g1000 v8.xx software loading and post installation...

190-00577-04 June 2007 Revision 1

G1000 V8.XX Software Loading and Post Installation Checkout

Columbia 350/400

Page A G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Revision 1 190-00577-04

© COPYRIGHT 2007 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. 151st Street

Olathe, KS 66062 USA Telephone: 913-397-8200

www.garmin.com

Garmin AT, Inc Garmin (Europe) Ltd. 2345 Turner Rd., SE Unit 5, The Quadrangle Salem, OR 97302 USA Abbey Park Industrial Estate Telephone: 503 581-8101 Romsey, SO51 9DL U.K.

44/1794.519944 44/1794.519222

RECORD OF REVISIONS

Revision Revision Date Description ECO #

1 6/22/07 Initial release. Applicable to GDU software V8.10 and greater.

------

DOCUMENT PAGINATION

Section Pagination

Table of Contents i – vi Section 1 1-1 – 1-8 Section 2 2-1 – 2-24 Section 3 3-1 – 3-50 Section 4 4-1 – 4-6

Appendix A A-1 – A-2

G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Page i 190-00577-04 Revision 1

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 of the United States without first obtaining an export license. A violation of the EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to $1,000,000 under Section 2410 of the Export Administration Act of 1979. Include this notice with any reproduced portion of this document.

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 104x’s 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

CAUTION 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. Further, all options may not be available in all SD loader card configuration.

IMPORTANT This Post Installation document is to be used with system software 00530.04 or greater including upgrades from previous versions to 00530.04. Previous software loads should use Post Installation document GPN 190-00577-02.

Page ii G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Revision 1 190-00577-04

(this page intentionally left blank)

G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Page iii 190-00577-04 Revision 1

TABLE OF CONTENTS

1 INTRODUCTION ...................................................................................................1-1

1.1 General Information .................................................................................................................................. 1-1

1.2 Reference Documents ................................................................................................................................. 1-1

1.3 Post-Installation Procedures Summary.................................................................................................... 1-1 1.3.1 New Installation Checkout ....................................................................................................................... 1-1 1.3.2 Software Reload ....................................................................................................................................... 1-1

1.4 Post Installation Process ............................................................................................................................ 1-2

1.5 System Description ..................................................................................................................................... 1-2

1.6 G1000 System Communication ................................................................................................................. 1-4

1.7 G1000 Control Interface ............................................................................................................................ 1-6 1.7.1 FMS Cursor.............................................................................................................................................. 1-7 1.7.2 Softkeys.................................................................................................................................................... 1-7 1.7.3 AFCS Controls ......................................................................................................................................... 1-7 1.7.4 GMA 1347 Control .................................................................................................................................. 1-8 1.7.5 Starting Configuration Mode ................................................................................................................... 1-8

2 POST INSTALLATION PROCEDURES ...............................................................2-1

2.1 Required Test Equipment.......................................................................................................................... 2-1

2.2 Wiring Harness Checkout.......................................................................................................................... 2-1

2.3 G1000 Hardware/Software Compatibility Check.................................................................................... 2-1

2.4 System Installation ..................................................................................................................................... 2-1

2.5 G1000 Software/Configuration Procedure............................................................................................... 2-2 2.5.1 System Power Up..................................................................................................................................... 2-3 2.5.2 MFD & PFD Software Load .................................................................................................................... 2-3 2.5.3 G1000 System Software Upload .............................................................................................................. 2-5 2.5.4 GIA 63 Boot Block Update...................................................................................................................... 2-8

2.6 Software Load Confirmation................................................................................................................... 2-11

2.7 Final Configuration and Setup Items ..................................................................................................... 2-12 2.7.1 Optional System Activation ................................................................................................................... 2-12 2.7.2 Aircraft Registration Number Entry....................................................................................................... 2-18 2.7.3 TAWS Activation (if installed) .............................................................................................................. 2-19 2.7.4 ChartView (if installed).......................................................................................................................... 2-19 2.7.5 Terrain/Obstacle/SafeTaxi Database Cards............................................................................................ 2-20 2.7.6 Aviation Database Loading.................................................................................................................... 2-21

2.8 Software/Configuration Troubleshooting............................................................................................... 2-22 2.8.1 System Communication Hierarchy ........................................................................................................ 2-23

Page iv G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Revision 1 190-00577-04

3 SYSTEM TESTING & CHECKOUT.......................................................................3-1

3.1 Aircraft Interface Testing – Configuration Mode ................................................................................... 3-1 3.1.1 Discrete Inputs ......................................................................................................................................... 3-1 3.1.2 Carbon Monoxide Warning System......................................................................................................... 3-8 3.1.3 WX-500 Stormscope (if installed) ........................................................................................................... 3-9 3.1.4 Ryan TCAD 9900BX (if installed) ........................................................................................................ 3-10

3.2 Calibration and Activation ...................................................................................................................... 3-11 3.2.1 Aileron and Elevator Trim Calibration .................................................................................................. 3-11 3.2.2 Fuel Quantity Transducer Calibration.................................................................................................... 3-12

3.3 Initial Display Testing .............................................................................................................................. 3-17 3.3.1 GPS Signal Acquisition.......................................................................................................................... 3-19

3.4 Aircraft Interface Testing – Normal Mode ............................................................................................ 3-19 3.4.1 CHT Probes............................................................................................................................................ 3-19 3.4.2 EGT Probes ............................................................................................................................................ 3-19 3.4.3 TIT Probes (C400 only) ......................................................................................................................... 3-20 3.4.4 Door Open.............................................................................................................................................. 3-20 3.4.5 Rudder Hold (C400 Only)...................................................................................................................... 3-20 3.4.6 Rudder Limiter (C350 Only).................................................................................................................. 3-20 3.4.7 Electrical Bus Voltages, Battery Currents and Alert Audio ................................................................... 3-21 3.4.8 Cooling Fans .......................................................................................................................................... 3-22 3.4.9 Fuel System Discretes ............................................................................................................................ 3-22 3.4.10 Lighting ............................................................................................................................................. 3-22

3.5 GMA 1347 Testing.................................................................................................................................... 3-24 3.5.1 Intercom System (ICS) Check................................................................................................................ 3-24 3.5.2 Transceiver Operational Check.............................................................................................................. 3-24 3.5.3 Failsafe Operation Check....................................................................................................................... 3-24 3.5.4 Marker Beacon Test ............................................................................................................................... 3-24

3.6 GIA 63 Testing.......................................................................................................................................... 3-25 3.6.1 VHF COM Interference Test.................................................................................................................. 3-25 3.6.2 VOR/LOC/GS Test ................................................................................................................................ 3-26 3.6.3 COM Antenna VSWR Checks............................................................................................................... 3-26

3.7 GDL 69 Testing......................................................................................................................................... 3-26

3.8 GTX 33 Testing......................................................................................................................................... 3-27

3.9 GDC 74A TESTING................................................................................................................................. 3-27 3.9.1 Pitot/Static Airspeed Test....................................................................................................................... 3-27 3.9.2 Static Port Vertical Speed (Rate of Climb) Test .................................................................................... 3-27 3.9.3 OAT Probe Check .................................................................................................................................. 3-28

3.10 GRS 77/GMU 44 Initial Alignment......................................................................................................... 3-28 3.10.1 GRS 77 Pitch/Roll Offset Calibration................................................................................................ 3-28

3.11 Engine Start .............................................................................................................................................. 3-29

3.12 Final GRS 77/GMU 44 Calibration Procedures .................................................................................... 3-31 3.12.1 Site Evaluation of Magnetic Disturbances for Magnetometer Calibration Procedure (Optional)...... 3-31 3.12.2 GRS 77/GMU 44 Magnetic Calibration ............................................................................................ 3-32 3.12.3 Engine Run-Up Vibration Test .......................................................................................................... 3-34 3.12.4 Magnetometer Interference Test ........................................................................................................ 3-36

G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Page v 190-00577-04 Revision 1

3.13 Alternator Checks .................................................................................................................................... 3-38

3.14 TAWS ........................................................................................................................................................ 3-38

