Garmin SA01456Wi-D System Maintenance Manual
G1000 / GFC 700
System Maintenance Manual
Hawker Beechcraft
Model C90A/C90GT/C90GTi King Air
Contains Instructions
For Continued Airworthiness
For STC #SA01456WI-D
190-00682-01 November 2012 Revision F
This page intentionally left blank.
© Copyright 2007-2012
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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written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual
and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and
to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of
this manual or revision must contain the complete text of this copyright notice and provided further that
any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.
Garmin International, Inc.
1200 E. 151
st
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 #
A 11/9/2007 Initial release for STC -----B 11/19/2007 Update Release Spec & repaginated document 48811
C 02/18/2008 Updated Sections 1.1, 3.8, 3.9, 4.1, 4.4, 4.7, 4.14
51033
and 4.15. Added Sections 7.21 and 7.22
D 02/15/2010 Updated G1000 System Software Version to
71674
0636.02. Add Loader Card Creation procedure
Section 3.8.2. Add SVS/Pathways.
E 10/17/2012 Updated G1000 System Software Version to
95142
0636.03. Added ESP. Misc updates.
F 11/5/2012 Minor change update (clerical) 95629
DOCUMENT PAGINATION
Section Pagination
Table of Contents i – vi
Section 1 1-1 – 1-6
Section 2 2-1 – 2-14
Section 3 3-1 – 3-54
Section 4 4-1 – 4-40
Section 5 5-1 – 5-88
Section 6 6-1 – 6-18
Section 7 7-1 – 7-56
Section 8 8-1 – 8-14
Page A G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
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.
Page B G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
TABLE OF CONTENTS
PARAGRAPH PAGE
1 INTRODUCTION ............................................................................................................................ 1-1
1.1 C
1.2 O
1.3 D
1.4 P
1.5 R
ONTENT, SCOPE, PURPOSE ........................................................................................................ 1-1
RGANIZATION ........................................................................................................................... 1-3
EFINITIONS/ABBREVIATIONS .................................................................................................... 1-4
UBLICATIONS ............................................................................................................................. 1-5
EVISION AND DISTRIBUTION ..................................................................................................... 1-6
2 SYSTEM DESCRIPTION ............................................................................................................... 2-1
2.1 E
2.2 G1000
2.3 E
2.4 S
2.5 G1000
QUIPMENT DESCRIPTIONS ......................................................................................................... 2-1
OPTIONAL INTERFACES ................................................................................................... 2-9
LECTRICAL POWER DISTRIBUTION .......................................................................................... 2-10
HIELD BLOCK GROUNDS ......................................................................................................... 2-12
/GFC700 BLOCK DIAGRAM ........................................................................................... 2-13
3 G1000 CONTROL & OPERATION ............................................................................................... 3-1
3.1 GDU
3.2 GCU
3.3 GMC
3.4 GMA
3.5 G1000
3.6 R
3.7 C
3.8 G1000
3.9 G1000
3.10 A
3.11 S
3.12 C
1040A AND GDU 1500 DISPLAYS ..................................................................................... 3-1
475 - MFD CONTROLLER ................................................................................................... 3-3
710 - AFCS CONTROLS ..................................................................................................... 3-3
1347D AUDIO PANEL ........................................................................................................ 3-4
NORMAL MODE ............................................................................................................... 3-6
EVERSIONARY MODE ................................................................................................................ 3-7
ONFIGURATION MODE OVERVIEW ............................................................................................ 3-8
/ GFC 700 SOFTWARE INFORMATION ............................................................................ 3-13
SOFTWARE/CONFIGURATION PROCEDURE .................................................................... 3-25
IRCRAFT REGISTRATION NUMBER ENTRY .............................................................................. 3-52
PLASH SCREEN LOADING ........................................................................................................ 3-52
LEARING DEFAULT USER SETTINGS ....................................................................................... 3-53
4 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS........................................................ 4-1
4.1 A
4.2 S
4.3 M
4.4 V
4.5 E
4.6 GRS
4.7 GSA
4.8 F
4.9 S
4.10 G1000
4.11 E
4.12 T
4.13 G1000
4.14 N
4.15 I
4.16 S
IRWORTHINESS LIMITATIONS ................................................................................................... 4-1
ERVICING INFORMATION ........................................................................................................... 4-3
