Garmin G1000 NXi: Beechcraft Baron G58 G1000 NXi Maintenance Manual for Textron G36/G58, includes Instructions for Continued Airworthiness for STC SA01830WI

Supplemental Maintenance

Manual

Textron Aviation

G36/G58

Includes Instructions for Continued Airworthiness for STC SA01830WI

190-02128-05 2018 Revision

© Copyright 2017-2018

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 (Europe) Ltd.

Liberty House, Bulls Copse Road

Hounsdown Business Park

Southampton, SO40 9RB, UK

Phone: +44 (0) 23 8052 4000

Fax: +44 (0) 23 8052 4004

Garmin AT, Inc.

2345 Turner Rd., SE

Salem, OR 97302 USA

Telephone: 503.581.8101

RECORD OF REVISIONS

1

Description

11/16/2016 Initial Release

Updated Loader Card Creation Instructions

Procedures (Section 7.13 and 8.7)

DOCUMENT PAGINATION

Section Pagination

Table of Contents i – vi pSection 1

Section 2

Section 3

1-1 – 1-5

2-1 – 2-9

3-1 – 3-43

Section 4

Section 5

Section 6

Section 7

Section 8

Section 9

4-1– 4-11

5-1 – 5-34

6-1 – 6-12

7-1– 7-52

8-1 – 8-6

9-1 - 9-10

G1000 System Maintenance Manual

Textron Aviation G36/G58

190-02128-05

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Revision 3

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

This document may contain information which is subject to the Export Administration

Regulations (“EAR”) issued by the United States Department of Commerce (15 CFR, Chapter

VII Subchapter C) and which may not be exported, released or disclosed to foreign nationals inside or outside the United States without first obtaining an export license. The preceding statement is required to be included on any and all reproductions in whole or in part of this manual.

WARNING

This product, its packaging, and its components contain chemicals known to the State of

California to cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65.

CAUTION

The GDU lens is coated with a special anti-reflective coating that is very sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-

REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective coatings.

IMPORTANT

All G1000 screen shots used in this document are current at the time of publication. Screen shots are intended to provide visual reference only. All information depicted in screen shots, including software file names, versions and part numbers, is subject to change and may not be up to date.

G1000 System Maintenance Manual


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TABLE OF CONTENTS

PARAGRAPH PAGE

1.

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

1.1

Content, Scope, Purpose .............................................................................................. 1-1

1.2

Organization .................................................................................................................. 1-2

1.3

Definitions/Abbreviations .............................................................................................. 1-3

1.4

Units of Measure ........................................................................................................... 1-4

1.5

Publications................................................................................................................... 1-4

1.6

Revision and Distribution .............................................................................................. 1-5

2.

SYSTEM DESCRIPTION .................................................................................................... 2-1

2.1

Equipment Descriptions ................................................................................................ 2-1

2.2

G1000 Optional Interfaces ............................................................................................ 2-7

2.3

Electrical Power Distribution ......................................................................................... 2-7

2.4

Pitot/Static System ........................................................................................................ 2-7

2.5

GDU 1050 and GDU 1055 Displays ............................................................................. 2-7

2.6

Softkeys ........................................................................................................................ 2-7

2.7

FMS Knob ..................................................................................................................... 2-7

2.8

G1000 Normal Mode ..................................................................................................... 2-8

2.9

Reversionary Mode ....................................................................................................... 2-9

3.

SOFTWARE AND CONFIGURATION ................................................................................ 3-1

3.1

Configuration Mode Overview ....................................................................................... 3-1

3.2

Configuration Mode ..................................................................................................... 3-15

3.3

G1000 Hardware/Software Compatibility Check ......................................................... 3-15

3.4

Equipment Verification (Third Party/Optional Equipment Documentation) ................. 3-15

3.5

G1000 Software/Configuration Procedure .................................................................. 3-17

3.6

System Software and Configuration Load .................................................................. 3-18

3.7

Feature Enablement ................................................................................................... 3-32

3.8

Aircraft Registration Number Entry and Flight ID Configuration ................................. 3-36

3.9

Configuration Manager ............................................................................................... 3-38

3.10

Splash Screen Loading ............................................................................................... 3-38

3.11

Database Loading ....................................................................................................... 3-39

3.12

Configuration of Navigation Map for Traffic System ................................................... 3-41

3.13

Clearing Default User Settings .................................................................................... 3-41

3.14

Interface Confirmation ................................................................................................. 3-42

4.

