Garmin Cessna Caravan G1000 Manual

190-00682-00 January 2008 Revision 5
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G1000 / GFC 700 Post Installation Checkout Procedure
Hawker / Beechcraft King Air C90

Page A G1000/GFC 700 Post Installation Checkout Procedure
Hawker / Beechcraft King Air C90
Revision 5 190-00682-00
© Copyright 2008
Garmin Ltd. or its subsidiaries
All Rights Reserved
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any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.
Garmin International, Inc.
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Olathe, KS 66062 USA
Telephone: [phone]
www.garmin.com
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Phone: [phone]
Fax: [phone]
RECORD OF REVISIONS
Revision Revision Date Description ECO #
1 05/07/2007 Initial release -------
2 07/02/2007
Revised document to include latest functionality and minor
corrections. 45777
3 09/27/2007 Modified title and made minor corrections through out. 47582
4 10/25/2007 Updated procedures 2.6.2 and 6.2 on sheets 2-9 and 6-4 48254
5 1/14/2008
Update procedures 2.6, 2.7, 2.8, 2.9, and 4.3. Added
procedures 2.5.4, 2.5.5 and 3.20. 50256
DOCUMENT PAGINATION
Section Pagination
Table of Contents iii – iv
Section 1 1-1 – 1-8
Section 2 2-1 – 2-22
Section 3 3-1 – 3-34
Section 4 4-1 – 4-6
Section 5 5-1 – 5-10
Section 6 6-1 – 6-10
Section 7 7-1 – 7-6
Section 8 8-1 – 8-6
Section 9 9-1 – 9-1

G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page i
190-00682-00 Revision 5
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.
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.
The GDU 1040A PFDs and GDU 1500 MFD use a lens 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
All G1000 screen shots used in this document are current at the time of initial 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.
CAUTION
WARNING
IMPORTANT

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G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page iii
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TABLE OF CONTENTS
1INTRODUCTION 1-1
1.1 Scope .................................................................................................................................................1-1
1.2 Organization.......................................................................................................................................1-1
1.3 Reference Documents........................................................................................................................1-2
1.4 System Description ............................................................................................................................1-3
1.5 G1000 Control Interface.....................................................................................................................1-6
2POST INSTALLATION PROCEDURES 2-1
2.1 Required Test Equipment...................................................................................................................2-1
2.2 G1000 Hardware/Software Compatibility Check................................................................................2-1
2.3 G1000 Software/Configuration Procedure.........................................................................................2-2
2.4 Software Load Confirmation...............................................................................................................2-5
2.5 King Air C90 Airframe Configuration..................................................................................................2-7
2.6 Traffic System Option Configuration................................................................................................2-11
2.7 StormScope (WX-500) Option Configuration...................................................................................2-12
2.8 ADF – 60 Option Configuration.......................................................................................................2-15
2.9 DME 42 Option Configuration..........................................................................................................2-15
2.10FliteCharts Configuration..................................................................................................................2-16
2.11ChartView Configuration ..................................................................................................................2-17
2.12TAWS Configuration.........................................................................................................................2-18
2.13Aircraft Registration Number Entry ..................................................................................................2-19
2.14Terrain/Obstacle Database Loading ................................................................................................2-19
2.15Aviation Database Loading ..............................................................................................................2-20
2.16Clearing Default User Settings.........................................................................................................2-20
2.17Software/Configuration Troubleshooting..........................................................................................2-21
3G1000 INITIAL SYSTEM TESTING 3-1
3.1 Electrical Power Distribution Testing..................................................................................................3-1
3.2 Electrical Load Test Procedures........................................................................................................3-5
3.3 Display Testing.................................................................................................................................3-10
3.4 GPS Signal Acquisiton.....................................................................................................................3-13
3.5 GMA 1347D Testing.........................................................................................................................3-14
3.6 VHF COMM Operational Check.......................................................................................................3-15
3.7 Marker Beacon Test.........................................................................................................................3-15
3.8 VHF COM Interference Test ............................................................................................................3-15
3.9 VOR/LOC/GS Test...........................................................................................................................3-16
3.10COM Antenna VSWR Checks..........................................................................................................3-16
3.11GTX 33 Testing................................................................................................................................3-17
3.12Pitot Static System Leak Checks.....................................................................................................3-18
3.13GDC 74B Testing.............................................................................................................................3-19
3.14GDL 69A Functional Check..............................................................................................................3-22
3.15GEA Functional Check.....................................................................................................................3-26
3.16TAWS Functional Check..................................................................................................................3-27
3.17FliteCharts Functional Check...........................................................................................................3-28
3.18ChartView Functional Check............................................................................................................3-29
3.19SafeTaxi Functional Check ..............................................................................................................3-30
3.20Aircraft Weight Configuration Functional Check ..............................................................................3-31
4INTERFACE TESTING 4-1
4.1 GWX 68 Weather Radar Check.........................................................................................................4-1
4.2 Optional Stormscope Functional Check.............................................................................................4-2
4.3 Optional Traffic System Functional Check.........................................................................................4-4
4.4 Optional DME Functional Check........................................................................................................4-5
4.5 Optional ADF Functional Checks.......................................................................................................4-6
5GRS 77/GMU 44 INITIAL ALIGNMENT and STBY COMPASS CALIBRATION 5-1
5.1 Procedure A: GRS 77 Pitch/Roll Offset Calibration ..........................................................................5-1
5.2 Engine Start........................................................................................................................................5-2
5.3 Final GRS 77/GMU 44 Calibration Procedures..................................................................................5-3