AINTENANCE INTERVALS ......................................................................................................... 4-5
ISUAL INSPECTION .................................................................................................................. 4-10
LECTRICAL BONDING TEST ..................................................................................................... 4-15
77 EARTH MAGNETIC FIELD UPDATES ............................................................................. 4-18
8X GREASING PROCEDURE ............................................................................................... 4-18
LAPS-IN-MOTION DISCRETE INPUT CHECK ............................................................................. 4-19
LIP CLUTCH TORQUE CHECK PROCEDURE AND SERVO CURRENT DISPLAY CHECK .............. 4-20
REDUNDANT CONNECTION CHECK ............................................................................... 4-28
NGINE DATA CHECK ............................................................................................................... 4-31
RIM ANNUNCIATOR CHECK ..................................................................................................... 4-33
MISCOMPARE CHECKS ................................................................................................... 4-34
OSE AVIONICS COMPARTMENT FANS OPERATIONAL CHECK ................................................ 4-36
NSTRUMENT PANEL FANS OPERATIONAL CHECK .................................................................... 4-36
TANDBY BATTERY PERIODIC CHECKS .................................................................................... 4-36
5 TROUBLESHOOTING ................................................................................................................... 5-1
5.1 G1000
5.2 S
ALERTING SYSTEM .......................................................................................................... 5-2
YSTEM ANNUNCIATIONS ........................................................................................................... 5-4
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page i
190-00682-01 Revision F
5.3 C90A/C90GT/C90GTI SPECIFIC ALERTS ................................................................................. 5-27
5.4 TAWS
5.5 S
5.6 GFC
5.7 B
5.8 GDU
5.9 GDU
5.10 GIA
5.11 GIA
5.12 GEA
5.13 GTX
5.14 GDL
5.15 GRS
5.16 GDC
5.17 GWX
5.18 GMC
5.19 GCU
5.20 S
5.21 B
5.22 S
5.23 S
5.24 S
TROUBLESHOOTING ...................................................................................................... 5-28
YNTHETIC VISION AND PATHWAYS TROUBLESHOOTING ........................................................ 5-29
700 AFCS TROUBLESHOOTING ........................................................................................ 5-30
ACKUP COMMUNICATIONS PATH CHECKS .............................................................................. 5-46
104X TROUBLESHOOTING ............................................................................................... 5-47
104X ALERTS ................................................................................................................... 5-49
63 TROUBLESHOOTING ...................................................................................................... 5-57
ALERT MESSAGES ............................................................................................................. 5-59
TROUBLESHOOTING .......................................................................................................... 5-66
TROUBLESHOOTING .......................................................................................................... 5-67
69A TROUBLESHOOTING .................................................................................................. 5-68
77/GMU 44 TROUBLESHOOTING ...................................................................................... 5-70
74B TROUBLESHOOTING .................................................................................................. 5-76
68 TROUBLESHOOTING ................................................................................................... 5-77
710 TROUBLESHOOTING .................................................................................................. 5-78
475 TROUBLESHOOTING ................................................................................................... 5-79
OFTWARE/CONFIGURATION TROUBLESHOOTING ................................................................... 5-80
ACKSHELL CONNECTORS ........................................................................................................ 5-82
TANDBY AIRSPEED INDICATOR TROUBLESHOOTING .............................................................. 5-86
TANDBY ALTIMETER TROUBLESHOOTING .............................................................................. 5-87
TANDBY BATTERY TROUBLESHOOTING .................................................................................. 5-87
6 EQUIPMENT REMOVAL & REPLACEMENT ......................................................................... 6-1
6.1 GDU
6.2 GMA
6.3 GIA
6.4 GEA
6.5 GTX
6.6 GDC
6.7 GTP
6.8 GRS
6.9 GMU
6.10 GDL
6.11 GSA
6.12 GSM
6.13 GCU
6.14 GMC
6.15 GWX
6.16 C
6.17 GEA
6.18 GPS/WAAS
6.19 E
6.20 S
6.21 I
6.22 L-3
6.23 S
6.24 S
6.25 S
6.26 A
6.27 GDU
1040A/1500 ....................................................................................................................... 6-2
1347D AUDIO PANEL ........................................................................................................ 6-2
