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SA01535Wi-D

Garmin SA01535Wi-D System Maintenance Manual

G1000 / GFC 700 System Maintenance Manual Hawker Beechcraft Model 200/B200 Series King Air
Contains Instructions For Continued Airworthiness For STC SA01535WI-D
190-00915-01 October 2012 Revision 7
This page intentionally left blank.
© Copyright 2009-2012
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior 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 #
3 7/17/09 Added GSM 86, TAWS-A, Radio Altimeter 62341 4 11/1/10 Added GDL59, GSR 56, GTS 8XX and ESP
76618
options
5 5/11/12 Updated procedures for software version 0985.04 90414 6 7/19/12
7 10/24/12
Corrected GA drawing reference error in Section
3.8.2 Add SW v0985.06, added GDC 7400 option, updated section 4 airworthiness limitations
93256 95300
DOCUMENT PAGINATION
Section Pagination
Table of Contents i – viii
Section 1 1-1 – 1-6 Section 2 2-1 – 2-16 Section 3 3-1 – 3-54 Section 4 4-1 – 4-38 Section 5 5-1 – 5-90 Section 6 6-1 – 6-20 Section 7 7-1 – 7-66 Section 8 8-1 – 8-16
Page A G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
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 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
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
EVISON AND DISTRIBUTION ...................................................................................................... 1-6
2 SYSTEM DESCRIPTION ............................................................................................................... 2-1
2.1 E
2.2 G1000
2.3 E
2.4 P
2.5 S
2.6 G1000
QUIPMENT DESCRIPTIONS ......................................................................................................... 2-1
OPTIONAL INTERFACES .................................................................................................. 2-11
LECTRICAL POWER DISTRIBUTION .......................................................................................... 2-12
ITOT/STATIC SYSTEM .............................................................................................................. 2-15
HIELD BLOCK GROUNDS ......................................................................................................... 2-16
/GFC700 BLOCK DIAGRAM ........................................................................................... 2-16
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 TAWS-A
3.11 TAWS-A
3.12 TAWS-A
3.13 ADF
3.14 DME
3.15 RAD
3.16 N
3.17 GTS
3.18 S
3.19 S
3.20 ESP
3.21 ESP
3.22 GDL
3.23 GSR
3.24 POTS
3.25 GSM
3.26 GSM
3.27 V
3.28 F
3.29 C
3.30 TAWS-B
3.31 TAWS-A
3.32 S
3.33 SVS/P
3.34 ESP
1040A AND GDU 1500 DISPLAYS ...................................................................................... 3-1
477 - MFD CONTROLLER ................................................................................................... 3-3
710 - AFCS CONTROLS ...................................................................................................... 3-3
1347D AUDIO PANEL ........................................................................................................ 3-4
NORMAL MODE ................................................................................................................ 3-5
EVERSIONARY MODE ................................................................................................................ 3-6
ONFIGURATION MODE OVERVIEW ............................................................................................ 3-7
/ GFC 700 SOFTWARE INFORMATION ............................................................................ 3-11
SOFTWARE/CONFIGURATION PROCEDURE .................................................................... 3-18
SUPPORT CONFIGURATION .................................................................................... 3-24
VOICE NO CALLOUT OPTION CONFIGURATION ..................................................... 3-25
VOICE CALLOUT OPTION CONFIGURATION ........................................................... 3-26
OPTION CONFIGURATION .............................................................................................. 3-27
OPTION CONFIGURATION ............................................................................................. 3-28
ALT OPTION CONFIGURATION ..................................................................................... 3-29
ON-GARMIN TRAFFIC SYSTEM OPTION CONFIGURATION .................................................. 3-30
8XX TRAFFIC SYSTEM CONFIGURATION ...................................................................... 3-31
TORMSCOPE (WX-500) OPTION CONFIGURATION .............................................................. 3-32
TORMSCOPE (WX-500) CONFIGURATION LOAD CONFIRMATION. ...................................... 3-33
SUPPORT (WITH AOA) OPTION CONFIGURATION .......................................................... 3-34
SUPPORT (NO AOA) OPTION CONFIGURATION .............................................................. 3-35
59 WI-FI DATA LINK OPTION CONFIGURATION ........................................................... 3-36
56 SATELLITE RECIEVER OPTION CONFIGURATION ...................................................... 3-37
HANDSET CONFIGURATION ......................................................................................... 3-38
85A SERVO MOUNT CONFIGURATION .......................................................................... 3-38
86 SERVO MOUNT CONFIGURATION ............................................................................ 3-39
ERIFICATION OF SERVO MOUNT CONFIGURATION .............................................................. 3-40
LITECHARTS CONFIGURATION ............................................................................................. 3-41
HARTVIEW ENABLE ............................................................................................................. 3-41
ENABLE .................................................................................................................. 3-42
ENABLE .................................................................................................................. 3-43
UPPLEMENTAL DATABASE LOADING ................................................................................... 3-44
ATHWAYS ENABLE ...................................................................................................... 3-45
ENABLE .......................................................................................................................... 3-46
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page i 190-00915-01 Revision 7
3.35 GDC 74B AIR DATA COMPUTER SOFTWARE/CONFIGURATION ............................................ 3-47
3.36 GDC
3.37 A
3.38 S
3.39 N
3.40 C
3.41 C
7400 AIR DATA COMPUTER SOFTWARE/CONFIGURATION........................................... 3-48
IRCRAFT REGISTRATION NUMBER ENTRY .......................................................................... 3-49
PLASH SCREEN LOADING ..................................................................................................... 3-50
AVIGATION DATABASE LOADING ....................................................................................... 3-51
ONFIGURATION OF NAVIGATION MAP FOR TRAFFIC SYSTEM ............................................. 3-53
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 GSM
4.10 G1000
4.11 E
4.12 T
4.13 G1000
4.14 N
4.15 I
4.16 S
4.17 P
IRWORTHINESS LIMITATIONS ................................................................................................... 4-1
ERVICING INFORMATION ........................................................................................................... 4-2
AINTENANCE INTERVALS ......................................................................................................... 4-4
ISUAL INSPECTION .................................................................................................................. 4-10
LECTRICAL BONDING TEST ..................................................................................................... 4-15
77 EARTH MAGNETIC FIELD UPDATES ............................................................................. 4-18
80 GREASING PROCEDURE ................................................................................................ 4-18
LAPS-IN-MOTION DISCRETE INPUT CHECK .............................................................................. 4-19
85A/GSM 86 SLIP CLUTCH TORQUE CHECK PROCEDURE .............................................. 4-20
REDUNDANT CONNECTION CHECK ............................................................................ 4-24
NGINE DATA CHECK ............................................................................................................ 4-27
RIM ANNUNCIATOR CHECK ................................................................................................. 4-30
MISCOMPARE CHECKS ............................................................................................... 4-31
OSE AVIONICS COMPARTMENT FANS OPERATIONAL CHECK ............................................. 4-33
NSTRUMENT PANEL FANS OPERATIONAL CHECK ................................................................ 4-33
TANDBY BATTERY PERIODIC CHECKS ................................................................................. 4-34
OWER BUS CHECK ............................................................................................................... 4-37
5 TROUBLESHOOTING ................................................................................................................... 5-1
5.1 G1000
5.2 S
5.3 200/B200
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
5.25 S
5.26 GDL
ALERTING SYSTEM .......................................................................................................... 5-2
YSTEM ANNUNCIATIONS ........................................................................................................... 5-4
SPECIFIC ALERTS ...................................................................................................... 5-25
TROUBLESHOOTING ....................................................................................................... 5-26
YNTHETIC VISION AND PATHWAYS TROUBLESHOOTING ........................................................ 5-27
700 AFCS TROUBLESHOOTING ......................................................................................... 5-30
ACKUP COMMUNICATIONS PATH CHECKS .............................................................................. 5-43
104X TROUBLESHOOTING ................................................................................................ 5-44
