Verify
the autopilot does not disconnect and amber comparator window text “IAS MISCOMP” is displayed
on PFD 1 and PFD2.
12. Reduce ADC1 and ADC2 airspeeds to 0 kts.
13. Slowly rotate AHRS1 along the lateral (pitch) axis to a pitch attitude of greater than 5 degrees,
verify the following:
a. AHRS2 pitch attitude does not change
b. An amber “PIT MISCOMP” is annunciated on PFD1 and PFD2
c.
Autopilot disconnects at approximately 5 deg AHRS1 / AHRS2 miscompare
d. The autopilot disconnect audio alert (two hi-low tones) sounds
e. A red flashing AP annunciator on PFD1 and PFD2
f.
Flight director command bars remain in view with PIT and ROL modes annunciated
14. Replace AHRS1 to normal attitude and verify that attitude display on PFD1 displays current aircraft
attitude.
15. Use the AFCS mode controller to re-engage autopilot.
16. Slowly rotate AHRS1 along the longitudinal (roll) axis to a roll attitude of greater than 5 degrees,
verify the following:
a. AHRS2 roll attitude does not change
b. An amber “ROL MISCOMP” is annunciated on PFD1 and PFD2
c.
Autopilot disconnects at approximately 5 deg AHRS1 / AHRS2 miscompare
d. The autopilot disconnect audio alert (two hi-low tones) sounds
e. A red flashing AP annunciator on PFD1 and PFD2
f.
Flight director command bars remain in view with autopilot in PIT and ROL mode
17. Replace AHRS1 to normal attitude and verify that attitude display on PFD1 displays current aircraft
attitude.
18. Repeat Steps 13 through 17 for AHRS2.
19. The G1000 Miscompare checks are complete.
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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
and GTX units. The fan speed monitoring circuits and annunciations are checked by the G1000 Cooling
System Electrical Check in Section 9.2.1 and a Visual Inspection of the fan 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 GTX and verify airflow is present.
3. Reconnect the cooling fan hose to the GTX and secure per Nose Bay Electrical Equipment Install
drawing 005-00375-34, Rev 5 or subsequent.
4. Disconnect cooling fan hose from the pilot side GIA GTX and verify airflow is present.
5. Reconnect the cooling fan hose to the GIA and secure per Nose Bay Electrical Equipment Install
drawing 005-00375-34, Rev 5 or subsequent.
6. Repeat Steps 2 through 5 for the copilot side GTX and GIA.
7. The Nose Avionics Compartment Fans Operational Check is complete.
4.15 Instrument Panel Fans Operational Check
This procedure will verify that airflow is present from the PFD1, MFD and PFD2 cooling fans. The fan
speed monitoring circuits and annunciations are checked by the G1000 Cooling System Electrical Check
in Section 9.2.1. 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 1-2.
With the PS-835 battery installed in the aircraft and aircraft power applied, verify all four Battery Voltage
LEDs are lit to indicate the battery is being charged (see Figure 4-8).
With the PS-835 battery installed in the aircraft and no aircraft power applied, press TEST SWITCH (Figure
4-8, Item 4) into TEST position for 5 seconds. The PS-835 indicates that it is adequately charged when the
VOLTAGE LEVEL 24Vdc LED (Figure 4-8, Item 2) illuminates momentarily, AND the 20Vdc LED (Figure
4-8, 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.
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Table 4-12, Standby Battery Required Equipment
DESCRIPTION
VENDOR/SPECIFICATION
Power Supply
0-30 VDC, 20A capacity
DVM
Fluke Model 8050A
Load Resistor
7Ω +/- 1% 250 watt
Stopwatch
Capable of measuring to the minute
Figure 4-8, 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 4-8, 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 4-8, 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.
3. Connect Digital Voltmeter leads to J1 connector pins 11 (+) and 7 (-).
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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 (PS-835D) or at 5-minute intervals (PS835C).
6. Note voltage on Digital Voltmeter at 48.0 minutes (PS-835D) or at 20.0 minutes for the (PS-835C).
This voltage must be greater than 20.0 Vdc.

All INDIVIDUAL CELL MONITOR LED’s (Figure 4-8, Item 1) must remain on.

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 4-8, 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 4-8, Item 4). If no OUTPUT VOLTAGE MONITOR LED's come
on:
1. Position all INDIVIDUAL CELL DIP SWITCHES (Figure 4-8, Item 5) to the ON position.
2. Press and hold TEST SWITCH (Figure 4-8, Item 4) and observe the INDIVIDUAL CELL MONITOR
LED's (Figure 4-8, Item 1).

If all INDIVIDUAL CELL MONITOR LED’s come on except DS12, the unit is damaged and
requires repair at an authorized repair station.

If all INDIVIDUAL CELL MONITOR LED’s are on, a low-battery voltage condition exists.
B. Perform the Charging Procedure.
4.16.4 Charging Procedure
(Constant-Voltage Charging Method)
Locally manufacture a power cable using 16AWG wire and the appropriate mating connector. Include a
Diode (15 Adc (min), 50.0 PIV or greater) to prevent battery discharge in case of loss of power from the
power source. Using the external power supply apply 30.0 Vdc (10A maximum current limited) to J1
connector pins 11 (+) and 7 (-) and charge the unit for 16 hours. The batteries should reach 80% capacity
within 1 hour and full charge at 16 hours.
Figure 4-9, Power Supply Connection
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5
TROUBLESHOOTING
This section provides instructions and guidance for G1000 system troubleshooting, as installed in the King
Air C90 Series.
IMPORTANT
Sections 6, 7 and 8 provide detailed instructions on equipment removal,
replacement, configuration, and return-to-service testing.
Anytime a G1000
component or LRU is removed, swapped, or replaced, the technician must follow
the procedures given in Sections 6, 7 and 8 to ensure proper operation of the system.
Troubleshoot the G1000 system by first identifying, then isolating the specific failure to the responsible
LRU. There are several indications that the G1000 presents to the pilot or technician, showing overall
system condition. A course of action should be determined based on the information presented on the
display. This section shows possible scenarios likely to be encountered during normal operation and gives
troubleshooting guidance to the technician to resolve problems.
Figure 5-1, AUX – System Status Page
The AUX – System Status page displays the following information for each LRU and sub-function:

Status: A green checkmark (√) 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 a green checkmark (√) and that the
correct software is loaded in each unit. Additional airframe and database information is also displayed on
this page.
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5.1
G1000 Alerting System
Figure 5-2, 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 changes to ADVISORY as shown in Figure
5-3. Pressing the softkey annunciation acknowledges the presence of the alert and displays the advisory
message in the Alerts Window.
Figure 5-3, ADVISORY Softkey Annunciation
System Failure Annunciations:
Typically, a large red X appears in windows when a failure is detected in the LRU providing the information
to the window.
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5.1.1
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)
TIS Traffic Advisory
No Traffic (voice)
TIS Traffic Unavailable
“Minimums, Minimums” (voice)
Minimums Aural Alert
Alt Alert
Altitude Alerting Function
“Caution Terrain, Caution Terrain” (voice) and
“Terrain Ahead, Terrain Ahead” (voice)
TAWS Caution alert: Reduced required terrain
clearance
Or Imminent impact with terrain.
“Terrain Terrain, Pull Up Pull Up” (voice) and
“Terrain Ahead Pull Up, Terrain Ahead Pull Up”
TAWS Warning alert: Reduced required terrain
clearance
Or Imminent impact with terrain.
“Too Low Terrain” (voice)
TAWS Caution alert: Premature descent alert
(PDA)
“Sink Rate” (voice)
TAWS Caution alert: Ground Proximity envelope 1,
2, or 3, Excessive Descent Rate
“Pull Up” (voice)
TAWS Warning alert: Ground Proximity envelope
1, 2, or 3, Excessive Descent Rate
“Don’t Sink” (voice) and
“Too Low Terrain”
TAWS Caution alert: Ground Proximity altitude loss
after takeoff
“Five Hundred” (voice)
TAWS Caution alert: Ground proximity voice
callout
“Caution Obstacle, Caution Obstacle” (voice) or
“Obstacle Ahead, Obstacle Ahead ” (voice)
TAWS Caution alert: Obstacle awareness caution.
“Obstacle Obstacle Pull Up Pull Up” (voice) or
“Obstacle Ahead Pull Up, Obstacle Ahead Pull Up”
(voice)
TAWS Warning
warning.
“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
alert:
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5.2
System Annunciations
If data fields become invalid due to an LRU failure, the PFD/MFD typically annunciates the failure with a
large red X, as shown in Figure 5-4.
Figure 5-4, System Annunciations
5.2.1
Failed Path Messages
The following message indicates there is a data path connected to the GDU (PFD1, PFD1, or MFD) or the
GIA 63W (1 or 2) that has failed.

FAILED PATH – A data path has failed.
The FAILED PATH message is triggered by a timeout of any one digital channel. The channels that are
checked are listed on these pages in config mode:

GDU RS-232 / ARINC 429 CONFIG (PFD1/2, and MFD)

GIA RS-232 / ARINC 429 CONFIG (GIA1 and GIA2)

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.
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NOTE
Reference Table 3-1 for interpretation of data indicator symbols
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 configuration mode pages listed below.
5.2.1.1
GDU RS-232 / ARINC 429 CONFIG Page
PFD 1 RS-232
Channel
LRU
Indicator
Status
PFD1/GMC 710 data path is functioning correctly.
PFD1/GMC 710 data path is not functioning correctly.
CHNL 2
GMC 710

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 to a green
checkmark (√) 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
Status
PFD1/GRS1 data path is functioning correctly.
PFD1/GRS1 data path is not functioning correctly.
IN 1

Verify GRS1 status is “OK” using the System Status page on
the MFD. If it is not, correct condition before proceeding,
reference GRS troubleshooting sections.

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 to a green
checkmark (√) after swapping displays.
GRS #1

Swap GRS1 and GRS2 (no reconfiguration required) to
confirm if the problem is in the original GRS1.
o Replace original GRS1 if box turns to a green
checkmark (√) after swapping units.
Check the PFD1/GRS1 interconnect wiring for faults.
PFD1/GRS1 data path functionally is unknown. Reload PFD1
configuration file.
PFD1/GDC 74 #1 data path is functioning correctly
PFD1/GDC 74 #1 data path is not functioning correctly.
IN 2
GDC 74 #1

Verify GDC 74 #1 status is “OK” using the System Status
page on the MFD. If it is not, correct condition before
proceeding, reference GDC troubleshooting sections.

Load PFD1 and GDC 74 #1 configuration files.

Swap PFD1 and PFD2 to confirm if the problem is in the
original PFD1.
o Replace original PFD1 if box turns to a green
checkmark (√) after swapping displays.
 Check the PFD1/GDC 74 #1 interconnect wiring for faults.
Replace GDC 74 #1 if problem remains.
PFD1/GDC 74 #1 data path functionality is unknown. Reload
PFD1 configuration file.
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PFD 2 RS-232
Channel
LRU
Indicator
Status
PFD2/GMC 710 data path is functioning correctly.
PFD2/GMC 710 data path is not functioning correctly.
CHNL 2
GMC 710

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 to a green
checkmark (√) after swapping displays.

Check the PFD2/GMC 710 interconnect wiring for faults.
Replace GMC 710 if problem remains.
PFD2/GMC 710 data path functionality is unknown. Reload PFD2
configuration file.
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PFD 2 ARINC 429
Channel
LRU
Indicator
Status
PFD2/GRS2 data path is functioning correctly.
PFD2/GRS2 data path is not functioning correctly.
IN 1

Verify GRS2 status is “OK” using the System Status page on
the MFD. If it is not, correct condition before proceeding,
reference GRS troubleshooting sections.

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 to a green
checkmark (√) 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/GRS2 interconnect wiring for faults.
GRS #2
PFD2/GRS2 data path functionality is unknown. Reload PFD2
configuration file.
PFD2/GDC 74 #2 data path is functioning correctly.
PFD2/GDC 74 #2 data path is not functioning correctly.
IN 2
GDC 74 #2

Verify GDC 74 #2 status is “OK” using the System Status
page on the MFD. If it is not, correct condition before
proceeding, reference GDC troubleshooting sections.

Load PFD2 and GDC 74 #2 configuration files.

Swap PFD2 and PFD1 to confirm if the problem is in the
original PFD2.
o Replace original PFD2 if box turns to a green
checkmark (√) after swapping displays.
 Check the PFD2/GDC 74 #2 interconnect wiring for faults.
Replace GDC 74 #2 if problem remains.
PFD2/GDC 74 #2 data path functionality is unknown. Reload
PFD2 configuration file.
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MFD1 RS-232
Channel
LRU
Indicator
Status
MFD1/GCU 475 data path is functioning correctly.
MFD1/GCU 475 data path is not functioning correctly.
CHNL 1

Verify GCU 475 is powered on.
o If GCU 475 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 475.

Load MFD1 and GCU 475 configuration files.

Check the MFD1/GCU 475 interconnect wiring for faults.
GCU 475
 Replace GCU 475.
Replace MFD if problem remains.
MFD1/GCU data path functionality is unknown. Reload MFD1
configuration file.
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5.2.1.2
GIA RS-232 / ARINC 429 CONFIG Page
GIA1 RS-232
Channel
LRU
Indicator
Status
GIA1/GDC 74 #1 data path is functioning correctly.
GIA1/GDC 74 #1 data path is not functioning correctly.
CHNL 1
GDC 74 #1

Load GIA1 and GDC 74 #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 to a green
checkmark (√) after swapping units.
 Check the GIA1/GDC 74 #1 interconnect wiring for faults.
Replace GDC 74 #1 if problem remains.
GIA1/GDC 74 #1 data path functionality is unknown. Reload
GIA1 configuration files.
CHNL 2
GRS #2
(output only)
GIA1/GRS2 output data path is not monitored. A black box N/A
is normal.
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Channel
LRU
Indicator
Status
GIA1/GTX 33 #1 data path is functioning correctly.
GIA1/GTX 33 #1 data path is not functioning correctly.
CHNL 5

Load GIA1 and GTX 33 #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 to a green
checkmark (√) after swapping units.
GTX 33D #1
w/TIS
 Check the GIA1/GTX 33 #1 interconnect wiring for faults.
Replace GTX 33 #1 if problem remains.
GIA1/GTX 33D #1 data path functionality is unknown. Reload
GIA1 configuration files.
GIA1/GRS1 data path is functioning correctly.
GIA1/GRS1 data path is not functioning correctly.
CHNL 6
GRS #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 Replace original GIA1 if box turns to a green
checkmark (√) 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 to a green
checkmark (√) after swapping units.
Check the GIA1/GRS1 interconnect wiring for faults.
GIA1/GRS1 data path functionality is unknown. Reload GIA1
configuration files.
GIA1/GMA 1347D #1 data path is functioning correctly.
GIA1/GMA 1347D #1 data path is not functioning correctly.
CHNL 7
GMA
1347D #1

Load GIA1 and GMA 1347 #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 to a
green checkmark (√) 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 to a green
checkmark (√) 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.
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GIA1 ARINC 429
Channel
LRU
Indicator
Status
GIA1/GRS2 data path is functioning correctly.
GIA1/ GRS2 data path is not functioning correctly.

Load 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 Replace original GIA1 if box turns to a green
checkmark (√) after swapping units.

Swap GRS1 and GRS2 (no reconfiguration required) to
confirm if the problem is in the original GRS2.
o Replace original GRS2 if box turns to a green
checkmark (√) after swapping units.

Check the GIA1/ GRS2 interconnect wiring for faults.
IN 2
(applies only
with SW
Image
0636.03 and
subs)
GRS #2
GIA1/ GRS2 data path functionality is unknown. Reload GIA1
configuration files.
GIA1/GDC 74 #1 data path is functioning correctly.
GIA1/GDC 74 #1 data path is not functioning correctly.
IN 5
GDC 74 #1

Load GIA1 and GDC 74 #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 to a green
checkmark (√) after swapping units.
 Check the GIA1/GDC 74 #1 interconnect wiring for faults.
Replace GDC 74 #1 if problem remains.
GIA1/GDC 74 #1 data path functionality is unknown. Reload
GIA1 configuration files.
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GIA1/GRS1 data path is functioning correctly.
GIA1/GRS1 data path is not functioning correctly.
IN 6
GRS #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 Replace original GIA1 if box turns to a green
checkmark (√) after swapping units.

Swap GRS1 and GRS2 (no reconfiguration required, ref.
GRS Configuration and Testing sections) to confirm if the
problem is in the original GRS1.
o Replace original GRS1 if box turns to a green
checkmark (√) after swapping units.
Check the GIA1/GRS1 interconnect wiring for faults.
GIA1/GRS1 data path functionality is unknown. Reload GIA1
configuration files.
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GIA2 RS-232
Channel
LRU
Indicator
Status
GIA2/GDC 74 #2 data path is functioning correctly.
GIA2/GDC 74 #2 data path is not functioning correctly.
CHNL 1

Load GIA2 and GDC 74 #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 to a green
checkmark (√) after swapping units.
GDC 74B #2

Check the GIA1/GDC 74 #2 interconnect wiring for
faults.
Replace GDC 74 #2 if problem remains.
GIA2/GDC 74B #2 data path functionality is unknown.
Reload GIA2 configuration files.
CHNL 2
GRS #1 (output only)
GIA2/GRS1 output data path is not monitored. A black
N/A box is normal.
GIA2/GTX 33 #2 data path is functioning correctly.
GIA2/GTX 33 #2 data path is not functioning correctly.
CHNL 5

Load GIA2 and GTX 33 #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 to a green
checkmark (√) after swapping units.
GTX #2 w/TIS

Check the GIA2/GTX 33/33D #2 interconnect wiring
for faults.
Replace GTX 33/33D #2 if problem remains.
GIA2/GTX 33 #2 data path functionality is unknown.
Reload GIA2 configuration files.
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Channel
LRU
Indicator
Status
GIA2/GRS2 data path is functioning correctly.
GIA2/GRS2 data path is not functioning correctly.
CHNL 6
GRS #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 GIA1.
o Replace original GIA2 if box turns to a green
checkmark (√) 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 to a green
checkmark (√) after swapping units.
Check the GIA2/GRS2 interconnect wiring for faults.
GIA2/GRS2 data path functionality is unknown. Reload GIA2
configuration files.
GIA2/GMA 1347D #2 data path is functioning correctly.
GIA2/GMA 1347D #2 data path is not functioning correctly.
CHNL 7
GMA
1347D #2

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 to a
green checkmark (√) 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 to a green
checkmark (√) after swapping units.
Check the GIA1/GMA 1347 #2 interconnect wiring for faults.
GIA1/GMA 1347D #2 data path functionality is unknown. Reload
GIA2 configuration files.
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GIA2 ARINC 429
Channel
LRU
Indicator
Status
GIA2/GRS1 data path is functioning correctly.
GIA2/ GRS1 data path is not functioning correctly.
IN 2
(applies only
with SW
Image
0636.03 and
subs)
GRS #1

Load GIA2 configuration file.

Swap GIA1 and GIA2, 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 to a green
checkmark (√) 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 to a green
checkmark (√) after swapping units.

Check the GIA2/ GRS1 interconnect wiring for faults.
GIA2/ GRS1 data path functionality is unknown. Reload GIA2
configuration files.
GIA2/GDC 74 #2 data path is functioning correctly.
GIA2/GDC 74 #2 data path is not functioning correctly.
IN 5
GDC 74 #2

Load GIA2 and GDC 74 #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.
o Replace original GIA2 if box turns to a green
checkmark (√) after swapping units.
 Check the GIA2/GDC 74 #2 interconnect wiring for faults.
Replace GDC 74 #2 if problem remains.
GIA2/GDC 74 #2 data path functionality is unknown. Reload
GIA2 configuration files.
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Channel
LRU
Indicator
Status
GIA2/GRS2 data path is functioning correctly.
GIA2/GRS2 data path is not functioning correctly.
IN 6
GRS #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 Replace original GIA2 if box turns to a green
checkmark (√) 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 to a green
checkmark (√) after swapping units.
Check the GIA2/GRS2 interconnect wiring for faults.
GIA2/GRS data path functionality is unknown.
configuration files.
Reload GIA2
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5.2.1.3
GIA CAN / RS-485 CONFIGURATION Page
GIA1 RS-485
Channel
LRU
Indicator
Status
GIA1/GEA1 data path is functioning correctly.
GIA1/GEA1 data path is not functioning correctly.
CHNL 1

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 to a green checkmark
(√) after swapping units.
GEA1

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 to a green checkmark
(√) after swapping units.
Check the GIA1/GEA1 interconnect wiring for faults.
GIA1/GEA1 data path functionality is unknown.
configuration files.
Reload GIA1
GIA1/GEA2 data path is functioning correctly.
GIA1/GEA2 data path is not functioning correctly.
CHNL 2

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 to a green checkmark
(√) after swapping units.
GEA2

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 to a green checkmark
(√) after swapping units.
Check the GIA1/GEA2 interconnect wiring for faults.
GIA1/GEA2 data path functionality is unknown.
configuration files.
Reload GIA1
GIA1/GFC 700 data path is functioning correctly.
GIA1/GFC 700 data path is not functioning correctly.

CHNL 4
GFC 700
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.
GIA1/GFC 700 data path functionality is unknown.
configuration files.
Reload GIA1
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GIA2 RS-485
Channel
LRU
Indicator
Status
GIA2/GEA1 data path is functioning correctly.
CHNL 1
GEA1
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 to a green
checkmark (√) 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 to a green
checkmark (√) after swapping units.
Check the GIA2/GEA1 interconnect wiring for faults.
GIA2/GEA1 data path functionality is unknown. Reload GIA2
configuration files.
GIA2/GEA2 data path is functioning correctly.
CHNL 2
GEA2
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 to a green
checkmark (√) 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 to a green
checkmark (√) after swapping units.
Check the GIA2/GEA2 interconnect wiring for faults.
GIA2GEA2 data path functionality is unknown. Reload GIA2
configuration files.
GIA2/GFC 700 data path is functioning correctly.
CHNL 4
GFC 700
GIA2/GFC 700 data path is not functioning correctly.
 Load GIA2 configuration files, GIA Gains file and GSA
software and gains file (if LRU and Card versions are
different).
Reference GFC section for further troubleshooting.
GIA2/GFC 700 data path functionality is unknown. Reload GIA2
configuration files.
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5.2.2
System Failure Troubleshooting
The following table provides basic troubleshooting guidance for LRU failures. Refer to G1000/GFC 700
Wiring Diagram, listed in Table 1-2, as needed to verify interconnects.
Associated
LRU(s)
Invalid Data Field
Solution
Low Speed Awareness Band
permanently displayed
NOTE
Reference Table 3-1 for interpretation of data
indicator symbols

With aircraft weight on wheels and the G1000 in
Configuration Mode, check that the RH GEAR ON
GROUND Discrete In indication on GIA I/O
CONFIGURATION page is VALID or TRUE.