63W INTEGRATED AVIONICS UNITS .................................................................................... 6-3
71 ENGINE/AIRFRAME UNIT ............................................................................................... 6-3
33 TRANSPONDER ............................................................................................................... 6-4
74B AIR DATA COMPUTER ................................................................................................ 6-4
59 OAT PROBE .................................................................................................................... 6-4
77 AHRS ............................................................................................................................. 6-5
44 MAGNETOMETER .......................................................................................................... 6-5
69A ..................................................................................................................................... 6-5
80/81 SERVOS ..................................................................................................................... 6-6
85A / GSM 86 SERVO MOUNTS ......................................................................................... 6-6
475 ...................................................................................................................................... 6-7
710 ..................................................................................................................................... 6-7
68 ...................................................................................................................................... 6-8
ONFIGURATION MODULE REMOVAL & REPLACEMENT ............................................................ 6-9
71 BACKSHELL THERMOCOUPLE REMOVAL & REPLACEMENT ....................................... 6-11
ANTENNAS ............................................................................................................ 6-12
NGINE SIGNAL CONDITIONERS ................................................................................................ 6-12
ENIOR AEROSPACE PC920 SIGNAL CONDITIONING UNIT ....................................................... 6-13
NSTRUMENT PANEL ANNUNCIATORS (PROP SYNCH AND STANDBY BATTERY) ...................... 6-14
AVIONICS (BF GOODRICH) PS-835(C OR D MODEL) EMERGENCY BATTERY ................... 6-14
TANDBY AIRSPEED INDICATOR ............................................................................................... 6-15
TANDBY ALTIMETER ............................................................................................................... 6-15
TANDBY ATTITUDE INDICATOR............................................................................................... 6-16
VIONICS COOLING FANS ......................................................................................................... 6-16
COOLING FANS ................................................................................................................. 6-17
7 G1000 EQUIPMENT CONFIGURATION & TESTING ............................................................. 7-1
Page ii G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
7.1 GDU 1040/1500 MFD & PFD ..................................................................................................... 7-1
7.2 GMA
7.3 GIA
7.4 GEA
7.5 GTX
7.6 GDC
7.7 GRS
7.8 GDL
7.9 GSA
7.10 GCU
7.11 GMC
7.12 GWX
7.13 T
7.14 L
7.15 TAWS
7.16 F
7.17 C
7.18 S
7.19 DME
7.20 ADF
7.21 A
7.22 W
7.23 ESP
1347D AUDIO PANEL ........................................................................................................ 7-3
63W INTEGRATED AVIONICS UNIT ................................................................................... 7-10
71 ENGINE/AIRFRAME UNIT ............................................................................................. 7-13
33 TRANSPONDER ............................................................................................................. 7-20
74B AIR DATA COMPUTER .............................................................................................. 7-22
77 AHRS / GMU 44 MAGNETOMETER ............................................................................. 7-26
69A XM DATA LINK ........................................................................................................ 7-36
80/81 SERVOS ................................................................................................................... 7-36
475 FMS CONTROLLER .................................................................................................... 7-37
710 AFCS CONTROLLER ................................................................................................. 7-38
68 WEATHER RADAR ..................................................................................................... 7-39
RAFFIC (NON-GARMIN) SYSTEM FUNCTIONAL CHECK .......................................................... 7-40
IGHTNING DETECTION FUNCTIONAL CHECK .......................................................................... 7-41
FUNCTIONAL CHECK ..................................................................................................... 7-43
LITECHARTS FUNCTIONAL CHECK .......................................................................................... 7-44
HARTVIEW FUNCTIONAL CHECK ............................................................................................ 7-45
AFETAXI FUNCTIONAL CHECK ................................................................................................ 7-46