3.15 Optional System Checkouts ..................................................................................................................... 3-39 3.15.1 WX500 Stormscope (if installed) ...................................................................................................... 3-39 3.15.2 9900 BX TCAD (if installed) ............................................................................................................ 3-40 3.15.3 Oxygen System (if installed) ............................................................................................................. 3-41

3.16 Final System Checkout............................................................................................................................. 3-42 3.16.1 GPS Failure Test................................................................................................................................ 3-42 3.16.2 GIA Failure Test ................................................................................................................................ 3-42 3.16.3 Display Failure Test........................................................................................................................... 3-43 3.16.4 AHRS/ADC Backup Path Test .......................................................................................................... 3-43

3.17 Lighting Setup........................................................................................................................................... 3-44 3.17.1 Main Lighting Page ........................................................................................................................... 3-44

3.18 Cockpit Lighting Setup ............................................................................................................................ 3-47

3.19 COM Setup Page ...................................................................................................................................... 3-49

3.20 GMA Configuration Page ........................................................................................................................ 3-50

4 GFC 700 AUTOPILOT GROUND CHECKS..........................................................4-1

4.1 Autopilot Pre-Flight Test ........................................................................................................................... 4-1

4.2 AFCS Switch Checks.................................................................................................................................. 4-2

4.3 Autopilot Clutch Overpower Check ......................................................................................................... 4-3

4.4 Autopilot Disengagement Check ............................................................................................................... 4-4

4.5 Manual Electric Trim Check..................................................................................................................... 4-4

4.6 Autopilot Operation Checks ...................................................................................................................... 4-4

Page vi G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Revision 1 190-00577-04

LIST OF ILLUSTRATIONS

FIGURE PAGE

FIGURE 1-1. G1000 SYSTEM INTERFACE 1-4 FIGURE 1-2. EIS INTERFACE 1-5 FIGURE 1-3. FLIGHT INSTRUMENTATION INTERFACE 1-5 FIGURE 1-4. GDU 1040/1042 CONTROL INTERFACE 1-6 FIGURE 1-5. GDU SOFTKEYS 1-7 FIGURE 1-6. AFCS CONTROLS 1-7 FIGURE 1-7. GMA 1347 CONTROL INTERFACE 1-8 FIGURE 2-1. SOFTWARE/CONFIGURATION OVERVIEW 2-2 FIGURE 3-1. AILERON AND ELEVATOR TRIM CALIBRATION 3-11 FIGURE 3-2. MFD POWER UP PAGE - COLUMBIA 400 3-17 FIGURE 3-3. DISPLAY INVALID DATA FIELDS 3-18 FIGURE 3-4. 3RD AUX PAGE 3-19 FIGURE 3-5. MARKER BEACON SYMBOLOGY 3-24 FIGURE 3-6. PITCH/ROLL OFFSET 3-28 FIGURE 3-7. ENGINE/AIRFRAME INDICATORS (FULL EIS PAGE) 3-30 FIGURE 3-8. ENGINE RUN-UP TEST 3-34 FIGURE 3-9. MAGNETOMETER INTERFERENCE TEST 3-36 FIGURE 3-10. MAGNETOMETER INTERFERENCE TEST COMPLETE 3-37 FIGURE 3-11. MAIN LIGHTING PAGE 3-45 FIGURE 3-12. LIGHTING CURVE VERTICES 3-46 FIGURE 3-13. DIMMER BUS LIGHTING 3-47 FIGURE 3-14. COM SETUP PAGE 3-49 FIGURE 3-15. GMA CONFIGURATION PAGE 3-50 FIGURE 4-1. GFC 700 PRE-FLIGHT TEST 4-2

LIST OF TABLES

TABLE PAGE TABLE 1-1. REFERENCED DOCUMENTATION................................................................................................ 1-1

G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Page 1-1 190-00577-04 Revision 1

1 INTRODUCTION This document provides information to configure and test software load 0053002 (or greater) of the Garmin G1000 Integrated Avio nics System in the Columbia 350/400. The person performing the configuration and testing should read through this entire document prior to beginning any procedures.

NOTE

This Post Installation document to be used with system software 00530.04 or greater including upgrades from previous versions to 00530.04. Previous software loads should use Post Installation checkout document, GPN 190-00577-02.

1.1 General Information This document applies to only the Columbia 400 aircraft. The figures of the displays are for the Columbia 400 unless noted otherwise.

1.2 Reference Documents

The information that is provided in this document is applicable to the installation of the G1000 system in the Columbia 400. For additional information on the installation, refer to the documents below.

Table 1-1. Referenced Documentation

Part Number Document

005-W0016-00 Wiring Diagram – Columbia 400 Avionics (N999GL only) 190-00355-04 GDL 69/69A XM™ Satellite Radio Activation Instructions 190-00567-00 G1000 Cockpit Reference Guide for the Columbia 350/400 010-00533-00 SD loader card – GIA 63 Boot Block version 4.01 LB53401000 Wiring, G1000 System, GIFD (350 and 400) LB53402200 Autopilot Assembly, GIFD LB53403000 Avionics and Navigation Equipment Installation, GIFD RB050005 Columbia 350 (G1000) Pilot’s Operating Handbook and FAA Approved AFM RC050005 Columbia 400 (G1000) Pilot’s Operating Handbook and FAA Approved AFM RB011002 Required Equipment List, Garmin G1000, Columbia Models LC41 and LC42

1.3 Post-Installation Procedures Summary

This document covers the procedures that must be performed to verify the function and integrity of the mechanical and electrical installations. Installation work must be completed in accordance with the approved installation drawings before beginning the associated procedure in this document.

1.3.1 New Installation Checkout For new product installations, this entire procedure (or equivalent) must be successfully accomplished in order for the G1000 and GFC 700 Automatic Flight Control System (AFCS) to be airworthy.

1.3.2 Software Reload If new software becomes available prior to delivery of the aircraft, the G1000 software and configuration will have to be reloaded using the new loader card. On those aircraft that have had the post installation checkout procedures previously completed and are only having the software reloaded, it is only necessary to do the following:

2 G1000 V8.XX S/W Load and Post Install Checkout – Columbia 350/400 Revision 1 190-00577-04

• verify software loads in accordance with section 2.6 • reconfigure optional systems and verify setup items in accordance with section 2.7 • perform the Final System Checkout in accordance with section 3 • perform the GFC System Checkout in accordance with section 4

1.4 Post Installation Process

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 the Required Equipment List (REL), Columbia Part Number RB011002.

Section 3: Ground checks include exercising and testing basic G1000 functions, calibrating the AHRS, and conducting a final systems checkout.

Section 4: Detailed GFC 700-specific ground checks are given in this section.

1.5 System Description

The G1000 avionics system is comprised of the following Line Replaceable Units (LRUs): • One GDU 1040 (Primary Flight Display) • One GDU 104X (Multi-function Flight Display) • Two GIA 63/63W Integrated Avionics Units • GCU 476 Remote Keypad • GEA 71 Engine and Airframe Unit • GDC 74A Air Data Computer (ADC) • GTP 59 Outside Air Temperature (OAT) Probe • GRS 77 Attitude & Heading Reference System (AHRS) • GMU 44 Magnetometer • GMA 1347 Audio System with integrated Marker Beacon Receiver • GTX 33 Mode S Transponder • GDL 69A XM Data Link Receiver • GSA 81 Servos (Pitch and Roll) • GTA 82 Pitch Trim Adapter • Data base cards for the PFD and MFD

In addition, there are four Configuration Modules (one each for the GDU 1040 PFD, GEA 71, GDC 74A and the GRS 77).

The following equipment, systems and sensors interface to the G1000 avionics systems: • Existing Manifold Pressure sensor • Existing Tachometer sensor • Existing Oil pressure sensor and low pressure switch • Existing Oil temperature sensor • Existing Cylinder Head Temperature (CHT) sensors • Exhaust Gas Temperature (EGT) sensors • Existing Turbine Inlet Temperature (TIT) sensors (Columbia 400 only) • Existing Fuel Level sensors (four) • Existing low fuel switches (L and R) • Existing fuel selector position switches • Existing Fuel Flow sensor • Existing Electrical System sensors and alternator inop switches


• Existing open door detection switch • Existing aileron and elevator position sensors • Existing oxygen system sensors and switches • Existing starter engage system • Existing WX-500 Stormscope Weather Mapping System • Existing Ryan TCAD Traffic System • Existing VOR/LOC/Glideslope antenna system • Existing VHF COMM 1 and VHF COMM 2 antennas • Existing transponder (L-band) antenna • Existing Marker Beacon antenna • Existing GPS 1 and GPS 2 antennas

The attitude indicator, airspeed indicator, altimeter and non-stabilized compass serve as secondary displays in the event of a failure of the associated primary indicator(s) and or sensors.