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6Final System Checkout 6-1
1. GPS Failure Test................................................................................................................................6-1
6.1 GIA Failure Test.................................................................................................................................6-2
6.2 Display Failure Test............................................................................................................................6-3
6.3 Cooling Fan Failure Annunciations....................................................................................................6-5
6.4 Standby Electrical Power Checks......................................................................................................6-5
6.5 G1000 Backup Path Tests .................................................................................................................6-7
7GFC 700 GROUND CHECKS 7-1
7.1 Pre-Flight Test....................................................................................................................................7-1
7.2 AFCS Switch Checks.........................................................................................................................7-2
7.3 Autopilot Clutch Overpower Check....................................................................................................7-3
7.4 Manual Electric Pitch Trim Speed Check...........................................................................................7-3
7.5 Autopilot Operation Checks ...............................................................................................................7-3
8GFC 700, TAWS and POST MODIFICATION FLIGHT TEST PROCEDURE 8-1
8.1 Before Take-Off..................................................................................................................................8-1
8.2 Initial Engagement..............................................................................................................................8-1
8.3 Vertical Speed (VS) Mode..................................................................................................................8-1
8.4 Pitch Mode (PIT) & Altitude Alerting...................................................................................................8-2
8.5 Flight Level Change (FLC) Mode & Altitude Capture.........................................................................8-2
8.6 Altitude Hold (ALT) Mode & Heading Select (HDG) Mode ................................................................8-3
8.7 Overspeed Protection Mode ..............................................................................................................8-3
8.8 NAV Modes........................................................................................................................................8-3
8.9 TAWS ‘FIVE HUNDRED’ Call-out......................................................................................................8-5
9SIGNATURES 9-1
LIST OF ILLUSTRATIONS
LIST OF TABLES
Figure 1-1. G1000 & GFC 700 in King Air C90A/C90GT..........................................................................1-4
Figure 2-1. Software/Configuration Overview...........................................................................................2-2
Figure 3-1. MFD Power Up Page............................................................................................................3-10
Figure 3-2. PFD Power-up System Annunciations .................................................................................3-11
Figure 3-3. 4th AUX Page.......................................................................................................................3-13
Figure 3-4. Marker Beacon Symbology ..................................................................................................3-15
Figure 5-1. Pitch/Roll Offset......................................................................................................................5-1
Figure 5-2. G1000 Engine/Airframe Indicators .........................................................................................5-2
Figure 5-3. AHRS Information Valid..........................................................................................................5-7
Figure 5-4. Magnetometer Interference Test............................................................................................5-8
Figure 7-1. Pre-Flight Test........................................................................................................................7-1
Table 1-1. Referenced Documentation.....................................................................................................1-2
Table 5-1. Magnetometer Interference Test Sequence............................................................................5-9