FUNCTIONAL CHECK ....................................................................................................... 7-47
FUNCTIONAL CHECK ........................................................................................................ 7-48
IRCRAFT WEIGHT CONFIGURATION FUNCTIONAL CHECK ..................................................... 7-48
EIGHT ON WHEELS AND LOW SPEED AWARENESS BAND TEST ............................................ 7-53
FUNCTIONAL CHECK ......................................................................................................... 7-54
8 SYSTEM RETURN TO SERVICE PROCEDURE ...................................................................... 8-1
8.1 B
8.2 GFC
8.3 M
ACKUP PATH SYSTEM TESTING ................................................................................................ 8-2
700 GROUND CHECKOUT .................................................................................................. 8-10
AINTENANCE RECORDS .......................................................................................................... 8-14
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page iii
190-00682-01 Revision F
LIST OF ILLUSTRATIONS
FIGURE PAGE
Figure 2-1. C90 Electrical Distribution ................................................................................................... 2-11
Figure 2-2. Avionics Master Power Schematic....................................................................................... 2-11
Figure 2-3. G1000 Component Power Sources....................................................................................... 2-12
Figure 2-4. G1000/GFC 700 Block Diagram .......................................................................................... 2-13
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 ............................................................................ 3-23
Figure 3-16. GRS/GDC Configuration Settings Storage ........................................................................ 3-24
Figure 3-17. Software/Configuration Overview ..................................................................................... 3-25
Figure 3-18. System Upload Page ........................................................................................................... 3-27
Figure 3-19. System Status ..................................................................................................................... 3-29
Figure 3-20. ESP Support Configuration ................................................................................................. 3-42
Figure 3-21. Servo Mount Configuration Verification ............................................................................ 3-43
Figure 3-22. Navigation Database Synchronization ................................................................................ 3-49
Figure 3-24. Aircraft Registration ........................................................................................................... 3-52
Figure 4-1. Servo Gear ............................................................................................................................. 4-18
Figure 4-2 GFC Status Page ................................................................................................................... 4-20
Figure 4-3 GFC Status Page ................................................................................................................... 4-22
Figure 4-4 GFC Status Page ...................................................................................................
................ 4-27
Figure 4-5, Standby Battery ..................................................................................................................... 4-37
Figure 4-6, Power Supply Connection .................................................................................................... 4-39
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................................................................................................................... 5-33
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. GDC 74B Backshell Connector (P74B1) ........................................................................... 5-84
Figure 5-16. GDL 69A Backshell Connector (P69A1) ........................................................................... 5-84
Figure 5-17. GCU 475 Backshell Connector (P4751) ............................................................................ 5-85
Figure 5-18. GMC 710 Backshell Connector (P7101) ............................................................................ 5-85
Page iv G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
Figure 5-19. GWX 68 Backshell Connector (P681) ............................................................................... 5-85
Figure 5-20, Signal Conditioner Mating Connector (PVIB1) ................................................................. 5-85
Figure 6-1. Configuration Module Installation ......................................................................................... 6-9
Figure 6-2. GEA Backshell Thermocouple ............................................................................................. 6-11
Figure 7-1. G1000 Normal Mode Check .................................................................................................. 7-2
Figure 7-2. Marker Beacon Symbology .................................................................................................... 7-6
Figure 7-3. AUX – GPS STATUS Page (MFD) ..................................................................................... 7-10