104X ALERTS ................................................................................................................... 5-46
63 TROUBLESHOOTING .................................................................................................. 5-54
ALERT MESSAGES .......................................................................................................... 5-56
TROUBLESHOOTING ...................................................................................................... 5-63
TROUBLESHOOTING ...................................................................................................... 5-64
69A TROUBLESHOOTING .............................................................................................. 5-65
77/GMU 44 TROUBLESHOOTING ................................................................................... 5-67
74B/GDC 7400 TROUBLESHOOTING ............................................................................ 5-73
68 TROUBLESHOOTING ................................................................................................ 5-74
710 TROUBLESHOOTING .............................................................................................. 5-75
477 TROUBLESHOOTING ............................................................................................... 5-76
OFTWARE/CONFIGURATION TROUBLESHOOTING ................................................................ 5-77
ACKSHELL/BACKPLATE CONNECTORS ................................................................................ 5-79
TANDBY ATTITUDE INDICATOR TROUBLESHOOTING .......................................................... 5-84
TANDBY AIRSPEED INDICATOR TROUBLESHOOTING ........................................................... 5-84
TANDBY ALTIMETER TROUBLESHOOTING ........................................................................... 5-85
AFE FLIGHT LIFT COMPUTER TROUBLESHOOTING .............................................................. 5-85
59 TROUBLESHOOTING ................................................................................................. 5-87
Page ii G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
5.27 GSR 56 TROUBLESHOOTING .................................................................................................. 5-88
5.28 GTS
820/850 TROUBLESHOOTING ......................................................................................... 5-88
6 EQUIPMENT REMOVAL & INSTALLATION .......................................................................... 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 D
6.20 I
6.21 W
6.22 S
6.23 I
6.24 L-3
6.25 S
6.26 S
6.27 S
6.28 N
6.29 GDU
6.30 GTS
6.31 GPA
6.32 GA
6.33 GDL
6.34 GSR
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/GDC 7400 AIR DATA COMPUTER .............................................................................. 6-4
59 OAT PROBE .................................................................................................................... 6-4
77 AHRS ............................................................................................................................. 6-5
44 MAGNETOMETER .......................................................................................................... 6-5
69A ................................................................................................................................. 6-5
80 SERVOS ....................................................................................................................... 6-6
85A/86 SERVO GEARBOX ............................................................................................... 6-7
477 .................................................................................................................................. 6-7
710 ................................................................................................................................. 6-8
68 ................................................................................................................................... 6-8
ONFIGURATION MODULE REMOVAL & REPLACEMENT ........................................................ 6-9
71 BACKSHELL THERMOCOUPLE REMOVAL & REPLACEMENT .................................... 6-11
ANTENNAS ........................................................................................................ 6-12
IVERSITY TRANSPONDER ANTENNA.................................................................................... 6-12
RIDIUM ANTENNA ................................................................................................................. 6-13
I-FI ANTENNA ..................................................................................................................... 6-13
IGNAL CONDITIONERS .......................................................................................................... 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
OSE AVIONICS BAY COOLING FANS .................................................................................... 6-16
COOLING FANS ............................................................................................................. 6-16
8XX TRAFFIC UNIT ....................................................................................................... 6-17
65 PA/LNA UNIT .......................................................................................................... 6-17
58 TRAFFIC ANTENNAS ................................................................................................... 6-18
59 WI-FI DATALINK ...................................................................................................... 6-18
56 SATELLITE RECEIVER ............................................................................................... 6-19
7 G1000 EQUIPMENT CONFIGURATION & TESTING ............................................................. 7-1
7.1 GDU
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 N
7.14 S
1040/1500 MFD & PFD ..................................................................................................... 7-1
1347D AUDIO PANEL ........................................................................................................ 7-3
63W INTEGRATED AVIONICS UNIT ...................................................................................... 7-6
71 ENGINE/AIRFRAME UNIT ............................................................................................... 7-9
33( ) TRANSPONDER ......................................................................................................... 7-12
74B/GDC 7400 AIR DATA COMPUTER ............................................................................ 7-13
77 AHRS / GMU 44 MAGNETOMETER ............................................................................. 7-18
69A XM DATA LINK ........................................................................................................ 7-26
80 SERVOS ........................................................................................................................ 7-26
477 FMS CONTROLLER ................................................................................................ 7-27
710 AFCS CONTROLLER .............................................................................................. 7-29
68 WEATHER RADAR .................................................................................................. 7-30
ON-GARMIN TRAFFIC SYSTEM FUNCTIONAL CHECK .......................................................... 7-31
TORMSCOPE FUNCTIONAL CHECK ....................................................................................... 7-32
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page iii 190-00915-01 Revision 7
7.15 TAWS FUNCTIONAL CHECK .................................................................................................. 7-34
7.16 F
7.17 C
7.18 S
7.19 DME
7.20 ADF
7.21 R
7.22 W
7.23 RVSM
7.24 S
7.25 ESP
7.26 GTS
7.27 A
7.28 GDL
7.29 GSR
LITECHARTS FUNCTIONAL CHECK ...................................................................................... 7-37
HARTVIEW FUNCTIONAL CHECK ........................................................................................ 7-38
AFETAXI FUNCTIONAL CHECK ............................................................................................ 7-39
FUNCTIONAL CHECK .................................................................................................... 7-40
FUNCTIONAL CHECK ..................................................................................................... 7-41
ADIO ALTIMETER CHECK .................................................................................................... 7-41
EIGHT ON WHEELS AND LOW SPEED AWARENESS BAND CHECK ...................................... 7-42
CHECKS ...................................................................................................................... 7-43
AFE FLIGHT LIFT COMPUTER GROUND CALIBRATION ........................................................ 7-49
FUNCTIONAL CHECK ...................................................................................................... 7-57
8XX TRAFFIC SYSTEM FUNCTIONAL CHECK ................................................................ 7-61
CTIVATION OF GARMIN FLIGHT DATA SERVICES ............................................................... 7-63
59 WI-FI DATA LINK FUNCTIONAL CHECK .................................................................. 7-65
56 SATELLITE RECEIVER FUNCTIONAL CHECK ............................................................. 7-66
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 .......................................................................................................... 8-15
Page iv G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
LIST OF ILLUSTRATIONS
FIGURE PAGE
Figure 2-1, Display Units ........................................................................................................................... 2-1
Figure 2-2, Audio Panel ............................................................................................................................. 2-2
Figure 2-3, AFCS Controller ..................................................................................................................... 2-2
Figure 2-4, FMS Controller ....................................................................................................................... 2-3
Figure 2-5, Transponder ............................................................................................................................. 2-3