INSTRUCTIONS FOR CONTINUED AIRWORTHINESS ................................................... 4-1

4.1

Airworthiness Limitations .............................................................................................. 4-1

4.2

Servicing Information .................................................................................................... 4-2

4.3

Maintenance Intervals ................................................................................................... 4-4

4.4

Electrical Bonding Test ................................................................................................. 4-5

4.5

GRS 79 Earth Magnetic Field Updates ......................................................................... 4-7

4.6

G1000 Redundant Connection Check .......................................................................... 4-8

4.7

GSM 86 Spring Cartridge Torque Check ...................................................................... 4-9

5.

TROUBLESHOOTING ........................................................................................................ 5-1

5.1

System Annunciations .................................................................................................. 5-2

5.2

G1000 Alerting System ............................................................................................... 5-13

5.3

Synthetic Vision and Pathways Troubleshooting ........................................................ 5-14

5.4

Backup Communications Path Checks ....................................................................... 5-15

5.5

GDU 105X Troubleshooting ........................................................................................ 5-16

5.6

GDU 105X Alerts ........................................................................................................ 5-18

5.7

GTX Troubleshooting .................................................................................................. 5-22

5.8

GDL69A SXM Troubleshooting (if installed) ............................................................... 5-23

5.9

GEA 71B Troubleshooting (if installed) ....................................................................... 5-23

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5.10

GIA 64W Troubleshooting (if installed) ....................................................................... 5-23

5.11

GMA 1360 Troubleshooting (if installed) ..................................................................... 5-23

5.12

GWX 75 Troubleshooting (if installed) ........................................................................ 5-23

5.13

GSR 56 Troubleshooting ............................................................................................ 5-23

5.14

GRS 79 and GMU 44 Troubleshooting ....................................................................... 5-24

5.15

GDC 72 Troubleshooting ............................................................................................ 5-29

5.16

Software/Configuration Troubleshooting ..................................................................... 5-29

5.17

Backshell/Backplate Connectors ................................................................................ 5-31

6.

EQUIPMENT REMOVAL & INSTALLATION ..................................................................... 6-1

6.1

GDU 1050/1055 ............................................................................................................ 6-2

6.2

GTX 335R/GTRX 345R Transponder (if installed) ........................................................ 6-2

6.3

GRS 79 AHRS (if installed) ........................................................................................... 6-3

6.4

GDC 72 ADC (if installed) ............................................................................................. 6-3

6.5

GDL 69A SXM (if installed) ........................................................................................... 6-4

6.6

GTS 800 Traffic System (if installed) ............................................................................ 6-4

6.7

Configuration Modules .................................................................................................. 6-4

6.8

GMA 1360 Audio Panel (if installed) ............................................................................. 6-8

6.9

GIA 64W Integrated Avionics Unit (if installed) ............................................................. 6-8

6.10

GSR 56 Satellite Transceiver (if installed) ................................................................... 6-9

6.11

Iridium Antenna (if installed) ......................................................................................... 6-9

6.12

GEA 71B Engine/Airframe Unit (if installed) ............................................................... 6-10

6.13

FS 510 Wifi/Bluetooth Data Link (if installed) .............................................................. 6-10

6.14

GSA 81 Servo Actuator (if installed) ........................................................................... 6-11

6.15

GSM 86 Servo Gearbox (if installed) .......................................................................... 6-12

6.16

GWX 75 Weather Radar (if installed) .......................................................................... 6-12

7.

GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING .......................... 7-1

7.1

GDU 1050 PFD & GDU 1055 MFD ............................................................................... 7-1

7.2

GMA 1347 or GMA 1360 Audio Panel .......................................................................... 7-4

7.3

GIA 63W or GIA64W Integrated Avionics Unit .............................................................. 7-8

7.4

GEA 71 or GEA 71B Engine/Airframe Unit ................................................................. 7-16

7.5

GTX 335R, GTX 345R, or GTX 33 Transponder ........................................................ 7-19

7.6

GRS 79 AHRS (if installed) ......................................................................................... 7-22

7.7

GDC 72 ADC (if installed) ........................................................................................... 7-24

7.8

GDC 74A Air Data ....................................................................................................... 7-25

7.9

GRS 77 AHRS (if installed) ......................................................................................... 7-30

7.10

GMU 44 Magnetometer .............................................................................................. 7-32

7.11

GRS/GMU Calibration Procedures ............................................................................. 7-33

7.12

GDL 69A or GDL 69A SXM Data Link (if installed) ..................................................... 7-42

7.13

GSA 81 Servos (if installed) ........................................................................................ 7-44

7.14

Garmin Traffic Systems (GTS 800 or GTS 820) (if installed) ...................................... 7-46

7.15

GSR 56 ....................................................................................................................... 7-50

7.16

GWX 75 Weather Radar ............................................................................................. 7-51

8.

SUBSYSTEM FUNCTIONAL CHECKS .............................................................................. 8-1

8.1

Stormscope Functional Check (if installed) ................................................................... 8-1

8.2

TAWS Functional Check ............................................................................................... 8-1

8.3

FliteCharts Functional Check ........................................................................................ 8-1

8.4

ChartView Functional Check ......................................................................................... 8-2

8.5

SafeTaxi Functional Check ........................................................................................... 8-3

8.6

DME Functional Check ................................................................................................. 8-4

8.7

GTS Traffic System Functional Check .......................................................................... 8-4

9.

G1000 SYSTEM RETURN TO SERVICE PROCEDURE ................................................... 9-1

9.1

Display Test .................................................................................................................. 9-1

9.2

Display Failure Test ...................................................................................................... 9-4



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9.3

Reversion Mode Check ................................................................................................. 9-5

9.4

GPS Signal Acquisition ................................................................................................. 9-6

9.5

GPS Failure Test .......................................................................................................... 9-7

9.6

GIA Failure Test ............................................................................................................ 9-8

9.7

GEA Functional Check .................................................................................................. 9-9

9.8

G1000 Backup Path Test ............................................................................................ 9-10

9.9

GFC 700 Autopilot Clutch Overpower Check ............................................................. 9-10

9.10

Maintenance Records ................................................................................................. 9-10

LIST OF ILLUSTRATIONS

FIGURE PAGE

Figure 2-1 Flight Stream 510 .................................................................................................... 2-1

Figure 2-2, GTX 345R/GTX 335R Transponder ........................................................................ 2-2

Figure 2-3 GRS 79 AHRS with Mounting Tray ......................................................................... 2-2

Figure 2-4 GDC 72 ADC with Mounting Tray ............................................................................ 2-3

Figure 2-5, GDL 69A SXM Datalink ........................................................................................... 2-3

Figure 2-6 GTS 800 Traffic System Processor .......................................................................... 2-4

Figure 2-7, GSA 81 Servo Actuator, GSM 86 Servo Gearbox ................................................... 2-4

Figure 2-8, GMA 1360 Audio Panel ........................................................................................... 2-5

Figure 2-9, GIA 64W Integrated Avionics Unit ........................................................................... 2-5

Figure 2-10, GEA 71B Engine Airframe Unit ............................................................................. 2-6

Figure 2-11, GSR 56 Satellite Transceiver ................................................................................ 2-6

Figure 2-12, G1000 Softkeys ..................................................................................................... 2-7

Figure 2-13, Normal Mode ......................................................................................................... 2-8

Figure 2-13, Automatic Reversion with MFD failure ................................................................. 2-9

Figure 3-1, SET>ACTV Diagram ............................................................................................... 3-2

Figure 3-2, Loss of Communication ........................................................................................... 3-3

Figure 3-3, Configuration Status ................................................................................................ 3-3

Figure 3-4, Data Transmission Indicators .................................................................................. 3-3

Figure 3-5, GRS and GDC Configuration Settings Storage ..................................................... 3-14

Figure 3-6, Garmin Unit S/N Location ...................................................................................... 3-16

Figure 3-7, Software/Configuration Overview .......................................................................... 3-17