If indication is VALID or TRUE, switch GIA1 and GIA2,
to verify location of problem:
 If problem is resolved, replace defective unit.
 If indication is INVALID or FALSE, check for wiring
faults between the GIAs and aircraft squat switch
system.
GDU
Low Speed Awareness Band
permanently inhibited
NOTE
Reference Table 3-1 for interpretation of data
indicator symbols

With aircraft weight off wheels and the G1000 in
Configuration Mode, check that the RH GEAR ON
GROUND Discrete In indication on GIA I/O
CONFIGURATION page is INVALID or FALSE.

If indication is INVALID or FALSE, switch GIA1 and
GIA2, to verify location of problem:
 If problem is resolved, replace unit.
 If indication is VALID or TRUE, 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
NAV1 & COM1
GIA1
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Invalid Data Field
Associate
d 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 page 4.
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 33





TAS FAIL
AIRSPEED FAIL
ALTITUDE FAIL
VERT SPEED FAIL


GDC 74B


Check GTX 33 configuration settings for GIA1 and GIA2.
Check GTX 33/GIA1 interconnect.
Check GTX 33/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 33.
 If problem persists, replace GIA.
Inspect GDC 74B pitot/static plumbing integrity.
Inspect pitot/static ports and associated equipment for
faults.
For TAS failure, also check GTP 59 probe.
Check GDC 74B configuration settings for the PFDs, MFD,
GIA1, and GIA2.
1. If PFDs, MFD, and GIA configuration settings are
correct, replace the GDC configuration module.



OAT
GTP 59


If problem persists, replace the GDC 74B.
Check OAT probe wiring and connectors for faults.
Check GDC config module wiring for damage, replace if
any is found.
Replace GDC config module
Replace GDC 74B with a known good unit:
 If problem persists, replace the GTP 59.
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Invalid Data Field
Associated
LRU(s)
Solution




ATTITUDE FAIL

GRS AHRS




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 GRS power to restart initialization.
Ensure GRS connecter is secure and proper wire
harness strain relief is provided.
Ensure the GRS is fastened down tightly in its
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 GRS to go offline.
Load configuration files to the PFD, MFD, GIA1, and
GIA2.
Calibrate the GRS (Pitch/Roll Offset and
Magnetometer Calibration).
Replace the GRS.
 If problem persists replace GRS configuration
module.
 Contact Garmin Aviation Product Support if
condition continues after replacing the GRS and
config module for additional assistance.
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Invalid Data Field
Associated
LRU(s)
Solution



GRS AHRS
HDG FAIL
&

GMU 44




Ensure metal objects (tool boxes, power carts, etc.)
are not interfering with the magnetometer and aircraft
is not in hangar, near other buildings, parked over
metal drainage culverts or on hard surfaces that may
contain steel reinforcements
Ensure that a cell phone or a device using cell phone
technology is not turned on (even in a monitoring
state) in the cabin.
Cycle power 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 GRS and GMU 44 connectors are secure.
Check the wiring and any inline connectors between
the GRS and GMU for faults.
Recalibrate the GMU 44,
Load configuration files to the PFD1, PFD2, GIA1, and
GIA2
 If problem persists replace the GMU 44.
 If problem persists, replace the GRS.
GRS AHRS
&
GMU 44

If this message persists longer than five minutes,
perform AHRS calibration procedures as described in
Section 7.7.2.
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Associated
LRU(s)
Invalid Data Field
Solution

Engine/Airframe Sensors (All
Invalid)


GEA 71
&
GIA 63W



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 right-most 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 valid (green
checkmark (√)). If they are invalid (red X), 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.
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5.2.3
Engine/Airframe Instrument Failures
The following table provides guidance for troubleshooting individual engine/airframe sensor failures. Be
sure to also follow previous guidance given for the GEA 71. The technician should troubleshoot to isolate
the fault by checking sensor-to-GEA wiring, replacing the suspect sensor, and finally by replacing the
GEA 71. Replace one part at a time. Refer to Sections 7.4.2 and 7.4.3 to check for correct operation of
the sensors and GEA 71 after any part has been replaced. Refer to G1000/GFC 700 Wiring Diagram and
King Air Model 90 Series Maintenance Manual (listed in Table 1-2) as needed.
Invalid Field
5.2.4
Sensor
Possible Solutions (for applicable engine/system)
ITT



Check thermocouple cable.
Replace thermocouple cable.
Replace GEA 71.
Torque




Check torque transmitter interface wiring to GEA.
Check power input to torque transmitter.
Replace torque transmitter.
Replace GEA 71.
Prop RPM






Check prop tachometer - Signal Conditioner wiring.
Check Signal Conditioner interface wiring to GEA.
Check power input to Signal Conditioner.
Replace prop tachometer sensor.
Replace Signal Conditioner. Refer to Section 6.19.
Replace GEA 71.
Turbine RPM






Check engine speed tachometer - Signal Conditioner wiring.
Check Signal Conditioner interface wiring to GEA .
Check power input to Signal Conditioner.
Replace engine speed tachometer sensor.
Replace Signal Conditioner. Refer to Section 6.19.
Replace GEA 71.
Fuel Flow






Check fuel flow transmitter – Signal Conditioner wiring.
Check Signal Conditioner - GEA wiring.
Check power input to Signal Conditioner.
Replace fuel flow transmitter.
Replace Signal Conditioner. Refer to Section 6.20.
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.
ADF/DME Failure
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A DME or ADF failure is represented by the following red X’s. Refer to G1000/GFC 700 Wiring Diagram
and King Air Model 90 Series Maintenance Manual (listed in Table 1-2) as needed.
Invalid Field
Sensor
Rockwell Collins
ADF
Rockwell Collins
DME
Solutions










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
Model 90 Series Maintenance Manual, listed in Table 1-2.
Ensure that GIA 63 #1 is properly functioning.
Reload the DME option configurations.
Check for proper operation of the DME receiver. Ensure
that the receiver is receiving power.
Check DME – GIA1 interconnect.
For other failures of the DME system, refer to the King Air
Model 90 Series Maintenance Manual, listed in Table 1-2.
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5.3
C90 Series Specific Alerts
The following alerts are configured specifically for the C90 Series:
ANNUNCIATION ADVISORY Alerts
Message Advisory
Solution
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 1-2.
Replace cooling fan. Refer to Sections 6.26 and
6.27.
MFD FAN FAIL – MFD cooling fan is
inoperative.
ESP FAIL – ESP is inoperative.
Troubleshoot the GFC 700 AFCS. Refer to Section 5.6.
ESP OFF – ESP selected off.
Check that the MFD AUX-SYSTEM SETUP 2 page
shows “Stability & Protection” status is “ENABLED”.
ESP DEGRADE - ESP IAS mode is
inoperative.
Ensure ADC1 and ADC2 circuit breakers are closed and
units are providing valid airspeed data.

ESP CONFIG – ESP config error. Config
service req’d.
Ensure that the “ESP Support Option” has been
installed per Section 3.4.19.
 Ensure that the “Enhanced AFCS unlock card” has
been installed per Section 3.4.27.
If the ESP option needs to be removed, reload the
baseline configuration for the specific airframe and all
applicable options as described in Section 3.9.
Reloading the baseline configuration disables all
previously enabled options.
NOTE
From this point forward, all message advisory alerts presented are common to all G1000
systems and are not specific to the C90 Series. Messages are grouped according to LRU.
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5.4
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, reconfigure per Section 3.9.6.
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
disabled
Enable TAWS system alerting by pressing
the INHIBIT softkey on the MAP – TAWS
page.
alerting
is

GPS system integrity not high
enough to enable TAWS


Ensure valid GPS position is received
from the AUX – GPS STATUS page.
Check GPS antenna & associated
coaxial cabling.
Troubleshoot GIAs.
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5.5
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
Symptom
Recommended Action
“SYN VIS” softkey does not
appear on PFD softkey tier.
Follow the steps in Section 3.9.11 to reactivate the SVS/Pathways
feature.
1. Verify that P/N 010-00330-43 terrain datacards are installed in the
lower slot of the PFDs and MFD.
2. Verify that the alert messages shown in Table 5-2 are not displayed
on the PFD Alerts Window. If so, follow the solutions described in
Table 5-2.
3D terrain presentation does
not appear on PFD.
3. 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 5.10.4
and 5.14.
4. If a terrain database update has just been performed, allow the
system time to initialize and verify the data. When the databases
have been verified, the current database cycle and version are
reported on the MFD AUX – System Status page.
The following table provides SVS/Pathways specific alert messages which may appear in the Alerts Window
on the PFD (press the ALERTS softkey on the PFD to view the Alerts Window):
Table 5-2, SVS-Related Alert Messages
Failure Message
Cause
Solution
SVS – SVS DISABLED: Out of
available terrain region.
SVS is disabled because the
aircraft exceeded the
boundaries of the loaded
terrain database.
Geographical operation limitations
are defined in the AFMS listed in
Table 1-2.
Ensure that operations are within
this geographic area.
SVS is disabled because a 9
Arc-Second or better database
is not currently loaded.
Ensure the P/N 010-00330-43
Terrain Cards are installed in the
lower slot of each display.
If terrain data has been recently
updated, ensure that the correct 9
Arc-Second databases were used.
SVS – SVS DISABLED:
Terrain DB resolution too low
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5.6
GFC 700 AFCS Troubleshooting
The GFC 700 is a digital Automatic Flight Control System (AFCS) which is integrated into various
components of the G1000. This section touches upon key items to note while troubleshooting the GFC
700.
Should a problem be encountered during the operation of the GFC 700, the pilot and technician should first
evaluate the overall status and condition of the G1000 system at the AUX – System Status page (on MFD).
Any alert messages, annunciations, or other abnormal behaviors should be noted in an effort to pinpoint
the fault. The object is to locate the fault within a LRU or LRUs in efforts to replace the defective equipment.
The GFC 700 AFCS Annunciation field is located above the airspeed tape on the PFD as shown:
Figure 5-5, AFCS Annunciation Field
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5.6.1
General Troubleshooting
The following annunciations may appear in the AFCS Annunciation field:
Table 5-3, AFCS Annunciation Troubleshooting
Annunciation
Condition
Resolution
1. Confirm AFCS Servo circuit breaker IN
2. Ensure that the G1000 system is in proper working order.
Check specifically for proper operation of the:

GIA 63 Integrated Avionics Units

GRS AHRS Units

GDC 74B Air Data Computers

All GSA Servos
3. Check that no red X’s are present on the MFD and PFD
displays.
AFCS System
Failure
4. Check that no related alert messages are present on the
PFD displays (press the ALERTS softkey).
5. Go to the AUX SYSTEM STATUS page on the MFD and
verify that all LRUs have a ‘green’ check (see Section 5).
6. In Configuration mode, review the GFC 700 equipment
status, software, and certification gains.
7. Reload software, configuration, and certification gains to
the GIAs and GSA servos.
8. Check the GFC Status page for additional GFC 700
system information.
9. Review the fault and assert logs for the GIAs and servos
(see Section 5.6.4)
10. Isolate the fault to an LRU. Replace this LRU and
confirm the resolution of the annunciation.
Pitch Axis Failure
Pitch Trim Axis
Failure
Yaw Axis Failure
Roll Axis Failure
AHRS Monitor
Failure
1. Check the AUX – SYSTEM STATUS page to see if the
servo is online (green check).
2. Check that the affected servo is receiving power.
3. Check the servo wiring and connector.
4. For pitch trim, check pitch trim switch operation to verify
switch contacts are not stuck.
5. 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.
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Annunciation
Condition
Elevator Mistrim
Down
Resolution
1. 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.
2. Check the servo wiring and connectors. Ensure the
servo is receiving power.
3. Check the aircraft control adjustments.
Elevator Mistrim Up
Aileron Mistrim
Right
Aileron Mistrim Left
Rudder Mistrim
Right
Rudder Mistrim Left
4. If mistrim condition still exists, remove and replace the
affected servo.
1. Check for possible fuel imbalance.
2. Check aileron control adjustments.
3. If mistrim condition still exists remove and replace the roll
servo.
1. Check rudder control adjustments.
2. If mistrim condition still exists remove and replace the
yaw servo.
1. Allow the system to complete pre-flight tests.
Pre-Flight Test
Fails
2. 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 5.6.5 for additional PFT
diagnostics.
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Table 5-4, AFCS General Troubleshooting
Condition
Resolution
1. Check each servo mount slip clutch per Section 4.9. Verify
the clutches are not excessively loose and are within
torque limits.
Poor AP Performance
(Limited AP Authority)
2. Check aircraft controls for proper adjustment per the King
Air Model 90 Series Maintenance Manual.
3. Check aircraft control cables for proper tension per the
King Air Model 90 Series Maintenance Manual.
1. For intermittent nuisance disconnects with no AFCS of PFT
alert, check A/P disconnect switch and wiring for
intermittent faults.
2. If an AFCS or PFT alert is displayed at the time of the
disconnect, troubleshoot per Section 5.5.
AP DISC Problems
3. Check the GIA AFCS Fault Logs according to Section
5.6.4. 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.
4. Contact Garmin Product Support for assistance.
1. Check pitch trim servo status.
Loss of Manual Electric Trim
2. Check MET switch discrete inputs to both GIAs by going to
the GIA I/O Configuration page and selecting DISCRETE
IN inputs.
1. Check flap-in-motion discrete inputs to both GIAs for proper
operation by going to the GIA I/O Configuration page and
selected DISCRETE IN inputs. See Section 4.8.
Autotrim Inoperative
2. If DATA indicator fails to illuminate or illuminates
incorrectly, troubleshoot flap motor & discrete input wiring
(refer to G1000/GFC 700 Wiring Diagram, listed in Table
1-2).
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5.6.2
GFC Configuration Alerts (SW Version 0636.03 and Subs)
Failure Message
MANIFEST – GFC software
mismatch. Communication
Halted.
5.6.3
Cause
Solution
The system has detected an
incorrect software version
loaded in the GSA 8X servos,
or the system has not been
able to detect a serial number
from the GSA 8X servo(s).
1. Load the correct software. See
Section 3.4 for the Software
Loading procedure.
NOTE
The software version loaded to
the servo is determined by the
serial number of the GSA 8X
unit. When the serial number is
not reported by either the
monitor or motor-control circuit
board, this failure message will
be present.
2.
If a GSA 8X servo is not showing
on the SYSTEM UPLOAD page
after loading completes, check
the monitor board entry (ex: GSA
ROLL MON, GSA PTCH TRM M)
and motor-control board entry
(ex: GSA ROLL CTL, GSA PTCH
TRM C) on the SYSTEM
STATUS page. If the unit is not
reporting serial number for either
or both boards, replace the servo.
GFC Status Page
The GFC Status page is presented in configuration mode and gives status information regarding the
autopilot servos and AP disconnect status.
Figure 5-6, GFC Status Page
NOTE
Reference Table 3-1 for interpretation of data indicator symbols
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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 valid data indicator shows the AP DISC switch is closed and the
GFC 700 is actively receiving 28. volts. An invalid indicator box 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. An invalid data indicator box indicates a corrupt or missing load cell
calibration; return the servo to Garmin.
DRIVE SERVO
Allows the technician to enter a desired RPM at which to manually drive the selected servo. Direction of
rotation 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 valid data indicator box indicates the servo clutch is engaged.
SLIP CLUTCH TEST RESULTS
This window is used during the automatic slip clutch torque measurement check.
5.6.4
GIA Fault Log Descriptions
The section was created to help determine why the GFC 700 has failed the Pre-Flight Test indicated by the
red PFT annunciation
, 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.
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NOTE
Thoroughly understanding the operation of the G1000 system in Configuration mode is
recommended before starting this procedure. The GFC Status page may be used to check
the status of the servos and engage them to aid in troubleshooting.
To access the GIA and GSA Maintenance Logs, perform the following steps –
1. Start the G1000 in Configuration mode.
2. Use the FMS knob on PFD1 to go to the Diagnostics Terminal page in the System group. This
page allows the technician to view maintenance logs associated with the GFC 700.
3. Choose ‘GIA 1’ or ‘GIA 2’ in the LRU window.
4. 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.
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.
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
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.
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 AHRS for the cause of the failure.

Stuck switch invalidated parameter: <AXIS>
An 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.
5.6.5
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.
PFT Step 3: System initialization, verify selected side
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This step is checking to make sure the PFD1 is online and sending the selected AFCS side data over
HSDB to GIA1.
If this step fails, then make sure the PFD is powered up and there is an Ethernet connection from the
PFD to the GIA.
PFT Step 4: System initialization, verify AHRS monitor
This step is checking to make sure the AHRS monitor is valid and not reporting an AHRS failure. NOTE:
AHRS monitor will be assumed valid if on the ground.
If this step fails, then make sure the AHRS and ADC is powered up and sending valid attitude data to
the G1000.
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.
PFT Step 10: Updating servo RTC
This step is setting the system time in the servos to the same time as the GIA system time.
This step should never fail.
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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 powered and communicating by checking for green
boxes on the GFC configuration page.
PFT Step 14: Verify cross GIA PFT is completed
This step is checking to make sure the other GIA is also on step 14 of its PFT.
If this step fails, try cycling power on GIA1, GIA2, and all servos. If PFT still fails at step 14 then you
will need to go check the PFT status of the other GIA and see what step it is failing. NOTE: The PFT
status is communicated between GIA1 and GIA2 using HSDB. As a result, both the PFD and MFD
must be powered for this state to pass.
PFT Step 15: PFT completed
The PFT has successfully completed.
PFT Step 16: PFT failed
The PFT has failed.
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5.6.5.1
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.
Monitor Processor
The monitor processor contains the logs that are found in these processors 2 – Pitch Servo
4 – Roll Servo
6 - Yaw
8 – Pitch Trim Servo
There are two main groupings of faults that can occur in the monitor processor:
The first grouping of faults can occur during the GSA unit pre-flight test (PFT). If there is a fault during
PFT the unit will not be able to transition to normal mode and the only way to clear this state would be
to cycle unit power.
The second grouping of faults can occur during normal mode. These faults generally cause a
disconnect of power to the GSA and report to the GIA that a fault has occurred.
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.
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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
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
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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 to the GIA that a fault has occurred.
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
"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
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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
5.6.5.2
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 PFD1/2 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. Verify that the softkey text grays out. This
indicates the recording function is active and all text that is displayed in the OUTPUT window will
be saved to the card.
5. Enable the curser 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”.
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.
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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.
5.7
5.7.1
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 AHRS and GDC 74B each have
four separate ARINC 429 data lines that are all capable of sending data to the displays. The GEA 71, GTX
33, and GMA 1347D each have two redundant serial communication paths for the same purpose. See
Figure 2-4 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 1-2.
NOTE
Refer to Section 9.1 for procedures on checking the status of each configured G1000
backup data path.
5.7.2
Data Path Failures
Failure Message
Cause
Solutions
Determine which data path has failed:
See Section 5.2.1.
FAILED PATH – A data path has
failed.
A communications data path
status is not being received by the
G1000.
Check wiring continuity for the failed
path.
Swap or replace the affected LRU.
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5.8
5.8.1
GDU 104X Troubleshooting
GDU 104X Symptoms
Symptom
Recommended Action


Display is blank

Display resets



Display flickers





SD card is stuck in GDU





A button/knob/joystick
does not appear to
function
Ensure that a cell phone or a device using cell phone technology is not
turned on (even in a monitoring state) in the cabin.
Cycle power.
 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.
Ensure GDU is receiving power. If a circuit breaker is tripped, determine
source of short before closing the 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.
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 Garmin for repair.
Go to the GDU TEST page in configuration mode and verify button, knob,
or joystick operates correctly by observing a change in color from red to
green in the button/knob/joystick icon when the button/knob/joystick is
pressed. If a button is stuck, the button icon will be green without pressing
the button as soon as you turn to the GDU TEST page.
 If problem is verified, replace GDU.
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Symptom
Recommended Action

Terrain/Obstacle/SafeTax
i does not display


Display will
dimmer bus
not
track
Keyboard will not track
dimmer bus
5.8.2
5.8.2.1
Ensure supplemental data cards are inserted correctly in the lower slots
of all three GDU’s.
Allow the system to verify the data on the cards for approximately five
minutes after power-up.
If a database does not activate, reload the problem database onto the SD
Card or replace the card.


Reload GDU configuration files.
If display is a PFD, swap PFD1 and PFD2 to see if problem remains with
display.
 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.
GDU 104X Alerts
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 7.1 for GDU 1040
Software Loading procedure.
The system has detected an
incorrect software version
loaded in MFD.
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Failure Message
Cause
Solution

CNFG MODULE – PFD 1
configuration module is
inoperative.
The PFD master configuration
module has failed.
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
cards 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.
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
PFD 2 CONFIG – PFD 2
configuration error. Config
service req’d.
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be
replaced if the master configuration
module is changed. The G1000
System ID number will change to a
new number when installing a new
master config module. The old
Terrain and other cards will no
longer work as they will remain
locked to the old System ID
number.
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5.8.2.2
Database Alerts
Failure Message
Cause
MFD1 DB ERR – MFD1
aviation database error exists.
PFD 1 DB ERR – PFD 1
aviation database error exists.
PFD 2 DB ERR – PFD 2
aviation database error exists.
MFD1 DB ERR – MFD1 terrain
database error exists.
Solution

The MFD or specified PFD has
encountered an error in the
Jeppesen aviation database.
The MFD has encountered an
error in the terrain database.



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.

The specified PFD has
encountered an error in the
terrain database.
The MFD has encountered an
error in the obstacle database.


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.

The specified PFD has
encountered an error in the
obstacle database.
The MFD has encountered an
error in the airport terrain
database.


PFD 1 DB ERR – PFD 1
airport terrain database error
exists.
PFD 2 DB ERR – PFD 2
airport terrain database error
exists.
DB MISMATCH – Aviation
database version mismatch.
Xtalk is off.

The specified PFD has
encountered an error in the
airport terrain database.
The system has found the
Jeppesen aviation database
cycles in the PFDs and/or
MFD do not match.

Reload aviation database into
the display.
Contact Garmin Product
Support for further assistance if
needed.
Confirm supplemental data card
is inserted fully.
Reload the database or replace
the supplemental datacard.
Contact Garmin Product
Support for further assistance if
needed.
Confirm supplemental data card
is inserted fully.
Reload the database or replace
the supplemental datacard.
Contact Garmin Product
Support for further assistance if
needed.
Confirm supplemental data card
is inserted fully.
Reload the database or replace
the supplemental datacard.
Contact Garmin Product
Support for further assistance if
needed.
Load current aviation database
versions to all displays.
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Revision L
DB MISMATCH – Aviation
database type mismatch.
Xtalk is off.
The system has found the
Jeppesen aviation database
types in the PFDs and/or MFD
do not match (i.e., different
regions: Americas,
International, Atlantic, etc.)
DB MISMATCH – Airport
Terrain database version
mismatch. Xtalk is off.
The PFDs and/or MFD have
different Airport Terrain
database versions installed.
DB MISMATCH – Terrain
database version mismatch.
The PFDs and/or MFD have
different terrain database
versions installed.
DB MISMATCH – Obstacle
database version mismatch.
The PFDs and/or MFD have
different obstacle database
versions installed.
DB MISMATCH – Terrain
database type mismatch.
The PFDs and/or MFD have
different terrain database
types installed (i.e., different
regions: Americas,
International, Atlantic, etc.).
5.8.2.3

Load same type aviation
database to all displays.