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1 INTRODUCTION
1.1 Scope
This document presents the post-installation procedures which are required to be performed after
installing the G1000 Integrated Cockpit System in the Hawker Beechcraft King Air C90 series aircraft.
This document and revision are effective for the following aircraft:
Aircraft Model Model Name G1000 System
Software Version
C90A / C90GT King Air Ref. General Arrangement, G1000/GFC 700 AFCS,
King Air C90A/GT (005-00375-22)
Refer to the General Arrangement, G1000/GFC 700 AFCS, King Air C90A/GT (005-00375-22) for details
on specific aircraft eligibility for this STC.
Additional STC documents are listed in the Master Drawing List, 005-00375-30.
1.2 Organization
Follow the procedures in this document to configure and test a newly-installed Garmin G1000 Integrated
Avionics System with GFC 700 Automatic Flight Control System in the Hawker Beechcraft King Air Model
C90A/GT. The person performing the configuration and testing should read through this entire document
prior to beginning any procedures.
Section 1:
Introduction, reference documents, system description and operation.
Section 2:
Software and system configuration loading procedures. Manual configuration items are also
addressed. At the end, all software versions and part numbers are verified against drawing 005-
00375-22 “General Arrangement, King Air C90A/GT”.
Section 3:
Ground checks include exercising and testing basic G1000 functions.
Section 4:
Ground checks of G1000 interfaced equipment including GWX 68, StormScope®, Traffic
System, DME and ADF.
Section 5:
AHRS alignment and calibration procedures.
Section 6:
Final systems checkout.
Section 7:
Detailed GFC 700 ground checks are given in this section.
Section 8:
Flight testing procedures are given where mode function checks are conducted, and final
autopilot and TAWS checks are made.

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1.3 Reference Documents
For additional information on the installation, refer to the documents below.
GWX 68 Radar Install, King Air C90A/C90GT 005-00375-19
Antenna Install, King Air C90A 005-00375-21
General Arrangement, G1000/GFC 700 AFCS, King Air
C90A/C90GT 005-00375-22
Control Wheel Modification G1000/GFC700, King Air C90 005-00375-23
Overhead Control Panel Modification, G1000/GFC700,
King Air C90A 005-00375-25
Pedestal Re-configuration, King Air C90A 005-00375-26
Main Instrument Panel Installation, King Air C90A/C90GT 005-00375-28
Circuit Breaker Panel Modification, King Air C90A 005-00375-29
Circuit Breaker Panel Modification, King Air C90A 005-00375-70
Wire Harness Routing, Tail, King Air C90 005-00375-31
Electrical Equipment Install, Nose Bay, King Air C90A 005-00375-34
Removal, Collins AP65 Servos, King Air C90A 005-00375-36
Pitot-Static-Vacuum Line Removal, King Air C90A 005-00375-37
Roll Servo Install, King Air C90A 005-00375-41
Yaw Servo Install, King Air C90A 005-00375-42
Pitch Servo Install, King Air C90A 005-00375-43
Pitch Trim Servo Install, King Air C90A 005-00375-44
Magnetometer Install, King Air C90A/C90GT 005-00375-53
OAT Sensor Install, King Air C90A/C90GT 005-00375-54
Wire Harness Routing, Nose, King Air C90A/C90GT 005-00375-55
Wire Harness Routing, Cabin, King Air C90A 005-00375-56
Wiring Diagram G1000/GFC 700, King Air C90A/C90GT 005-W0022-00
Bracket, Servo Mount, Pitch Trim, C90 115-00860-XX
Fan Bracket 115-00861-XX
Panel, Main Instrument, G1000, C90 115-00862-XX
Cable Assy, GFC 700, C90 233-20006-XX
Wire Harness Assy, G1000/GFC 700, King Air
C90A/C90GT 320-00326-XX
Table 1-1. Referenced Documentation

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1.4 System Description
1.4.1 Equipment
The G1000 and GFC 700 AFCS is comprised of the following equipment:
Control & Display:
•Two GDU 1040A PFDs
•GDU 1500 MFD
•GCU 475 FMS Control Unit
Communication, Navigation, & Surveillance:
•Two GIA 63W Integrated Avionics Units
•Two GMA 1347D Audio Panels
•Two GTX 33 Mode S Transponders
•GDL 69A Datalink
Sensors:
•Two GDC 74B Air Data Computers (ADC)
•Two GRS 77 Attitude & Heading Reference Systems (AHRS)
•Two GMU 44 Magnetometers
•Two GEA 71 Engine/Airframe Units
•GEA engine parameter function supported by 2 Sandia tach-gen adaptors and a Senior
Aerospace fuel flow signal conditioner.
Autopilot:
•GMC 710 AFCS Mode Controller
•GSA 80 Servos (Yaw, Pitch & Roll)
•GSA 81 Servos (Pitch Trim)
•GSM85 Servo Mount
•GSM85A Servo Mount