Figure 7-4. Normal Engine Instrument Markings (MFD) ...................................................................... 7-13
Figure 7-5, Aircraft Registration .............................................................................................................. 7-20
Figure 7-6. GRS 77 Pitch/Roll Offset Calibration Page ......................................................................... 7-28
Figure 7-7, Engine Run-Up Test Page ..................................................................................................... 7-33
Figure 7-8. Normal Mode AHRS Check ................................................................................................ 7-35
Figure 7-9. Low Speed Awareness Band Symbolization ........................................................................ 7-53
Figure 8-1. GDU Data Verification (ARINC 429) .................................................................................... 8-7
Figure 8-2. GIA Data Verification (ARINC429/RS-232) .......................................................................... 8-8
Figure 8-3. GIA Data Verification (RS-485) ............................................................................................. 8-9
Figure 8-4. Pre-Flight Test ...................................................................................................................... 8-10
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 ............................................................................... 3-21
Table 3-3. Default Airframe Weight Configurations .............................................................................. 3-33
Table 3-4. Optional Airframe Weight Configurations for SW Version 0636.01 .................................... 3-33
Table 3-5. Optional Airframe Weight Configurations for SW Version 0636.02 and Subs .................... 3-34
Table 4-1. Maintenance Intervals .............................................................................................................. 4-5
Table 4-2. Discontinued Maintenance Intervals ....................................................................................... 4-9
Table 4-3. Nose Section Visual Inspection Procedure ............................................................................ 4-10
Table 4-4. Nose Avionics Compartment Visual Inspection Procedure .................................................. 4-10
Table 4-5. Pilot’s Compartment Visual Inspection Procedure ................................................................ 4-11
Table 4-6. Instrument Panel G1000 Equipment Visual Inspection Procedure ....................................... 4-12
Table 4-7. Cabin Area Visual Inspection Procedure ............................................................................... 4-13
Table 4-8. Rear Fuselage and Empennage Visual Inspection Procedure ................................................ 4-14
Table 4-9, Lightning Strike Inspection Procedure ................................................................................... 4-14
Table 4-10. Measured Torque ................................................................................................................. 4-24
Table 4-11. Slip Clutch Torque Settings ................................................................................................. 4-26
Table 4-12, Standby Battery Required Equipment .................................................................................. 4-37
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 ............................................................................................ 5-32
Table 5-5. Magnetometer Interference Test Sequence (Example) .......................................................... 5-74
Table 6-1. Configuration Module Kit – 011-00979-00 ............................................................................. 6-9
Table 6-2. Thermocouple Kit (011-00981-00) ....................................................................................... 6-11
Table 7-1. Airspeed and Altitude Table .................................................................................................. 7-24
Table 7-2. Vertical Speed Table ............................................................................................................. 7-25
Table 7-3. Required GRS/GMU Calibrations ......................................................................................... 7-27
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page v
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Page vi G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
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 C90A/C90GT/C90GTi
King Air, under 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.
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.
1.1.1 Applicability
This document applies to all Model C90A/C90GT/C90GTi King Air aircraft (herein referred to also as
C90A/GT/GTi) equipped with the G1000 and optional GFC700 AFCS systems.
Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft operator to
include the maintenance information provided by this document in the operator’s Aircraft Maintenance
Manual and the operator’s Aircraft Scheduled Maintenance Program.
1.1.2 Identifying an STC Configuration
Table 1-1 lists the approved configurations for this STC as defined by the Master Drawing List (MDL),
Garmin document 005-00375-30.
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 0636.03 is added with STC MDL Rev. 6 and is the
recommended software. G1000 System Software Versions 0636.01 and 0636.02 will
remain to support fielded aircraft.