Confirm supplemental data card
is inserted fully.
Reload the database or replace
the supplemental datacard.

Cooling Alerts
Failure Message
Cause
Solution

MFD1 COOLING – has poor
cooling. Reducing power
usage.
MFD1 has exceeded its
operating temperature range.

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 Product Support for
assistance.

PFD 1 COOLING – has poor
cooling. Reducing power
usage.
PFD 1 has exceeded its
operating temperature range.
Check cooling fan and wiring
for proper operation (if
applicable).
 Replace cooling fan if
unable to determine if
operating correctly.
 If problem persists, replace
the PFD1.
 If problem continues contact
Garmin Product Support for
assistance.
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Failure Message
Cause
Solution

PFD 2 COOLING – has poor
cooling. Reducing power
usage.
5.8.2.4
PFD 2 has exceeded its
operating temperature range.
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 Product Support for
assistance.
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.
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5.8.2.5
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.
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
Cause
Solution


MFD1 SERVICE – needs
service. Return unit for repair.
The G1000 has determined
MFD1 needs service.



PFD 1 SERVICE – needs
service. Return unit for repair.
The G1000 has determined the
specified PFD needs service.
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 – MDF1 has
low voltage. Reducing power
usage.
Ensure the MFD connector is
fully seated and locked.
If the unit was started in a very
dark environment the photocells
may not have enough light to
initially raise the CCFT level. Go
to the GDU STATUS page in
configuration mode, ensure
CCFT CRNT 1 & 2 levels are
above 50.
 If the CCFT levels are not
above 50, apply light to the
photocell and observe if the
CCFT level rises.
 If the CCFT level rises,
disregard the message.
 If the CCFT level does not
rise, replace the MFD
Replace the MFD
Ensure the PFD connector is
fully seated and locked.
If the unit was started in a very
dark environment the photocells
may not have enough light to
initially raise the CCFT level. Go
to the GDU STATUS page in
configuration mode, ensure
CCFT CRNT 1 & 2 levels are
above 50.
 If the CCFT levels are not
above 50, apply light to the
photocell and observe if the
CCFT level rises.
 If the CCFT level rises,
disregard the message.
 If the CCFT level does not
rise, replace the PFD
Replace the PFD.
The specified PFD supply
voltage is low.


Check input voltage to PFD.
If input voltage is ok, replace
PFD..
The MFD supply voltage is
low.


Check input voltage to MFD.
If input voltage is ok, replace
MFD.
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5.9
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 power cycled (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.
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5.9.1
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 1347
needs service.


GMA1 FAIL – GMA1 in
inoperative.
GMA2 FAIL – GMA2 in
inoperative.
MANIFEST – GMA1 software
mismatch. Communication
Halted.
MANIFEST – GMA2 software
mismatch. Communication
Halted.
The system has detected a
failure in the specified
GMA 1347.
The system has detected an

incorrect software version
loaded in the specified
GMA 1347.
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.
Replace GMA1.
Load the correct unit software.
See Section 7.2 for the Software
Loading procedure.

GMA1 CONFIG – GMA1
configuration error. Config
service req’d.
GMA2 CONFIG – GMA2
configuration error. Config
service req’d.
Replace GMA .
The system has detected a
GMA 1347D configuration
mismatch for the specified
unit.
Load GMA configuration files,
see Section 7.2.
 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 cards will no
longer work as they will remain
locked to the old System ID
number.
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5.10 GIA 63 Troubleshooting
5.10.1 COM Symptoms
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
5.10.2 NAV Symptoms
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.
5.10.3 Glideslope Receiver Symptoms
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.
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5.10.4 GPS Symptoms
Symptom
Recommended Action




Will Not Acquire Satellites

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, clear the GPS almanac by performing
the following steps –
o Using the PFD in config mode, go to the GIA RS-232/ARNIC
429 Config Page.
o At the top of the screen, select the GIA that cannot acquire
satellites (GIA1 or GIA2) and press the ENT key.
o Press the “CLR NV” softkey at the bottom of the screen.
o Select “OK” in the “Clear GIA nonvolatile memory?” pop-up
window.
o Next reload GIA Audio and Config files from a loader card,
see Section 7.3 and on for instructions. Be sure to reload
the config files for any optional equipment installed on the
aircraft that require the GIA config to be updated.
Cycle power on the system and allow it to restart in normal mode.
Place the aircraft outside and allow 15-30 minutes for the GPS to
acquire a position and download a new almanac.
 If clearing nonvolatile memory is unsuccessful and the GPS still
cannot acquire a position, replace the GIA.
 If problem does not follow unit, check GPS antenna and
cabling.
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5.10.5 GIA Alert Messages
5.10.5.1 COM Alerts
Failure Message
Cause
Solutions
COM1 SERVICE – COM1
needs service. Return unit for
repair.
The system has determined
COM1 needs service.

Replace GIA1 according to
instructions in Section 6.
COM2 SERVICE – COM2
needs service. Return unit for
repair.
The system has determined
COM2 needs service.

Replace GIA2 according to
instructions in Section 6.

Press the push-to-talk switch(s)
again to cycle its operation.
Check push-to-talk switch(s) and
wiring.
Check GIA1/GMA 1347D #1
interconnect.
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
defective GMA 1347D #1.


COM1 PTT – COM1 push-totalk key is stuck.
The COM1 external push-totalk (PTT) switch is stuck in
the enabled (or “pressed”)
state.




COM2 PTT – COM2 push-totalk key is stuck.
The COM2 external push-totalk (PTT) switch is stuck in
the enabled (or “pressed”)
state.

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
defective GMA 1347D #2.
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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.



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 Product Support for
assistance.
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5.10.5.2 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.
NAV2 SERVICE – NAV2
needs service. Return unit for
repair.
The system has detected a
failure in NAV2 receiver.

Replace GIA2.
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.
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5.10.5.3 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.
G/S2 SERVICE – G/S2 needs
service. Return unit for repair.
The system has detected a
failure in G/S2 receiver.

Replace GIA2.

Switch GIA1 and GIA2 to verify
location of problem:
√ If problem follows the unit,
replace GIA.
√ If problem does not follow
unit, check G/S1 antenna
and cabling.

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.
G/S1 FAIL – G/S1 is
inoperative.
G/S2 FAIL – G/S2 is
inoperative.
The system has detected a
failure in G/S1 receiver.
The system has detected a
failure in G/S2 receiver.
5.10.5.4 GPS Alerts
NOTE
Before troubleshooting, ensure that no cell phones or devices using cell phone technology
are turned on, even in a monitoring state, in the cabin.
Failure Message
Cause
Solution
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.
Load the correct GPS software.
See Section 7.3 for the Software
Loading procedure.
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.

Replace GIA.
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.
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.
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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
website
http://www.gps.gov/support/user/
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.
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5.10.5.5 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.

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.
GIA1 COOLING – GIA1 over
temperature.
GIA1 has exceeded its
operating temperature range.




GIA2 COOLING – GIA2 over
temperature.
GIA2 has exceeded its
operating temperature range.



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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5.10.5.6 GIA Configuration Alerts
Failure Message
Cause
Solution
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.
Load the correct software. See
Section 7.3 for the Software
Loading procedure.

Reload audio configuration files.

Load the configuration files for
that GIA. See Section 7.3 for
GIA 63 Configuration Loading
procedure.
If problem persists, replace
master configuration module,
check config module harness for
faults and replace if necessary.
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.
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.
HW MISMATCH – GIA
hardware mismatch, GIA1
communication halted.
HW MISMATCH – GIA
hardware mismatch, GIA2
communication halted.
GIA1 SERVICE – GIA1 needs
service. Return unit for repair.
GIA2 SERVICE – GIA2 needs
service. Return unit for repair.
NOTE
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.
The G1000 has detected a
non-WAAS GIA 63.

Replace GIA with a WAAS unit.
The G1000 has detected a
failure in the specified GIA.

Replace suspect GIA.
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5.11 GEA Troubleshooting
5.11.1 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.

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
GEA1 CONFIG – GEA2
configuration error. Config
service req’d.
The system has detected a
configuration mismatch in the
specified GEA 71.
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.
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5.12 GTX Troubleshooting
5.12.1 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 33.

Reload software. See Section
7.5 for the Software Load
Procedure.

Perform a SET>ACTV
configuration reset on the GTX
Config page and verify the
aircraft registration is present.

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.
XPDR1 CONFIG – XPDR1
configuration error. Config
service req’d.
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.
The system has detected a
configuration mismatch for the
specified GTX 33.
The G1000 has detected a
failure in the specified GTX 33.
The specified GTX 33 is not
responding.
NOTE
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.

Replace GTX 33.

Check wiring between GIA’s
and GTX.
Replace GTX 33.

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XPDR1 ADS-B FAIL – XPDR
1 unable to transmit ADS-B
message.
XPDR 2 ADS-B FAIL – XPDR
2 unable to transmit ADS-B
message.
The specified GTX 33
transponder is not able to
transmit ADS-B data.

Check wiring between GIA’s
and GPS antenna.
 Check wiring between GIA’s
and GTX.
5.13 GDL 69A or GDL 69A SXM Troubleshooting
5.13.1 GDL 69A or GDL 69A SXM Symptoms
Symptom
Recommended Action
No XM 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 SiruisXM 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 69/69A antenna and cabling for faults.
√
Reseat the GDL 69A/69A SXM to verify the coax
connector is fully seated.
√ If unit is not active, go to www.siriusxm.com/refresh and enter
your radio id numbers (there are two) to have a refresh signal
sent to your unit. 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.
√ If there is still problems receiving weather products after
performing the above step, call SiriusXM for further
troubleshooting on the SiriusXM account.
√ Verify there is a good ground connection through the aircraft
between the MFD and the GDL69A/69A SXM 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.
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5.13.2 GDL 69A/69A SXM Alerts
Failure Message
Cause
GDL 69 FAIL – GDL 69 has
failed.
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.

Reload configuration file. See
Section 7.8.1 for the
Configuration Procedure.
If problem persists, replace
master configuration module,
check config module harness for
faults and replace if necessary.

NOTE
GDL69 CONFIG – GDL 69
configuration error. Config
service req’d.
The G1000 has detected a
GDL 69A/69A SXM
configuration mismatch.
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.
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.
See Section 7.8.1 for the
Software Load Procedure.
Page 5-68
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5.14 GRS and GMU Troubleshooting
5.14.1 AHRS Symptoms
Symptom
Recommended Action


AHRS does not complete
initialization






Attitude appears unstable




Ensure that a cell phone or a device using cell phone technology is not
turned on (even in a monitoring state) in the cabin.
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 GRS.
Check GRS configuration module wiring for damage.
Check GRS connector for bent pins.
 If no damage can be found, replace GRS configuration module.
 If problem persists, replace the GRS.
Ensure that a cell phone or a device using cell phone technology is not
turned on (even in a monitoring state) in the cabin.
Ensure the four GRS mounting screws are tight. Finger tight is not
sufficient, a screwdriver must be used to verify.
Ensure mounting rack and airframe shelf are secure and all hardware
and brackets are present (CAUTION - do not loosen the mounting rack
hardware to the airframe shelf or the aircraft will need to be re-leveled
and the PITCH/ROLL OFFSET procedure performed)..
Ensure GRS connector is securely fastened and proper strain relief is
provided.
Remove GRS connector and verify there are no bent pins.
Replace the GRS.
Contact Garmin for further troubleshooting if required.
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5.14.2 GRS 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.

Load correct software version.
See Section 7.7 for the Software
Load Procedure.

Load updated AHRS magnetic
field file. See Section 4.6.

Operate the aircraft only within
the limits as specified in the
G1000 King Air C90 Series
AFMS, listed in Table 1-3.

Check GRS/GDC interconnect
for faults.
Replace the GDC 74:
If problem persists, replace the
GRS.
The AHRS magnetic field
model should be updated for
the specified unit. Appears on
ground only.
No magnetic compass
information available due to
being too far north or south.
The specified GRS is not
receiving airspeed from the
GDC 74B.
AHRS1 GPS – AHRS1 not
receiving backup GPS
information.
The GRS1 is not receiving
backup GPS information from
either GIA 63.
AHRS1 GPS – AHRS1
operating exclusively in noGPS mode.
The GRS1 is operating in the
absence of GPS.
AHRS1 GPS – AHRS1 not
receiving any GPS
information.
The GRS1 is not receiving
GPS data from the GPS
receivers.
AHRS1 GPS – AHRS1 using
backup GPS source.
The GRS1 is using the backup
GPS data path.






AHRS2 GPS – AHRS2 not
receiving backup GPS
information.
The GRS2 is not receiving
backup GPS information from
either GIA 63.
AHRS2 GPS – AHRS2
operating exclusively in noGPS mode.
The GRS2 is operating in the
absence of GPS.
AHRS2 GPS – AHRS2 not
receiving any GPS
information.
The GRS2 is not receiving
GPS data from the GPS
receivers.


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 GRS1.
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
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Failure Message
Cause
AHRS2 GPS – AHRS2 using
backup GPS source.
The GRS2 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.
Solutions
position lock, see GPS
troubleshooting section.
 Troubleshoot GIA1/2–GRS2
wiring for faults (ref. Failed Path
troubleshooting section).
 Replace the GRS2.

Load AHRS magnetic model
field in both GRS units.

If flying near large radio towers
or other sources of possible
electromagnetic interference, the
condition should correct itself as
the aircraft leaves the area.
If problem persists, run magnetic
interference check in Section
5.15.4 to check for magnetic
interference in the aircraft.
MAG VAR WARN – Large
magnetic variance. Verify all
course angles.
Magnetic variance value from
GMU 44 is not accurate.
PIT MISCOMP
Difference in the pitch sensors
is greater than 5 degrees.
Perform Calibration Procedure A1:
GRS Pitch/Roll Offset Calibration
(reference Section 7.7.3).
ROL MISCOMP
Difference in the roll sensors is
greater than 6 degrees.
Perform Calibration Procedure A1:
GRS Pitch/Roll Offset Calibration
(reference Section 7.7.3).

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5.14.3 GMU Alerts
Failure Message
Cause
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 MISCOMP
Solutions
The system has detected an
incorrect software version
loaded in the specified GMU
44.
A fault has occurred in the
specified magnetometer;
heading will be flagged invalid.
Load the correct software version.
See Section 7.7 for the Software
Load Procedure.
Check GMU 44/GRS interconnect for
faults.
 Replace GMU 44.
 If problem persists, replace
GRS.
Difference in the heading
sensors is greater than 6
degrees.
Perform Calibration Procedure E:
Magnetometer Interference Test
(reference Section 5.14.4) and
Procedure B: GRS and GMU 44
Magnetometer Calibration
(reference Section 7.7.5).
5.14.4 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 or mechanical device interferes 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.
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Figure 5-7, Magnetometer Interference Test
1. Initiate the AHRS magnetometer interference test procedure by performing the following steps:
2. 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:
i)
softkey 9
ii)
softkey 10
iii) softkey 11
iv) softkey 12
4. Select MAG INTERFERENCE TEST and press the ENT key.
5. Follow the checklist items displayed on the PFD, and press the ENT key as each one is completed
or confirmed.
NOTE
The 3rd item on the checklist instructs the operator to “prepare a detailed test sequence
with precise start and stop times for exercising all electronic devices”. The list of relevant
electronic devices are given in Table 5-5. Begin test with flaps retracted, flight controls in
a neutral position and all lights selected OFF.
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Table 5-5, Magnetometer Interference Test Sequence (Example)
Elapsed Time
since Start of
Test (min:secs)
0:00
00:10
00:20
00:30
00:40
00:50
01:00
01:10
01:20
01:30
01:40
01:50
02:00
02:10
02:20
02:30
02:40
02:50
03:00
03:10
03:20
03:30
03:40
03:50
04:00
04:10
04:20
04:30
04:40
04:50
05:00
05:10
05:20
Action
Test begins
Elevator full nose up
Elevator full nose down
Rudder full right
Rudder full left
Rudder neutral
Elevator manual trim full nose up
Elevator manual trim full nose down
Rudder manual trim full right
Rudder manual trim full left
Flaps down
Flaps up
Navigation lights on
Navigation lights off
Landing lights on
Landing lights off
Landing + Taxi lights on
Landing + Taxi lights off
Taxi lights on
Taxi lights off
Strobes on
Strobes off
Recognition lights on
Recognition lights off
Beacon on
Beacon off
Tail flood lights on (if installed)
Tail flood lights off (if installed)
Left pitot heat on
Left pitot heat off
Right pitot heat on
Right pitot heat off
End of test
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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Figure 5-8, Magnetometer Interference Test Complete
7. The operator should carry out the actions called for in the prepared test sequence.
NOTE
It is important that all actions are carried out in the order and at the precise elapsed time
as specified in the prepared test sequence.
8. When the operator has completed the actions specified in the test sequence, press the ENTER
button to indicate that the process is complete. When this is done, the TEST COMPLETE field
stops blinking.
9. The PFD informs the operator if the installation has passed or failed the magnetometer interference
test. If the test passes, no further action is required for this test.

If the test fails, the installation should be considered unreliable until the source of magnetic
interference is identified and remedied. When the magnetometer interference test fails,
record the three magnetometer maximum deviation values and their corresponding
timestamps. Reference the appropriate installation manual for the GRS 77 (GPN 19000303-10) and GRS 7800 (GPN 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
Two common reasons for a failed magnetometer interference test are: 1) new equipment
is installed in close proximity to the GMU 44 magnetometer, and 2) 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.
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5.15 GDC 74B Troubleshooting
5.15.1 Air Data Symptoms
Symptom
Recommended Action

than

GDC Config file does not load.

√
Altitude is different
standby altimeter
Perform a pitot/static check per Section 7.6 of this manual. Allow
the GDC to warm up for fifteen minutes before checking accuracy,
per Garmin Service Advisory 0606.
Determine which instrument is outside limits and replace. The
GDC may be field adjusted per Garmin Service Advisory 0720.
Note: Both units may individually be in spec but show a difference
in altitude. Do not return the GDC to Garmin for service if not
outside limits.
Replace GDC config module.
If problem persists, replace GDC config module wire harness.
5.15.2 GDC 74B Alerts
Failure Message
MANIFEST – GDC1 software
mismatch Communication
halted.
MANIFEST – GDC2 software
mismatch Communication
halted.
Cause
Solutions
The system has detected an
incorrect software version
loaded in the specified GDC
74B.

Load correct software version.
See Section 7.6 for the Software
Load Procedure.
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5.16 GWX 68 or GWX 70 Troubleshooting
NOTE
References to GWX in this section can imply either Garmin Weather Radar Model GWX
68 or GWX 70. Differences to a specific GWX model will be identified with the applicable
GWX model number.
5.16.1 GWX 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 the GWX 70 is 10 feet.
Failure Message
Cause
Solutions

Load GWX configuration files,
√
Replace GWX.
√
If problem persists, replace
master
configuration
module,
check
config
module wiring for faults and
replace if necessary.
NOTE
GWX CONFIG – GWX
configuration error.
Configuration service required.
The G1000 has detected a
GWX configuration
mismatch.
GWX FAIL – GWX is
inoperative.
The G1000 has detected a
failure in the GWX.
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.


Check
Ethernet
connection
between the GWX and GDL69A
for faults.
Replace the GWX.
GWX SERVICE – Needs
service. Return unit for repair.
The G1000 has detected a
failure in GWX.

Replace the GWX.
MANIFEST – GWX software
mismatch. Communication
halted.
The system has detected an
incorrect software version
loaded in the GWX.

Load correct software version.
See Section 7.12.1 for the
Software Load Procedure.
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5.17 GMC 710 Troubleshooting
5.17.1 GMC 710 Alerts and Problems
Failure Message
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
GMC CNFG – GMC Config
error. Config service req’d.
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.
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.
a. Check wiring for faults (ref Failed
Path troubleshooting section).
b. Replace the GMC 710.
c.
Load the correct software
version. See Section 7.11.1 for
the Software Load Procedure.
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5.18 GCU 475 Troubleshooting
5.18.1 GCU 475 Alerts and Problems
Failure Message
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
GCU CNFG – GCU Config error.
Config service req’d.
The G1000 has detected a
GCU 475 configuration
mismatch.
GCU FAIL – GCU is inoperative.
The G1000 has detected a
failure in the GCU 475.
MANIFEST – GCU software
mismatch. Communication
halted.
The system has detected an
incorrect software version
loaded in GCU 475.
New
Terrain/Obstacle
cards,
Jeppesen Aviation Database and
other optional features (i.e. TAWS
unlock card) will need to be replaced
if the master configuration module is
changed. The G1000 System ID
number will change to a new number
when installing a new master config
module. The old Terrain and other
cards will no longer work as they will
remain locked to the old System ID
number.
d. Check wiring for faults (ref Failed
Path troubleshooting section).
e. Replace the GCU 475.
f.
Load the correct software
version. See Section 7.10.1 for
the Software Load Procedure.
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5.19 Software/Configuration Troubleshooting
Problem
Solutions
MFD or PFD displays do not power up:
 Ensure that the criteria listed in Section 5.20.1
are fulfilled for the applicable situation.
 Ensure power is present at display backshell
connector.
 Troubleshoot per the “Blank Display” GDU
section..
Software file load fails:
 Ensure that criteria listed in Section 5.20.1 are




Configuration file load fails:
 Ensure that the criteria listed in Section 5.20.1




GIA1 and/or GIA2 to ‘LRU’ data path not working
fulfilled for the applicable situation.
Ensure that LRU is reporting data on System
Status page (LRU is ‘ONLINE’). Check data
path wiring as needed.
Retry software file load or try using a different
card. Ensure that the MFD is not touched
during the loading process.
Ensure that LRU part number is compatible
with software version and Card Loader. Refer
to the General Arrangement Drawing.
Replace LRU.
are fulfilled for the applicable situation.
Ensure that LRU is reporting data on System
Status page (LRU is ‘ONLINE’). Check data
path wiring as needed.
Retry configuration file load or try using a
different card. Ensure that the MFD is not
touched during the loading process.
Ensure that LRU part number is compatible
with Card Loader. Refer to the General
Arrangement Drawing .
Replace LRU.
 Ensure that the criteria listed in Section 5.20.1
are fulfilled for the applicable situation.
 Ensure GIA1 and GIA2 are configured
correctly.
 Check wiring, connectors & pins as needed.
Software File Mismatch Alert appears in lower
right corner of PFD when started in normal mode:
 Ensure that proper software file part number
and version were loaded to LRU. Refer to the
General Arrangement Drawing and to Section
5.20.1.
 Check and ensure that correct Card Loader
was used during load process. Refer to the
General Arrangement Drawing.
 Reload software to LRU.
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5.19.1 System Communication Hierarchy
The following criteria must be satisfied to be able to perform the desired operation:
Desired Operation
Load Software to MFD or PFD Displays
Criteria for Success



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
- GDC 74B
- GEA 71
- GRS 77 (software only)
- GRS 7800
- GMU 44 (software only)
- GTX 33( )






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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5.20 Backshell Connectors
The following figures depict the backshell connectors as viewed with the LRU removed.
COM BOARD CONNECTOR (P601)
COM ANTENNA CONNECTOR
COOLING PORT
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 2930
31 32 33 34 35 36 37 38 39 40 41 42 43 44
MAIN DISCRETE CONNECTOR (P604)
MAIN SERIAL CONNECTOR (P603)
GPS ANTENNA CONNECTOR
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 (P602)
NAV ANTENNA CONNECTOR
Figure 5-9, GIA 63W Backshell Connectors
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P712
P711
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, GEA 71 Backshell 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 5-11, GMA 1347D Backshell 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 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
TOP ANTENNA CONNECTOR
BOTTOM ANTENNA CONNECTOR
Figure 5-12, GTX 33/33D Backshell Connectors
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Figure 5-13, GDU 1040A/1500 Backshell Connector (P10401 or P15001)
Figure 5-14, GRS 77 Backshell Connector (P771)
Figure 5-15, GRS 7800 Backshell Connector (P78001)
Figure 5-16, GDC 74B Backshell Connector (P74B1)
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Figure 5-17, GDL 69A/GDL 69A SXM Backshell Connector (P69A1)
Figure 5-18, GCU 475 Backshell Connector (P4751)
Figure 5-19, GMC 710 Backshell Connector (P7101)
Figure 5-20, GWX 68 Backshell Connector (P681)
Figure 5-21, GWX 70 Backshell Connector (P751)
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Figure 5-22, Signal Conditioner Mating Connector (PVIB1)
5.21 Standby Attitude Indicator Troubleshooting
5.21.1 Standby Attitude Indicator Symptoms
Symptom
Recommended Action

Warning flag pops into view,
indicating that the gyro motor
is not receiving sufficient
power to operate
Perform the Standby Instrument Electrical Power Checks in
Section 8.1.5.
 Remove the unit per Section 6.25 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 See Section 6.25 for
removal instructions. Contact the manufacturer to find a
qualified service facility

Unit fails to perform to
specifications
The unit must be removed and serviced by a qualified service
facility. See Section 6.25 for removal instructions. Contact the
manufacturer to find a qualified service facility.
5.22 Standby Airspeed Indicator Troubleshooting
5.22.1 Standby Airspeed Indicator Symptoms
Symptom
Recommended Action

Airspeed Indicator lighting is
inoperative or malfunctioning
Perform the Standby Instrument Electrical Power Checks in
Section 8.1.5.
 Remove standby airspeed indicator per Section 6.23 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.
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Symptom
Recommended Action

Airspeed displayed is incorrect
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 6.23 for removal instructions.
5.23 Standby Altimeter Troubleshooting
5.23.1 Standby Altimeter Symptoms
Symptom
Recommended Action

Altimeter lighting is inoperative
or malfunctioning
Altimeter Vibrator is
inoperative or malfunctioning
Perform the Standby Instrument Electrical Power Checks in
Section 8.1.5.
 Remove standby altimeter per Section 6.24 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.