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GDU 1040A (PFD1)
GDU 1500 (MFD)
No. 1 GIA 63W
System Integration
Processors
I/O Processors
VHF COM
VHF NAV/LOC
GPS
Glideslope
WAAS
VNAV
AFCS Mode Logic
No. 1 Flight Director
Servo Communication
No. 1 GDC 74B
Air Data Computer
Airspeed, Altitude,
Vertical Speed, OAT
No. 1 GEA
Engine / Airframe
Unit
GSA 80
Roll Servo GSA 81
Pitch Trim Servo
GSA 80
Pitch Servo
No. 1 GTX 33
Mode S Transponder
No. 2 GMA
1347D
GDL69A
XM Satalite Datalink
(WX & Radio)
No.1 GTP59
OAT Probe
GMC 710 (AFCS Controller)
No. 1 GMU44
Magnotometer
GSA 80
Yaw Servo
DME
WX-500
SKY899
No. 2 GIA 63W
System Integration
Processors
I/O Processors
VHF COM
VHF NAV/LOC
GPS
Glideslope
WAAS
VNAV
AFCS Mode Logic
No. 2 Flight Director
Servo Communication
No. 2 GDC 74B
Air Data Computer
Airspeed, Altitude,
Vertical Speed, OAT
No. 2 GEA
Engine / Airframe
Unit
No. 2 GRS 77 AHRS
Atitude
Rate of Turn
Slip/Skid
No. 1 GRS 77 AHRS
Atitude
Rate of Turn
Slip/Skid
No. 2 GMU44
Magnotometer
No. 2 GTX 33
Mode S Transponder
No. 2 GTP59
OAT Probe
GDU 1040A (PFD2)
No. 1 GMA
1347D
GCU 475 (FMS Controller)
GWX 68
WX Radar
No. 1 ST—26
Tach-Gen
Adapter
No. 2 ST—26
Tach-Gen
Adapter
PC-920
FF Signal
Conditioner
Figure 1-1. G1000 & GFC 700 in King Air C90A/C90GT

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1.4.2 GFC 700 Operation
The GFC 700 is a fail-passive digital flight control system composed of multiple G1000 LRUs and servos.
The following functions are provided by the GFC 700 in this installation:
•Flight Director
•Autopilot
•Pitch Trim
•Yaw Damper
Flight Director:
The Flight Directors operate within the GIA 63Ws and use data from the G1000 system, including air,
attitude, and flight data, to calculate commands for display to the pilot and for the Autopilot. Flight director
command bars and mode annunciations are sent to the PFDs through a high-speed Ethernet connection
for display to the pilot and copilot. The flight directors operate independently of the autopilot, and allows
the pilot to hand-fly the command bars, if desired. The GMC 710 allows the pilot to switch the active
director between flight director #1 (GIA1) and flight director #2 (GIA2).
Autopilot:
The autopilot operates within one GSA 81 servo (pitch trim) and three GSA 80 servos (pitch, roll and
yaw). Flight director data is processed within the servos and turned into aircraft flight control surface
commands. The autopilot cannot operate unless the flight director is engaged.
Manual Electric Trim:
When the autopilot is not engaged, the pitch trim servo may be used to provide a Manual Electric Pitch
Trim (MEPT) function. This allows the pilot or co-pilot to adjust pitch trim from the PITCH TRIM switch on
the control wheel in lieu of using the elevator trim wheel. Trim speeds are scheduled to provide easier
control over a wide speed or configuration range. The PITCH TRIM switch is split into two halves. The left
half arms MEPT. The right half controls direction. Both halves must be actuated at the same time to
command the pitch trim servo to operate. If only one half of the PITCH TRIM switch is actuated for more
than 3 seconds, a red PTRM message will appear on the PFDs.
Yaw Damper:
The yaw damper reduces dutch roll tendencies and coordinates turns. It can operate independently of the
autopilot and may be used during normal hand-flight maneuvers.