1.6 G1000 System Communication

GDC Configuration ModuleGDC Configuration Module

RS-485RS-485

GDC 74AGDC 74AAir DataAir Data

ComputerComputer

GTP 59 OAT ProbeGTP 59 OAT Probe

AHRS Configuration ModuleAHRS Configuration Module

ARINC 429ARINC 429

GRS 77GRS 77AHRSAHRS

GMU 44GMU 44MagnetometerMagnetometer

ARINC 429ARINC 429

ARINC 429ARINC 429

ETHERNETETHERNET

REVERSIONARY SWITCHREVERSIONARY SWITCH

ETHERNETETHERNET

ARINC 429ARINC 429

RS-232RS-232

ARINC 429ARINC 429

RS-485RS-485

No. 1No. 1GIA 63GIA 63

IntegratedIntegratedAvionicsAvionics

UnitUnit

Master Configuration ModuleMaster Configuration Module

GDU 1040GDU 1040PFDPFD

GDU 1042GDU 1042MFDMFD

No. 2No. 2GIA 63GIA 63

IntegratedIntegratedAvionicsAvionics

UnitUnit

GSA 81GSA 81Pitch ServoPitch Servo

RS-485RS-485

RS-232RS-232

ARINC 429ARINC 429

ARINC 429ARINC 429

RS-232RS-232

REVERSIONARY SWITCHREVERSIONARY SWITCH

ETHERNETETHERNET

ETHERNETETHERNET

ARINC 429ARINC 429

ARINC 429ARINC 429

RS-232RS-232

GSA 81GSA 81Roll ServoRoll Servo

RS-232RS-232

RS-232RS-232

GEA 71GEA 71Engine/AirframeEngine/Airframe

UnitUnit GTX 33GTX 33TransponderTransponder RS-232RS-232RS-232RS-232

RS-485RS-485

RS-485RS-485

GMA 1347GMA 1347AudioAudioPanelPanel

GTA 82GTA 82Pitch Trim AdapterPitch Trim Adapter

GDL 69AGDL 69AXM Data LinkXM Data Link

ReceiverReceiver

ETHERNETETHERNET

GCU 476GCU 476RemoteRemote

Control PanelControl Panel

RS-232RS-232

RS-232RS-232

RS-232RS-232

Figure 1-1. G1000 System Interface


No. 1 GIA 63

IntegratedAvionics Unit

GEA 71

Engine/AirframeUnit

No. GIA 632Integrated

Avionics Unit

GDU 1042MFD

Display ofEngine/Airframe

Instruments

High-Speed Data Bus (Ethernet)

GDU 1040PFD

Display ofEngine/Airframe

Instruments(Reversionary Mode Only)

Engine/AirframeTransducers:

RPM, Manifold Pressure, Oil Pressure,Oil Temperature, CHT/EGT, TIT, Fuel Flow,

Fuel Quantity, Fuel Low Discretes, Fuel SelectorValve Position, Bus Volts, Starter Engaged System,

Battery Current, Alternator Current, Low Oil PressureDiscrete, Aileron Trim Position, Elevator Trim Position,Oxygen Pressure, Alternator Inop, Door Open Discrete

Figure 1-2. EIS Interface

GDU 1040PFD

Display of Flight Instrumentation

GDU 1042MFD

Display of Flight Instrumentation(Reversionary

Mode Only)

No. 1 GIA 63 Integrated

Avionics Unit

No. 2 GIA 63 Integrated

Avionics Unit

GDC 74AAir Data

ComputerOAT

AirspeedAltitude

Vertical Speed

GRS 77AHRSAttitude

Rate of TurnSlip/Skid

GMU 44Magnetometer

Heading

GPS Output

GPS Output

High-Speed Data Bus (Ethernet)

Figure 1-3. Flight Instrumentation Interface


1.7 G1000 Control Interface

Control and operation of G1000 equipment is through the PFD, MFD or GMA 1347 audio panel. See the following documents for detailed information regarding control and operation.

• G1000 Pilot’s Guide for Columbia 350/ 400, Garmin P/N 190-00552-00 Revision A or later. • G1000 Cockpit Reference Guide for the Columbia 400, Garmin P/N 190-00567-00 Revision

A or later. • Columbia 400 (G1000) Pilot’s Operating Handbook and FAA Approved AFMS, Columbia

P/N RC050005 Revision -- or later. • Columbia 350 (G1000) Pilot’s Operating Handbook and FAA Approved AFMS, Columbia

P/N RB050005 Revision -- or later.

NOTE Except where specifically noted, the PFD is the primary control/display to be used through all procedures. The GDU 1040 PFD buttons are identical to that of the GDU 1042 MFD, except for the AFCS keypad, located on the lower left portion of the bezel.

COM Frequency Toggle Key

COM Frequency Selector Knob

Course (Inner)/Baro (Outer)Selector Knob

Map Panning/RangeJoystick

Navigation SystemsControls

Flight Management System(FMS) Knob

Multi-Function Softkeys (Numbered 1-12, left to right)

NAV Frequency Toggle Key

NAV Frequency Tuner Knob

Heading Bug Selector

NAV Volume/IdentKnob

Altitude SelectorKnob

COM Volume/SquelchKnob

GFC 700 AFCS Controls

Figure 1-4. GDU 1040/1042 Control Interface


1.7.1 FMS Cursor The FMS knob is the primary control for the G1000 system. Operation is similar to the Garmin 400/500 Series units.

• To cycle through different configuration screens:

To change page groups: Rotate the large FMS knob.

To change pages in a group: Rotate the small FMS knob.

• To activate the cursor for a page, press the small FMS knob directly in, as one would push a regular button.

• To cycle the cursor through different data fields, rotate the large FMS knob.

• To change the contents of a highlighted data field, rotate the small FMS knob. This action either brings up an options menu for the particular field, or in some cases allows the operator to enter data for the field.

• To confirm a selection, press the ENT key.

• To cancel a selection, press the small FMS knob in or press the CLR key. Pressing the small FMS knob in again deactivates the cursor.

1.7.2 Softkeys Some configuration pages have commands or selections that are activated by the GDU 1040 softkeys. If a softkey is associated with a command, that command will be displayed directly above the key. A grayed-out softkey shows a command that is unavailable. Also, a softkey that is highlighted shows the current active selection.

Figure 1-5. GDU Softkeys

1.7.3 AFCS Controls The dedicated AFCS controls on the GDU 1042 are discussed in detail in the GFC 700 Pilot’s Guide for Columbia 350/400, P/N 190-00567-00. The following figure is provided for reference.

Heading Mode Key

Approach Mode Key

NOSE UP Key

NOSE DN Key

Autopilot Key

Flight Director Key

Navigation Mode Key

Altitude Hold Mode Key

Vertical Speed Mode Key

Flight Level Change Mode Key

Figure 1-6. AFCS Controls


1.7.4 GMA 1347 Control

Display BackupReversionary Button

Volume/SquelchControl

ICS Isolation

Digital Recording PlaybackManual Squelch

Navigation Radio Audio

Navigation Radio Audio

Marker Beacon Signal SensitivityMarker Beacon/Mute

SpeakerPassenger Address

Split COM

Transmitters Transceiver Audio

Cellular Telephone

Figure 1-7. GMA 1347 Control Interface

1.7.5 Starting Configuration Mode To complete this aircraft checkout, a basic understanding of the G1000 configuration mode is required. The configuration mode allows a technician to access certain areas of the system in order to carry out various configurations, calibrations, and checks.

1. To start a GDU 1040 in configuration mode, hold down the ENT key while applying power.

2. Continue to hold the ENT key until the white letters INITIALIZING SYSTEM appear in the upper left corner of the display.