Altitude displayed is incorrect
Using a pitot-static ramp tester, check altitude displayed on
standby altimeter against altitude display from ADC2.
√ If the altitudes are the same, inspect the pitot/static ports and
associated equipment for faults.
√ If the altitudes are different, replace the standby altimeter or
contact the manufacturer for further troubleshooting. See
Section 6.24 for removal instructions.
5.24 Standby Battery Troubleshooting
Refer to King Air Series Component Maintenance Manual, listed in Table 1-2, for troubleshooting.
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6
Equipment Removal & Replacement
This section describes how to remove and replace G1000 equipment in the King Air C90 Series associated
with this STC. After removal and replacement, LRUs must be configured and tested as instructed in Section
7.
CAUTION
When removing and/or replacing any G1000 component, always ensure that aircraft power
is off. Unplug any auxiliary power supplies. Before performing maintenance, it is required
that the technician verify the LRU software part number and version number matches the
software configuration listed in the General Arrangement drawing, listed in Table 1-2.
NOTE
After installation or maintenance of electrical components near the GMU 44
magnetometers, perform the Calibration Procedure E: Magnetometer Interference Test
(reference Section 5) and Procedure B: GRS AHRS and GMU 44 Magnetic Calibration
(reference Section 7).
To check an LRU software part number and/or version, follow the procedure defined in Section 3.5.1.
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.
6.1
GDU 1040A/1500
Removal:
1. Remove Garmin database and other SD cards from the display. Retain the cards for installation
in replacement display. Do not leave any cards in the display when returning the unit to Garmin.
2. Using a 3/32” hex tool, rotate all ¼-turn fasteners counter-clockwise until they reach their stops.
3. Carefully remove the display from the panel.
4. While supporting the display, disconnect the connector.
Reinstallation:
1. Visually inspect the connector and pins for signs of damage. Repair any damage. While
supporting the display, connect the connector to the rear of the unit.
2. Rock the GDU connector from top to bottom to verify the connector locking tabs are engaged.
3. Carefully insert the display into the panel cutout, ensuring that all 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 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.
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6.2
GMA 1347D Audio Panel
Removal:
1. Using a 3/32” hex tool, turn the hex nut counter-clockwise until it stops.
2. Carefully remove the GMA 1347D from its rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any
damage.
2. Gently insert the GMA 1347D into the rack until the locking tab engages the rack.
3. Begin to turn the hex nut clockwise. This draws the unit into the rack until seated. Tighten until
snug, do not over-tighten the nut.
4. Configure and test the GMA 1347D according to Section 7.2.
6.3
GIA 63W Integrated Avionics Units
Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Unlock the GIA 63W handle by loosening the Phillips screw on the handle.
3. Pull the handle upward to unlock the GIA 63W. Gently remove the unit from the rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any
damage.
2. Gently insert the GIA 63W into its rack. The handle should engage the dogleg track.
3. Press down BUT DO NOT FORCE the GIA 63W handle to lock the unit into the rack. If strong
resistance is felt, remove unit and check for misaligned rear connector plates and bent
connector pins.
4. Lock the handle to the GIA 63W body using the Philips screw.
5. Configure and test the GIA 63W(s) according to Section 7.3.
6.4
GEA 71 Engine/Airframe Unit
Removal:
1. Gain access by removing the appropriate GDU 1040A display unit (see Section 6.1.)
2. Unlock the GEA 71 handle by unscrewing the Phillips screw.
3. Firmly grasp the GEA 71 handle and pull it up vertically. This unlocks the unit from the rack.
4. Gently remove the GEA 71 from its rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any
damage.
2. Gently insert the GEA 71 into the rack. The handle should engage the dogleg track.
3. Press down on the handle to lock the unit into place.
4. Lock the handle to the GEA 71 body using the Philips screw.
5. Configure and test the GEA 71 according to Section 7.4.
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6.5
GTX 33 Transponder
Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
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.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any
damage.
2. 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.
5. Configure and test the GTX 33 according to Section 7.5.
6.6
GDC 74B Air Data Computer
Removal:
1. Gain access by removing the appropriate GDU 1040A display unit (see Section 6.1.)
2. Disconnect the pitot/static plumbing from the rear of the unit. Disconnect the single connector.
3. Loosen each thumbscrew on the hold-down clamp and remove the clamp.
4. Carefully remove the unit from its mount.
Reinstallation:
1. Inspect the connector and pins for damage. Inspect the pitot/static plumbing for damage.
Repair any damage.
2. Place the unit in the mounting tray.
thumbscrews.
Position the locking clamp and fasten using the
3. Connect the backshell assembly and pitot/static plumbing to the unit.
4. Configure and test the GDC 74B according to Section 7.6.
6.7
GTP 59 OAT Probe
Removal:
1. Using a deep-socket to hold the probe in place on the outside of the aircraft, loosen the GTP
59 mounting nut and remove the GTP 59.
Reinstallation:
1. Do not remove the serial number tag.
2. Reinstallation is the reverse of removal.
3. No configuration is required for the GTP 59. Test according to Section 7.6.4.
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6.8
GRS 77 / GRS 7800 AHRS
6.8.1
GRS 77 AHRS
GRS 77 Removal:
1. Gain access to the forward avionics compartment in the nose of the aircraft.
2. Disconnect the AHRS connector.
3. Remove the four Phillips thumbscrews with a screwdriver and set them aside.
4. Gently lift the GRS 77 from the mounting rack. Do not loosen the rack mounting bolts. If the
mounting rack is loosened or removed, the GRS 77 must be re-calibrated. See Section 7.7.
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. Fasten the unit to the plate using the Phillips thumbscrews.
4. Connect the connector to the GRS 77.
5. Rock the connector side to side to verify the connector locking tabs are engaged.
6. Calibrate and test the GRS 77 according to Section 7.7.
6.8.2
GRS 7800 AHRS
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 simultaneously 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 rack mounting bolts. If the mounting rack is
removed, the GRS 7800 must be re-calibrated. See Section 7.7.
GRS 7800 Reinstallation:
1. Visually inspect the connectors 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.
5. Connect the connector to the GRS 7800.
6. Calibrate and test the GRS 7800 according to Section 7.7.
6.9
GMU 44 Magnetometer
Removal:
1. Gain access to the GMU 44 units by removing the antenna panel located on the port side of the
vertical stabilizer.
2. Loosen three screws connecting the unit to the aircraft mounting bracket using a non-magnetic
Phillips screwdriver.
3. Disconnect the wiring harness.
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Reinstallation
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any
damage. Connect the wiring harness to the GMU 44.
2. Fasten the GMU to the aircraft mounting bracket using a non-magnetic Phillips screwdriver.
3. Calibrate and test the GMU 44 according to Section 7.7.
6.10 GDL 69A/ or GDL69A SXM
Removal:
1. Gain access to the GDL 69A/69A SXM by removing PFD2 (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/69A SXM. Gently remove the unit from the
rack.
Reinstallation:
1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any
damage.
2. Gently insert the GDL 69A/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.
5. Configure and test the GDL 69A/69A SXM according to Section 7.8.
6.11 GSA 80/81 Servos
Removal:
1. Gain access to the desired servo(s).
2. Disconnect the servo harness connector.
3. Use a socket or open-wrench to loosen and remove the servo attachment bolts. The PitchTrim servo bracket will need to be removed to access all the Pitch-Trim servo attachment bolts.
4. Carefully remove the servo and place a protective cover on the output gear.
5. Place a protective cover over the GSM 85A (or GSM 86) servo mount.
Reinstallation:
1. Inspect the output gear for abnormal wear or the absence of grease. If grease is required, refer
to Section 4.7 and grease the gear.
2. Carefully place the servo into the servo mount, ensuring proper orientation and alignment.
3. Fasten the servo to the servo mount using the existing hardware.
4. Inspect the harness connectors and check that no pins are bent or otherwise damaged.
5. Connect the harness and secure it appropriately.
6. If no further maintenance is required, continue to Section 7.9.
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6.12 GSM 85A / GSM 86 Servo Mounts
Removal:
1. Remove the desired servo(s) per Section 6.11.
2. For the Roll, Pitch and Yaw Servos: remove the servo cable from the control cable clamps. For
the Pitch-Trim Servo: remove the servo cable from the outboard turnbuckle and Y-splice.
3. Use a socket or open-wrench to loosen and remove the servo attachment bolts.
4. Carefully remove the servo mount(s).
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 1-2.
2. If no other maintenance is to be performed, reinstall the servo(s) per Section 6.11. There is no
software or configuration file loading for servo mount replacement.
6.13 GCU 475
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 for damaged pins.
2. Connect the connector to the unit.
3. Rock the connector side to side to verify the connector locking tabs are engaged.
4. Hold unit flush with the instrument panel, ensuring locking stud alignment marks are in the
vertical position.
5. 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.
6. Configure and test the GCU 475 according to Section 7.10.
6.14 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 for damaged pins.
2. Connect to connector to the unit.
3. Rock the connector side to side to verify the connector locking tabs are engaged.
4. Hold unit flush with the instrument panel, ensuring locking stud alignment marks are in the
vertical position.
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5. 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.
6. Configure and test the GMC 710 according to Section 7.11.
6.15 GWX 68 / 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 the connector to the unit.
5. On the GWX 68 only, rock the connector side to side to verify the connector locking tabs are
engaged.
6. Configure and test the GWX according to Section 7.12.
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6.16 Configuration Module
6.16.1 Configuration Module Removal & Replacement
Configuration modules (Reference Figure 6-1 and Table 6-1, Item 1 shown below) are located in the
following LRU harness connector backshells (Item 6): GDU 1040A PFD, GRS 77 AHRS, GDC 74B Air
Data Computer, and the GEA 71 Engine/Airframe Unit. Additionally, the GRS 7800 has a different
configuration module that is located in the GRS 7800 connector backshell. Refer to Section 6.16.2 for the
GRS 7800 configuration module removal and replacement instructions. Refer to the Master Drawing List,
listed in Table 1-2, for specific installation drawings.
Figure 6-1, Configuration Module Installation
Table 6-1, Configuration Module Kit – 011-00979-03
Item
1
3
4
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Description
Qty Needed
Configuration Module PCB Board Assembly w/EEPROM & Temp
Sensor, Potted
Cable, 4-Conductor Harness
Pins, #22 AWG (HD)
1
1
4
Garmin Part
Number
011-02178-00
325-00122-00
336-00021-00
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Removal:
1. Disconnect connector from LRU.
2. Remove 2 screws (8) from cover (7) and remove cove.
3. Unplug connector from configuration module (1).
4. Remove configuration module.
Replacement:
1. Inspect connector for damaged pins (4).
2. Place configuration module (1) in position.
3. Insert connector into configuration module (1).
4. Assembly of the connector is the reverse of disassembly.
5. Continue to Section 6.16.3.
6.16.2 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 6-21-2, for specific installation drawings.
2X
WASHERS, RING TERMINALS
4X
Figure 6-2, 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).
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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. Continue to Section 6.16.3.
6.16.3 Configuration Module Checkout
If a GRS 77 AHRS Configuration Module is replaced:
All three GRS AHRS/GMU 44 calibration procedures must be performed. Proceed to Section 7.7.2.
If a GRS 7800 AHRS Configuration Module is replaced:
Configuration settings must be reloaded and all GRS/GMU calibration procedures performed. Proceed to
Section 7.7.1.
If a GDC 74B Configuration Module is replaced:
Configuration settings must be reloaded to the GDC 74B. Proceed to Section 7.6.
If a GEA 71 Configuration Module is replaced:
Proceed to Section 7.4.1.
If only the Master Configuration Module is replaced:
New Terrain/Obstacle cards, Jeppesen Aviation Database and other optional features (i.e. TAWS unlock
card) will need to be replaced if the master configuration module is changed. The G1000 System ID number
will change to a new number when installing a new master config module. The old Terrain and other cards
will no longer work as they will remain locked to the old System ID number.
1. 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:
New Terrain/Obstacle cards, Jeppesen Aviation Database and other optional features (i.e. TAWS unlock
card) will need to be replaced if the master configuration module is changed. The G1000 System ID number
will change to a new number when installing a new master config module. The old Terrain and other cards
will no longer work as they will remain locked to the old System ID number.
1. The entire G1000 system must be re-configured. Insert the correct G1000 software loader card
into PFD 1.
2. Start the G1000 in configuration mode. Go to the System Upload Page on PFD 1.
3. See Section 3.9 for instructions on how to use the System Upload page. Check all configuration
files and reload them.
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4. After reloading configuration files, examine the G1000 installation for any installed configuration
options. Options are listed in Section 3.9.4.3. Load optional files as necessary.
5. Continue to Section 8 and conduct the return to service checkout.
6.17 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 6-3, GEA Backshell Thermocouple
Table 6-3, Thermocouple Kit (011-00981-00)
Item #
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 J711, item 5, from the backplate.
4. Remove cover, item 6 from the backshell.
5. Unscrew thermocouple from boss on backshell. Extract the thermocouple pins from the connector.
Replacement:
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1. Crimp pins, item 2, onto each of the thermocouple wires, item 1. Ensure that pre-stripped wire
length is 1/8” prior to crimping.
2. Insert newly crimped pins and wires into the appropriate connector housing location, item 4, as
specified by King Air C90 Wiring Diagram, listed in Table 1-2.
3. Place thermocouple body, item 1, onto the backshell boss, item 5. Place the thermocouple as
shown in Figure 6-2 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 the provided screws, item 7.
6. Continue to Section 7.4.1 and verify that the ITT indications are valid on the MFD.
6.18 GPS/WAAS Antennas
Remove and install the GPS/WAAS antennas in accordance with the antenna installation drawing (refer to
Master Drawing List, listed in Table 1-2, for specific drawing number). For procedural instructions on
accessing the GPS antennas, refer to the King Air Model 90 Series Maintenance Manual, listed in Table
1-2.
Proceed to Section 7.3.1 GPS Signal Acquisition for testing.
6.19 Engine Signal Conditioners
Removal:
1. For the Signal Conditioner No. 1, remove PFD1 from the instrument panel as per Section 6.1. For
the Signal Conditioner No. 2, remove PFD2 from the instrument panel as per Section 6.1.
2. Remove three 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.
NOTE
The signal conditioner ground strap was added by STC SA01456WI-D Master Drawing
List, 005-00375-30, Revision 5 and subsequent approved revisions for aircraft with VibroMeter Signal Conditioner. The ground strap is not applicable to installations with the
Sandia ST26 tach-gen adapter unit.
Reinstallation:
1. Reinstallation of the signal conditioner unit is the reverse of the removal. Reference the Main
Instrument Panel Installation drawing, listed in Table 1-2, for more details.
2. Proceed to Section 7.4.2 for testing.
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6.20 Senior Aerospace PC920 Signal Conditioning Unit
NOTE
The PC920 is applicable to installations with STC SA01456WI-D Master Drawing List, 00500375-30, Revision 4 and previous approved revisions for aircraft with Senior Aerospace
Ketema fuel flow transducer, part number 1/2-2-81-306.
Removal:
1. Remove PFD1 from the instrument panel as per Section 6.1.
2. Remove 3 top screws from PC920 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 PC920 connector.
4. Remove the four mounting bolts and remove the PC920 unit.
Reinstallation:
1. Reinstallation of the PC920 unit is the reverse of the removal. Reference the Main Instrument
Panel Installation drawing, listed in Table 1-2, for more details.
2. Perform PC920 portion of the Bonding Check in Section 4.5 for each PC920 unit installed by this
procedure.
3. Proceed to Section 7.4.2 for testing.
6.21 Instrument Panel Annunciators (Prop Synch and Standby Battery)
Removal:
1. Remove MFD from the instrument panel as per Section 6.1.
2. Using a M22885/108T8234 extraction tool, disconnect connector from the back of the switch.
3. Pull the pushbutton cap fully out of the switch body and allow the cap to rotate 90° where it is held
by the retaining element.
4. While holding the retaining sleeve (back side of the instrument panel), loosen the two screws inside
the switch body until the switch is free to come out.
5. Remove the mounting sleeve and switch from the instrument panel.
Reinstallation:
1. Reinstallation of the Prop Synch and Standby Battery switches is the reverse of the removal.
Reference the Main Instrument Panel Installation drawing, listed in Table 1-2, for more details.
2. Press and hold the cockpit annunciator “Press To Test” switch located to the left of the annunciator
panel, and verify the following:
a. For the Standby Battery Annunciator/Switch: STBY Battery Switch legends illuminates and
reflects “STANDBY BATTERY” in white, “ARM” in green, and “ON” in amber.
b. 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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6.22 L-3 Avionics (BF Goodrich) PS-835(C or D Model) Emergency Battery
The emergency battery was added by this STC (in the nose equipment compartment) for aircraft that did
not have a pre-existing factory installation (typically located in the tail). For aircraft with the factory
installation, refer to the King Air Model 90 Series Maintenance Manual, listed in Table 1-2, for removal and
replacement information.
Removal:
1. Unscrew the knurled hold-down nut to allow it to move free of the unit.
2. Remove the unit from the rack.
Reinstallation:
1. Install the emergency battery in accordance with the standby battery installation drawing (refer to
Master Drawing List, listed in Table 1-2, for specific drawing number). Refer to the King Air Model
90 Series Maintenance Manual, listed in Table 1-2, for access requirements as needed. For aircraft
which the standby battery was installed by this STC, the maintenance will be as per the King Air
manual but the access will be through the nose avionics compartment.
2. If further maintenance is not required, proceed to Section 9.
6.23 Standby Airspeed Indicator
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect pitot-static plumbing from the back of the standby airspeed indicator.
3. Disconnect the electrical connector from the standby airspeed indicator.
4. Use a Phillips screwdriver to remove the three attachment screws from the front of the standby
airspeed indicator.
5. Remove the standby airspeed indicator.
Replacement:
1. Reinstallation of the standby airspeed indicator is the reverse of the removal. Reference the Main
Instrument Panel Installation drawing, listed in Table 1-2, for more details.
2. If further maintenance is not required, proceed to Section 9.
6.24 Standby Altimeter
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect pitot-static plumbing from the back of the standby altimeter.
3. Disconnect the electrical connector from the standby altimeter.
4. Use a Phillips screwdriver to remove the three attachment screws from the front of the standby
altimeter.
5. Remove the standby altimeter.
Replacement:
1. Reinstallation of the standby altimeter is the reverse of the removal. Reference the Main Instrument
Panel Installation drawing, listed in Table 1-2, for more details.
2. If further maintenance is not required, proceed to Section 9.
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6.25
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 with care. Refer to the 4200 Series Attitude Indicator
Installation Manual, listed in Table 1-2, for more handling instructions.
Removal:
1. Remove MFD per Section 6.1.
2. Disconnect the electrical connector of the standby attitude indicator.
3. Use a 0.060” 6-Spline wrench to remove the knob from the front of the standby attitude indicator.
4. Use a Phillips screwdriver to remove the three attachment screws from the front of the standby
attitude indicator.
5. Remove the standby attitude indicator.
Reinstallation:
1. Ensure the lighting control voltage switches on rear of unit are set for 28V.
28V
2. Reinstallation of the standby attitude indicator is the reverse of the removal. Reference the Main
Instrument Panel Installation drawing, listed in Table 1-2, for more details.
3. If further maintenance is not required, proceed to Section 9.
6.26 Avionics Cooling Fans
Removal:
1. Gain access into the nose avionics equipment bay.
2. Disconnect the cooling fan hoses from the cooling fan.
3. Disconnect the electrical connector of the cooling fan.
4. Use a Phillips screwdriver to remove the three attachment screws from the cooling fan.
5. Remove the cooling fan.
Replacement:
1. Reinstallation of the avionics cooling fan is the reverse of the removal. Reference the Electrical
Equipment Install, Nose Bay drawing, listed in Table 1-2, for more details.
2. If further maintenance is not required, proceed to Section 9.
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6.27 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 four attachment screws from the cooling fan.
4. Remove the cooling fan.
Replacement:
1. Reinstallation of the GDU cooling fan is the reverse of the removal. Reference the Main Instrument
Panel Installation drawing, listed in Table 1-2, for more details.
2. If further maintenance is not required, proceed to Section 9.
6.28 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 GTX 33D transponder install drawing listed in Table 1-2
or the applicable airplane maintenance manual for existing transponder antennas.
2. Disconnect the antenna coaxial cable.
3. Remove the fasteners 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 GTX 33D transponder install drawing listed in Table 1-2
or the applicable airplane maintenance manual for existing transponder antennas.
4. Reinstall cabin interior ceiling panel.
5. Proceed to Section 7.5.3 for testing of the GTX 33( ) transponder.
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7
G1000 Hardware Replacement - Software Loading and Testing
This section provides procedures to be followed after a piece of G1000 equipment is replaced. At the
beginning of each LRU section, instructions are given to guide the technician for various
removal/replacement scenarios. These instructions define necessary procedures to be followed for
situations where original equipment was reinstalled as well as for situations where new equipment (new
serial number) is installed.
CAUTION
Remove Supplemental Database Cards from the lower slot of all displays before loading
software into any unit. Not removing the cards may corrupt them. Replacing corrupted
database cards are not covered under warranty.
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.
WARNING
Connect a ground power unit to the aircraft for software loading. Do not rely on only the
aircraft batteries to prevent loss of power during the software loading process. DO NOT
ALLOW POWER TO BE REMOVED FROM THE SYSTEM WHEN LOADING
SOFTWARE! Remove power only when told to do so by the following procedure. As a
general rule all displays should be in the same mode (configuration or normal), unless
instructed differently.
7.1
GDU 1040/1500 MFD & PFD
Original Display Reinstalled
If the removed display(s) are re-installed in their original positions, no software or configuration loading is
required. This does not include units that were returned for repair as their software and configuration files
are deleted during the repair testing process. Continue to Section 7.1.2.
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.
Do not swap the MFD with a PFD. Continue to Section 7.1.2.
New, Repaired, or Exchange Display(s) Installed
If a new, repaired, or exchange GDU 1040A or GDU 1500 is installed, the correct software, configuration,
Jeppesen NAV database, and Garmin database card must be loaded to the unit. Continue to Section 7.1.1.
NOTES
If replacing PFD1 with a new, repaired, or exchanged GDU, the new GDU must be placed
in the PFD2 location and the GDU system files loaded there to prevent calibration and
other configuration data residing in the PFD1 config module from being deleted. It is not
necessary to install a display in the PFD1 position to load GDU software into the
replacement display installed in the PFD2 position. After loading GDU software into the
replacement display in the PFD2 position, turn off the system and move the GDU to the
PFD1 position in the instrument panel and continue the install by loading the configuration
files.
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Remove the Garmin database card from the old display to install in the new display. Cards
left in displays returned to Garmin will not be returned.
7.1.1
GDU Display Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Make a list of the following to determine what configuration software files to load in the following
steps.
a. Turn on the MFD and record the Airframe Configuration Number or “Baseline” in the upper right
corner of the splash screen display. If the MFD is the failed display, power on PFD1 in
configuration mode and go to the GDU - AIRFRAME CONFIGURATION page. Record the
Airframe Configuration Number or “Baseline” as shown in the IDENTIFICATION window.
b. Determine and record if the aircraft has a Gross Weight Increase STC that increased the max
gross, landing, and zero fuel weights over Beechcraft TC weights. For reference on weights
available, see Section 3.4.11.1.
c.
Determine and record if the aircraft has a Raisbeck Prop STC that affects airspeed indicator
markings. For reference on determining what airspeed option files will need to be loaded later
in this procedure, see Section 3.4.11.3.
d. Third party avionics equipment interfaced to G1000 (ADF, DME, etc.).
e. Record GMA1 and GMA2 Configuration settings for marker beacon settings. A system
software load will change these to default values, so they may need to be reentered at the end
of the procedure to return marker beacon performance to previous configuration settings.
f.
Determine what optional features that require Unlock Cards (i.e. SVT, TAWS-B, etc.) are
installed and locate the Unlock Cards for later use.
3. Install the replacement display in the panel. Note that a new PFD1 must be installed in the PFD2
position for initial software loading to prevent overwriting PFD1 config module data.
4. Remove the Garmin database cards from the lower card slots of each display.
5. Insert the G1000 software loader card in the top slot of the replacement display.
6. Open the MFD, PFD 1 (PRI), PFD 1 (SEC), and PFD 2 circuit breakers.
7. Turn on the Avionics electrical busses.
8. On the replacement display, press and hold the ENT key.
9. Close the circuit breaker for the display.
10. When the words “INITIALIZING SYSTEM” appear in the top left corner of the display, release the
ENT key.
11. If the display prompts to load Boot Block files, press the YES softkey. This prompt only appears for
older displays and system software that requires this update, so it will not appear if not needed.
The display automatically determines if this update is needed for the installer.
12. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, press the YES
softkey.
13. After the new GDU software is loaded, 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.
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14. When complete, the display starts in configuration mode displaying the “SYSTEM STATUS” page.
Open the circuit breaker for the display.
15. If the replacement display is going to be PFD1, turn off the G1000 system and relocate the display
to the PFD1 position and reinstall PFD2.
16. Put the G1000 system loader card in the top slot of PFD1.
17. Close all circuit breakers and start the G1000 system in configuration mode.
18. On PFD1, when the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, press the
NO softkey.
19. The replacement display may prompt that it is verifying the Basemap database file. Follow the
onscreen prompts to continue.
20. After one minute, turn off the G1000 system. This allows system config data like System ID to
crossfill before continuing.
21. Start the G1000 system in configuration mode.
22. On PFD1, when the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, press the
NO softkey.
23. The replacement display may prompt that it is verifying the Basemap database file. Follow the
onscreen prompts to continue.
24. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
25. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
26. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
27. Press the CLR ALL softkey.
28. Press the CHK CFG softkey.
29. Press the LOAD softkey.
30. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
31. Press the ENT key to acknowledge upload complete.
32. Move the cursor to the GROUP window.
33. If the Airframe Configuration recorded in Step 1A is 2-22, highlight and select “C90CONFIGURATIONS”. If the Airframe Configuration said “Baseline”, skip to Step 39.
34. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight the Airframe Configuration
number recorded in Step 2a and press the ENT key.
35. Press the CHK ALL softkey.
36. Press the LOAD softkey.
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37. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
38. Press the ENT key to acknowledge upload complete.
39. Move the cursor to the GROUP window and rotate FMS inner knob to display drop down menu.
Highlight “C90-Weight and Airspeed” and press ENT key.
40. In the ITEM window, rotate the inner FMS knob to view the list of available C90 option files. Highlight
the correct airframe weight option file as determined n Step 2b above and press the ENT to select.
41. Verify the correct configuration file is displayed in the ITEM window and the AIRFRAME
configuration box is checked.
42. Press the LOAD softkey.
43. Monitor load progress. Verify software load completes without errors as indicated by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
44. Press the ENT key to acknowledge upload complete.
45. If the aircraft requires an optional airspeed indicator file to be loaded, move the cursor to the
GROUP window and rotate FMS inner knob to display drop down menu. Highlight “C90-Weight
and Airspeed” and press the ENT key. If the aircraft does not require an optional airspeed file,
skip to Step 52.
46. In the ITEM window, rotate the inner FMS knob to view the list of available C90 configurations.
Highlight the correct airspeed indicator marking configuration file as determined in Step 2c above
and press the ENT key.
47. Verify the correct configuration file is displayed in the ITEM window and the configuration box is
checked.
48. Press the LOAD softkey.
49. Monitor load progress. Verify software load completes without errors as indicated by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
50. Press the ENT key to acknowledge upload complete.
51. Load the next airspeed file if needed following steps 46 through 50.
52. Reload the Option files for all Garmin units and third party units. See Sections 3.4.12 - 3.4.19 for
load instructions for the Option files.
53. Enter the Aircraft Registration number. See Section 3.4.29 for instructions.
54. Check and update the GMA marker beacon config settings to match previous values. See Section
3.4.30 for instructions.
55. Press the UPT CFG softkey.
56. Open PFD1 circuit breaker and remove the system loader card.
57. Unlock optional features such as SVT, TAWS-B, etc.. See Sections 3.4.22 - 3.4.28 for unlock
instructions for the features.
58. Clear user settings and load the Splash Screen per Section 3.4.31.
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59. Load navigation database per Section 3.6.1.
60. Insert Garmin Database cards in the bottom card slot of each display per Section 3.6.2.
61. If aircraft equipped with traffic system, setup map per Section 3.6.3.
62. Continue to Section 7.1.2.
7.1.2
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 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 AHRS is valid on both displays.
6. Check that the engine instrument fields are valid on the MFD.
7. Verify the engine gauge markings are correct for the Engine/Prop installation (Beechcraft C90 TC
and Third Party engine/prop combinations) per the Beechcraft AFM and Third Party AFMS if
applicable.
Figure 7-1, G1000 Normal Mode Check
8. Push the red DISPLAY BACKUP button on the pilot-side GMA 1347D. Verify that the pilot-side
PFD and MFD displays enter reversion mode. MFD should have valid altitude, airspeed, vertical
speed, COMM1, COMM2, NAV1, NAV2 and engine instruments.
9. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD 1 and
MFD return to normal display modes.
10. Repeat Step 1 using GMA2. Ensure that PFD 2 and MFD enter reversion mode and MFD displays
valid altitude, airspeed, vertical speed, COMM1, COMM2, NAV1, NAV2 and engine instruments.
11. De-activate co-pilot’s side reversion mode by pushing the DISPLAY BACKUP button. Verify PFD
2 and MFD return to normal display modes.
12. If TAWS was activated, select the TAWS page (4th page in the MAP group) on the MFD.
a. Verify that the title at the top of the page reads “MAP – TAWS-B”. If TAWS has not been
enabled, the title will read “MAP – TERRAIN PROXIMITY” or “MAP – TERRAIN”.
b. Press the MENU button and select “Test TAWS” from the pop-up menu.
c.
After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over the
cockpit speaker.
13. Check airspeed tape markings for correct color band ranges per Section 3.7.9. Pay particular
attention to Vmca airspeed value and Vmo red line value for correct values.
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14. If aircraft equipped with Stormscope system, check configuration for Stormscope per Section 3.5.3.
15. If no other service is to be performed, perform final return-to-service test as specified in Section 9.
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7.2
GMA 1347D Audio Panel
Original GMA 1347D Reinstalled
No software/configuration loading or testing is required if the removed GMA 1347D is re-installed. This
does not include units that were returned for repair as their software and configuration files are deleted
during the repair testing process. Continue to Section 7.2.2.
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.
Continue to 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. Continue to Section 7.2.1.
7.2.1
GMA Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GMA (1 or 2 for unit replaced) - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Load the Optional Files for this equipment if installed - ADF-60, DME-42.
14. Turn off the G1000 system.
15. Remove the Software Loader card.
16. Turn on the G1000 system in normal mode.
17. Continue to Section 7.2.2.
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7.2.2
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.
Perform the following Sections in order.
7.2.2.1
Intercom System (ICS) Check for GMA 1347D, PN 011-01257-00.
NOTE
This procedure is applicable only to aircraft equipped with GMA 1347D Part Number 01101257-00. Reference Figure 3-6 for control button identification and location for the GMA
1347D, PN 011-01257-00.
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 (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.
7.2.2.2
Intercom System (ICS) Check for GMA 1347D, PN 011-01257-20.
NOTE
This procedure is applicable only to aircraft equipped with GMA 1347D Part Number 01101257-20. Reference Figure 3-7 for control button identification and location for the GMA
1347D, PN 011-01257-20.
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1. Ensure that the MAN SQ key is off (no light).
2. Adjust GMA1 and GMA2 ICS volume to a comfortable level.
3. One at a time, plug a headset into each left and right CABIN ICS jack location (one headset on
right, one headset on left).
4. Verify the following:

Two-way communication between each CABIN ICS jack position.

CABIN ICS positions cannot be heard by the pilot or copilot.
5. Select GMA1 INTR COM button and verify the following:

Passengers can communicate with each other.

GMA2 INTR COM light is illuminated.

The pilot and copilot can communicate with each other and cannot hear passengers.
6. Deselect INTR COM.
7. On GMA1 select CABIN button and verify the following:

Passengers can communicate with each other.

The pilot (copilot if GMA2 CABIN selected) and passengers can all hear each other.

On GMA1 deselect CABIN button.
8. Repeat step 7 using GMA2.
9. Select CABIN button on both GMAs and verify the following:

Passengers can communicate with each other.

The pilot and copilot can communicate with each other and the passengers.
10. Deselect the CABIN button on both GMAs.
11. On both GMAs select COM1 MIC and AUDIO.
12. Ensure INTR COM is deselected on GMA1 or GMA2. Verify an active (green) COM1 frequency is
displayed on both PFDs.
13. On GMA1, select PA and verify the PA select annunciator is illuminated on GMA1. Verify COM1
active frequency is displayed white.
14. On GMA 2, select PA and verify the PA select annunciator is illuminated on GMA2. Verify COM1
active frequency is displayed white.
15. Initiate passenger address using pilot’s headset boom mic by keying the pilots PTT. Verify clear
PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator on
GMA1 flashes ~ once per second during PA address. Repeat using pilot hand mic.
16. Initiate passenger address using copilot’s headset boom mic by keying the copilots PTT. Verify
clear PA audio can be heard over cabin speaker and passenger headsets, PA selected annunciator
on GMA1 flashes ~ once per second during PA address. Repeat using copilot hand mic.
7.2.2.3
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 the pilot’s audio panel and verify that the selected audio is heard over the
pilot’s speaker.
3. On the co-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 co-pilot’s headset.
4. Press the SPKR key on the co-pilot’s audio panel and verify that the selected audio is heard over
the co-pilot’s speaker.
7.2.2.4
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.
7.2.2.5
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.
7.2.2.6
Marker Beacon Test
Figure 7-2, Marker Beacon Symbology
1. Using a ramp tester, simulate the outer marker, middle marker and inner marker signals by following
the test equipment manufacturer’s instructions. Verify that each marker audio signal is present
over the pilot and co-pilot headphones and speaker.
2. Verify that the outer, middle, and inner annunciations appear on PFD 1 and PFD 2 when the
corresponding signal is applied. Marker beacon annunciations appear at the upper left corner of
the altitude indicator on the PFD (Figure 7-2). Operate the MKR MUTE key on the #1 and #2 GMA
1347D and ensure that the audio signal is muted.
3. If no other service is to be performed, continue to the return-to-service checks in Section 9.
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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 Section 7.3.2.
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. Continue to 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. Continue to Section 7.3.1.
7.3.1
GIA 63W Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GIA (1 or 2 for unit replaced) - Software and Configuration files

GIA 1 GEA-CFG - Configuration file (for v0636.06 system software and later only)

NAV (1 or 2 for unit replaced) - Software file (for -20 GIA units only)

COM (1 or 2 for unit replaced) - Software and Configuration files (for -20 GIA units only)

GPS (1 or 2 for unit replaced) - Software file

AUD - Software and Configuration files

GIA CERT - Software file
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete.
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13. Load the C90-Option files for the equipment listed below if installed. Target load the GIA 1 or 2
configuration file as noted below:

ADF-60 (for GIA2 replacement only), load GIA2 Configuration file.

DME-42 (for GIA1 replacement only), load GIA1 Configuration file.

ESP Support (If previously installed), load GIA (1 or 2 for unit replaced) Configuration file.

GRS77 AHRS, load GIA (1 or 2 for unit replaced) Configuration file.

GRS 7800 AHRS, load GIA (1 or 2 for unit replaced) Configuration file.

Non-Garmin Radar Altimeter Option (for GIA2 replacement only), load GIA2 Configuration file.

Non-Garmin Traffic System Option (for GIA2 replacement only), load GIA2 Configuration file.

WX500 Option (for GIA2 replacement only), load GIA2 Configuration file.

GTX33 ES Transponder, load GIA (1 or 2 for unit replaced) Configuration file.
14. Turn off the G1000 system.
15. Remove the Software Loader card.
16. Turn on the G1000 system in normal mode.
17. Continue to Section 7.3.2.
7.3.2
GIA 63W Test
Perform the following Sections in order.
7.3.2.1
GPS Signal Acquisition
Figure 7-3, AUX – GPS STATUS Page (MFD)
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 GPS STATUS page on the
MFD (4th page in AUX group). Two softkeys on the bottom of the display allow the user to toggle between
GPS 1 and GPS 2. Verify that both receivers show 3D DIFF NAV on the MFD.
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NOTE
It may be necessary to temporarily disable or move away from GPS repeaters while testing,
as repeaters may adversely affect GPS receiver performance.
7.3.2.2
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:

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.
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7.3.2.3
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.
7.3.2.4
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.
3. Tune the NAV 1 and NAV 2 receivers to the simulation frequency.
4. Set the HSI on PFD1 to VOR1 by pressing the CDI soft key until VOR1 is selected.
5. Set the HSI on PFD2 to VOR2 by pressing the CDI soft key until VOR2 is selected.
6. 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.)
7. Verify full scale deflection of VOR1 and VOR2 CDI by varying CRS1 and CRS2 selected course at
least 10° left and right.
8. Reset course pointers to aircraft heading.
9. Engage the autopilot and press the NAV key on the AFCS mode controller.
10. Using the CRS1 knob alter course by 10° to the right.
11. Verify the flight director and aircraft controls respond by flying to the VOR course. Repeat to the
left.
12. Couple FD to PFD2 by pressing the XFR button on the AFCS mode controller.
13. Verify FD is coupled right as indicate by a right pointing arrow on the AFCS mode controller next
to the XFR button.
14. Repeat Steps 9-11 using CRS2 knob while coupled to PFD2.
15. Set CRS1 and CRS2 course pointers to aircraft heading.
16. Simulate a Localizer/Glideslope signal.
17. Tune this signal on NAV 1 and NAV 2 receiver.
18. Set the PFD1 HSI to LOC1 and PFD2 HSI to LOC2 by pressing CDI soft key until LOC1 and LOC2
is selected.
19. Use the test equipment to center the deviation bars (localizer and glideslope) on PFD1 and PFD2.
20. 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.
21. Apply right/left and up/down localizer/glideslope signals using the test equipment. Verify that the
Flight Director and flight controls respond appropriately.
22. Couple FD to PFD1 by pressing the XFR button on the AFCS mode controller.
23. Verify FD is coupled to PFD1 as indicate by a left pointing arrow on the AFCS mode controller next
to the XFR button.
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24. Repeat Steps 20-21 using while coupled to PFD1.
25. If no other service is to be performed, continue to the return-to-service checks in Section 9.
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 Section 7.4.2.
Original GEA 71 Installed in Opposite Locations for Troubleshooting
Configuration Files loading is required if the original GEA units are installed in opposite locations (GEA #1
and GEA #2 in opposite unit racks). Continue to Section 7.4.1.
New, Repaired, or Exchange GEA 71 Installed
If a new, repaired, or exchange GEA 71 is installed, the correct software and configuration files must be
loaded to the unit. Continue to Section 7.4.1.
7.4.1
GEA 71 Software and Configuration Loading
1. Insert the G1000 Software Loader card in the top slot of PFD1.
2. Apply system power and place all displays in Configuration Mode.
3. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
4. On PFD1, go to the GDU - AIRFRAME CONFIGURATION page.
5. Record the Airframe Configuration Number or “Baseline” as shown in the IDENTIFICATION
window.
6. Go to the SYSTEM UPLOAD page using the small FMS knob.
7. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
8. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
9. Press the CLR ALL softkey.
10. Using the FMS knob and ENT key, select the following files to load:

GEA (1 or 2 for unit replaced) - Software and Configuration files.
11. After the files are selected, press the LOAD softkey.
12. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
13. Press the ENT key to acknowledge upload complete.
14. Move the cursor to the GROUP window.
15. If the Airframe Configuration recorded in Step 5 is 2-22, highlight and select “C90CONFIGURATIONS”. If the Airframe Configuration said “Baseline”, skip to Step 22.
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16. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight the Airframe Configuration
number recorded in Step 5 and press the ENT key.
17. Press the CLR ALL softkey.
18. Using the FMS knob and ENT key, select the following files to load:

GEA (1 or 2 for unit replaced) - Configuration file.
19. After the file is selected, press the LOAD softkey.
20. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
21. Press the ENT key to acknowledge upload complete.
22. Turn off the G1000 system.
23. Remove the Software Loader card.
24. Continue to Section 7.4.2.
7.4.2
GEA 71 Test
1. Turn on the G1000 system in normal mode.
2. On the MFD, check the indication for each of the sensor or monitor inputs with the aircraft engines
off.
3. Verify all engine and system instruments show valid static normal values and markings with no red
Xs or erratic indications. Reference figure below for normal engine instrument marking appearance
(baseline configuration instruments shown, color band ranges may change for alternate Aircraft
Configuration numbers).
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Figure 7-4, Normal Engine Instrument Markings (MFD)
4. If any engine instrument readouts appear inaccurate or unreliable, continue to Section 7.4.3 to
functional check the instruments.
5. If engine instrument readouts appear accurate, continue to Section 9.
7.4.3
Additional GEA 71 Functional Tests
This section provides additional functional tests for individual GEA parameters.
7.4.3.1
Torque Functional Test
Required test equipment:
Test Equipment
Make/Requirement
Model/Part Nbr
Signal Generator
0-10Vdc / 0 – 1k Hz
As appropriate
1. For a GEA 1 check, using a signal generator inject a DC signal into the left engine firewall
connectors-pins J102-C (HI) and J102-R (LO).
2. For a GEA 2 check, using a signal generator inject a DC signal into the right engine firewall
connectors-pins J103-C (HI) and J103-R (LO).
3. Simulate the following voltages, and verify the indication and status:
Test Point (Vdc)
Indication (ft-lbs)
0.00 +/- .02
0
Status
Configurations
bottom of green band
Green digital
all
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Test Point (Vdc)
Indication (ft-lbs)
2.53 +/- .02
1320
Status
Configurations
red digital*
4-10, 21-22
NOTE: red radial
1315
red digital*
2.90 +/- .02
1525
2-3, 17-19
NOTE: red radial
1520
(*) steady after 5 seconds
4. On the right hand circuit breaker panel, open the GIA 1 (PRI) and GIA 1 (SEC) circuit breakers,
and verify the last observed left torque indication remains unchanged.
5. Close the GIA 1 (PRI) and GIA 1 (SEC) circuit breakers, and wait until the COM1 and NAV1 fields
are valid.
6. Open the GIA 2 circuit breaker, and verify the last observed right torque indication remains
unchanged.
7. Close the GIA 2 circuit breaker, and wait until the COM2 and NAV2 field are valid.
8. If no other tests will be completed in this section, do the following:
a. Disconnect test equipment.
b. Ensure firewall connectors are reconnected.
c.
Verify all engine parameters are displayed valid on the MFD with no Red X’s.
d. Continue to Section 9.
9. Continue to Section 7.4.3.2.
7.4.3.2
ITT Functional Test
Required test equipment:
Test Equipment
Make/Requirement
Model/Part Nbr
Signal Generator
0-10Vdc / 0 – 1k Hz
As appropriate
1. For a GEA 1 check, remove left engine ITT thermocouple terminals from sensor. Using a signal
generator, inject a DC signal into the left engine firewall connectors-pins, as follows:

S/N LJ-1063 thru LJ-1360, LJ-1362: J104-T* (LO) and J104-W* (HI)

S/N LJ-1361, LJ-1363 and after: J104-P* (LO) and J104-S* (HI)
2. For a GEA 2 check, remove right engine ITT thermocouple terminals from sensor. Using a signal
generator, inject a DC signal into the firewall connectors-pins specified below.