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1.5 G1000 Control Interface
Control and operation of the following G1000 and GFC 700 equipment occurs through the PFDs, MFD,
GMC , GCU or GMA 1347D audio panels. See the following documents for detailed information
regarding control and operation.
•G1000/GFC 700 and TAWS in Hawker Beechcraft King Air C90A/GT Airplane Flight Manual
Supplement, Garmin P/N 190-00682-02 Revision A or later.
•G1000 in Hawker Beechcraft King Air C90A/GT Cockpit Reference Guide, Garmin P/N 190-
00664-00 Revision A or later.
1.5.1 GMC 710 AFCS Controls
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 CRG.
1.5.2 GCU 475 FMS Controller
The GCU 475 functions as the primary control interface to the GDU 1500 MFD, since the MFD does not
possess any knobs or controls other than softkeys.
1.5.3 GMA 1347D Control
The Garmin GMA 1347D audio panels integrate NAV/COM digital audio, intercom system and marker
beacon controls. Manual display reversion mode (red DISPLAY BACKUP button) for PFD1, PFD2, and
MFD is controlled by the GMA 1347D. Warning and alert audio received by the GMA 1347Ds is
processed by and received from the GIA 63W Integrated Avionics Units (IAUs).
1.5.4 GRS 77 Attitude and Heading Reference System
The Garmin GRS 77 is an attitude and heading reference systems (AHRS) that provides aircraft attitude
(roll, pitch, and heading), angular rate and acceleration information to the GMUs, GIAs, GDU 1500 and
GDU1040A LRUs.
1.5.5 GDC 74B Air Data Computer
The Garmin GDC 74B processes data from the pitot/static system as well as the OAT probe. This unit
provides pressure altitude, airspeed, vertical speed and OAT information to the G1000 system, and
communicates with the on-side GIA 63W, on-side GDU 1040A and on-side GRS 77, using an ARINC 429
digital interface.
1.5.6 GIA 63W Integrated Avionics Unit (IAU) – (WAAS Enabled)
The Garmin GIA 63W functions as main communication hub to the G1000 system linking all LRUs with
the PFD and MFD displays. The GIA 63W contains the GPS/WAAS receiver, VHF COM/NAV receivers,
and system integration microprocessors.
1.5.7 GEA 71 Engine/Airframe Unit
The Garmin GEA 71 Engine/Airframe unit receives and processes signals from engine sensors.
Communication interface is to GIA63W via RS-485.
1.5.8 GDL 69A Data Link
The Garmin GDL 69A Data Link is an XM Satellite Radio data link receiver that receives broadcast
weather data and XM Satellite Radio. The GDL 69A is a derivative of the GDL 69 and provides the same
functionality as the GDL 69 except for the addition of XM Satellite Radio audio entertainment.

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1.5.9 GMU 44 Magnetometer
The Garmin GMU 44 Magnetometer senses magnetic field information and sends this data to the GRS 77
ARHS for processing to determine aircraft magnetic heading.
1.5.10 GTX 33 Mode S Transponder
The Garmin GTX 33 Mode S Transponder provides Mode A, C, and S capabilities for ATC, TIS and TCAS I
surveillance requirements. The GTX 33s interface with the No. 1 and No. 2 GIA63W G1000 LRUs via RS-232.
1.5.11 GSA 80 Servo Actuator
The Garmin GSA 80 Servo Actuator is an electromechanical unit that will provide pitch, roll and yaw damp and turn
coordination.
1.5.12 GSA 81 Servo Actuator
The Garmin GSA 81 Servo Actuator is an electromechanical unit that will provide automatic control of the,
pitch trim.
1.5.13 GSM 85/85A
The Garmin GSM 85 and 85A Servo Mounts will attach to an adapter plate, which will mount to an
existing bracket and is responsible for transferring the output torque of the GSA 80 /81 servo actuators to
the mechanical flight control surface linkage.