Appendix A contains a diagram showing how the configuration mode pages are organized. Refer to this diagram as an aid to navigate through the pages of the configuration mode.


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 Columbia drawings LB53403000 Avionics and Navigation Equipment Installation, GIFD, and LB53402200 Autopilot Assembly, GIFD before beginning any of the procedures in this document.

2.1 Required Test Equipment

The following test equipment is required to conduct and complete all post installation checkout procedures: (All test equipment should have current calibration records)

• A VHF NAV/COM/ILS ramp tester or equivalent. • A transponder ramp tester or equivalent. • A TCAS / Skywatch ramp tester or equivalent. • A pitot/static ramp tester. • VSWR/wattmeter (in-line type). • A Digital Multi-Meter (DMM). • A ground power unit capable of supplying 28 Vdc power to the aircraft systems and avionics. • Outdoor line-of-sight to GPS satellite signals or GPS indoor repeater. • PC computer or laptop. • Headset/Microphone. • Means to level the aircraft.

2.2 Wiring Harness Checkout Prior to installing any LRUs, the wiring harness should be checked for proper connections to the aircraft systems and other avionics systems. Point to point continuity should be checked to expose any faults such as shorting to ground. Any faults or discrepancies found should be corrected before proceeding.

After accomplishing a continuity check, perform power and ground checks to verify proper power distribution to the LRUs. Any faults or discrepancies should be corrected at this time. Remove power to the aircraft upon completion of harness checkout.

2.3 G1000 Hardware/Software Compatibility Check Before installing hardware, the technician must first ensure that hardware part numbers are compatible with the G1000-Columbia 400 Loader Card that is to be used. A G1000-Columbia 400 Loader Card is required to install software and configuration settings to a newly installed G1000 system. Should software part numbers or versions change, a new Loader Card part number is issued.

The Required Equipment List (REL), Columbia Part Number RB011002, shows all available combinations of hardware and Loader Cards. Using the REL, the technician must verify that the Columbia 350/400 model and all hardware part numbers are compatible with the Loader Card to be used. The REL allows the technician to correlate each LRU hardware part number to a compatible Loader Card.

IMPORTANT

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.

2.4 System Installation Upon completion of continuity, power, and compatibility checks, the LRUs can be installed in accordance with Columbia drawing LB53403000, Avionics & Navigation Equipment Instl, GIFD. Each LRU must be installed into its respective rack and secured. The units and accessories must be connected to the


wiring harness. Any additional connections, such as pitot/static plumbing, must also be accomplished at this time.

NOTE Throughout the next section of this document, many screen shots and examples are used to illustrate the software and configuration loading process. Although every effort has been made to ensure accuracy of such examples, changes may occur. Always refer to the Required Equipment List for the correct software file names, versions and part numbers.

2.5 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 2.8. It is extremely important that each LRU software load be completed successfully.

Figure 2-1. Software/Configuration Overview


2.5.1 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. Turn on the L BAT MASTER, R BAT MASTER, AVIONICS MASTER and CROSS TIE switches. At this moment, all G1000 equipment is receiving power.

2.5.2 MFD & PFD Software Load 1. Pull the MFD and PFD circuit breakers.

2. Insert the correct G1000-Columbia 350/400 Loader Card into the MFD top card slot (refer to the Required Equipment List document for the correct card part number).

3. While holding the ENT key on the MFD, restore power by closing the MFD circuit breaker.

4. When the words appear in the upper left corner of the MFD, release the ENT key.

5. The system first automatically compares the existing GDU 104X boot block with the version on the loader card. If a difference exists, the GDU prompts to load new boot block:

6. Ensure that power will remain applied to the system. Press the ENT key and new boot block will

be loaded:

7. Press the ENT key to acknowledge the following prompt to load new software (NOTE: A

softkey labeled ‘YES’ appears in the lower right corner and may be used in lieu of the ENT key):


8. The following screen is displayed:

9. New software is loaded to the MFD. When complete, the MFD starts in configuration mode.

10. Remove the G1000 Loader Card from the MFD and insert it into the top card slot on the PFD. Repeat Steps 3 through 7 for the PFD.

11. When the PFD load is complete, it starts in the configuration mode. Do not remove power.

IMPORTANT

For the rest of the software/configuration procedure, do not operate the MFD while loading software or configuration files unless specifically instructed to do so. A failed or cancelled load may result.


2.5.3 G1000 System Software Upload 1. On the PFD, go to the System Upload page using the small FMS knob.

2. Activate the cursor and use the small FMS knob to highlight the airframe type in the AIRFRAME field. Select the appropriate aircraft type (C400 or C350) and press the ENT key.

IMPORTANT!

Ensure that the correct airframe type is selected before proceeding; otherwise, incorrect configuration information will be loaded.


3. Once an airframe type is selected the cursor moves to the FILE window. Rotate the small FMS knob to active the drop-down menu. Move the cursor to highlight the appropriate FQIS fuel tank option. 49 gallon (non-adjusted); 49 gallon (adjusted); 51 gallon (adjusted) and press ENT.

IMPORTANT! It is at this step where the choice is given to load WAAS or non-WAAS G1000 software. Be sure to select the correct option.


4. The PRODUCT window will populate and display software and configuration file information for each G1000 LRU. The LRU VERS column shows the currently loaded software version in the LRU, whereas the CARD VERS column shows the LRU software version stored on the Loader Card. Each check designates a file to be loaded to the G1000.

By default, if an inequality between the LRU and CARD columns exists, the SOFTWARE and CONFIGURATION boxes will be pre-selected (checked).

The following softkeys provide an easy way to select files:

CHK ALL: Selects all files, both configuration and software

CHK SW: Selects all software files only.

CHK CFG: Selects all configuration files only.

CLR ALL: Clears all selections.

IMPORTANT

If this is the first time loading software and configuration to a new installation, it is advised to leave all check boxes selected.

5. After verifying that the desired software and configuration files are checked, press the LOAD softkey. The G1000 system automatically begins loading software and default configuration files to the selected LRUs in the proper order.

IMPORTANT If non-WAAS GIA 63s are installed, the software boot block version must be checked while software is being loaded to EACH GIA 63. Wait until the software loading process begins to load the GIA 63 software. On the MFD, go to the System Status page and


activate the cursor. Highlight GIA1. Observe the DESCRIPTION field and when it changes to read ‘G1000 GIA 6X BBL’, verify that the reported VERSION is 4.01 or higher. Repeat this for GIA2. If either GIA 63 has software boot block less than version 4.01, current boot block software must be loaded per Section 2.5.4.

6. When the system finishes loading, it prompts the technician accordingly. Press the ENT key to acknowledge that the upload is finished:

7. Verify that each column indicates in green when the loading process has finished and inspect the SUMMARY window as well to ensure that the load is successful.

2.5.4 GIA 63 Boot Block Update For GIA 63s, boot block version 4.01 or higher is required. Some GIAs with older dates of manufacture may not have this version. If it was determined in the previous software loading procedure that the GIA 63s did not have boot block version 4.01 or higher, follow this procedure to update the GIA 63’s software boot block. Note that this does not apply to GIA 63Ws.

IMPORTANT! It is critical that electrical power be kept on during the boot block update procedure. Take steps to ensure that a 28 VDC ground power supply is properly connected and is not disturbed during the update.

1. Obtain the required GIA 63 Boot Block loader card from Garmin. The card part number is listed in Table 1-1. Referenced Documentation

2. Insert the card into the top slot of the PFD, hold down the ENT key on the PFD, and apply system power to the G1000.

3. When “INITIALIZING SYSTEM” appears in the upper left corner of the PFD, release the ENT key.

4. On the PFD, go to the System Upload page using the FMS knob.

5. Activate the cursor and in the AIRFRAME field select GIA Boot Block. Press the ENT key.

6. The cursor drops down to the FILE field. Rotate the small FMS knob and select GIA Boot Block 4.01 and press the ENT key.


7. Verify that the SOFTWARE boxes are check for both GIA 1 and GIA 2. Press the LOAD

softkey.