Figure 2-6, GIA unit .................................................................................................................................. 2-4
Figure 2-7, GEA unit ................................................................................................................................. 2-5
Figure 2-9, OAT probe .............................................................................................................................. 2-6
Figure 2-10, AHRS .................................................................................................................................... 2-7
Figure 2-11, Magnetometer ....................................................................................................................... 2-7
Figure 2-12, GDL 69A Datalink ................................................................................................................ 2-8
Figure 2-13, GDL 59 Wi-Fi Datalink ........................................................................................................ 2-8
Figure 2-14, GSR 56 Satellite Receiver ..................................................................................................... 2-9
Figure 2-15, GTS 8XX Traffic System ...................................................................................................... 2-9
Figure 2-16, Weather Radar ....................................................................................................................... 2-9
Figure 2-17, Servo ................................................................................................................................... 2-10
Figure 2-18, 200/B200 Electrical Distribution (Post G1000 STC) .......................................................... 2-13
Figure 2-19, G1000 Component Power Sources...................................................................................... 2-14
Figure 2-20, Pitot/Static System (Post G1000 STC) ................................................................................ 2-15
Figure 2-21, G1000/GFC 700 Block Diagram ......................................................................................... 2-16
Figure 3-1, GDU 1040A Control Interface ................................................................................................ 3-1
Figure 3-2, GDU 1500 Control Interface ................................................................................................... 3-2
Figure 3-3, G1000 Softkeys ....................................................................................................................... 3-2
Figure 3-4, MFD Controls (GCU 477 shown) ........................................................................................... 3-3
Figure 3-5, AFCS Controls (GMC 710 shown) ......................................................................................... 3-3
Figure 3-6, GMA 1347D Controls ............................................................................................................. 3-4
Figure 3-7, Normal Mode .......................................................................................................................... 3-5
Figure 3-8, Automatic Reversion with MFD failure ................................................................................. 3-6
Figure 3-9, Manual Reversion with pilot PFD failure .............................................................................. 3-6
Figure 3-10, SET>ACTV Diagram ........................................................................................................... 3-8
Figure 3-11, Loss of Communication ....................................................................................................... 3-9
Figure 3-12, Configuration Status ............................................................................................................. 3-9
Figure 3-13, Data Transmission Indicators ............................................................................................... 3-9
Figure 3-14, G1000 LRU Configuration File Storage ............................................................................ 3-16
Figure 3-15, GRS/GDC Configuration Settings Storage ........................................................................ 3-17
Figure 3-16, Software/Configuration Overview ..................................................................................... 3-18
Figure 3-17, Airframe Options ................................................................................................................ 3-20
Figure 3-18, Propeller Options ................................................................................................................ 3-20
Figure 3-19, Configuration/Software Load Page .................................................................................... 3-21
Figure 3-20, System Status ...................................................................................................................... 3-22
Figure 3-21, TAWS-A Support Configuration ........................................................................................ 3-24
Figure 3-22, TAWS-A Voice No Callout Configuration ......................................................................... 3-25
Figure 3-23, TAWS-A Voice Callout Configuration ............................................................................... 3-26
Figure 3-24, ADF Configuration ............................................................................................................ 3-27
Figure 3-25, DME Configuration ............................................................................................................. 3-28
Figure 3-26, RAD ALT Configuration .................................................................................................... 3-29
Figure 3-27, Non-Garmin Traffic System Configuration ........................................................................ 3-30
Figure 3-28, GTS 8XX TAS/TCAS1 Configuration ............................................................................... 3-31
Figure 3-29, Lightning System Option Configuration ............................................................................. 3-32
Figure 3-30, Stormscope Configuration Page ......................................................................................... 3-33
Figure 3-31, Stormscope Configuration .................................................................................................. 3-33
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page v 190-00915-01 Revision 7
Figure 3-32, ESP Support Configuration ................................................................................................. 3-34
Figure 3-33, ESP Support Configuration ................................................................................................. 3-35
Figure 3-34, GDL 59 Configuration ........................................................................................................ 3-36
Figure 3-35, GSR 56 Configuration ......................................................................................................... 3-37
Figure 3-36, GSM 85A Servo Mount Configuration ............................................................................... 3-38
Figure 3-37, GSM 86 Servo Mount Configuration .................................................................................. 3-39
Figure 3-38, Servo Mount Configuration Verification ............................................................................ 3-40
Figure 3-39, ChartView Enable ............................................................................................................... 3-41
Figure 3-40, TAWS-B Enable ................................................................................................................. 3-42
Figure 3-41, TAWS-A Enable ................................................................................................................. 3-43
Figure 3-42, Supplemental Database Synchronization ............................................................................ 3-44
Figure 3-43, SVS Enable ......................................................................................................................... 3-45
Figure 3-44, ESP Enable .......................................................................................................................... 3-46
Figure 3-45, GDC 74B Configuration ..................................................................................................... 3-47
Figure 3-46, GDC 7400 Configuration .................................................................................................... 3-48
Figure 3-47, Aircraft Registration ............................................................................................................ 3-49
Figure 3-48, Navigation Database Synchronization ................................................................................ 3-52
Figure 4-1, GIA I/O Page ........................................................................................................................ 4-19
Figure 4-2, Discrete Valid/Invalid Indications ........................................................................................ 4-19
Figure 4-3, GFC Status Page................................................................................................................... 4-20
Figure 4-4, GFC Status Page................................................................................................................... 4-21
Figure 4-5, Ambient Temperature Conversion Chart .............................................................................. 4-28
Figure 4-7, Power Supply Connection .................................................................................................... 4-36
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 ................................................................................................................... 5-31
Figure 5-7, Magnetometer Interference Test .......................................................................................... 5-70
Figure 5-8, GIA 63W Backplate Connectors .......................................................................................... 5-79
Figure 5-9, GEA 71 Backplate Connectors ............................................................................................ 5-80
Figure 5-10, GMA 1347D Backplate Connectors................................................................................... 5-80
Figure 5-11, GTX 33/33D Backplate Connectors................................................................................... 5-80