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2 POST INSTALLATION PROCEDURES
This section covers the procedures that must be performed after accomplishing the mechanical and
electrical installations. It is assumed that the person performing the post-installation checks is familiar
with the aircraft, has a working knowledge of typical avionics systems, and has experience using the test
equipment defined in this section. All installation work must be completed in accordance with this STC
before beginning any of the procedures in this document.
Following initial system installation, this entire procedure must be successfully
accomplished in order for the G1000 and GFC 700 system to be airworthy in the King Air
C90A/GT.
2.1 Required Test Equipment
The following test equipment is required to conduct and complete all post installation checkout
procedures in this section: (All calibrated test equipment should have current calibration records)
•A VHF NAV/COM, ILS, & DME ramp tester
•A transponder ramp tester
•A pitot/static ramp tester
•A Digital Multi-Meter (DMM)
•A ground power unit capable of supplying 28 Vdc power to the aircraft systems and avionics
•Outdoor line-of-site to GPS satellite signals or GPS indoor repeater
•Headset/Microphone
•Hand Microphone
•Digital Level or equivalent
•Plum Bob
•In-line type VSWR/wattmeter
•Ambient temperature thermometer
•ITT, N1, N2, Torque, Fuel Flow test equipment. Reference “Engine Indicating – Maintenance
Practices” Raytheon (Hawker Beechcraft) King Air (A/B/C/E) Series Maintenance Manual Part
No. 90-590012-13 Revision B11 or later, section 77-00-00.
•Clamp-On type Amp Meter (Fluke 336 or equivalent)
2.2 G1000 Hardware/Software Compatibility Check
Before installing hardware, the technician must first ensure that hardware part numbers are compatible
with the G1000/C90 loader card that is to be used. A G1000/C90 loader card is required to install
software and configuration settings to a newly installed G1000 system. The part number of this card is
directly associated with the combination of software file part numbers and version levels that are defined
on the card. Should software part numbers or versions change, a new loader card part number is issued.
The G1000/GFC 700 General Arrangement (GA) drawing, Garmin Part Number 005-00375-22, shows all
available combinations of hardware and loader cards. Using the GA drawing, the technician must verify
that all hardware part numbers are compatible with the loader card to be used. The GA drawing allows
the technician to correlate each LRU hardware part number to a compatible loader card.
After verifying hardware/loader card compatibility, record the loader card part number and
all LRU hardware part numbers in the appropriate aircraft records before proceeding.
Throughout the next section of this document, screen shots and examples are used to
illustrate the software and configuration loading process. These screen shots are
provided as reference only. Always refer to the General Arrangement drawing for the
correct software file names, versions and part numbers.
NOTE
IMPORTANT
NOTE

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2.3 G1000 Software/Configuration Procedure
The G1000 is not airworthy unless software and configuration are accomplished successfully as
described in these procedures. The following diagram depicts an overview of the software/configuration
sequence for the G1000 system. If any problems are encountered during the loading process, see
Section 2.17. It is extremely important that each LRU software load be completed successfully.
Figure 2-1. Software/Configuration Overview

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2.3.1 System Power Up
Apply power to the G1000 by doing the following:
1. Connect a ground power unit to the external power receptacle, and turn on the ground power unit.
2. Set the BAT, EXT PWR and AVIONICS MASTER switches to ON.
2.3.2 MFD & PFD Software Load
1. Pull the MFD, PFD1 (PRI), PFD1 (SEC) and PFD2 circuit breakers.
2. Insert the correct G1000/C90 Loader Card (Ref. General Arrangement, G1000/GFC 700 AFCS,
King Air C90A/GT 005-00375-22) into PFD2 top card slot.
3. While holding the ENT key on PFD2, restore power by closing the PFD2 circuit breaker.
4. When the words appear in the upper left corner of PFD2, release
the PFD2 ENT key.
5. Press the PFD2 ENT key to acknowledge the following prompt (NOTE: A softkey labeled ‘YES’
appears in the lower right corner and may be used in lieu of the ENT key):
6. The following screen is displayed.
7. New software is loaded to PFD2. When complete, the PFD starts in configuration mode
displaying the “System Status” page . Do not remove power.
8. Remove the G1000/C90 Loader Card from PFD2 and insert it into the top card slot on the MFD.
Repeat Steps 3 through 6 for the MFD, using the far right softkey on the MFD in lieu of the ENT
key where called out in Steps 3 through 6.
Note: The ENT key for the MFD is located on the GCU 475 FMS controller and will not function prior
to software load.
9. When MFD update is complete, it starts in the configuration mode. Do not remove power.
Repeat Steps 3 through 6 for PFD1. When complete, all three displays should be in configuration
mode, with the Loader Card remaining in the top slot of PFD1.
For the rest of the software/configuration procedure, do not operate the MFD or PFD2
while loading software or configuration files unless specifically instructed to do so. A
failed or cancelled load may result.
IMPORTANT