S/N LJ-1063 thru LJ-1360, LJ-1362: J105-T* (LO) and J105-W* (HI)

S/N LJ-1361, LJ-1363 and after: J105-P* (LO) and J105-S* (HI)
3. Simulate the following voltages, and verify the indication and status:
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Test Point (mV)
Indication (degC)
16.40 +/- .28
400*
44.3 +/- .28
1090*
Status
Configurations
bottom of green band
green digital
red triangle, start
mode
all
all
red digital**
(*) verify value displayed is within test point tolerances
(**) steady after 5 seconds
4. On the right hand circuit breaker panel, open the GIA 1 (PRI) and GIA 1 (SEC) circuit breakers,
and verify the last observed left ITT indication remains unchanged.
5. Close the GIA 1 (PRI) and GIA 1 (SEC) circuit breakers, and wait until the COM1 and NAV1 fields
are valid.
6. Open the GIA 2 circuit breaker, and verify the last observed right ITT indication remains unchanged.
7. Close the GIA 2 circuit breaker, and wait until the COM2 and NAV2 field are valid.
8. If no other tests will be completed in this section, do the following:
a. Disconnect test equipment.
b. Ensure firewall connectors are reconnected.
c.
Verify all engine parameters are displayed valid on the MFD with no Red X’s.
d. Continue to Section 9.
9. Continue to Section 7.4.3.3
7.4.3.3
Oil Pressure Functional Test
Required test equipment:
Test Equipment
Make/Requirement
Model/Part Nbr
DC Power Supply
0-10Vdc
As appropriate
1. For a GEA 1 check, use a DC power supply to inject a DC signal into the left engine firewall
connectors-pins J104-A (LO) and J104-B (HI).
2. For a GEA 2 check, use a DC power supply to inject a DC signal into the right engine firewall
connectors-pins J105-A (LO) and J105-B (HI).
3. Simulate the following voltages, and verify the indication and status:
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Test Point (Vdc)
Indication (PSI)
Status
Configurations
red digital
.98 +/- .1
39 +/- 1
2.0 +/- .1
80 +/- 1
2.1 +/- .1
85 +/- 1
NOTE: low red radial
40
bottom of green band
Green digital
bottom of green band
Green digital
all
4-10, 21-22
2-3, 17-19
4. On the right hand circuit breaker panel, open the GIA 1 (PRI) and GIA 1 (SEC) circuit breakers,
and verify the last observed left oil pressure indication remains unchanged.
5. Close the GIA 1 (PRI) and GIA 1 (SEC) circuit breakers, and wait until the COM1 and NAV1 fields
are valid.
6. Open the GIA 2 circuit breaker, and verify the last observed right oil pressure indication remains
unchanged.
7. Close the GIA 2 circuit breaker, and wait until the COM2 and NAV2 field are valid.
8. If no other tests will be completed in this section, do the following:
a. Disconnect test equipment.
b. Ensure firewall connectors are reconnected.
c.
Verify all engine parameters are displayed valid on the MFD with no Red X’s.
d. Continue to Section 9.
9. Continue to Section 7.4.3.4.
7.4.3.4
Oil Temperature Functional Test
Required test equipment:
Test Equipment
Decade Box
Make/Requirement
Model/Part Nbr
0-1k ohms
As appropriate
1. For a GEA 1 check, use a decade box or equivalent to simulate resistance values into the left
engine firewall connectors-pins J104-W (HI) and J104-X (LO).
2. For a GEA 2 check, use a decade box or equivalent to simulate resistance values into the right
engine firewall connectors-pins J105-W (HI) and J105-X (LO)
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3. Simulate the following resistances, and verify the indication and status:
Test Point (ohms)
Indication (DegC)
129 +/- 10
100
Status
Configurations
red digital*
all
NOTE: red radial 99
(*) steady after 5 seconds
4. If no other tests will be completed in this section, do the following:
a. Disconnect test equipment.
b. Ensure firewall connectors are reconnected.
c.
Verify all engine parameters are displayed valid on the MFD with no Red X’s.
d. Continue to Section 9.
5. Continue to Section 7.4.3.5.
7.4.3.5
Turbine Tach (N1) Functional Test
Required test equipment:
Test Equipment
Make/Requirement
Model/Part Nbr
Signal Generator
0-10Vdc / 0 – 1k Hz
As appropriate
1. For a GEA 1 check, on aircraft equipped with a ST-26 signal conditioner the left tach filter will need
to be disconnected and a 2.6Vrms signal injected into the P261 connector pins 15 (HI) and 14 (LO).
For Vibro-meter signal conditioner equipped aircraft, inject a 3Vrms signal into the No. 1 TACHGEN Adapter via left engine firewall connectors-pins J104-J and J104-K.
2. For a GEA 2 check, on aircraft equipped with a ST-26 signal conditioner the right tach filter will
need to be disconnected and a 2.6 Vrms signal injected into the P261 connector pins 15 (HI) and
14 (LO). For Vibro-meter signal conditioner equipped aircraft, inject a 3Vrms signal into the No. 2
TACH-GEN Adapter via right engine firewall connectors-pins J105-J and J105-K.
3. Simulate the following frequencies, and verify the indication and status:
Test Point (Hz)
Indication (%)
35.7 +/- .35
51
40.6 +/- .35
58
Status
Configurations
bottom of green band
4-6, 9, 21-22
green digital
bottom of green band
green digital
1-3, 7-8, 10, 17-19
red digital*
71.4 +/- .35
102
NOTE: red radial
101.5
all
(*) steady after 5 seconds
4. If no other tests will be completed in this section, do the following:
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a. Disconnect test equipment.
b. Ensure firewall and tach filter connectors are reconnected.
c.
Verify all engine parameters are displayed valid on the MFD with no Red X’s.
d. Continue to Section 9.
5. Continue to Section 7.4.3.6.
7.4.3.6
Prop Tach (N2) Functional Test
Required test equipment:
Test Equipment
Make/Requirement
Model/Part Nbr
Signal Generator
0-10Vdc / 0 – 1k Hz
As appropriate
1. For a GEA 1 check, on aircraft equipped with a ST-26 signal conditioner the left tach filter will need
to be disconnected and a 2.6Vrms signal injected into the P261 connector pins 18 (HI) and 17 (LO).
For Vibro-meter signal conditioner equipped aircraft, inject a 2.5Vrms signal into the No. 1 TACHGEN Adapter via left engine firewall connectors-pins J102-W and J102-X.
2. For a GEA 2 check, on aircraft equipped with a ST-26 signal conditioner the right tach filter will
need to be disconnected and a 2.6Vrms signal injected into the P261 connector pins 18 (HI) and
17 (LO). For Vibro-meter signal conditioner equipped aircraft, inject a 2.5Vrms signal into the No.
2 TACH-GEN Adapter via left engine firewall connectors-pins J103-W and J103-X
3. Simulate the following frequencies, and verify the indication and status:
Test Point (Hz)
Indication (rpm)
Status
Configurations
35.1 +/- .4
1100
9-10,17-18
47.9 +/- .4
1500
bottom of green band
19
51.1 +/- .4
1600
Green digital
2-8
57.5 +/- .4
1800
62.3 +/- .4
1950
21-22
red digital*
NOTE: red radial
1900
2-3, 17-19
red digital*
71.8 +/- .4
2250
NOTE: red radial
2200
4-10, 21-22
(*) steady after 5 seconds
4. If no other tests will be completed in this section, do the following:
a. Disconnect test equipment.
b. Ensure firewall and tach filter connectors are reconnected.
c.
Verify all engine parameters are displayed valid on the MFD with no Red X’s.
d. Continue to Section 9.
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5. Reconnect tach filters (if equipped) and continue to Section 7.4.3.7.
7.4.3.7
Fuel Flow Functional Test
Required test equipment:
Test Equipment
Make/Requirement
Model/Part Nbr
0-1k ohms
As appropriate
0-10Vdc / 0 – 1k Hz
As appropriate
Decade Box
Signal Generator
1. For a GEA 1 check, perform the following:
a. For S/N LJ-1283 and after only use a decade box or equivalent, simulate 1000 ohms into
left engine signal conditioner via left engine firewall connectors-pins J104-E and J104-F.
b. Using a signal generator, inject a 100 mV RMS / 0Hz signal into the left engine signal
conditioner via left engine firewall connectors-pins, as follows:

S/N LJ-1063 thru LJ-1282: J104-F and J104-E

S/N LJ-1283 and after: J104-V and J104-U
2. For a GEA 2 check, perform the following:
a. S/N LJ-1283 and after only: using a decade box or equivalent, simulate 1000 ohms into
right engine signal conditioner unit via right engine firewall connectors-pins J105-E and
J105-F.
b. Using a signal generator, inject a 100 mV RMS / 0Hz signal into the right engine signal
conditioner via left engine firewall connectors-pins, as follows:

S/N LJ-1063 thru LJ-1282: J105-F and J105-E

S/N LJ-1283 and after: J105-V and J105-U
3. Simulate the following frequency, and verify the indication and status:
Test Point (Hz)
Indication (pph)
Status
Configurations
100 +/- 10
green digital
all
140
4. Disconnect test equipment.
5. Ensure firewall connectors are reconnected.
6. Verify all engine parameters are displayed valid on the MFD with no Red X’s.
7. Continue to Section 9.
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7.5
GTX 33 Transponder
Original GTX 33 is Reinstalled
No software or configuration loading is required if the removed GTX 33 is re-installed. This does not include
units that were returned for repair as their software and configuration files are deleted during the repair
testing process. Continue to Section 7.5.3.
Original GTX 33 Installed in Opposite Locations for Troubleshooting
Transponder Configuration is required if the original GTX #1 and GTX #2 are installed in opposite locations.
Continue to Section 7.5.1.
New, Repaired, or Exchange GTX 33 is Installed
If a new, repaired, or exchange GTX 33 is installed, the correct software and configuration files must be
loaded to the unit. Continue to Section 7.5.1.
7.5.1
GTX 33 Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GTX (1 or 2 for unit replaced) - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Load the GTX33 ES Option File if ES Transponders are installed.
14. Continue to Section 7.5.2.
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7.5.2
Aircraft Registration Number Configuration
NOTE
There are two different procedures in this section, one for G1000 System Software Version
0636.05 and previous and one for G1000 System Software Version 0636.06 and
subsequent. Follow the procedure for your system software version.
7.5.2.1
System Software Version 0636.05 and Previous
1. On PFD1, go to the GTX page group then select the TRANSPONDER CONFIGURATION page.
2. Select or verify selected, XPDR1 is in the SELECT TRANSPONDER window.
3. Ensure that the ‘ADDRESS TYPE’ is ‘US TAIL’ under the ‘SET’ and ‘ACTIVE’ columns.
4. Activate the cursor and highlight the ‘ADDRESS’ field. Use the small/large FMS knobs to enter the
aircraft registration number.
Figure 7-5, Aircraft Registration
5. Once the correct registration number is entered, press the ENT key. The transponders are
configured.
6. Press the ENT key on PFD1 to acknowledge prompt.
7. Verify FLIGHT ID TYPE = SAME AS TAIL under SET and ACTIVE columns.
8. After completing transponder configuration, deactivate the cursor.
9. Continue to Section 7.5.3.
7.5.2.2
System Software Version 0636.06 and Subsequent
1. On PFD1, go to the AIRCRAFT CONFIGURATION page.
2. Turn on the cursor and enter the aircraft’s tail number in the AIRCRAFT REGISTRATION field.
Press the ENT key after entering the number to save.
3. Move the cursor to the ICAO ADDRESS field and enter the aircraft’s 24 bit ICAO address. This
field populates automatically with the entry of a “N” registration number. Press the ENT key after
entering the number to save.
4. If applicable, move the cursor to the IATA AIRLINE DESIGNATOR field and enter the airline’s
designator code. Press the ENT key after entering the number to save.
5. Move the cursor to the VFR CODE field and enter the desired code that will become active when
the VFR key on the GDU is pressed. Press the ENT key after entering the number to save.
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6. Press the “SET GTX1” softkey and acknowledge the GTX #1 save prompt by pressing the ”ENT
key.
7. Press the ENT key to acknowledge upload complete.
8. Press the “SET GTX2” softkey and acknowledge the GTX #2 save prompt by pressing the ENT
key.
9. Press the ENT key to acknowledge upload complete.
10. After completing transponder configuration, turn off the cursor.
11. Continue to Section 7.5.3.
7.5.3
GTX 33 Test
Operation of the GTX 33 Mode-S transponder is accomplished using PFD 1, PFD 2 or the MFD. Refer to
G1000 in King Air C90 Cockpit Reference Guide, listed in Table 1-2, for basic operation.
The integrated transponder/altitude reporting system must be verified in accordance with Title 14 of the
Code of Federal Regulations (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 Title 14 CFR Part 43
Appendix F for testing criteria.
If no other service is to be performed, continue to the return-to-service checks in Section 9.
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7.6
GDC 74B Air Data Computer
Original GDC 74B is Reinstalled
No software or configuration loading is required if the removed GDC 74B is re-installed. This does not
include units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Continue to Section 7.6.2.
Original GDC 74B Installed in Opposite Locations for Troubleshooting
No software loading is required if the original GDC #1 and GDC #2 are installed in opposite locations.
Continue to Section 7.6.2.
New, Repaired, or Exchange GDC 74B is Installed
If a new, repaired, or exchange GDC 74B is installed, the correct software and configuration files must be
loaded to the unit. Continue to Section 7.6.1.
New GDC 74B Configuration Module is Installed
The correct configuration files must be loaded if the GDC 74B configuration module has been replaced.
Continue to Section 7.6.1.
7.6.1
GDC Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GDC (1 or 2 for unit replaced) - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Turn off the G1000 system.
14. Remove the Software Loader card.
15. Turn on the G1000 system in normal mode.
16. Continue to Section 7.6.2.
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7.6.2
Air Data Test (GDC 74B and STBY Instruments)
The G1000 system must be maintained in accordance with the G1000 System Maintenance Manual listed
in Table 1-3 and appropriate regulations. When the GDC 74B is tested in accordance with 14 CFR Part
43, Appendix E, note the following exceptions:

For paragraph (b)(1)(i) Scale Error, use Table 7-1 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 regulatory
required testing. This test must be performed on both pilot and copilot systems with a calibrated Air Data
Test Set (ADTS) with a combined accuracy/repeatability specification of less than ±20 feet for the test
altitude range.
NOTE
Allow both GDC 74B units to stabilize for 15 minutes while powered before conducting the
following tests.
1. 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.
2. Perform pitot static system leak check of each system as specified below. Reference King Air 90
Series Maintenance Manual, 34-00-00.
a. Perform a leak test of the aircraft pitot plumbing at an altitude of 30,000 ft and airspeed of 226
knots. When pitot pressure has stabilized, verify the cumulative leak rate is 1 knot/minute or
less.
b. Perform a leak test of the aircraft static plumbing at an altitude of 30,000 feet and an airspeed
of 120 knots. When static pressure has stabilized, verify the cumulative leak rate is 200
ft/minute or less.
3. Verify that the PFD1 altimeter baro setting is set to 29.92 in Hg (1013.25 mb).
4. Restart 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 in AIR DATA 1 and
AIR DATA 2 windows.
5. Place the MFD in reversionary mode by pressing the red “display backup” button on the GMA1.
The Baro setting can then be read from the MFD. The Baro setting on the MFD will apply to the
values displayed on PFD1 in configuration mode for both ADC1 and ADC2 regardless of the sensor
selected on the MFD. The copilot's display can be ignored for this test.
6. Simulate the altitudes and airspeeds in the order as shown in Table 7-1. Wait for ADTS to report
that target values have been achieved before continuing.
7. On Table 7-1, record the altitude (B ALT) displayed on PFD1 for AIR DATA 1 and AIR DATA 2 for
each condition.
8. On Table 7-1, record the airspeed (IAS) displayed on PFD1 for AIR DATA 1 and AIR DATA 2 for
each condition.
9. Verify that the indicated altitudes and airspeeds are within the tolerances specified in the table.
10. Continue to Section 7.6.3.
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.
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Table 7-1, Airspeed and Altitude Table
Test
Point
Altitude
Airspeed
PFD1
PFD2
STBY
PFD1
PFD2
STBY
Tolerance
Tolerance
Tolerance
Tolerance
Tolerance
Tolerance
Actual
+/-20
Actual
+/-20
Actual
+/-20
Actual
+/-2
Actual
+/-2
Actual
+/-5
+/-20
+/-20
+/-20
N/A
N/A
N/A
+/-20
+/-20
+/-20
+/-2
+/-2
+/-5
+/-20
+/-20
+/-20
+/-2
+/-2
+/-5
+/-25
+/-25
+/-25
+/-2
+/-2
+/-5
+/-30
+/-30
+/-30
+/-2
+/-2
+/-5
+/-30
+/-30
+/-30
+/-2
+/-2
+/-5
+/-35
+/-35
+/-35
+/-2
+/-2
+/-5
+/-40
+/-40
+/-40
+/-2
+/-2
+/-5
8000
+/-60
+/-60
+/-60
+/-2
+/-2
+/-5
80
10000
+/-80
+/-80
+/-80
+/-2
+/-2
+/-5
ALT
AS
-1000
50
0
N/A
500
50
1000
50
1500
50
2000
50
3000
80
4000
80
6000
80
120
(continued next page)
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12000
+/-90
+/-90
+/-90
+/-2
+/-2
+/-5
120
14000
+/-100
+/-100
+/-100
+/-2
+/-2
+/-5
150
16000
+/-110
+/-110
+/-110
+/-2
+/-2
+/-5
180
18000
+/-120
+/-120
+/-120
+/-2
+/-2
+/-5
210
20000
+/-130
+/-130
+/-130
+/-2
+/-2
+/-5
210
22000
+/-140
+/-140
+/-140
+/-2
+/-2
+/-5
100
25000
+/-155
+/-155
+/-155
+/-2
+/-2
+/-5
100
30000
+/-180
+/-180
+/-180
+/-2
+/-2
+/-5
100
Aircraft S/N: _____________________
ADTS
Date: __________________
Operator:
___________________
ADC1
ADC2
Make: _______________________
Model: GDC 74B
Model: GDC 74B
Model: _______________________
P/N: 011-01110-____
P/N: 011-01110-____
S/N: ___________________
S/N: ___________________
S/N: _______________________
Cal.Date: ______________________
Leak Check Static System at 30,000 ft, 120 kts (pass if <200 ft in 1 min)
Pilot: _____________ Feet/Min
Copilot: ___________ Feet/Min
Leak Check Pitot System at 226 kts (pass if <1 KIAS in 1 min)
Pilot: _____________ KIAS/Min
Copilot: ___________ KIAS/Min
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7.6.3
Static Port Vertical Speed (Rate of Climb) Test
1. Cycle power on PFD1 and start in normal mode.
2. Command ADTS to change the altitude at the rates shown in the table below.
3. Wait for ADTS to report that target rates have been achieved.
4. Verify that the Rate of Climb reported by the Vertical Speed field on PFD1 and PFD2 are within
the tolerances specified in Table 7-2:
Table 7-2, Vertical Speed Table
Vertical Speed, feet/minute
Allowed tolerance, ±feet/minute
6000
100
2000
100
1000
50
500
45
200
45
0
N/A (No VS Display)
-200
45
-500
45
-1000
50
-2000
100
-6000
100
5. Continue to Section 7.6.4.
7.6.4
OAT Probe Check
1. Verify OAT box is not Red-X’d on PFD1 and PFD2.
2. Verify that the outside air temperature (OAT) measurement shown on PFD1 and PFD2
indicates ambient temperature within +/- 2ºC of a calibrated standard.
3. Continue to Section 9.
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7.7
GRS AHRS / GMU 44 Magnetometer
NOTE
References to GRS in this section can imply either Garmin AHRS Model GRS 77 or GRS
7800. Differences to a specific GRS model will be identified with the applicable GRS model
number.
Original GRS is Reinstalled
If the original GRS was reinstalled, then no software or configuration file 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 Section 7.7.7.
If the GRS rack was removed or loosened, recalibration is required. Continue to Section 7.7.2.
Original GRS Installed in Opposite Locations 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 or configuration loading is required.
If the GRS rack(s) was not removed or loosened, continue to Section 7.7.7.
If the GRS rack(s) was removed or loosened, recalibration is required. Continue to Section 7.7.2.
New, Repaired, or Exchange GRS is Installed
If a new, repaired, or exchange GRS is installed, then software must be loaded and the unit must be
calibrated. Continue to Section 7.7.1.
New GRS Configuration Module is Installed
If the GRS 77 configuration module was replaced, no software or configuration file loading is required but
recalibration is required. Continue to Section 7.7.2.
If the GRS 7800 configuration module was replaced, configuration file loading is required and recalibration.
Continue to Section 7.7.1.
Original GMU 44 is Reinstalled
If the original GMU 44 was reinstalled in its original location, then no software or configuration file 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 Section 7.7.7.
Original GMU 44 Installed in Opposite Locations 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 or configuration file loading is required. However, performing the Magnetometer
Calibration Procedure is required. Continue to the Section 7.7.5.
New, Repaired, or Exchange GMU 44 is Installed
If a new, repaired, or exchange GMU 44 is installed, then software must be loaded. Continue to Section
7.7.1 for software loading.
7.7.1
GRS/GMU Software and Configuration Loading
NOTE
There are two different procedures in this section, one for G1000 System Software Version
0636.05 and previous and one for G1000 System Software Version 0636.06 and
subsequent. Follow the procedure for your system software version
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7.7.1.1
System Software Version 0636.05 and Previous
GRS 77 was the only AHRS option for this software version. The GRS7800 will not load with this version.
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GRS (1 or 2 for unit replaced, skip if GMU replaced) - Software file.