Figure 5-12, GDU 1040A/1500 Backshell Connector (P10401 or P15001) ........................................... 5-81
Figure 5-13, GRS 77 Backshell Connector (P771) ................................................................................. 5-81
Figure 5-14, GDC 74B Backshell Connector (P74B1) ........................................................................... 5-81
Figure 5-15, GDC 7400 Mating Connector (P74001) ............................................................................ 5-81
Figure 5-16, GDL 69A Backplate Connector (P69A1) .......................................................................... 5-81
Figure 5-17, GCU 477 Backshell Connector (P4751) ............................................................................ 5-82
Figure 5-18, GMC 710 Backshell Connector (P7101) ............................................................................ 5-82
Figure 5-19, GWX 68 Backshell Connector (P681) ............................................................................... 5-82
Figure 5-20, GTS 820/850 Mating Connectors (P8001 and P8002) ....................................................... 5-82
Figure 5-21, GTS 820/850 Mating Connector (P8003) .......................................................................... 5-82
Figure 5-22, GPA 65 Mating Connector (P651) ..................................................................................... 5-83
Figure 5-23, Signal Conditioner (1PVIB1 and 2PVIB1) ........................................................................ 5-83
Figure 5-24, GDL 59 Mating Connector (1P591) ................................................................................... 5-83
Figure 5-25, GSR 56 Mating Connector (1P561) .................................................................................... 5-83
Figure 6-1, Servo Gear ............................................................................................................................... 6-6
Figure 6-2, Configuration Module Installation ......................................................................................... 6-9
Figure 6-3, GEA Backshell Thermocouple ............................................................................................. 6-11
Figure 7-1, G1000 Normal Mode Check .................................................................................................. 7-2
Figure 7-2, Marker Beacon Symbology .................................................................................................... 7-4
Page vi G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
Figure 7-3, AUX – GPS STATUS Page (MFD) ....................................................................................... 7-6
Figure 7-4, Normal Engine Instrument Markings (MFD) ........................................................................ 7-9
Figure 7-5, Aircraft Registration .............................................................................................................. 7-12
Figure 7-6, Engine Run-Up Test Page ..................................................................................................... 7-24
Figure 7-7, Normal Mode AHRS Check ................................................................................................ 7-25
Figure 7-8, Low Speed Awareness Band Symbolization ........................................................................ 7-42
Figure 7-9, RVSM Critical Region .......................................................................................................... 7-44
Figure 7-10, Dial Indicator ...................................................................................................................... 7-45
Figure 7-11, Static Port Measurement ..................................................................................................... 7-45
Figure 7-12, Static Port Measurement locations ...................................................................................... 7-46
Figure 7-13, Static Port Measurement Log .............................................................................................. 7-46
Figure 7-14, C-05606-1 Lift Computer .................................................................................................... 7-54
Figure 7-15, Breakout Box ...................................................................................................................... 7-55
Figure 7-16, Force Applicator Usage Instructions ................................................................................... 7-56
Figure 7-17, GTS 8XX GND TEST softkey ............................................................................................ 7-61
Figure 7-18, GSR56 Configuration Page ................................................................................................. 7-66
Figure 7-19, AUX-TELEPHONE page ................................................................................................... 7-66
Figure 8-1, GDU Data Verification (ARINC 429) .................................................................................... 8-7
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, G1000 System Software Version ............................................................................................ 1-1
Table 1-2, Required Documents ............................................................................................................... 1-5
Table 1-3, Reference Publications ............................................................................................................ 1-6
Table 3-1, Software Verification ............................................................................................................. 3-23
Table 4-1, Maintenance Intervals .............................................................................................................. 4-4
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 ....................................... 4-11
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 ................................................................................................................. 4-22
Table 4-11, GSM 85A/GSM 86 Slip Clutch Torque Settings ................................................................ 4-23
Table 4-12, Engine Data Check Test Equipment ..................................................................................... 4-27
Table 4-13, Oil Pressure Indication Test Points....................................................................................... 4-27
Table 4-14, ITT Indication Test Points .................................................................................................... 4-28
Table 4-15, Torque Indication Test Points ............................................................................................... 4-29
Table 4-16, Standby Battery Required Equipment .................................................................................. 4-34
Table 5-1, SVS Troubleshooting ............................................................................................................. 5-27
Table 5-2, SVS-Related Alert Messages ................................................................................................. 5-27
Table 5-3, AFCS Annunciation Troubleshooting ................................................................................... 5-28
Table 5-4, AFCS General Troubleshooting ............................................................................................ 5-29
Table 5-5, Magnetometer Interference Test Sequence ........................................................................... 5-71
Table 7-1, Fuel Flow Indication Special Equipment ............................................................................... 7-10
Table 7-2, Fuel Flow Test Points ............................................................................................................. 7-10
Table 7-3, Oil Pressure Indication Special Equipment ............................................................................ 7-11
Table 7-4, Oil Pressure Test Points .......................................................................................................... 7-11
Table 7-5, Air Data System Test ............................................................................................................. 7-15
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page vii 190-00915-01 Revision 7
Table 7-6, Vertical Speed Table ............................................................................................................. 7-17
Table 7-7, Required GRS/GMU Calibrations ......................................................................................... 7-19
Table 7-8, RVSM Required Avionics ...................................................................................................... 7-43
Table 7-9, In-Flight Altitude Hold Performance Test .............................................................................. 7-48
Page viii G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
1 INTRODUCTION
1.1 Content, Scope, Purpose
This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control System (AFCS) as installed in the Hawker Beechcraft Model 200/B200 series King Air, under STC SA01535WI-D. This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and Appendix G. Information in this document is required to maintain the continued airworthiness of the G1000 and GFC700.
1.1.1 Applicability
This document applies to all Model 200/B200 series King Air aircraft equipped with the G1000 and GFC700 AFCS systems.
Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft operator to include the maintenance information provided by this document in the operator’s Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program.
Aircraft modified by this STC have been shown to qualify for operation in Reduced Vertical Separation Minimum (RVSM) airspace as a group aircraft in accordance with Title 14 of the Code of Federal Regulations (14 CFR) Part 91, Appendix G, “Operations in Reduced Vertical Separation Minimum (RVSM) Airspace”, and Federal Aviation Administration (FAA) Document No. 91-RVSM, Change 2 dated 2/10/2004, “Guidance Material On The Approval Of Operators/Aircraft For RVSM Operations”. This qualification is based on analysis of the configuration and performance of the air data, automatic altitude control, altitude alerting, and altitude reporting systems. These systems must be maintained in accordance with the inspections and tests specified in this document and other current maintenance practices to guarantee continued compliance to RVSM specifications.
1.1.2 Identifying an STC Configuration
Table 1-1 lists the G1000 System Software Version numbers approved for this STC.