Table 1-1. MDL Configurations Summary
MDL
Configuration
-1 C90A/C90GT King Air
-1 C90A/C90GT King Air
-1 C90A/C90GT/C90GTi King Air
Aircraft
Model
G1000 System
Software Version
0636.01
0636.02
0636.03
Notes
STC MDL Rev. 4 Approval
STC MDL Rev. 5 Approval
STC MDL Rev. 6 Approval
This STC addresses multiple C90A/GT/GTi configurations. These configuration variants are added by
loading the applicable airframe configuration and related options. Refer the General Arrangement
Drawing, Garmin Part Number 005-00375-22, for additional information.
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 1-1
190-00682-01 Revision F
IMPORTANT!
If the technician is unsure of an aircraft’s STC Configuration, perform the
following steps:
1. Inspect the aircraft maintenance logs for records of which STC configuration is 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. Following MFD power-up, observe upper right section of MFD splash screen for airframe
configuration.
OR
After acknowledgement of the splash screen, use the FMS knob on the GCU 475 controller to go to
the AUX – SYSTEM STATUS page on the MFD. In the AIRFRAME section (upper right corner,)
the display shows the current G1000 airframe configuration and system software version number.
The airframe configuration is shown in the AIRFRAME field and the system software version
number is shown in the following format: ‘System Software Version XXXX.XX’. It correlates to the
G1000 software used to load the software to the system:
EXAMPLE:
System Software Version ‘0636.02’ = G1000 Software P/N 006-B0636-02
The G1000/GFC 700 C90 General Arrangement Drawing, Garmin Document 005-00375-22, defines
the approved G1000 software for this STC.
Page 1-2 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
1.2 Organization
The following outline briefly describes the organization of this manual:
Section 2: System Description
Provides a complete description of the type design change associated with installing the G1000
integrated cockpit system in the C90A/GT/GTi King Air. An overview of the G1000 and GFC 700
system interface is also provided.
Section 3: G1000 Control & Operation
Presents basic control and operation information specifically tailored to maintenance practices. Basic
G1000 Configuration Mode operation is also described.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for continued airworthiness of the G1000 and GFC 700 systems.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with the
G1000 and GFC 700 systems.
Section 6: G1000 Equipment Removal & Replacement
Gives instructions for the removal and replacement of G1000 and GFC700 equipment.
Section 7: G1000 Equipment Configuration & Testing
Gives instructions for loading software, configuring, and testing of G1000 equipment.
Section 8: System Return to Service Procedure
Specifies return-to-service procedures to be performed upon completion of maintenance of the G1000
system.
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 1-3
190-00682-01 Revision F
1.3 Definitions/Abbreviations
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
CDU: Control Display Unit
CFR: Code of Federal Regulations
DME: Distance Measuring Equipment
EAU: Engine/Airframe Unit
ESP: Electronic Stability and Protection
GPS: Global Positioning System
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
1.3.1 Units of Measure
Unless otherwise stated, all units of measure are English units.
Page 1-4 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
1.4 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 68 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
Hawker 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
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
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 1-5
190-00682-01 Revision F
85-292-1-1033 Signal Conditioner Installation Manual (Meggitt Sensing Systems)
TP-336 L-3 Avionics Systems – Emergency Power Supply Installation Manual, PS-835
NOTE
Drawings, associated with this project, which include C90, C90A, or C90A/C90GT in the title apply to
the C90A, C90GT, and C90GTi unless specifically otherwise stated within the drawing or elsewhere in
the STC data package.
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
190-00664-XX G1000/King Air C90A/C90GT Cockpit Reference Guide
190-00355-04 GDL 69/69A XM Satellite Radio Activation Instructions
190-00907-00 G1000 System Maintenance Manual
190-00303-72 GSA8X/GSM85(A) Installation Manual
190-00303-83 GSM 86 Installation Manual
98-39006 Structural Inspection and Repair Manual
G1000/GFC 700, King Air C90A/C90GT Airplane Flight Manual
Supplement
Hawker Beechcraft Document
Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealer Resource
Center’ section of the Garmin web site; refer to Section 1.5 for details.
1.5 Revision and Distribution
This document is required for maintaining the continued airworthiness of the aircraft. When this
document is revised, every page will be revised to indicate current revision level.
Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource Center
website.
Owner/operators may obtain the latest revision of this document from the https://fly.garmin.com/ Support
page, or by contacting a Garmin dealer, contacting Garmin Product Support at 913-397-8200, toll free
866-739-5687, or using around the world contact information on https://fly.garmin.com/.
A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the
revision is determined to be significant.
Page 1-6 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
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 CDU cooling fans are also
installed behind the panel for PFD and MFD cooling.
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-1
190-00682-01 Revision F
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/King Air
C90A/C90GT/C90GTi 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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Revision F 190-00682-01
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 80 (all) and GSA 81
• GRS 77, #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)
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-3
190-00682-01 Revision F
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
2.1.7 GTX 33 Mode S Transponder (2)
The GTX 33 Non-Extended Squitter or GTX 33 Extended Squitter (ES) (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 units interface with the existing 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) transponder.
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Revision F 190-00682-01
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 77 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 Hawker Beechcraft Company.
Reference drawing Main Instrument Panel Installation KingAir C90A/C90GT, p/n 005-00375-28 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 airdata computers.
2.1.10 GRS 77 Attitude & Heading Reference System (2)
The Garmin GRS 77 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 units by the triple-fed bus. Additionally, a secondary power
source is provided to the No. 1 GRS 77 by the center bus. The GRS 77 interfaces with and provides power
to the GMU 44 Magnetometer. The GRS 77 supplies attitude and heading information directly to the PFDs,
MFD, and GIAs.
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-5
190-00682-01 Revision F
2.1.11 GMU 44 Magnetometer (2)
The GMU 44 provides horizontal and vertical magnetic field information to the GRS 77 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 77 units and communicate with the GRS
77 units via RS-485 digital interface.
2.1.12 GDL 69A Datalink
The GDL 69A provides the interface to the GWX 68 weather radar by acting as a communications hub
between the MFD and GWX68 via HSDB. The GDL 69A also provides XM Radio weather and music
entertainment through means of a dedicated satellite data link. The GDL 69A is mounted behind the
instrument panel. Power to the GDL 69A is received from the avionics No. 3 bus. The GDL 69A sends
weather data through the HSDB bus to the MFD, where the data link interface is controlled. Digital audio is
sent directly to the GMA 1347D Audio Panel.
2.1.13 GWX 68 Weather Radar
The GWX 68 Airborne Weather Radar provides weather radar data output to the GDU 1500 MFD. The
GWX 68 is mounted forward of the forward bulkhead at F.S. 30. Power to the GWX 68 is received from the
avionics No. 2 bus. Data received from the GWX 68 is routed through the GDL 69A data link unit to the
MFD via high-speed data bus (Ethernet).
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Revision F 190-00682-01
2.1.14 GSA 81 Servo, GSA 80 Servo (3) and GSM 85A/86 Servo Mount (4)
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 (optional 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 serviceable and can be adjusted to the specified torque
value. The GSM 86 has a clutch cartridge that is not field serviceable, that cannot be adjusted, if the
specified torque value is not within limits the clutch cartridge must be replaced.
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 Airspeed Indicator
Either a Thommen 5A58.22.26K.28.1.ET, 5A58.22.26K.28.1.FE, 5A58.22.26K.28.1.FA or
5A58.22.26K.28.1.FP unit is installed as the standby airspeed indicator. The difference between the part
numbers is the location of the Vmca red radial; 80 KT, 85 KT and 90 KT respectively. The General
Arrangement drawing, listed in Table
number. 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.
1-2, contains Table 4, which shows the applicability of each part
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 4200-10 Attitude Indicator
The Model 4200-10 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
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:
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-7
190-00682-01 Revision F
• 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 005-0037593 Tach-Gen Filter Assembly were replaced by the Vibro-Meter (Meggit) Signal Conditioner Signal
Conditioner. Reference the Main Instrument Panel Installation drawing listed in Table 1-2 for the locations
of the Signal Conditioner Components.