GMU (1 or 2 for unit replaced, skip if GRS replaced) - Software file
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Continue to Section 7.7.2.
7.7.1.2
System Software Version 0636.06 and Subsequent
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90 Options’ in the GROUP field.
Press the ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 - GRS77 AHRS
Option” or “King Air C90 - GRS7800 AHRS Option” file for the unit installed and press the ENT
key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GRS (1 or 2 for unit replaced, skip if GMU replaced) - Software and Configuration files.
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
GMU (1 or 2 for unit replaced, skip if GRS replaced) - Software and Configuration files
10. After the GRS or GMU files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete.
13. Continue to Section 7.7.2.
7.7.2
GRS/GMU Calibration Procedures
GRS/GMU Recalibration Criteria
There following calibration procedures are provided for the GRS and GMU 44:

Pitch/Roll Offset: (Procedure A1, PROVIDED IN SECTION 7.7.3)

Magnetometer Calibration: (Procedure B, PROVIDED IN SECTION 7.7.5)

Engine Run-Up Vibration Test: (Procedure D, PROVIDED IN SECTION 7.7.6)

Magnetometer Interference Test: (Procedure E, PROVIDED IN SECTION 5.14.4)
When ready to perform the procedures, shut the PFDs and MFD off by pulling the PFD and MFD circuit
breakers. Restart all displays in configuration mode. Follow the steps given for each procedure on-screen
at the GRS/GMU CALIBRATION page. Note that the CALIBRATE command cannot be selected and
activated until the installer acknowledges all required steps have been carried out by pressing the ENT key
on each step.
Table 7-3, Required GRS/GMU Calibrations
Calibrations Required
Condition
Procedure A1:
GRS Pitch/Roll
Offset
Either GMU 44 was removed and
reinstalled. (no change in serial
number)
X
GRS AHRS was removed and/or
replaced. The mounting tray was NOT
removed and the mounting tray bolts
were NOT loosened.
GRS AHRS Configuration Module was
replaced.
Procedure D:
Engine Run-up
Vibration
Test
None Required.
Continue to GRS/GMU Test section.
GMU 44 was replaced with new unit.
(New serial number)
GRS AHRS was removed and/or
replaced. The mounting tray WAS
removed and/or mounting tray bolts
WERE loosened.
Procedure B:
GRS/GMU
Magnetic
Calibration
None Required.
Continue to GRS/GMU Test section.
X
X
X
X
X
X
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7.7.3
Procedure A1: GRS AHRS Pitch/Roll Offset Calibration
This procedure must be performed for both GRS units installed in the aircraft. This first procedure must be
carried out with the engine off.
Figure 7-6, GRS Pitch/Roll Offset Calibration Page
1. Level the aircraft to within 0.25° of zero pitch and zero roll using a digital level. (Follow instructions
in King Air Model 90 Series Maintenance Manual, listed in Table 1-2, for leveling)
2. Start the PFD1 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)
4. Ensure that the No. 1 GRS is selected in the SELECT GRS UNIT window on the PFD.
5. Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH/ROLL
OFFSET.
6. Press the ENT key.
7. Use the cursor to highlight the BEFORE CALIBRATION window.
8. Follow the checklist items displayed on the PFD and press the ENT key as each step is completed
or confirmed.
9. When the CALIBRATE field is blinking, press the ENT button to begin the procedure.
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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 1 through 12 for GRS #2.
7.7.4
Compass Rose Evaluation of Magnetic Disturbances for Magnetometer Calibration
Procedure (Optional)
NOTES
The Magnetometer Calibration Procedure that follows in Section 7.7.5 (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 this Section.
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 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 a second time turning counter-clockwise. Both times, the
procedure should be conducted as described in Section 7.7.5 of this document, with the exception that the
direction of turn for the second calibration procedure is counter clockwise.
Upon completion of the Magnetometer Calibration Procedure in the clockwise and counter-clockwise
direction, if the PFD1 GRS / GMU CALIBRATION config page displays the “CALIBRATION SUCCESSFUL
/ SITE IS CLEAN” message, 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, upon completion of the Magnetometer Calibration Procedure in either of the two directions, the PFD
displays either the “MAG FIELD AT SITE NOT UNIFORM”, or “MAG FIELD AT SITE DIFFERS FROM IGRF
MODEL” message, then the site contains magnetic disturbances that are too large.
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7.7.5
Procedure B: GRS AHRS/GMU 44 Magnetic Calibration
NOTE
Procedure A-1 (Section 7.7.3) must first be successfully accomplished before performing
Procedure B, only for situations where the GRS was replaced with a new unit.
Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free
of environmental magnetic disturbances. Attempting to carry out this maneuver on a typical ramp area may
not yield a successful calibration. The accuracy of the AHRS cannot be guaranteed if this calibration is not
performed on a magnetically clean compass rose. If the compass rose condition is not known, it is
recommended that the technician follow the guidance in Section 7.7.4.
1. Start the aircraft engine following the procedures referenced in the appropriate King Air AFM or
AFMS as listed in Table 1-2.
2. After aircraft engine startup, taxi the aircraft to a properly calibrated compass rose.
3. At the compass rose, align the aircraft to a heading of magnetic north (5°).
CAUTION
CALIBRATION PROCEDURE B MUST BE CARRIED OUT ON A COMPASS ROSE IN
ORDER TO GUARANTEE MEASUREMENTS FREE OF ENVIRONMENTAL MAGNETIC
DISTURBANCES. ATTEMPTING TO CARRY OUT THIS MANEUVER ON A TYPICAL
RAMP AREA MAY NOT YIELD A SUCCESSFUL CALIBRATION. THE ACCURACY OF
THE AHRS CANNOT BE GUARANTEED IF THIS CALIBRATION IS NOT PERFORMED
ON A MAGNETICALLY CLEAN COMPASS ROSE OR EQUIVALENT.
NOTE
This procedure provides instructions for calibrating both GRS magnetometers separately.
It is acceptable to calibrate both GRS magnetometers simultaneously by putting both PFD1
and PFD2 in configuration mode and following the procedure below, using PFD1 to
calibrate GRS1 and PFD2 to calibrate GRS2.
4. Restart the PFD1 and MFD 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:
a) 9
b) 10
c) 11
d) 12 (far right softkey)
7. Press the FMS small knob to turn on the cursor in the SELECT GRS UNIT window. The FMS small
knob can now be turned to highlight either GRS1 or GRS2 for calibration. Press the ENT key after
highlighting the desired GRS unit to calibrate.
8. Move the cursor to the SELECT PROCEDURE window. Using the FMS small knob, highlight
MAGNETOMETER and press the ENT button.
9. Move the cursor to 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 then enters its normal operational mode. Press the ENT button on the PFD to
conclude this procedure.
15. Repeat steps 4 through 14 for GRS2.
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7.7.6
Procedure D: Engine Run-Up Vibration Procedure
NOTE
Calibration Procedure D is performed in order to guarantee that the AHRS mounting is
sufficiently rigid and insensitive to vibration. This procedure must be performed for both
GRS units installed in the aircraft. Calibration Procedures A1 and B (Sections 7.7.3 and
0 respectively) are not required prior to this procedure.
Figure 7-7, Engine Run-Up Test Page
1. Press the FMS small knob to highlight GRS1. The FMS small knob can now be turned to select
either GRS1 or GRS2 for calibration. Press the ENT key after selecting the desired GRS unit to
calibrate. The SELECT PROCEDURE field is not blinking.
2. Initiate the AHRS engine run-up vibration test procedure by performing the following steps:
a) Select the ENGINE RUN-UP TEST procedure and press the ENT key.
b) Follow the checklist items displayed on the PFD, and press the ENT key as each one is
completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin
the procedure.
3. The PFD display instructs the operator to gradually increase power from idle to full throttle and back
to idle over a period of 2-4 minutes.
4. When the operator has completed the engine run-up and the engine 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.
5. The PFD informs the operator if the installation has passed or failed the vibration test. If the test
fails, the specific measurements causing the failure are identified and associated numeric values
are displayed on the PFD.
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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 GRS and/or GMU caused by neighboring equipment and/or
supports.
b) Mounting screws and other hardware for GRS and/or GMU not firmly attached.
c) GRS connector not firmly attached to unit.
d) Cabling leading to GRS or GMU not firmly secured to supporting structure.
e) An engine / propeller that is significantly out of balance.
6. Press the ENT key on the PFD to conclude this procedure
7. Repeats steps 1 through 6 for GRS #2
8. Continue to Section 7.7.7.
7.7.7
GRS/GMU Test
The aircraft can now be taxied back and the engine can be shut down for final testing. Restart the displays
in normal mode to conduct final system checks. When the PFDs power up in normal mode, the AHRS
attitude and heading information displayed should become valid within 1 minute of power-up, as shown in
Figure 7-8 (provided both GPS receivers have a valid position; if GPS is unavailable, AHRS initialization
may take as long as 2 minutes).
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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7.8
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/69A SXM 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 Section 7.8.2.
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. Continue
to Section 7.8.1.
7.8.1
GDL 69A/69A SXM Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90 Options’ in the GROUP field.
Press the ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 – GDL69A
Legacy” or ”King Air C90 – GDL69A SXM” file for the unit installed and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:
10. GWX - Software and Configuration files.
11. Press the CLR ALL softkey.
12. Using the FMS knob and ENT key, select the following files to load:

GDL - Software and Configuration files.
13. After the files are selected, press the LOAD softkey.
14. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
15. Press the ENT key to acknowledge upload complete.
16. Turn off the G1000 system.
17. Remove the Software Loader card.
18. Turn on the G1000 system in normal mode.
19. Go to the MFD AUX - XM INFORMATION page.
20. Press the INFO softkey.
21. Record the Data and Audio Radio ID numbers and contact SiriusXM for activation. Refer to the
GDL69A XM Satellite Radio Activation Instructions for information.
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22. Continue to Section 7.8.2.
7.8.2
GDL 69A/69A SXM Test
This test must be performed where the aircraft can receive SiriusXM signals.
1. Go to the MFD AUX - XM INFORMATION page.
2. Verify Channel 1 is displayed and can be heard over the headsets.
3. Press the INFO softkey.
4. Verify the Radio ID numbers are displayed.
5. Check the PFD ALERT window for Manifest error messages.
6. If the unit appears deactivated but had a current subscription, reactive by entering the Radio ID
numbers at https://care.siriusxm.com/refresh.
7. If the unit appears deactivated and no subscription can be verified, contact SiriusXM for activation.
Refer to the GDL69 Series SiriusXM Satellite Radio Activation Instructions in Table 1-3 for
information.
8. Continue to Section 9.
7.9
GSA 80/81 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 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. Continue to Section 7.9.1.
7.9.1
GSA Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Check and record if the aircraft has a Raisbeck STC that lowers Vmo speed to 208kts.
3. Insert the G1000 Software Loader card in the top slot of PFD1.
4. Apply system power and place all displays in Configuration Mode.
5. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
6. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
7. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
8. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
9. Press the CLR ALL softkey.
10. Using the FMS knob and ENT key, select the following files to load:

(PITCH, PITCH TRIM, ROLL, or YAW) (011-00878-XX) (for unit replaced) - Software and
Configuration files.

(PITCH, PITCH TRIM, ROLL, or YAW) CERT (for unit replaced) - Software file
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11. After the files are selected, press the LOAD softkey.
12. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
13. Press the ENT key to acknowledge upload complete
14. Move the cursor to the GROUP window. Highlight “C90-Options” file and press the ENT key.
15. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 - GSM 85A
Servo Mounts” or “King Air C90 - GSM 86 Servo Mounts” file for the units installed and press
the ENT key.
16. Press the CLR ALL softkey.
17. Using the FMS knob and ENT key, select the following file to load:

(PITCH, PITCH TRIM, ROLL, or YAW) SERVO (for unit replaced) - Configuration file.
18. After the file is selected, press the LOAD softkey.
19. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
20. Press the ENT key to acknowledge upload complete.
21. If the aircraft has a Raisbeck STC that lowers Vmo speed to 208kts, move the cursor to the GROUP
window. If the aircraft does not have a Raisbeck STC lowering Vmo, skip to Step 29.
22. Highlight “C90-Weight and Airspeed” and press the ENT key.
23. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 – 208kt Vmo
Airspeed Tape Marking” and press the ENT key.
24. Press the CLR ALL softkey.
25. Using the FMS knob and ENT key, select the following file to load:

(PITCH, PITCH TRIM, ROLL, or YAW) CERT (for unit replaced) - Software file.
26. After the file is selected, press the LOAD softkey.
27. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
28. Press the ENT key to acknowledge upload complete.
29. Turn off the G1000 system.
30. Remove the Software Loader card.
31. Turn on the G1000 system in normal mode.
32. Continue to Section 9 for testing.
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7.10 GCU 475 FMS Controller
Original GCU 475 Reinstalled
No software or configuration loading is required if the removed GCU 475 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 Section 7.10.2.
New, Repaired, or Exchange GCU 475 Installed
If a new, repaired, or exchange GCU 475 is installed, the correct software and configuration files must be
loaded to the unit. Continue to Section 7.10.1.
7.10.1 GCU Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GCU - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Turn off the G1000 system.
14. Remove the Software Loader card.
15. Turn on the G1000 system in normal mode.
16. Continue to Section 7.10.2.
7.10.2 GCU 475 Test
Perform the following key and knob presses and knob rotations on the GCU 475, 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
NAVIGATION MAP page.
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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.
12. Press the
key to display the DIRECT TO page.
13. Use the keypad to type KIXD (or alternate local airport) and verify KIXD is displayed on the MFD.
14. Press the SPC key to add a space and then the BACK key to delete the space.
15. Press the CLR key to clear the field.
16. Type K34 and then press the ENTER key twice. Verify that the flight path to K34 is displayed on
the map.
17. Press the FPL key to open the ACTIVE FLIGHT PLAN page. Press the FPL key again to close it.
18. Press the PROC key to open the PROCEDURES page. Press the PROC key again to close it.
19. Press the MENU key to open the MENU page. Press the MENU key again to close it.
20. Continue to Section 9.
7.11 GMC 710 AFCS Controller
Original GMC 710 Reinstalled
No software or configuration loading is required if the removed GMC 710 is re-installed. This does not
include units that were returned for repair as their software and configuration files are deleted during the
repair testing process. Continue to Section 7.11.2.
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. Continue to Section 7.11.1.
7.11.1 GMC Software and Configuration Loading
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
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9. Using the FMS knob and ENT key, select the following files to load:

GMC - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Turn off the G1000 system.
14. Remove the Software Loader card.
15. Turn on the G1000 system in normal mode.
16. Continue to Section 7.11.2.
7.11.2 GMC 710 Test
Perform a basic operational check on the GMC 710. The following knob, wheel and key presses and
rotations are to be performed on the GMC 710.
1. Ensure the G1000 is operating in normal mode and the autopilot is operational.
2. Press the FD key a few times; verify the Flight Director display on PFD1 toggles on and off. Leave
the flight director displayed.
3. Press the XFR key and verify the white-illuminated arrowhead points in the opposite direction.
Verify the green arrow displayed at the top of PFD 1 also points in the same direction.
4. Rotate the ALT SEL knob and verify the altitude bug, displayed on PFD 1 altitude tape, moves.
5. Rotate the UP/DN wheel and verify the flight director moves in the vertical direction.
6. Press the HDG key and verify the white illumination appears next to the key. Rotate the HDG knob
and verify the heading bug, displayed on PFD 1 compass card, moves and the flight director follows.
7. Press the HDG knob and verify the heading bug centers.
8. Press the YD key and verify the white illumination appears next to the key.
9. Press the VS key and verify the white illumination appears next to the key.
10. Press the FLC key and verify the white illumination appears next to the key.
11. Continue to Section 9.
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7.12 GWX 68/70 Weather Radar
NOTE
References to GWX in this section can imply either Garmin Weather Radar Model GWX
68 or GWX 70. Differences to a specific GWX model will be identified with the applicable
GWX model number.
Original GWX Reinstalled
No software or configuration loading is required if the removed GWX 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 Section 7.12.2.
New, Repaired, or Exchange GWX Installed
If a new, repaired, or exchange GWX is installed, the correct software and configuration files must be loaded
to the unit. Continue to Section 7.12.1.
7.12.1 GWX Software and Configuration Loading
NOTE
There are two different procedures in this section, one for G1000 System Software Version
0636.05 and previous and one for G1000 System Software Version 0636.06 and
subsequent. Follow the procedure for your system software version.
7.12.1.1 System Software Version 0636.05 and Previous
The GWX 68 was the only radar used with these versions. The GWX 70 will not load with these versions.
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90’ in the GROUP field. Press the
ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 Baseline” file
and press the ENT key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GWX - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.
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
“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Turn off the G1000 system.
14. Remove the Software Loader card.
15. Turn on the G1000 system in normal mode.
16. Continue to Section 7.12.2.
7.12.1.2 System Software Version 0636.06 and Subsequent
1. Obtain the correct G1000 System Software Loader card for the software version installed in the
system.
2. Insert the G1000 Software Loader card in the top slot of PFD1.
3. Apply system power and place all displays in Configuration Mode.
4. On PFD1, press the NO softkey at “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt.
5. On PFD1, go to the SYSTEM UPLOAD page using the small FMS knob.
6. Activate the cursor and use the small FMS knob to highlight ‘C90 Options’ in the GROUP field.
Press the ENT key to select.
7. Once an airframe type is selected the cursor moves to the ITEM window. Rotate the small FMS
knob to activate the drop-down menu. Move the cursor to highlight “King Air C90 - GWX 68 Radar
Option” or ”King Air C90 - GWX 70 Radar Option” file for the unit installed and press the ENT
key.
8. Press the CLR ALL softkey.
9. Using the FMS knob and ENT key, select the following files to load:

GWX - Software and Configuration files.
10. After the files are selected, press the LOAD softkey.
11. Observe software loading progress and verify software load completes without errors as indicated
by the following:

Green “PASS” in the Software and Configuration column for all items.

“Upload Complete………….COMPLETE” in the summary box.
12. Press the ENT key to acknowledge upload complete
13. Turn off the G1000 system.
14. Remove the Software Loader card.
15. Turn on the G1000 system in normal mode.
16. Continue to Section 7.12.2.
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7.12.2 GWX Test
Operation of the GWX Weather Radar is accomplished using the MFD/GCU 475. Refer to G1000 King Air
C90 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 Weather Radar page.
2. Select the MODE softkey.
3. Select the STANDBY softkey to initiate the one minute warm-up period. Verify the radar enters the
standby mode after the warm-up is complete.
4. Select the MODE softkey.
5. Select the WEATHER softkey. After reading the CAUTION statement, turn the large FMS knob to
select YES. Press the GCU ENT key.
6. Select the STAB ON softkey to activate antenna stabilization or select the STAB OFF softkey to
deactivate. Verify the current stabilization condition is shown in the upper right of the weather radar
display.
7. Select the BACK softkey.
8. Select the VERTICAL softkey.
9. Select the TILT softkey to activate the cursor in the TILT field.
10. On the GCU, turn the small FMS knob to select the desired antenna tilt angle. Press the GCU ENT
key. Press the GCU FMS knob to remove the cursor.
11. Select the GAIN softkey to activate the cursor in the GAIN field.
12. On the GCU, turn the small FMS knob to adjust the gain for the desirable level. Verify the gain
setting 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.
16. Continue to Section 9.
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8
G1000 Function and Interface Checks
8.1
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. This check can also be accomplished
in conjunction with the Weight on Wheels and Low Speed Awareness Band Test in Section 8.5
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.
1. Conduct the Landing Gear Retraction, Warning Horn check as stated in the King Air Model C90
Series Maintenance Manual, listed in Table 1-2.
2. Verify that the aural tone is played through the G1000 audio system and through both cockpit
speakers.
8.2
SiriusXM Audio Suppression Check for Aircraft with a Tone Generator
This procedure is applicable only to aircraft that have SiriusXM radio subscriptions.
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.
1. Select the AUX – XM RADIO page on the MFD.
2. Plug a set of headphones into the pilot and co-pilot stations and verify that you can hear the
SiriusXM radio playing in both channels.
3. Restart PFD1 in configuration mode.
4. Select page 4, Audio Alert Configuration, from the Systems menu by rotating the small FMS knob.
5. Select PLAY for the following audio and verify SiriusXM audio is temporarily muted while alert audio
is being played.
 GEAR
 STALL
6. Verify SiriusXM audio is temporarily muted in both pilot and co-pilot stations while alert audio is
being played.
7. Restart PFD1 in normal mode.
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WARNING
The following step requires moving the stall warning vane. Use caution when
handling the stall warning vane.
8. While monitoring pilot and copilot SiriusXM audio, actuate the stall warn transducer on the left wing
leading edge in an up position (for those aircraft equipped with a Safeflight computer, actuate in
the aft position), verify the following:
 Stall warning tone is active.
 Pilot and copilot SiriusXM audio is muted.
9. Release the stall warning transducer in the left wing leading edge, verify the following:
 Stall warning tone is silenced.
10. Verify SiriusXM audio returns.
8.3
SiriusXM Audio Suppression Check for Aircraft Without a Tone Generator
GDL69A/69A SXM discrete inputs from stall warning and landing gear control systems as detailed in G1000
Wiring Diagram are required for aircraft not equipped with a tone generator.
NOTE
This procedure is applicable only to aircraft equipped without 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.
WARNING
The following procedure requires operation of the aircraft landing gear. Observe all
applicable safety precautions. Before working in any landing gear wheel well,
ensure that all landing gear and gear door safety devices are installed. Exercise
extreme caution while working around landing gear or in landing gear wheel wells.
8.3.1
Gear Warning Discrete
1. Reference the King Air C90 Maintenance Manual listed in Table 1-2 and jack aircraft to allow
operation of landing gear.
2. Select the AUX – XM RADIO page on the MFD.
3. Plug a set of headphones into the pilot and co-pilot stations and verify that you can hear the
SiriusXM radio playing in both channels. Adjust volume to a comfortable level.
4. Ensure both left and right throttles are at IDLE position.
5. Retract landing gear to the full up and locked position.
6. Verify the landing gear warning horn is active.
7. Verify SiriusXM audio is muted in the pilot and co-pilot stations.
8. Increase both left and right throttles forward of IDLE position (towards takeoff position).
9. Verify landing gear warning horn is silenced and SiriusXM audio returns.
10. Extend landing gear to the full down and locked position and return both throttles to idle position.
11. Aircraft may be removed from jacks to accommodate other activities as required.
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8.3.2
Stall Warning Discrete
1. Select the AUX – XM RADIO page on the MFD.
2. Plug a set of headphones into the pilot and co-pilot stations and verify that you can hear the
SiriusXM radio playing in both channels.
3. Ensure STALL WARNING circuit breaker is closed.
4. While monitoring pilot and copilot SiriusXM audio, actuate the stall warn transducer on the left wing
leading edge in an up position, verify the following:
WARNING
The stall warning transducer is heated at all times. Use a heavy glove to prevent a
burn.
 Stall warning tone is active and annunciation is illuminated.
 Pilot and copilot SiriusXM audio is muted.
5. Release the stall warning transducer in the left wing leading edge, verify the following:
 Stall warning tone is silenced and annunciation extinguishes.
 Pilot and copilot SiriusXM audio returns.
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8.4
TAWS B Functional Check
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”.
NOTE
If TAWS-B has not been enabled, the title will read “MAP – TERRAIN PROXIMITY” or
“MAP – TERRAIN”. Refer to section 3.4.24 for enabling TAWS-B.
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.
5. Press the GCU MENU button again and select “Inhibit TAWS” from the pop-up menu and press
the ENT key. Verify “TAWS INHB” is displayed on PFD 1, PFD 2 and MFD.
6. Press the GCU MENU button again and select “Enable TAWS” from the prop-up menu and press
the ENT key. Verify the “TAWS INHB” annunciation on the PFDs and MFD has extinguished.
7. With a GPS position acquired, shield or disconnect the GPS antennas to remove the GPS signal.
8. Verify “No GPS Position” shows on the MFD and the “TAWS N/A” and “LOI” annunciations show
on the PFDs.
9. Reconnect or remove the shield from the GPS antennas.
10. Verify the MFD “No GPS Position” and PFD “TAWS N/A” and “LOI” annunciations are removed
once the GPS satellites are acquired.
11. Open PFD1 PRI and PFD1 SEC circuit breakers.
12. Start PFD1 in configuration mode.
13. On PFD1, go to the AUDIO ALERT CONFIGURATION page.
14. Ensure cockpit speaker is selected ON.
15. Use the PFD1 FMS knob to highlight each of the following messages then select PLAY. Verify each
of the following audio messages can be played:
Caution Obstacle (2x)
Caution Terrain (2x)
Don’t Sink
Obstacle Ahead (2x)
Obstacle Ahead, Pull-Up (2x)
Obstacle (x2); Pull-Up (2x)
Five Hundred
Pull-Up
Sink Rate
Terrain Ahead, Pull-Up (2x)
Terrain Ahead (2x)
Too Low, Terrain
Terrain (2x); Pull-Up (2x)
16. Open PFD1 PRI and PFD1 SEC circuit breakers
17. Start PFD1 in normal mode.
18. If no other service is to be performed, continue to the return-to-service checks in Section 9.
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8.5
Weight on Wheels and Low Speed Awareness Band Test
This check is accomplished to verify the integrity of the wiring interface between the right landing gear
safety switch assembly and the No. 1 and No. 2 GIA inputs (Discrete IN* 2A).
1. Ensure aircraft is positioned with weight on wheels.
2. Apply external power to the aircraft. Set BAT and AVIONICS MASTER switches to ON and wait for
all aircraft and avionics systems to complete their initialization and begin operating normally.
3. Check that the airspeed fields are valid within 2 minutes of power up on both PFD1 and PFD2.
4. Verify the Low Speed Awareness Band is NOT displayed in the airspeed field on 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 XM Audio Suppression Tests in this Section.
5. Place the airplane on jacks (Ref. Maintenance Manual Chapter 7-00-00) with the wheels clear of
the ground.
6. Verify the Low Speed Awareness Band (red band) at the low end of the airspeed tape on PFD1
and PFD2 (See Figure 8-1).
7. Remove airplane from jacks.
8. If no other service is to be performed, continue to the return-to-service checks in Section 9.
Figure 8-1, Low Speed Awareness Band Symbolization
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9
System Return to Service Procedure
After installing new system software or reinstalling any G1000 LRU, verify the correct LRU software part
numbers and versions against the numbers listed on the General Arrangement drawing, listed in Table 1-2.
To check an LRU software part number and/or version, follow the procedure defined in Section 3.5.1.
IMPORTANT
It is essential that the software versions be checked and matched against the listed
versions in the General Arrangement drawing listed in Table 1-2. Software
Configuration is a critical part of the G1000 operation and must be verified before
returning an aircraft to service.
9.1
Backup Path System Testing
This final checkout tests various secondary communications paths in the G1000 to ensure that the paths
function correctly. Additional aircraft systems checks are also performed in this section. Perform the
following steps and verify the results of each test.
9.1.1
GPS Failure Test
NOTE
Depending upon aircraft status and configuration, various other messages and alerts may
be present on GDUs during the failure tests
Step
Desired Result
Single GPS Failure Conditions:
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 page 4.
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 page 4.
6. Check for desired results.
7. Remove shroud from the GIA 2 GPS
antenna.
GPS Failure – For each of the specified GPS failure
conditions, the following shall remain valid on the PFD
throughout the procedure:

Attitude and Heading from AHRS.

Airspeed, Altitude, Vertical Speed, and OAT from
Air Data Computer.

GPS Course Deviation Indicator remains valid on
PFD.
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 Conditions:
1. Ensure GPS satellites are acquired.
2. Cover both GPS antennas. Verify loss of
signal on MFD AUX page 4.
3. Check for desired results.
4. Remove shrouds from GPS antennas.
5. Allow both receivers to re-acquire satellite
signals before continuing.
Dual GPS Failure - For a dual GPS failure, 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.

No GPS Position 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, DR annunciation removed,
& GPS data magenta).
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9.1.2
GIA Failure Test
Step
Desired Result
GIA 1 Failure Conditions:
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.

NAV 1 and COMM1 tuning fields on PFD1 and
PFD2 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 PFD1
and PFD2.

AHRS and ADC data remain valid on PFD1 and
PFD2.

NAV2 and COMM2 tuning fields on PFD1 and
PFD2 are invalid (red X).

L/R engine data remains valid.

XPDR2 is Inoperative.

GMA2 Is Inoperative.

AHRS2 is using backup GPS source.

AHRS1 not receiving backup GPS Information.

An amber BOTH ON GPS1 is displayed on PFD1
and PFD2.

AHRS and ADC data remain valid on PFD1 and
PFD2.
GIA 2 Failure Conditions:
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 Conditions:
1. Open GIA1 primary and secondary CBs and
GIA 2 CB.
2. Check for desired results.
3. Restore power to both GIA units.
Dual GIA Failure – For a dual GIA failure, the following
shall occur:

COM1/NAV1 & COM2/NAV2 fields flag invalid.

GPS CDI flags DR on PFD

NAV1 & NAV2 CDI loses deviation bar.

XPDR field flags invalid on PFD.

Engine Instrument field flags invalid on MFD.

All AHRS & ADC fields remain valid.

Red AFCS status annunciation given.

TAWS FAIL annunciation given.*

ADF/DME windows flag invalid.*
*If equipped.
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9.1.3
Display Failure Test
Step
Desired Result
MFD Display Failure Conditions:
1. Open MFD CB.
2. Verify desired results.
3. Close MFD CB.
The following shall occur when power is removed from
the MFD:
PFD2 Display Failure Conditions:
1. Open PFD 2 CB.
2. Verify desired results.
3. Close PFD 2 CB.
PFD1 Display Failure Conditions:
1. Open PFD 1 PRI and PFD1 SEC circuit
breakers.
2. Verify desired results.
3. Close PFD 1 PRI and PFD1 SEC circuit
breakers.
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
MFD goes blank.

All PFD1 and 2 primary flight information is
retained.

The COM 1/2 and NAV 1/2 tuning fields remain
valid and can be tuned by rotating the tuning
knobs on PFD1 and PFD2.

XPDR 1/2 fields remain valid and XPDRs can
adjusted via PFD softkeys.
The following shall occur when power is removed from
PFD2:

PFD2 goes blank.

PFD1 and MFD remain in normal display formats.
The following illuminate on PFD1:

HDG NO COMP illuminates on PFD1

ROLL NO COMP illuminates on PFD1

PIT NO COMP illuminates on PFD1

IAS NO COMP illuminates on PFD1

ALT NO COMP illuminates on PFD1

GMA2 Fail – GMA2 is inoperative.

XPDR2 Fail – XPDR2 is Inoperative.
The following shall occur when power is removed from
PFD1:

PFD1 goes blank.

PFD2 and MFD remain in normal display formats.
The following illuminate on PFD2:

HDG NO COMP illuminates on PFD2

ROLL NO COMP illuminates on PFD2

PIT NO COMP illuminates on PFD2

IAS NO COMP illuminates on PFD2

ALT NO COMP illuminates on PFD2

GMA1 Fail – GMA1 is inoperative.

XPDR1 Fail – XPDR1 is Inoperative.
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9.1.4
G1000 Backup Path Test
1. Remove power from the displays by opening the following circuit breakers:
a. PFD1 PRI
b. PFD1 SEC
c.
PFD2
d. MFD
2. Individually power the PFD1, PFD2 and MFD by closing their circuit breaker while holding the ENT
key on each display (far right key on MFD) until the words INITIALIZING SYSTEM appear.
3. In configuration mode, go to the GDU Page Group on PFD1.
4. On PFD1, activate the cursor and select PFD1 in the SELECT UNIT field and press ENT.
5. Observe the GRS AHRS and GDC 74 DATA indicators in the ARINC 429 window.
6. Verify both indicators are valid (GREEN √ ), indicating the channels are receiving data as shown
below:
NOTE
Reference Table 3-1 for interpretation of data indicator symbols
Figure 9-1, GDU Data Verification (ARINC 429)
7. On PFD1, activate the cursor and select PFD2 in the SELECT UNIT field and press the ENT key.
8. Repeat Steps 4 and 5.
9. On PFD1, activate the cursor and select MFD1 in the SELECT UNIT field and press the ENT key.
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10. Repeat Steps 4 and 5.
11. On PFD1, go to the GIA Page Group. Go to the RS-232 / ARINC 429 CONFIG page.
12. Verify that GIA1 is selected in the SELECT UNIT field.
13. Observe the data indicators for all configured RS-232 and ARINC 429 channels (except GIA
DEBUG), including the GRS AHRS and GDC 74 ARINC 429 channels.
14. Verify all DATA indicators are valid (GREEN√ ), indicating the channels are receiving data as shown
in the following image:
Figure 9-2, GIA Data Verification (ARINC429/RS-232)
15. Activate the cursor and select GIA2 in the SELECT UNIT field, and then press the ENT key.
16. Repeat Steps 12 and 13.
17. On PFD1, go to the CAN / RS-485 CONFIGURATION page in the GIA Page Group.
18. Verify that GIA1 is selected in the SELECT UNIT field.
19. Observe the data indicators for all configured RS-485 channels.
20. Verify all DATA indicators are valid (GREEN√ ), indicating the channels are receiving data as
shown:
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Figure 9-3, GIA Data Verification (RS-485)
21. Activate the cursor and select GIA2 in the SELECT UNIT field, and then press the ENT key.
22. Repeat Steps 18 and 19 for GIA2.
9.2
Miscellaneous System Tests
9.2.1
G1000 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 PFD 1 or PFD 2
Alerts Window.
2. Open the following cooling fan circuit
breakers:
a) PFD/GIA FANS LEFT
b) PFD/GIA FANS RIGHT
c) MFD FAN
Verify that the following alert messages are displayed
after a 30-second delay:

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
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Step
Desired Result
Fan Failure reset and acknowledgement:
1. Close all cooling fan circuit breakers.
2. Acknowledge alerts by pressing
ALERTS softkey on PFD1.
Verify the above alerts extinguish.
9.2.2
the
Standby Instrument Electrical Power Check
This section tests the standby electrical power for the standby attitude indicator, the standby altimeter and
the standby airspeed indicator. The magnetic compass is tested in each Phase inspection during the
cockpit lights check, (item 33 of the operational inspections) in the King Air Model 90 Series Maintenance
Manual, listed in Table 1-2.
Step
Desired Result
1. Remove or ensure external aircraft power is
removed. Set main battery switch to OFF.
2. Ensure the STBY ATT and STBY ALTM
circuit breakers are closed.
3. Ensure the MASTER PANEL LIGHTS
rocker switch in the overhead panel is in the
ON position.
4. Ensure the STBY INSTR knob is turned to
full bright.
Verify the STANDBY BATTERY annunciator/switch is
not illuminated
5. Select (depress) the STANDBY BATTERY
switch.
Verify the following:
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
STBY Attitude indicator motor is energized as
indicated by the indicator motor and the absence
of flag.

STBY altimeter vibrator is active as indicated by
vibrator noise.

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
6. Activate aircraft power by selecting the BAT
switch ON.
7. Ensure that the generator busses are tied
by closing the GEN TIES MAN switch.
Verify the following:
“ON” annunciation should extinguish on the
STANDBY BATTERY switch.

“ARM” should be fully illuminated (green) on the
STANDBY BATTERY switch.

The STBY attitude, STBY altimeter and STBY
airspeed instrument lighting reverts to the aircraft
settings.

The STBY attitude motor and STBY altimeter
vibrator remain active.

White STANDBY BATTERY legend on the
standby battery switch remains illuminated.
Verify the following:
8. Deselect the STANDBY BATTERY switch
9. Remove aircraft power by selecting the BAT
switch to “OFF” position.
9.3


“ARM” annunciation extinguishes
STANDBY BATTERY switch.

STBY attitude motor and STBY altimeter vibrator
remain active.

White STANDBY BATTERY legend on the
standby battery switch remains illuminated.
on
the
Verify the following:

The STBY Attitude motor is deactivated (the
sound of the motor may be present as the gyro
spools down).

The STBY altimeter vibrator is deactivated.

The STBY attitude, STBY altimeter, STBY
airspeed and magnetic compass are no longer
illuminated.

White STANDBY BATTERY legend on the
standby battery switch extinguishes.
GFC 700 Ground Test
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 the G1000
in King Air C90 Cockpit Reference Guide.
NOTE
In the sections that follow, an Autopilot disconnect should be accompanied by an aural
alert (two-second tone) unless otherwise specified.
Perform the following Sections in order.
9.3.1
Pre-Flight Test
1. If selected ON, select the AVIONICS MASTER switch and ground power unit to OFF.
2. After 30 seconds select the ground power unit and AVIONICS MASTER switch to ON.
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3. Verify the GFC 700 begins an automatic pre-flight test after AHRS and ADC parameters become
valid.
4. Verify that a white ‘PFT’ annunciation is displayed on PFD1 and PFD2, as shown in Figure 8-4
Figure 9-4, Pre-Flight Test
NOTE
A momentary red
annunciation displayed before PFT starts is acceptable.
5. 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.
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NOTE
If the ‘PFT’ annunciation turns red, the test has failed.
troubleshooting.
Return to Section 5 for
6. Repeat Steps 1 - 3 to test the PFT aural alert for the other GIA 63W.
9.3.2
AFCS Switch Check
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 UP to activate Manual
Electric Pitch Trim (MEPT). Verify the trim clutch engages and the trim wheel drives in the UP
direction.
2. Repeat Step 1 for the DOWN direction.
3. 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.
4. Release the AP/YD DISC TRIM INTRPT button and PITCH TRIM switch.
5. Engage the autopilot by pressing the AP key on AFCS mode controller.
6. 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.
7. Engage the autopilot again by pressing the AP key on the AFCS mode controller.
8. Verify the pitch and roll clutches engage and resist movement of the control wheel.
9. Press and hold the CWS switch and verify the control wheel moves freely when moved manually.
Verify the green ‘AP’ at the top of PFD1 and PFD2 is replaced by a white ‘CWS’.
10. Release the CWS switch and press the ‘XFR’ key on the AFCS mode controller.
11. Verify the clutches are engaged and resist movement of the control wheel.
12. Press and hold the CWS switch and verify the control wheel moves freely when moved manually.
Verify the green ‘AP’ at the top of PFD1 and PFD2 is replaced by a white ‘CWS’.
13. Release the CWS switch and press the AP/YD DISC TRIM INTRPT switch on the pilots control
wheel.
14. Verify the autopilot disengages with a flashing amber ‘AP’ annunciation on PFD1 and PFD2,
accompanied by an aural alert.
15. Verify that the control wheel is free in pitch and roll axes.
16. Engage the autopilot again by pressing the ‘AP’ key on the AFCS mode controller.
17. 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.
18. Verify no AFCS annunciations (e.g. AFCS, PFT, Mistrim) remain on PFD1 or PFD2.
19. Press the AP/YD DISC TRIM INTRPT switch to cancel the abnormal alert.
20. Close the AFCS SERVOS circuit breaker to restore power to the system and wait for completion of
the pre-flight test sequence to continue.
21. Engage the autopilot again by pressing the ‘AP’ key on the AFCS mode controller.
22. Ensure the autopilot is coupled to GIA1 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.
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23. Open GIA1 primary and secondary circuit breakers. Verify the autopilot disconnects with a
continuous aural alert and a flashing red/white ‘AP’ annunciation.
24. Press the AP/YD DISC TRIM INTRPT switch to cancel the alert and annunciation.
25. Close the GIA1 primary and secondary circuit breakers and wait for completion of the pre-flight test
sequence to continue.
26. Press the ‘XFR’ key on the AFCS mode controller and engage the autopilot by pressing the ‘AP’
key on the AFCS Mode Controller.
27. Press the AP/YD DISC TRIM INTRPT switch on the pilot side to disconnect the autopilot.
28. Verify the flashing amber ‘AP’ alert is displayed on PFD1 & 2.
29. Press the GO AROUND button on the left throttle.
30. Verify ‘TO’ is annunciated on PFD1 and PFD2 for both PITCH and ROLL modes and the command
bars should be at 8 degrees nose up and wings-level.
31. Press the Flight Director (FD) key on the AFCS mode controller to deactivate the GA mode.
32. Press the AP key to engage the autopilot.
33. Press the CWS button for a minimum of 5 seconds and release.
34. Verify there is no residual force on the control stick for the pitch axis.
35. Disengage the autopilot by pressing the AP/YD DISC TRIM INTRPT switch on the co-pilot’s control
wheel.
36. Engage VS mode by pressing the VS key on the AFCS mode controller.
37. Verify PFD1 and PFD2 display ‘VS’ in green and indicates a pitch reference of ‘0 FPM’.
38. Press the FLC key on the AFCS mode controller
39. Verify that ‘FLC’ is annunciated on PFD1 and PFD2 in green with a reference of 90 KTS.
40. Press the ALT SEL key on the AFCS mode controller.
41. Verify that the ‘ALT’ annunciation is displayed in green on PFD1 and PFD2 with an altitude
reference equal to the aircraft altitude (within the nearest 20 feet).
42. Press the FD key.
43. Verify that the mode annunciations and command bars are removed from the display.
9.3.3
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 slip-clutch settings.
1. Engage the Autopilot by pressing the AP key on the AFCS mode controller.
2. Manually overpower the autopilot clutches in pitch and roll. If the Autopilot servo mount clutches
cannot be overpowered, check the servo clutch torque settings per Section 4.9.
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 trim servo clutch
torque setting per Section 4.9.
4. Engage the autopilot by pressing the AP key on the AFCS mode controller.
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5. Actuate and hold the manual electric trim switch in either the up or down direction to disconnect
the autopilot.
6. Verify that the trim wheel moves smoothly in both directions throughout the entire trim range during
manual electric trim operation.
a. If the trim wheel hesitates, this may indicate that the pitch trim clutch is slipping and proper
clutch setting and cable tension should be verified. Refer to the Pitch Trim Servo Installation
drawing for clutch setting and Beechcraft C90 Maintenance Manual for cable tension.
b. If both clutch setting and cable tension are within tolerance, check the aircraft pitch trim system
for excessive friction. Refer to the Beechcraft C90 Maintenance Manual.
9.3.4
Manual Electric Pitch Trim Speed Check
1. Run MANUAL ELECTRIC PITCH TRIM in one direction until it runs against the mechanical stop.
2. Zero a stopwatch and prepare to start in the next step.
3. At the same time, start the stopwatch and start running the trim in the opposite direction.
4. Stop the stopwatch when the trim runs against the opposite mechanical stop.
5. Verify the elapsed time on the stopwatch for full trim travel measures 15  5 seconds.
9.3.5
Autopilot Operation Check
1. Engage the Autopilot by pressing the AP key on the AFCS mode controller.
2. Push the HDG knob to synchronize the heading bug to the current aircraft heading.
3. Select HDG mode by pressing the HDG key on the AFCS mode controller.
4. 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.)
5. 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.
6. Push and hold the CWS button and pull the control wheel to the center of the pitch control range.
Release the CWS button.
7. Verify the autopilot clutches re-engage and hold the wheel stationary.
8. Holding the control wheel lightly, rotate the NOSE UP/DN wheel on the AFCS mode controller two
clicks, to increase the pitch reference.
9. 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).
10. 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.
11. Release the CWS button and check that servo clutches re-engage before releasing the control
wheel.
12. Rotate the NOSE UP/DN wheel on the AFCS mode controller two clicks. Verify the command bars
command a pitch attitude 2 degrees lower and the control wheel begins moving forward.
13. Hold the controls and press CWS to re-center the command bars and stop control wheel
movement.
14. With the Autopilot still engaged and the CWS button pressed, move the control wheel to its aft limit.
15. 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.
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16. Grip the control wheel and press the CWS button. Verify trim motion stops.
17. Move the control wheel to the forward limit and release the CWS button.
18. Slowly move the control wheel aft. After a brief delay, verify the trim wheel begins to trim down.
19. Relieve pressure on the wheel and verify the trim motion stops.
20. Check that the trim wheel is free to turn.
21. Hold the control wheel and press the AP/YD DISC TRIM INTRPT switch to disconnect the autopilot.
9.3.6
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 PFD1 as indicated by a left pointing arrow next to the XFR button.
2. Simulate a VOR signal from the ramp test equipment to a radial equivalent to the aircraft heading.
3. Tune the NAV 1 and NAV 2 receivers to the simulation frequency.
4. On the MFD, go to the AUX - SYSTEM SETUP page and check CDI Synchronization setting.
Change setting to OFF if it is turned on.
5. On PFD1, set the HSI to VOR1 by pressing the CDI soft key until VOR1 is selected.
6. On PFD2, set the HSI on PFD2 to VOR2 by pressing the CDI soft key until VOR2 is selected.
7. On the AFCS mode controller, rotate CRS1 and CRS2 knobs to set VOR1 and VOR2 course
pointers to aircraft heading.
8. 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.
9. On the AFCS mode controller, engage the autopilot and press the NAV key. 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.
10. Press the XFR button on the AFCS mode controller to couple FD to PFD2. Verify FD is coupled
right as indicate by a right pointing arrow on the AFCS mode controller next to the XFR button.
11. Repeat step 9 using CRS2 knob while the FD is coupled to PFD2.
12. Set CRS1 and CRS2 course pointers to aircraft heading.
13. Simulate a Localizer/Glideslope signal.
14. Tune NAV 1 and NAV 2 receiver to the simulated frequency.
15. Set the PFD1 HSI to LOC1 and PFD2 HSI to LOC2 by pressing CDI soft key until LOC1 and LOC2
is selected.
16. Use the test equipment to center the deviation bars (localizer and glideslope) on PFD1 and PFD2.
17. Press the APR key on the AFCS mode controller. Verify that the LOC and GS annunciations are
green on PFD1 and PFD2.
18. Apply right/left and up/down localizer/glideslope signals using the test equipment. Verify that the
Flight Director and flight controls respond appropriately.
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19. Couple the FD to PFD1 by pressing the XFR button on the AFCS mode controller. Verify FD is
coupled to PFD1 as indicate by a left pointing arrow on the AFCS mode controller next to the XFR
button.
20. Repeat steps 17-18 using while coupled to PFD1.
21. Turn off the G1000 system.
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10
Maintenance Records
After conducting required return-to-service procedures in accordance with the King Air Model 90 Series
Maintenance Manual, listed in Table 1-2, the aircraft may be returned to service.
1. Record the following information in appropriate aircraft maintenance logs:
a. Part number of the G1000 software loader card used to perform software loading or software
updates.
b. Record part and serial numbers of any LRU which was replaced.
c. Record any database updates which were performed during maintenance.
d. Any other applicable information related to the maintenance work performed on the aircraft.
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