Table 1-1, G1000 System Software Version
Aircraft Model
200/B200 Series King Air
200/B200 Series King Air 0985.02 Updated GDU and GIA software
200/B200 Series King Air 0985.03 Updated GDU and GIA software
200/B200 Series King Air 0985.04 Updated GDU and GIA software
200/B200 Series King Air 0985.06 Updated GDU and GRS software
This STC allows multiple configurations for the King Air 200/B200 series. The correct configuration for a particular aircraft is loaded by choosing the applicable airframe/engine/propeller configuration. Refer to Table 6 of the General Arrangement Drawing, Garmin Part Number 005-00421-03, for configuration information for eligible engine and propeller combinations.
G1000 System Software Version
0985.01 superseded
Notes
Updated GIA software
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 1-1 190-00915-01 Revision 7
IMPORTANT!
If the technician is unsure of an aircraft’s STC configuration, perform the following:
After acknowledgement of the splash screen, use the FMS knob on the GCU 477 controller to go to the AUX – SYSTEM STATUS page on the MFD. In the AIRFRAME section (upper right corner,) the display shows the current G1000 airframe configuration and system software version number. The airframe configuration is shown in the AIRFRAME field and the system software version number is shown in the following format: ‘SYS SOFTWARE VERSION XXXX.XX’. It correlates to the software image used to load the software to the system:
EXAMPLE:
System Software Version
‘0985.01’ = Software Image P/N 006-B0985-01
Restart the MFD in configuration mode (see section 3.7) and use the FMS knob on the GCU 477 controller to go to the GDU-AIRFRAME CONFIGURATION page. In the AIRFRAME section (upper right corner), verify the correct configuration for SERIES, ENGINE and PROP.
EXAMPLE:
For a configuration that loaded “King Air B200 PT6A-42” with a “McCauley 3-BLADE” propeller, the AIRFRAME section should display:
SERIES: B200 ENGINE: PT6A-42 PROP: MCCAULEY 3
Page 1-2 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
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 200/B200 Series King Air. An overview of the G1000 and GFC 700 system interface is also provided.
Section 3: G1000 Control & Operation
Presents basic control and operation information specifically tailored to maintenance practices. Basic G1000 Configuration Mode operation is also described.
Section 4: Instructions for Continued Airworthiness
Provides maintenance instructions for continued airworthiness of the G1000 and GFC 700 systems.
Section 5: Troubleshooting
Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000 and GFC 700 systems.
Section 6: G1000 Equipment Removal & Replacement
Gives instructions for the removal and replacement of G1000 and GFC700 equipment.
Section 7: G1000 Equipment Configuration & Testing
Gives instructions for loading software, configuring, and testing of G1000 equipment.
Section 8: System Return to Service Procedure
Specifies return-to-service procedures to be performed upon completion of maintenance of the G1000 system.
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 1-3 190-00915-01 Revision 7
1.3 Definitions/Abbreviations
ADF: Automatic Direction Finder
ADTS: Air Data Test Set
AFCS: Automatic Flight Control System
AFM: Airplane Flight Manual
AFMS: Airplane Flight Manual Supplement
AHRS: Attitude Heading Reference System
CDU: Control Display Unit
CFR: Code of Federal Regulations
DME: Distance Measuring Equipment
EAU: Engine/Airframe Unit
ESP Electronic Stability and Protection
GPS: Global Positioning System
GPWS: Ground Proximity Warning System
HSDB: High-Speed Data Bus (Ethernet)
IAU: Integrated Avionics Unit
ICS: Inter-Com System
ITT: Interstage Turbine Temperature
LRU: Line Replaceable Unit
MFD: Multi-Function Display
OAT: Outside Air Temperature
PFD: Primary Flight Display
RVSM: Reduced Vertical Separation Minimum
STBY: Standby
STBY ATT: Standby Attitude Indicator
STBY ALT: Standby Altimeter
STBY A/S: Standby Airspeed Indicator
STC: Supplemental Type Certificate
TAWS: Terrain Awareness & Warning System
WAAS: Wide Area Augmentation System
VHF: Very High Frequency
1.3.1 Units of Measure
Unless otherwise stated, all units of measure are English units.
Page 1-4 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
1.4 Publications
The following documents are required by this maintenance manual to perform maintenance. It is the responsibility of the owner / operator to ensure latest versions of these documents are used during operation, servicing or maintenance of the airplane.
Table 1-2, Required Documents
Part Number Garmin Document
005-00421-00
005-W0025-00 Wiring Diagram, G1000/GFC 700 King 200/B200
005-00421-03 General Arrangement, G1000/GFC700 AFCS, in Hawker Beechcraft 200/B200 Series King Air 005-00421-32 GWX 68 Radar Install, King Air 200/B200 005-00421-33 Antenna Install, King Air 200/B200 005-00421-30 Main Instrument Panel Installation, King Air 200/B200 005-00421-34 Electrical Equipment Install, Nose Bay, King Air 200/B200 005-00421-35 Roll Servo Install, w/GSM 85A King Air 200/B200 005-00421-36 Yaw Servo Install, w/GSM 85A King Air 200/B200 005-00421-37 Pitch Servo Install, w/GSM 85A King Air 200/B200 005-00421-38 Pitch Trim Servo Install, w/GSM 85A King Air 200/B200 005-00421-39 Magnetometer Install, King Air 200/B200 005-00421-40 OAT Sensor Install, King Air 200/B200 005-00421-42 Datalink Install, King Air 200/B200 005-00421-45 Roll Servo Install, w/GSM 86 King Air 200/B200 005-00421-46 Yaw Servo Install, w/GSM 86 King Air 200/B200 005-00421-47 Pitch Servo Install, w/GSM 86 King Air 200/B200 005-00421-48 Pitch Trim Servo Install, w/GSM 86 King Air 200/B200 005-00421-51 Wire Harness Installation, Nose, King Air 200/B200 005-00421-52 Wire Harness Installation, Cabin, King Air 200/B200 005-00421-53 Wire Harness Installation, Tail, King Air 200/B200 005-00421-54 Control Wheel Modification,G1000/GFC 700, King Air 200/B200 005-00421-55 Overhead Control Panel Modification, G1000/GFC 700, King Air 200/B200 005-00421-31 Pedestal Re-Configuration, King Air 200/B200 005-00421-56 Circuit Breaker Panel Modification, King Air 200/B200 005-00421-58 Glareshield Lighting Modification, King Air 200/B200
101-590010-39 Beech Super King Air 200 and 200T Wiring Diagram Manual 101-590010-133 Super King Air Wiring Diagram Manual 101-590010-161 Super King Air Wiring Diagram Manual
101-590010-19 Super King Air 200 Series Maintenance Manual 101-590010-453 Super King Air 200 Series Airworthiness Limitations Manual
101-590097-13 King Air Series Component Maintenance Manua l
98-39006 Structural Inspection and Repair Manual
85-292-1-1033 Signal Conditioner Installation Manual (Meggitt/Vibro-Meter)
9016182
TP-336 L-3 Avionics Systems – Emergency Power Supply Installation Manual, PS-835
Master Drawing List, Garmin G1000/GFC 700 in Hawker Beechcraft Model 200/B200 Series King Air
Hawker Beechcraft Document
Other Documents
Mid-Continent Instruments - Installation Manual and Operating Instructions, 4200 Series Attitude Indicator
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 1-5 190-00915-01 Revision 7
The following publications are recommended to be on hand during the performance of maintenance activities.