8. The GIA boot block software is loaded. Be sure not to remove electrical power from the G1000 during this update.


9. When the boot block software finishes loading, acknowledge the following prompt by pressing the ENT key:

10. The boot block update procedure is complete. Remove the GIA Boot Block loader card from the PFD and re-insert the correct G1000/GFC700 Software Loader card.


2.6 Software Load Confirmation

1. Go to the System Status page using the FMS knob. Activate the cursor and toggle to the LRU

window.

2. Highlight each of the following items in the LRU window, and verify that the software part number and version matches the information in the Columbia Required Equipment List.

LRU SW VER OK LRU SW VER OK

PFD1 ___________ GMA1 ___________

PFD1 FPGA ___________ GMU1 ___________

MFD1 ___________ GMU1 FPGA ___________

MFD1 FPGA ___________ GDL69 ___________

GIA1 ___________ GFC CERT R M ___________

GIA2 ___________ GFC CERT R C ___________

GPS1 ___________ GFC CERT PT M ___________

GPS2 ___________ GFC CERT PT C ___________

GRS1 ___________ GFC CERT P M ___________

GRS1 FPGA ___________ GFC CERT P C ___________

GIA1 AUDIO ___________ GSA PTCH CTL ___________

GIA2 AUDIO ___________ GSA PTCH MON ___________

GFC CERT GIA1 ___________ GTA PTCH TRM ___________

GFC CERT GIA2 ___________ GSA ROLL CTL ___________

GTX1 ___________ GSA ROLL MON ___________


GEA1 ___________ GCU ___________

GDC1 ___________ GDC1 FPGA ___________

3. De-activate the cursor. IMPORTANT

If any software version and/or part number does not match those specified by the Required Equipment List, or if the software is not successfully loaded, DO NOT continue with post-installation procedures. Troubleshoot and resolve the issue before continuing.

2.7 Final Configuration and Setup Items

2.7.1 Optional System Activation This section describes the steps that must be completed in order to configure the G1000 for optional systems. Only those systems that are installed must be configured.

IMPORTANT If the configuration for an optional system is inadvertently loaded for a system that is NOT installed, the basic Columbia 400 or Columbia 350 configuration for GIA 2, GEA 1, GMA 1 and the Airframe must be reloaded. Following this, the configuration for the optional systems must be repeated.


2.7.1.1 ADF (if installed) If the Columbia aircraft being updated is equipped with the Becker model RA3502 ADF (alternative KR87), follow this procedure to configure the G1000. If the aircraft is not equipped with this option, this procedure MUST be skipped.

1. At the System Upload page, activate cursor and rotate the FMS knob once to activate the

AIRFRAME menu.

2. Select ‘Options’ from the AIRFRAME window and press ENT.

3. From the FILE window, select ‘Columbia Option – Becker 3502 ADF’ or “Columbia Option – KR87 ADF’ and press ENT.

4. Press the LOAD softkey.

5. Monitor the status of the upload. When the upload is finished, press ENT to acknowledge.

6. View the SUMMARY field and ensure that all items are ‘complete’: Verify that PASS appears in green at the check box(es) as shown:

7. De-activate the cursor.


2.7.1.2 DME (if installed) If the Columbia aircraft being updated is equipped with the Honeywell model KN63 DME, follow this procedure to configure the G1000. If the aircraft is not equipped with this option, this procedure MUST be skipped.


AIRFRAME menu.


3. From the FILE window, select ‘Columbia Option – KN63 DME’ and press ENT.






2.7.1.3 Oxygen System (if installed)


AIRFRAME menu.


3. From the FILE window, select the ‘Columbia Option – Oxygen’ in the FILE field and press ENT






2.7.1.4 9900 BX TCAD (if installed)


AIRFRAME menu.


3. From the FILE window, select the ‘Columbia Option – Ryan 9900BX’ in the FILE field.






2.7.1.5 WX-500 Stormscope (if installed)


AIRFRAME menu.


3. From the FILE window, select the ‘Columbia Option – WX 500’ in the FILE field.






2.7.2 Aircraft Registration Number Entry

1. Select the GTX page group, then select the TRANSPONDER CONFIGURATION page on the

PFD.

2. Ensure that the ‘ADDRESS TYPE’ is ‘US TAIL’ under the ‘SET’ and ‘ACTIVE’ columns.

NOTE If the aircraft registration number is not known at this point the ADDRESS field may be left blank. However, a configuration error will be annunciated when the system is in normal mode – this error can be cleared at a later time by entering the registration number when it becomes known.

3. Activate the cursor and highlight the ‘ADDRESS’ field. Use the small/large FMS knobs to enter the aircraft registration number.

4. Once the correct registration number is entered, press the ENT key. The transponder is configured:

5. The transponder then alerts the technician of complete configuration:

6. Press the ENT key on the PFD and deactivate the cursor.


2.7.3 TAWS Activation (if installed) Perform this procedure only if the aircraft is to be equipped with the Garmin TAWS option.

1. Remove power from the PFD by opening the PFD circuit breaker.

2. A special TAWS Unlock card is required to enable TAWS. Refer to the appropriate General Arrangement drawing for the correct part number. Insert this card in the upper slot of the PFD.

3. While holding the ENT key on the PFD and MFD, restore power to the displays.

4. When the words appear in the upper left corner of both displays, release the ENT keys.


6. Activate the cursor. Use the small FMS knob to select CONFIGURATION FILES in the AIRFRAME field and press the ENT key.

7. Highlight the FILE field. Use the small FMS knob to select the ‘Enable TAWS’ option and press the ENT key. Once the option is selected, the configuration files in the PRODUCT field will be displayed. All files should be checked. If not, press the CHK ALL softkey.


9. Monitor the status of the upload. When the upload is finished, press the ENT key to acknowledge the upload complete confirmation.

10. View the SUMMARY field and ensure that the item is ‘COMPLETE’.


12. Power down the system and remove the TAWS Enable card from the PFD.

2.7.4 ChartView (if installed) NOTE:

ChartView databases are subscription-based and are to be procured by the aircraft owner directly from Jeppesen. This procedure is only required if the ChartView option is purchased by the customer.

1. Remove power from the PFD by opening the PFD circuit breaker.

2. A special ChartView Unlock card is required to activate this feature. Refer to the appropriate General Arrangement drawing for the correct part number. Insert this card in the upper slot of the PFD.

3. While holding the ENT key on the PFD and MFD, restore power to both displays by closing the PFD and MFD circuit breakers.

4. When the words appear in the upper left corner of the displays, release the ENT key.


6. Activate the cursor. Use the small FMS knob to select CONFIGURATION FILES in the AIRFRAME field and press the ENT key.


7. Highlight the FILE field. Use the small FMS knob to select the “Enable ChartView” option and press the ENT key. Once the option is selected the configuration files in the PRODUCT field will be displayed. All files should be checked. If not, press the CHK ALL softkey.


9. Monitor the status of the upload. When the upload is finished, press the ENT key to acknowledge the upload complete confirmation.

10. View the SUMMARY field and ensure that the item is ‘COMPLETE’.


12. Power down the system and remove the ChartView Enable card from the PFD.

2.7.5 Terrain/Obstacle/SafeTaxi Database Cards 1. Remove power from the PFD and MFD using the respectively labeled breakers.

NOTE: If the G1000 is to be equipped with the FliteChart or ChartView display options, the appropriate databases are required to be loaded onto the Terrain/Obstacle cards before they are installed in the displays. ChartView database subscription services must be procured directly from Jeppesen and are usually sourced by the aircraft owner. Further, the ChartView feature must be ‘unlocked’ before the G1000 can use the databases (see 2.7.4). There is no unlock card for Garmin FliteCharts. A single cycle of Garmin FliteCharts is loaded on the database cards when they are manufactured at Garmin. Additional FliteChart database updates are obtained directly from Garmin’s web site and are updated on a periodic basis. The G1000 automatically detects the FliteChart databases and activates the display feature.

2. Insert one Terrain/Obstacle/SafeTaxi database cards into the lower slots of the MFD and PFD, respectively. Refer to the Columbia Required Equipment List for correct database card part numbers.