2.1.20.1 Sandia Aerospace ST26 Tach Generator Adapter Units (2)
The ST26 Tach Generator Adapter Units are used for converting the signal from the propeller speed and
turbine speed sensors into a signal that is usable by the GEAs. The output signal from this adapter unit will
be represented by a 5 VDC square wave signal at same frequency of input signal. The No. 1 ST26 (left side)
unit is connected to the No. 1 Triple-fed bus and the No. 2 ST26 (right side) unit is connected to the No. 2
triple-fed bus.
The Sandia Aerospace ST26 Tach Generator Adapter Unit is applicable only to installations using STC
SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions.
2.1.20.2 Senior Aerospace PC920 Signal Conditioning Unit
The PC920 unit was installed per this STC only for aircraft with Senior Aerospace Ketema fuel flow
transducer, part number 1/2-2-81-306. The PC920 unit is used for converting the signal from the fuel flow
sensor into a variable 0 to 5 VDC signal that is proportional to flow rate. The PC920 unit No. 1 channel is
connected to the No. 1 triple-fed bus and the No. 2 channel is connected to the No.2 triple-fed bus. The No.
1 channel (connector P9201) converts the fuel flow signal for the left engine and the No. 2 channel
(connector P9202) converts the fuel flow signal for the right engine.
The Senior Aerospace PC920 Signal Conditioner Unit is applicable only to installations using STC
SA01456WI-D Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions.
2.1.20.3 Garmin 005-00375-93 Tach-Gen Filter Assembly (2)
The Tach-Gen Filter Assembly is used to filter out high frequency signal noise and is installed between the
Sandia ST26 Signal Conditioner and both the propeller speed and turbine speed sensors. There is one 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
tach-gen filter assembly.
The Garmin Tach-Gen Filter Assembly, 005-00375-93 is applicable only to installations using STC SA01456WI-D
Master Drawing List (MDL) 005-00375-30, Revision 4 and previously approved revisions.
2.1.20.4 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
Page 2-8 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
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 (MDL) 005-00375-30, 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, Traffic System, Rockwell Collins ADF60A and Rockwell Collins DME-42. Refer to wiring diagram listed in Table 1-2, for specific interface
information.
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-9
190-00682-01 Revision F
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:
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 68, GSA 81 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:
connects those components whenever the bus ties are closed (ref. Figure 2-1). The center bus provides a
secondary
Triple-fed Bus:
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:
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 (MDL) 005-00375-30, 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 is a redundant power source to the Standby Attitude
indicator, Standby Altimeter, and the Standby Airspeed Indicator.
The center bus is fed by two generator buses and the hot battery bus, which automatically
power source for the following G1000 equipment: PFD 1, GIA 1, GDC 1, and GRS 1.
The triple-fed is powered from the hot battery bus and both generator buses (ref. Figure 2-1.)
The left and right generator buses receive power from their respective left
The Standby Emergency Battery (STBY BATT) system in the King
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.
Page 2-10 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
Figure 2-1. C90 Electrical Distribution
Figure 2-2. Avionics Master Power Schematic
G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air Page 2-11
190-00682-01 Revision F
Figure 2-3. G1000 Component Power Sources
2.4 Shield Block Grounds
The connectors on Garmin G1000 LRUs utilize the Shield Block grounding system to provide necessary
ground reference to wire shielding and/or transducers. The shield block termination method allows multiple
grounds to be terminated directly to a block mounted to the connector backshell assembly. Shielding and
grounding requirements for all other LRUs and connectors are shown in the respective install drawings.
Page 2-12 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
2.5 G1000 /GFC700 Block Diagram
Figure 2-4. G1000/GFC 700 Block Diagram
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190-00682-01 Revision F
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Page 2-14 G1000/GFC700 System Maintenance Manual – C90A/C90GT/C90GTi King Air
Revision F 190-00682-01
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