Table 1-3, Reference Publications
Part Number Garmin Document
190-00915-02 190-00929-01 G1000 King Air 200/B200 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 190-00313-63 GMU 44 Installation Location Magnetic Interference Survey Procedure
Airplane Flight Manual Supplement, G1000 Integrated Avionics System and GFC 700 AFCS in Hawker Beechcraft 200/B200 King Air
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 Revison 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.
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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 1347D Audio Panels are located outboard of each PFD. Additionally, a GMC 710 AFCS Controller is located in the upper instrument panel, above the MFD, and a GCU 477 is installed in the pedestal. The GCU 477 provides the control interface for the MFD.
The GDU 1500 communicates with the GDU 1040A units, GDL 69A datalink, GWX68 weather radar, optional GDL59 wi-fi datalink and optional GTS 8XX traffic through a high-speed data bus (HSDB) Ethernet connection. The GDU 1500 communicates with the GCU 477 via RS-232 digital interface.
The GDU 1040A units communicate with each other and the GIA 63W units through a high-speed data bus (HSDB) Ethernet connection.
PFD 1 receives primary electrical power from the new Essential Bus and secondary electrical power from Dual Fed Bus No. 1. PFD 2 receives electrical power from Dual Fed Bus No. 2. Electrical power to the MFD is also provided by the Essential Bus. The displays will power-up immediately with external or aircraft power or battery operation.
All displays are installed in the King Air panel using ¼-turn fasteners. Three CDU cooling fans are also installed behind the panel for PFD and MFD cooling.
Figure 2-1, Display Units
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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 200/B200 installation includes two GMA 1347D panels. The GMA 1347D panels provide control of all cockpit intercom/mic systems as well as NAV/COM/ILS audio. The units also provide display reversion mode control through a large red button. Warning and alert audio received by the GMA 1347Ds is processed by and received from the GIA 63W Integrated Avionics Units (IAUs). Electrical power to GMA 1 is provided from the Essential bus. Electrical power to GMA 2 is provided from Avionics Bus No. 1. GMA 1 will be powered immediately with external or aircraft power or battery operation. GMA 2 will operate after selecting Avionics Master on. The GMA 1347D units interface with the existing marker beacon antenna, as well as existing mic and phone jacks and oxygen mask mic.
Figure 2-2, Audio Panel
2.1.3 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 200/B200 Series Cockpit Reference Guide. The GMC 710 is powered by Dual Fed Bus No. 1.
Figure 2-3, AFCS Controller
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2.1.4 GCU 477 FMS Control Unit
The GCU 477 functions as the primary control interface to the GDU 1500 MFD. The GCU 477 provides alphanumeric, softkey, and flight planning function keys used to interface with the G1000; the MFD does not possess any knobs or controls other than softkeys. The GCU 477 is powered by the Essential Bus. The GCU 477 also provides the crew with the added functionality of tuning their receivers via the GCU as well as the PFD. Detailed instructions regarding the controls are discussed in the G1000 Cockpit Reference Guide.
Figure 2-4, FMS Controller
2.1.5 GTX 33( ) Extended Squitter Transponder (2)
The Garmin GTX 33( ) transponders communicates with the on-side GIA 63W through RS-232 digital interface. This STC installation allows for installation of two GTX 33 non-diversity transponders, two GTX 33D Diversity transponders, or one of each type. The units are mounted under the floor in the cabin just aft of fuselage station 246.750. Power is provided by the No. 1 GTX 33( ) from the Essential Bus. The No. 2 GTX 33( ) is powered from the Avionics Bus No. 1. Each GTX 33( ) transponder interfaces with a transponder antenna mounted to the bottom of the fuselage. Each GTX33D diversity transponder interfaces to a transponder antenna mounted to the top of the fuselage.
Figure 2-5, Transponder
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2.1.6 GIA 63W Integrated Avionics Unit (2)
Two Garmin GIA 63W Integrated Avionics Units (IAUs) contain the VHF COM/NAV receivers, WAAS GPS receiver, Flight Director, and system integration microprocessors. The GIAs also serve as a communication interface to all other G1000 LRUs in the system. Each GIA 63W communicates directly with the on-side GDU 1040A display using a HSDB Ethernet connection. Both GIAs are located remotely in the nose equipment bay.
GIA 1 receives primary electrical power from the Essential Bus and a secondary electrical power supply from Dual Fed Bus No.1. GIA 2 receives electrical power from Dual Fed Bus No. 2. The GIA 1’s COMM power supply (COMM 1) is provided by the Essential Bus. GIA 2’s COMM power supply (COMM 2) is provided by Avionics Bus No. 1. Therefore, both GIAs power-up immediately with external or aircraft power or battery operation, with the exception of COMM 2 operation which will become active after selection of Avionics Master on.
Both GIA 63Ws interface to the following equipment:
• Existing VOR/LOC/Glideslope Antenna System
• Existing VHF COM #1 & #2 Antennas
• Newly installed GA 36 and GA 37 GPS/WAAS Antennas
• GMA 1347D, #1 & #2
• GEA 71, #1 & #2
• GDU 1040A, #1 & #2
• GSA 80
• 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 (if installed)
• Stormscope (if installed)
• Radio Altimeter (if installed)
Figure 2-6, GIA unit
Page 2-4 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
2.1.7 GEA 71 Engine/Airframe Unit (2)
The Garmin GEA 71 Engine/Airframe Units provide engine/airframe data to the G1000 system. Data received from transducers/sensors is processed and sent to GIA 63Ws (via RS-485 digital interface), and subsequently to the GDU 1500 MFD. Engine parameters are normally displayed on the MFD. In the event of MFD failure, the engine parameters can be displayed on PFD 1 and/or PFD 2 using display reversion. The GEAs are located behind the instrument panel and is mounted in a vertical orientation. Electrical power to GEA 1 is provided from Dual Fed Bus No. 1 and to GEA 2 from Dual Fed Bus No. 2. Both GEA units will power-up immediately with external or aircraft power or battery operation.
NOTE
On serial numbers BB-1484, 1486 and subsequent, the electrical system includes the L ENG INSTR and R ENG INSTR buses which (after this STC) are powered from Dual Fed Bus No. 1 and No. 2 respectively. On these aircraft, GEA 1 receives power from Dual Fed Bus No. 1 via the L ENG INSTR bus and GEA 2 receives power from Dual Fed Bus No. 2 via the R ENG INSTR bus.