3. Continue to the Aviation Database Loading procedure.


2.7.6 Aviation Database Loading 1. Remove power from the system.

2. Insert an aviation database update SD card into the top slot of the PFD. Database updates are supplied by Jeppesen.

3. Turn the G1000 system on. The following prompt is displayed in the upper left corner of the PFD:

4. Press the ENT key to confirm the database update. The following prompt is displayed:

5. After the update completes, the PFD starts in normal mode. Remove the aviation database update

SD Card from the PFD.

6. Power the G1000 system down.

7. Repeat steps 1 through 4 for the MFD. The MFD and PFD aviation databases are now updated.

8. Confirm that the correct update cycle and version is loaded during startup of the MFD.

9. Remove the aviation database update SD Card from the MFD.

10. Continue to Section 3 for system testing and checkout.


2.8 Software/Configuration Troubleshooting

Problem Solutions

GDU 1040 MFD or PFD display does not power up • Ensure that the criteria listed in 2.8.1 are fulfilled for the applicable situation.

• Ensure power is present at display backshell connector.

• Replace display.

Software file load fails:

• Ensure that criteria listed in 2.8.1 are fulfilled for the applicable situation.

• Ensure that any data paths to the LRU are open at System Status page. Check data path wiring as needed.

• Retry software file load or try using a different card. Ensure that the MFD is not touched during the loading process.

• Ensure that LRU part number is compatible with software version and Loader Card. Refer to the Required Equipment List and to Section 2.5.3 of this document.

• Replace LRU.

Configuration file load fails:

• Ensure that criteria listed in 2.8.1 are fulfilled for the applicable situation.

• Ensure that LRU is reporting data on System Status page. Check data path wiring as needed.

• Retry configuration file load or try using a different card. Ensure that the MFD is not touched during the loading process.

• Ensure that LRU part number is compatible with Loader Card. Refer to the Required Equipment List and to Section 2.4.8 of this document.

• Replace LRU.

Software File Mismatch Alert appears in lower right corner of PFD when started in normal mode:

• Ensure that proper software file part number and version were loaded to LRU. Refer to the Required Equipment List, Sections2.6, and 2.8.1.

• Check and ensure that correct Loader Card was used during load process. Refer to the Required Equipment List.

• Reload software to LRU.


2.8.1 System Communication Hierarchy The following criteria must be satisfied to be able to perform the desired operation:

Desired Operation Criteria for Success

Load Software to GDU 1040 MFD or PFD Displays • G1000/Columbia 350/400 Loader Card must be inserted in top slot for each display to be loaded.

• ENT key must be held during power up of display until INITIALIZING is displayed.

• Power only one display on at a time during software loading.

Load Software files to GCU 476 remote control • G1000 system must be powered on.

• PFD and MFD must have correct software.

• PFD and MFD must be successfully configured with AIRFRAME, SYSTEM, MFD1, and PFD1 configuration files.

Load Software/Configuration files to GIA 63’s • G1000 system must be powered on.

• PFD and MFD must have correct software.

• PFD and MFD must be successfully configured with AIRFRAME, SYSTEM, MFD1, and PFD1 configuration files.

Load Software/Configuration files to:

- GMA 1347

- GDC 74A

- GEA 71

- GRS 77 (software only)

- GTX 33

- GDL 69A

- GSA 81’s

- GTA 82

- GCU 476 (configuration only)

• G1000 must be powered on.

• G1000-Columbia 350/400 Loader Card must be inserted into PFD top slot.

• PFD and MFD must have correct software and configuration settings.

• GIA 63s must have correct software.

• GIA 63s must be successfully configured with GIA1 and GIA2 configuration files.

• Serial data path from GIA1 to each LRU must be operational.


This page intentionally left blank


3 SYSTEM TESTING & CHECKOUT

For the first part of the system testing and checkout the system will be left in configuration mode.

3.1 Aircraft Interface Testing – Configuration Mode

3.1.1 Discrete Inputs Verify the operation of the G1000 discretes as follows:

1. Select the GIA I/O CONFIGURATION page (3rd page in GIA page group). The GIA 1 DISCRETE IN page should be shown by default.

2. Press the Go Around (GA) switch on the flaps panel above the throttle and verify that the box for

the AFCS GO AROUND (IN* 4) turns green while the switch is pressed, and is black otherwise.

3. Press the Control Wheel Steering (CWS) switch on the control stick and verify that the box for the PLT CTRL WHL (IN* 5) turns green while the switch is pressed, and is black otherwise.

4. Open the AVIONICS FANS circuit breaker and verify that the box for the GIA 1 FAN (IN* 12) turns green while the breaker is pulled, and is black otherwise. Close the AVIONICS FANS circuit breaker.

5. Briefly turn the vapor suppression switch ON and verify that the box for the VAPOR SUPPRESS L (IN 13) turns green while the switch is ON, and is black otherwise.

6. Extend the speed brakes and verify that the box for the SPEED BRAKE EXTE (IN 14) turns green while the speed brakes are extended, and is black otherwise.

7. Set the flaps to T/O and verify that the box for the FLAP EXTEND (IN 16) turns green while the flaps are extending, and is black otherwise.

8. Set the flaps to UP and verify that the box for the FLAP RETRACT (IN 17) turns green while the flaps are retracting, and is black otherwise.


9. Activate the cursor and use the small FMS knob to highlight GIA 2 in the SELECT GIA UNIT field and then press the ENT key. The GIA 2 DISCRETE IN page will now be shown.

10. Open the AVIONICS FANS circuit breaker and verify that the box for the GIA 2 FAN (IN* 12)

turns green while the breaker is pulled, and is black otherwise. Close the AVIONICS FANS circuit breaker.

11. Briefly switch the vapor suppression switch ON and verify that the box for the VAPOR SUPPRESS R (IN 13) turns green while the switch is ON, and is black otherwise.

12. Extend the speed brakes and verify that the box for the SPEED BRAKE EXTE (IN 14) turns green while the speed brakes are extended, and is black otherwise.

13. Deactivate the cursor and then select the GFC STATUS page (2nd page in GFC page group). The GIA 1 page for the Pitch Servo should be shown by default.


14. Verify that the A/P DISCONNECT boxes in the GIA STATUS, MONITOR BOARD STATUS

and CONTROL BOARD STATUS areas are green.

15. Press the A/P DISC switch on the pilot’s control stick and verify that the green boxes in the GIA STATUS and CONTROL BOARD STATUS areas are black while the A/P DISC switch is pressed.

NOTE The A/P DISCONNECT box in the MONITOR BOARD STATUS area will remain green for up to 20 seconds after the A/P DISC switch is pressed. It is not necessary to wait for this box to change from green to black, since this takes its input from the same pin as the CONTROL BOARD STATUS.

16. Press the A/P DISC switch on the copilot’s control stick and verify that the green boxes in the GIA STATUS and CONTROL BOARD STATUS areas are black while the A/P DISC switch is pressed.

NOTE If the servo PFT status is listed as FAILED and the HIGH RES LOAD CELL CAL and HIGH RNG LOAD CELL CAL boxes are green, reload the servo gains before replacing the servo.

17. In the MONITOR BOARD STATUS area, verify that the PFT says PASSED and the boxes beside the HIGH RES LOAD CELL CAL and HIGH RNG LOAD CELL CAL boxes are green. If the either or both of the boxes beside the HIGH RES LOAD CELL CAL and HIGH RNG LOAD CELL CAL are red or the PFT status is FAILED, the servo must be replaced.

18. Activate the cursor and use the small FMS knob to highlight ROLL SERVO in the SELECT SERVO AXIS field and then press the ENT key. The ROLL SERVO GFC STATUS page will now be shown.


19. Verify that the A/P DISCONNECT boxes in the GIA STATUS, MONITOR BOARD STATUS

and CONTROL BOARD STATUS areas are green.

20. Press the A/P DISC switch on the pilot’s control stick and verify that the green boxes in the GIA STATUS and CONTROL BOARD STATUS areas are black while the A/P DISC switch is pressed.

NOTE The A/P DISCONNECT box in the MONITOR BOARD STATUS area will remain green for up to 20 seconds after the A/P DISC switch is pressed. It is not necessary to wait for this box to change from green to black, since this takes its input from the same pin as the CONTROL BOARD STATUS.