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Revision 5 190-00682-00
2.3.3 Initial G1000 Configuration
The following “King Air C90 Baseline” is required for all airplanes covered by this STC.
1. Ensure loader card is inserted into top card slot of PFD1. On PFD1, select the “System Upload”
page using the PFD1 small FMS knob.
2. Activate the cursor and use the PFD1 small FMS knob to highlight “C90” in the AIRFRAME field.
Press the PFD1 ENT key to select the airframe type.
3. Once an airframe type is selected the cursor moves to the FILE window. Rotate the PFD1 small
FMS knob to activate the drop-down menu. Move the cursor to highlight “King Air C90
Baseline” and press ENT on PFD1.
Note: The PRODUCT window displays information regarding each G1000 LRU. The LRU column
depicts the reported software version of the LRU, whereas the CARD VERS column shows the LRU
software version stored on the Loader Card. The SOFTWARE and CONFIGURATION columns
default to having all required boxes checked. Each checked file is automatically loaded to the correct
G1000 LRU.
4. Press the LOAD softkey.
5. Observe software loading progress and verify software load completes without errors as indicated
by the following:
•Green “PASS” or N/A in SOFTWARE and CONFIGURATION columns.
•“Upload Complete………….COMPLETE” in the summary box.
6. Press PFD1 ENT key to acknowledge the “Upload Complete” box.
7. Remove power form the G1000 system then proceed to section 2.4.
IMPORTANT

G1000/GFC 700 Post Installation Checkout Procedure – Hawker / Beechcraft King Air C90 Page 2-5
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2.4 Software Load Confirmation
1. Start the G1000 system in Configuration Mode.
2. Select the System Status page using the small FMS knob. Activate the cursor and toggle to the
LRU window.
3. Highlight each of the following items in the LRU window, and verify that the software part number
and version matches the information in G1000/GFC 700 AFCS, King Air C90A/GT 005-00375-22
General Arrangement drawing.
Control & Display
SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK
PFD1 ______ PFD2 FPGA ______ GCU ______
PFD1 FPGA ______ MFD1 ______ GMC ______
PFD2 ______ MFD1 FPGA ______

Page 2-6 G1000/GFC 700 Post Installation Checkout Procedure - Hawker / Beechcraft King Air C90
Revision 5 190-00682-00
CNS:
SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK
GIA1 ______ GPS2 ______ GDL69 ______
GIA2 ______ GTX1 ______ GWX ______
GMA1 ______ GTX2 ______ GWX FPGA ______
GMA2 ______ GIA1 AUDIO ______
GPS1 ______ GIA2 AUDIO ______
Sensors:
SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK
GDC1 ______ GMU2 ______ GEA1 ______
GDC1 FPGA ______ GMU2 FPGA ______ GEA2 ______
GDC2 ______ GRS1 ______
GDC2 FPGA ______ GRS1 FPGA ______
GMU1 ______ GRS2 ______
GMU1 FPGA ______ GRS2 FPGA ______
AFCS SYSTEM:
SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK
GSA PTCH CTL _____ GSA PTCH TRM M _____ GSA YAW CTL _____
GSA PTCH MON _____ GSA ROLL CTL _____ GSA YAW MON _____
GSA PTCH TRM C _____ GSA ROLL MON _____
AFCS CERT GAINS:
SYSTEM SW VER OK SYSTEM SW VER OK SYSTEM SW VER OK
GFC CERT GIA1 _____ GFC CERT PT C _____ GFC CERT YC _____
GFC CERT GIA2 _____ GFC CERT PT M _____ GFC CERT YM _____
GFC CERT PC _____ GFC CERT RC _____
GFC CERT PM _____ GFC CERT RM _____
4. De-activate the cursor.
If any software version and/or part number does not match those specified by the General
Arrangement drawing, or if the software is not successfully loaded, DO NOT continue with post-
installation procedures. Troubleshoot and resolve the issue before continuing (see Section 2.17).
IMPORTANT