Each GEA interfaces to the following sensors for its onside engine:
• Oil Pressure Sensor
• Oil Temperature Sensor
• Fuel Flow Sensor (via onside Signal Conditioner)
• Turbine Speed Sensor (via onside Signal Conditioner)
• Propeller Speed Sensor(via onside Signal Conditioner)
• Torque Sensor
• Interstage Turbine Temperature (ITT) Sensor
Figure 2-7, GEA unit
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2.1.8 Digital Air Data Computer (2)
The Garmin GDC 74B or optional GDC 7400 air data computers compile information from the pitot/static system and various outside air temperature (OAT) and awareness sensors and provide digital air data computations to the G1000 system. The GDC communicates with the GIA 63W, GDU 1040A, and GRS 77 using ARINC 429 digital interface. The unit is mounted behind the instrument panel. GDC 1 receives primary electrical power from the Essential Bus and a secondary power supply from Dual Fed Bus No. 1. GDC 2 receives power from Dual Fed Bus No. 2. GDC 1 and GDC 2 connect to existing pitot/static ports. Refer to Figure 2-20 for a schematic of the aircraft’s pitot/static system and its connections to the G1000 STC installed equipment.
IMPORTANT!
Aircraft modified by this STC are eligible to be approved for RVSM operation. RVSM critical maintenance instructions contained in this document must be followed in order to guarantee performance within RVSM specifications.
GDC 74B GDC 7400 (optional)
Figure 2-8, Air Data Computer
2.1.9 OAT Probe (2)
The Garmin GTP 59 OAT Probes provide the GDC 74B or optional GDC7400 with air temperature data. The OAT probes are mounted to the bottom of the fuselage at F.S. 113.5.
Figure 2-9, OAT probe
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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 in the nose equipment bay, contain advanced tilt sensors, accelerometers, and rate sensors. The unit interfaces with the GDC 74B/GDC 7400 and GMU44 Magnetometer and utilizes GPS signals from the GIA 63Ws. Actual attitude and heading information is sent using ARINC 429 digital interface to both GDU 1040As and GIA 63Ws. The GRS 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.
GRS 1 receives primary electrical power from the Essential Bus and a secondary power supply from the Dual Fed No. 1 Bus. GRS 2 receives electrical power from Dual Fed No. 2 bus.
Figure 2-10, AHRS
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 tailcone. The units receive power directly from the GRS 77 units and communicate with the GRS 77 units via RS-485 digital interface.
Figure 2-11, Magnetometer
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2.1.12 GDL 69A Datalink
The GDL 69A provides the interface to the GWX 68 weather radar and optional GDL59 wi-fi datalink by acting as a communications hub between the MFD and GWX 68 and GDL 59 via HSDB. The GDL 69A also provides XM Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A is mounted behind the instrument panel. Power to the GDL 69A is received from the Avionics No. 2 bus. The GDL 69A sends weather data through the HSDB bus to the MFD, where the data link interface is controlled. Digital audio is sent directly to the GMA 1347D Audio Panel.
Optional remote control (GRC 10) and remote control transceiver (GRT 10) may be interfaced with the GDL 69A. Installation of the GRC 10 and GRT 10 is in accordance with Garmin STC SA01487SE or other approved data. Refer to the approved Instructions for Continued Airworthiness information for these units. It is recommended that GRT 10 be powered from the Entertainment Bus.
Figure 2-12, GDL 69A Datalink
2.1.13 GDL 59 Wi-Fi Datalink (optional)
The GDL 59 provides a POTS (plain old telephone service) phone interface and a high speed data link between the aircraft systems and ground computers while the aircraft is on the ground using the IEEE
802.11g (“Wi-Fi”) protocol. The GDL 59 also provides the interface to an optional GSR 56 satellite datalink, which adds airborne low speed data link and voice communication capability. The GDL 59 unit interfaces to the Garmin Integrated Flight Deck via the GDL69A using HSDB. The GDL 59 is located in the aft cabin floor area, just forward of the cabin door. The GDL 59 is powered from the Avionics No. 2 bus.
Figure 2-13, GDL 59 Wi-Fi Datalink
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2.1.14 GSR 56 Satellite Receiver (optional)
The GSR 56 provides airborne low speed data link and voice communication capability to Garmin Integrated Flight Deck installations. The GSR 56 contains a transceiver that operates on the Iridium Satellite network. The GSR 56 interfaces directly to the GDL 59 via an RS-232 interface. The GSR 56 is located in the aft cabin floor area, just forward of the cabin door. The GSR 56 is powered from the Avionics No. 2 bus.
Figure 2-14, GSR 56 Satellite Receiver
2.1.15 GTS 8XX Traffic System (optional)
The GTS 8XX is a traffic surveillance system that uses active interrogation of Mode S and Mode C transponders to provide traffic advisories to the pilot. The GTS 820 is a TAS unit; the GTS 850 is a TCAS I unit. The installation includes a top directional antenna (GA 58) paired with a GPA 65 power amplifier / low noise amplifier (PA/LNA) unit and a bottom, unamplified GA 58 antenna. The GTS 8XX is located in the nose avionics bay on the top, left shelf. The GPA 65 is located in the left sidewall area, just in front of the most forward cabin window. The GTS 8XX traffic system is powered from the Avionics No. 2 bus.
Figure 2-15, GTS 8XX Traffic System
2.1.16 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. 1 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).
Figure 2-16, Weather Radar
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2.1.17 GSA 80 Servos and GSM 85A/86 Servo Gearboxes (4)
The Garmin GFC 700 AFCS uses GSA 80 high torque servos to automatically control aircraft pitch, roll, yaw damper/turn coordination and pitch trim. The pitch trim variant of the GSA 80 is a high speed servo actuator. The GSA 80 contains a motor-control and monitor circuit board, as well as a solenoid and a brushless DC motor. The GSA 80 servo receives serial RS-485 data packets from the GIA 63Ws. The roll servo is located in the forward cabin lower fuselage at F.S. 185. The pitch, yaw, and pitch trim servos are located in the tail. Power to the servos is received from the avionics No. 2 bus. All servos mount to a Garmin GSM 85A or GSM 86 Servo Gearbox. The GSM 85A/86 is responsible for transferring the output torque of the GSA 80 servo actuators to the mechanical flight control surface linkage. The GSM 85A has a slip clutch that can be adjusted to a desired torque value. The GSM 86 has a clutch cartridge that cannot be adjusted to a different torque value.
Figure 2-17, Servo
2.1.18 Garmin G36 and 37 GPS/WAAS Antennas
This installation uses one G36 GPS/WAAS antenna and a G37 GPS/WAAS/XM antenna. The antennas are located in the upper, forward cabin, at F.S. 152.