21. Press the A/P DISC switch on the copilot’s control stick and verify that the green boxes in the GIA STATUS and CONTROL BOARD STATUS areas are black while the A/P DISC switch is pressed.

NOTE If the servo PFT status is listed as FAILED and the HIGH RES LOAD CELL CAL and HIGH RNG LOAD CELL CAL boxes are green, reload the servo gains before replacing the servo.

22. In the MONITOR BOARD STATUS area, verify that the PFT says PASSED and the boxes beside the HIGH RES LOAD CELL CAL and HIGH RNG LOAD CELL CAL boxes are green. If the either or both of the boxes beside the HIGH RES LOAD CELL CAL and HIGH RNG LOAD CELL CAL are red or the PFT status is FAILED, the servo must be replaced.

23. Activate the cursor and use the small FMS knob to highlight PITCH TRIM SERVO in the SELECT SERVO AXIS field and then press the ENT key. The PITCH TRIM SERVO GFC STATUS page will now be shown.


24. Ensure that the AP/TRIM MASTER in the overhead panel is switched to ON. Verify that the A/P

DISCONNECT boxes in the GIA STATUS, MONITOR BOARD STATUS areas are green.

25. Verify that the SERVO ENABLE box in the MONITOR BOARD STATUS area is green.

26. Set the AP/TRIM MASTER in the overhead panel to OFF. Verify that the A/P DISCONNECT and SERVO ENABLE boxes in the MONITOR BOARD STATUS area are black.

NOTE The A/P DISCONNECT box in the GIA STATUS area will remain green.

27. Set the AP/TRIM MASTER in the overhead panel to ON.

28. Press the A/P DISC switch on the pilot’s control stick and verify that the SERVO ENABLE box is black while the A/P DISC switch is depressed, and green otherwise.

29. Press the A/P DISC switch on the copilot’s control stick and verify that the SERVO ENABLE box is black while the A/P DISC switch is depressed, and green otherwise.

30. Move the trim switch on the pilot’s control stick to the TRIM UP position. Verify that the MANUAL TRIM CCW box is green while the switch is in the TRIM UP position and is black otherwise.

31. Move the trim switch on the pilot’s control stick to the TRIM DOWN position. Verify that the MANUAL TRIM CW box is green while the switch is in the TRIM DOWN position and is black otherwise.

32. Move the trim switch on the copilot’s control stick to the TRIM UP position. Verify that the MANUAL TRIM CCW box is green while the switch is in the TRIM UP position and is black otherwise.

33. Move the trim switch on the copilot’s control stick to the TRIM DOWN position. Verify that the MANUAL TRIM CW box is green while the switch is in the TRIM DOWN position and is black otherwise.


34. Activate the cursor and use the large FMS knob to select the GIA unit small FMS knob to highlight GIA 2 in the SELECT GIA UNIT field and then press the ENT key. The PITCH SERVO GFC STATUS page will now be shown.

35. Verify that the A/P DISCONNECT box in the GIA STATUS area is green.

36. Press the A/P DISC switch on the pilot’s control stick and verify that the green box in the GIA STATUS area is black while the A/P DISC switch is pressed.

37. Press the A/P DISC switch on the copilot’s control stick and verify that the green box in the GIA STATUS area is black while the A/P DISC switch is pressed.


38. Deactivate the cursor and select the GEA STATUS page (2nd page in the GEA page group). GEA 1 will be shown by default.

39. Press the DSCRT softkey to select the Discrete Inputs status page.

NOTE This section will verify that the discrete inputs are present. When the engine is started it will be verified that the discrete inputs ‘open’ by the lack of associated alerts.

NOTE Unless specified, the status of other discrete inputs may not match the figure above and does not matter for this portion of the test.

40. Verify that the boxes beside the “4A L FUEL XFER PUMP SWITCH ON” (low fuel pressure) and “7A ENG 1 LOW OIL P” are green.


3.1.2 Carbon Monoxide Warning System

1. Go to the System Status page using the FMS knob. The CO Guardian is the first item in the LRU

list.

2. Verify that the CO Guardian has its status displayed as ‘OK’.

3. Open the CO DETECTOR circuit breaker. Verify that the CO Guardian status changes to TIMEOUT after approximately five seconds.

4. Close the CO DETECTOR circuit breaker.


3.1.3 WX-500 Stormscope (if installed) NOTE

This procedure just verifies the WX-500 interface to the G1000. Other system checks must be carried out in accordance with the WX-500 Installation Manual.

1. Select the OTHER page group on the PFD. The STORMSCOPE page is shown by default.

2. Activate the cursor and highlight the DATA field. Use the small FMS knob to select ‘Config’ and press the ENT key on the PFD.

3. Verify that the DATA window shows the following: Hdg: None: J3-1 Open J3-2 Open Hdg Valid Flag N/A Flag Sense N/A Hdg Value NA Inhibit Line Off Antenna Mount Bottom J3-3 Open

Deactivate the cursor NOTE

The DATA window is only updated once every five seconds, so changes made to the inhibit line may not be displayed immediately.

4. Key the Pilot’s mic for at least five seconds and verify that the Inhibit Line field changes from Off to On while the mic is keyed.

5. If installed, key the Copilot’s mic for at least five seconds and verify that the Inhibit Line field changes from Off to On while the mic is keyed.


6. Activate the cursor and highlight the DATA field. Use the small FMS knob to select ‘Fault Log’ and press the ENT key on the PFD.

7. Verify that LIGHTNING FAILED is not displayed in yellow text in the Stormscope map displayed in the bottom right corner.

NOTE If LIGHTNING FAILED is displayed, ‘Fault Log’ may be selected in the data field to display the WX-500 fault log. The WX-500 installation manual can then be consulted for interpretation of the displayed fault codes and further troubleshooting information.

3.1.4 Ryan TCAD 9900BX (if installed)

NOTE For instructions on using a laptop and connecting to the TCAD LRU, refer to the Ryan TCAD Model 9900BX installation manual section on Personal Computer Setup.

1. Using the laptop, initiate the Calibration and Verification Interface.

2. Run the following tests and verify that they pass:

Bearing Verification

Coupler Verification

External Mute Verification

Gear Down Verification (in the Columbia, this is connected to the flaps control)

Suppression Bus Verification

TCAD Version Verification (TCAD MUST have ROM version 1.16 or later)

Audio Control Setting and Verification (TCAD volume must be set to 255)

Weight on Wheels Verification (in the Columbia, this is connected to an airspeed switch)


3.2 Calibration and Activation

3.2.1 Aileron and Elevator Trim Calibration

NOTE Before conducting the flaps and trim calibration procedure, ensure that the elevator, elevator trim, aileron and aileron trim systems have been properly rigged and adjusted.

1. Go to the CAL Page Group on the PFD.

2. Select the Flaps and Trim Calibration page (3rd page in CAL group), shown below:

Figure 3-1. Aileron and Elevator Trim Calibration

3. This page is protected and requires a keystroke password to perform the calibration. Press the following softkeys in sequence:

a) softkey 1 (Far Left softkey) b) softkey 2 c) softkey 3 d) softkey 4

4. Press the Elevator Trim RESET softkey (see Figure 3-1). Press ENT to acknowledge the following prompt after the RESET softkey is pressed:


5. Use the trim hat switch to run the elevator trim to the FULL UP position.

6. Press the Elevator Trim UP softkey on the PFD (see Figure 3-1).

7. Run the elevator trim to the FULL DOWN position. Press the Elevator Trim DN softkey on the PFD.

8. Run the elevator trim back to the FULL UP position.

9. Verify that the CAL VALUE in the ELEVATOR TRIM window indicates 1.00000 ± 0.02000. If it does not, repeat steps 4 to 8 until it does.

10. Press the Aileron Trim RESET softkey on the PFD (see Figure 3-1). Press ENT to acknowledge the following prompt after the RESET softkey is pressed:

11. Use the trim hat switch to run the aileron trim full RIGHT.

12. Press the Aileron Trim RIGHT softkey on the PFD (see Figure 3-1).

13. Use the hat trim switch in the aircraft to run the aileron trim full LEFT. Press the LEFT softkey on the PFD (see Figure 3-1).

14. Run the aileron trim full RIGHT.

15. Verify that the CAL VALUE in the AILERON TRIM window indicates 1.00000 ± 0.02000. If it does not, repeat steps 10 to 14 until it does.

16. Calibration is complete.

3.2.2 Fuel Quantity Transducer Calibration

NOTE The G1000 system can be calibrated for 49 as well as 51 gallon fuel tanks. Ensure the appropriate option has been selected when performing fuel calibration. Incorrect calibration will lead to misleading displays and potential fuel starvation of the aircraft. Attention to detail is imperative.

3.2.2.1 Calibration Setup 1. Level the aircraft, following instructions in the Columbia Maintenance Manual.

2. Drain all fuel from each fuel tank, and set the fuel selector switch to the ‘OFF’ position.

3. Fill each fuel tank with unusable fuel level, 2 gallons (for 51 gallon option) or 4 gallons (for 49 gallon option).

NOTE

Ensure appropriate option for calibration. Use proper precautions when handling fuel. Ensure that the aircraft is grounded correctly and that there is adequate ventilation.


4. Start the G1000 system in Configuration mode. Reboot the MFD in normal mode for this procedure by pulling, then resetting, the MFD circuit breaker. On the MFD, press the ENGINE softkey to display the full page engine instrumentation.

5. Go to the CAL Page Group on the PFD. The FUEL TANK CALIBRATION page should be displayed as shown:

6. This page is protected and requires a keystroke password to perform the calibration. Press the

following softkeys in sequence:

a) softkey 12 (Far Right softkey)

b) softkey 11

c) softkey 10

d) softkey 9

7. Press the TNK SEL softkey to activate the cursor in the CURRENT TANK field. Rotate the FMS knob as necessary throughout this procedure to select the RIGHT or LEFT tanks.


3.2.2.2 Empty Calibration 1. Verify that unusable fuel has been added to both tanks per section 3.2.2.1. Allow both fuel

probes to stabilize for at least 2 minutes.

2. Select the LEFT tank on the PFD.

3. Press the EMPTY softkey. The cursor will automatically activate and select the CALIBRATE? option. The calibrated value setting will default to 00.00.

4. Press the ENT key. A prompt appears requesting overwrite acknowledgement. Select YES and press the ENT key. The G1000 system will ‘zero’ the actual fuel quantity value to be displayed.

5. Select the RIGHT tank.

6. Press the EMPTY softkey. The cursor will automatically activate and select the CALIBRATE? option. The calibrated value setting will default to 00.00.

7. Press the ENT key. A prompt appears requesting overwrite acknowledgement. Select YES and press the ENT key. The G1000 system will ‘zero’ the actual fuel quantity value to be displayed.

8. Observe the CALIBRATED TOTAL indication for the RIGHT tank. Verify that it remains at 0.00.

9. Select the LEFT tank. Observe the CALIBRATED TOTAL indication for the LEFT tank. Verify that it remains at 0.00.

10. On the MFD, verify the fuel quantity indicators correctly point to ‘0’.

3.2.2.3 5 Gallon Calibration 1. Fill each fuel tank with 5 ± 0.1 gallons usable fuel.

2. Allow the fuel probes to stabilize at least 2 minutes before continuing.

3. Record the CALIBRATED TOTAL indication for the RIGHT tank. This is the pre-calibrated value.

RIGHT 1 SUB-TANK

Calibration Value Range Actual Useable

Fuel Minimum Allowed Indication

Maximum Allowed Indication

Record Actual Indicated Calibration Value

Here

Is Calibration Value Within Specified Range?

Yes / No

0 -0.5 0.5

4. Select the LEFT tank. Record the CALIBRATED TOTAL indication for the LEFT tank. This is the pre-calibrated value.

LEFT 1 SUB-TANK

Calibration Value Range Actual Useable

Fuel Minimum Allowed Indication

Maximum Allowed Indication

Record Actual Indicated Calibration Value

Here

Is Calibration Value Within Specified Range?

Yes / No

0 -0.5 0.5

5. With the LEFT tank selected, highlight the ACTUAL FUEL QUANTITY field and enter 5.00 gallons.

6. Press the ENT key. The cursor automatically selects the CALIBRATE? option.

7. Press the ENT key again to calibrate the 5 gallon point.

8. Verify a 5.00 gallon point appears in the CALIBRATION TABLE.


9. Verify that the CALIBRATED TOTAL value indicates 5.00.

10. Select the RIGHT tank. Highlight the ACTUAL FUEL QUANTITY field and enter 5.00 gallons.

11. Press the ENT key. The cursor automatically selects the CALIBRATE? option.

12. Press the ENT key again to calibrate the 5 gallon point.

13. Verify a 5.00 gallon point appears in the CALIBRATION TABLE.

14. Verify that the CALIBRATED TOTAL value indicates 5.00.

3.2.2.4 Low Fuel Level Check 1. Using the large FMS knob, select the GEA STATUS page (2nd page in the GEA page group).

GEA 1 will be shown by default.

2. Press the DSCRT softkey to select the Discrete Inputs status page.

NOTE Unless specified, the status of other discrete inputs may not match the figure above and does not matter for this portion of the test.

3. Verify that the boxes beside the “1A LOW MAIN FUEL L” (low fuel quantity left) and “2A LOW MAIN FUEL R” (low fuel quantity right) are green.

4. Continue to slowly add fuel to each tank one measured gallon at a time. Stop adding fuel when the associated LOW MAIN FUEL L or LOW MAIN FUEL R box changes from black to green.

5. Using the large FMS knob, select the FUEL CALIBRATION page (1st page in CAL page group).

6. In the table below, record the amount of usable fuel added to each tank. Also record the Calibration Value indications for both Right 1 and Left 1 Sub-Tanks. The amount of fuel added


to each tank to turn the discrete off must be 8 ± 2 gal, and the Calibration Values should be within ±2 gallon of the actual amount of usable fuel added.

NOTE If any calibration value is outside of the specified ranges, the fuel quantity system requires service

Allowable Range for Actual Fuel

TANK

Actual Useable

Fuel Added (gal)

Minimum Allowable Fuel

Maximum Allowable Fuel

Actual Indicated

Calibration Value (gal)

Tolerance on Calibration

Value (gal)

LEFT 1 SUB-TANK 6.0 gal 10.0 gal ± 2.0

RIGHT 1 SUB-TANK 6.0 gal 10.0 gal ± 2.0

3.2.2.5 Full Calibration 1. Verify that both fuel tanks are full. Allow both fuel probes to stabilize for at least 2 minutes

2. Select the LEFT tank on the PFD.

3. Press the FULL softkey. The cursor will automatically activate and select the CALIBRATE? option. The calibrated value setting will default to 49.00 or 51.00 as appropriate.

4. Press the ENT key. A prompt appears requesting overwrite acknowledgement. Select YES and press the ENT key. The G1000 system will set the actual fuel quantity value to be full.

5. Select the RIGHT tank.

6. Press the FULL softkey. The cursor will automatically activate and select the CALIBRATE? option. The calibrated value setting will default to 49.00 or 51.00.as appropriate.

7. Press the ENT key. A prompt appears requesting overwrite acknowledgement. Select YES and press the ENT key. The G1000 system will set the actual fuel quantity value to be full.

8. Observe the CALIBRATED TOTAL indication for the RIGHT tank. Verify that it remains at 49.00 or 51.00 as appropriate.

9. Select the LEFT tank. Observe the CALIBRATED TOTAL indication for the LEFT tank. Verify that it remains at 49.00 or 51.00 as appropriate.

10. On the MFD, verify the fuel quantity indicators correctly point to ‘F’.


3.3 Initial Display Testing

For the remainder of the system checkout procedures, the G1000 system is tested while operating in the normal mode unless otherwise specified.

1. Pull the MFD and PFD circuit breakers.

2. While holding the CLR key on the PFD, restore power by closing the PFD circuit breaker.

3. Press the 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):

4. The PFD will clear the user settings and then start up in normal mode.

5. Repeat steps 2 and 3 for the MFD.

6. The MFD will clear the user settings and then start up in normal mode. Look at the MFD