2.1.19 Signal Conditioner (2)
Each GEA 71 receives signals from its on-side engine turbine speed sensor, propeller speed sensor and fuel flow sensors via a Meggitt (Vibro-Meter) Signal Conditioner. This unit converts the signals from the engine sensors to a signal usable by the GEA 71. These units are installed behind the instrument panel. Electrical power to the No. 1 Engine Signal Conditioner is provided from Dual Fed Bus No. 1 and to the No. 2 Engine Signal Conditioner from Dual Fed Bus No. 2. Both signal conditioners will power-up immediately with external or aircraft power or battery operation.
NOTE
On serial numbers BB-1484, 1486 and subsequent, the electrical system includes the L ENG INSTR and R ENG INSTR buses which (after this STC) are powered from Dual Fed Bus No. 1 and No. 2 respectively. On these aircraft, the No. 1 Engine Signal Conditioner receives power from Dual Fed Bus No. 1 via the L ENG INSTR bus and the No. 2 Engine Signal Conditioner receives power from Dual Fed Bus No. 2 via the R ENG INSTR bus.
Page 2-10 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
2.1.20 Standby Airspeed Indicator
A Standby Airspeed indicator, Aerosonic part number 25030-0184, is installed between PFD 1 and the MFD. Due to varying airspeed marking requirements, four marking options are used. To determine the appropriate option for a specific aircraft configuration, refer to the General Arrangement drawing, Garmin Document 005-00421-03. The standby airspeed indicator does not require electrical power for normal operation except for internal instrument lighting, which is powered from Dual Fed No. 1 Bus and the emergency standby battery. This unit is connected to the right-hand pitot/static system.
2.1.21 Standby Altimeter
A standby altimeter, Aerosonic part number 16650-1172, or Thommen part number 3A43.22.35F.28.1.FU, is installed between PFD 1 and the MFD. This unit incorporates a vibrator to ensure accurate display altitude information. The vibrator is powered by the new Standby Instrument Bus and the emergency standby battery. Internal lighting of this unit is powered from Dual Fed No. 1 Bus and the emergency standby battery. This unit is connected to the right-hand static system.
2.1.22 Standby Attitude Indicator
The Mid-Continent Model 4200-11 Electric Attitude Indicator is used as the standby attitude indicator. It is connected to the new Standby Instrument Bus and the emergency standby battery. Gyro power and internal lighting of this unit is powered from Dual Fed No. 1 Bus and the emergency standby battery.
2.1.23 L-3 PS-835(C or D Model) Emergency Standby Battery
In the event of loss of all normal electrical power, the battery is designed to provide 24 Vdc (nominal) emergency power source for the following items:
• standby attitude indicator (operation and internal lighting)
standby altimeter (vibrator and internal lighting)
•
standby airspeed indicator (lighting only)
•
pilot side glareshield lighting
•
The aircraft power buss provides a trickle charge to the PS-835 under normal conditions. This battery is installed in the nose avionics bay. It is controlled using the standby battery switch indicator on the instrument panel.
2.1.24 Safe Flight Lift Computer
For the optional Electronic Stability and Protection (ESP) feature with Angle Of Attack modes, a new Safe Flight lift computer, part number C-05606-1, that is a direct replacement for the existing lift computer is installed to provide an additional Low Airspeed Awareness (LAA) output to support the Angle of Attack modes of Electronic Stability and Protection. The lift computer is located in the same location as the original lift computer, under the forward cabin floor. Note: this unit is not used for the “ESP – no AOA” option.
2.2 G1000 Optional Interfaces
Optional equipment interfaces include L-3 WX-500 Stormscope, traffic systems, radio altimeter, ADF systems and DME systems. The G1000 also provides a general purpose ARINC bus for use with third party entertainment and cabin equipment. Refer to wiring diagram listed in Table 1-2, for specific interface information.
G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Page 2-11 190-00915-01 Revision 7
2.3 Electrical Power Distribution
This airplane uses a multi-bus system, as detailed below and in Figure 2-18. This Figure shows the system post installation of this STC. Although this STC made several bussing changes to the distribution system, the core electrical generation and distribution system remains unchanged from the basic airplane design. Figure 2-19 shows the power sources for all equipment used by this STC. Each bus used or modified by this installation is described below.
Left and Right Generator Buses:
and right generators. The left and right generator buses also support all four dual fed buses and No. 1 and
No. 2 avionics buses, respectively. Isolation Bus: The Isolation bus is fed by two generator buses and the battery bus. The Isolation bus is used
in this installation to provide power to the new Standby Instrument Bus and the new Essential bus.
Dual-fed Buses:
document as Dual Fed No. 1 Bus, Dual Fed No. 2 Bus, Dual Fed No. 3 Bus and Dual Fed No. 4 Bus. Each of these dual fed buses are powered from the Left and the Right Generator buses.
Avionics Buses
relay. The No. 2 Avionics bus is powered from the Right Generator Bus via the Avionics No. 2 relay. Both
Avionics relays are controlled using the Avionics Master Switch.
Left and Right Engine Instrument Buses
system includes the L ENG INSTR and R ENG INSTR buses. This STC relocates these two buses such that they are powered from Dual Fed Bus No. 1 and No. 2 respectively. Prior to these serial numbers, these two buses are not installed and engine instruments are powered directly from the dual fed buses. (Figure 2-1 shows the system with these buses installed and relocated.).
Essential Bus
and the Isolation bus.
Standby Instrument Bus
Isolation bus and provides one source of power to the standby attitude indicator and standby altimeter
vibrator.
The electrical distribution uses four individual dual-fed buses referred through this
: The No. 1 Avionics bus is powered from the Left Generator Bus via the Avionics No. 1
: The Essential bus is a new bus added by this STC. It is powered from Dual Fed No. 1 bus
: The Standby Instrument bus is a new bus added by this STC. It is powered by the
The left and right generator buses receive power from their respective left
: On serial numbers BB-1484, 1486 and subsequent, the electrical
Entertainment Bus
Avionics bus via a newly installed Entertainment Bus relay. This relay is controlled via the existing Cabin Furnishing switch so that bus can be easily shed by pilot using single switch action along with the other cabin equipment.
Emergency Standby Battery:
200/B200 is designed to provide uninterrupted DC power to the Standby Attitude indicator (gyro motor), the Standby Altimeter (vibrator) and internal instrument lighting for the standby attitude indicator, standby altimeter and the standby airspeed indicator from the L-3 PS-835(C or D Model) Emergency Standby Battery. This standby battery power is independent from the normal electrical system and provides redundant power for the standby instruments in the event that all other electrical power is lost.
Page 2-12 G1000 / GFC 700 System Maintenance Manual - 200/B200 Series King Air Revision 7 190-00915-01
: The Entertainment Bus is a new bus added by this STC. It is powered from the No.2
The Standby Emergency Battery (STBY BATT) system in the King Air
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