Figure 3-8, Airframe Change Confirmation .............................................................................. 3-19

Figure 3-9, MFD Aux - Database Page DB Transfer ............................................................... 3-40

Figure 3-10, Stormscope Configuration Page .......................................................................... 3-42

Figure 3-11, Stormscope Configuration ................................................................................... 3-42

Figure 4-1, GFC Status Page .................................................................................................... 4-9

Figure 5-1, Aux – System Status Page ...................................................................................... 5-1

Figure 5-2, System Annunciations ............................................................................................. 5-2

Figure 5-3, Alerts & Annunciations .......................................................................................... 5-13

Figure 5-4, Alerts Softkey Annunciation ................................................................................... 5-13

Figure 5-5, Magnetometer Interference Test ........................................................................... 5-26

Figure 5-6, GTX 335R/345R Looking at Front of Connector (P3251) ...................................... 5-31

Figure 5-7, GTX 345R (Only) Looking at Front of Connector (P3252)..................................... 5-31

Figure 5-8, GDU 1054B/1050 Backshell Connector (P10401) ................................................ 5-32

Figure 5-9, GRS 79 Connector View from Front (P791) .......................................................... 5-32

Figure 5-10, GDC 72 Connector View from Front (P721) ........................................................ 5-32

Figure 5-11, GDL 69A SXM Backplate Connector (P69A1) .................................................... 5-32

Figure 5-12, GIA 64W Backplate Connectors .......................................................................... 5-33

Figure 5-13, GEA 71B Backplate Connectors ......................................................................... 5-33

Figure 5-14, GMA 1360 Backplate Connectors ....................................................................... 5-34

Figure 5-15, GSR 56 Mating Connector .................................................................................. 5-34



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Figure 5-16, GWX 75 Mating Connector .................................................................................. 5-34

Figure 6-1, Configuration Module Installation ............................................................................ 6-5

Figure 6-2, GRS 79 and GDC 72 Configuration Module Installation ......................................... 6-6

Figure 6-3, Servo Gear ............................................................................................................ 6-11

Figure 7-1, G1000 Normal Mode Check ................................................................................... 7-3

Figure 7-2, Aux – GPS Status Page (MFD) ............................................................................. 7-13

Figure 7-3, Normal Engine Instrument Markings (MFD) (G58 Shown, G36 similar) ............... 7-18

Figure 7-4, Aircraft Registration ............................................................................................... 7-21

Figure 7-5, GRS/GMU Calibration, Pitch/Roll Offset ............................................................... 7-35

Figure 7-6, GRS/GMU Calibration, Engine Run-Up ................................................................. 7-39

Figure 7-7, Normal Mode AHRS Check .................................................................................. 7-41

Figure 8-1, Traffic Map ............................................................................................................... 8-4

Figure 9-1, MFD Power Up Page ............................................................................................... 9-1

Figure 9-2, PFD Power-up System Annunciations .................................................................... 9-2

Figure 9-3, PFD Normal Operation ............................................................................................ 9-3

Figure 9-4, GDU Reversionary Mode ........................................................................................ 9-5

Figure 9-5, AUX-GPS Status Page ............................................................................................ 9-6

LIST OF TABLES

TABLE .................................................................................................................................. PAGE

Table 1-1, Required Documents ................................................................................................ 1-4

Table 1-2, Reference Publications ............................................................................................ 1-5

Table 4-1, Maintenance Intervals ............................................................................................... 4-4

Table 4-2, GSM 86 Allowable Torque Values (Automated Test) ............................................. 4-10

Table 4-3, GSM 86 Allowable Torque Values (Fixture Test) ................................................... 4-11

Table 5-1, SVS Troubleshooting .............................................................................................. 5-14

Table 5-2, SVS-Related Alert Messages ................................................................................ 5-15

Table 5-3, Magnetometer Interference Test Sequence ........................................................... 5-28

Table 6-1, Configuration Module Kit – 011-00979-00 ............................................................... 6-5

Table 6-2, GRS 79 and GDC 72 Configuration Module Kit – 011-00979-20 ............................. 6-6

Table 7-1, Altitude Test Points ................................................................................................. 7-28

Table 7-2, Airspeed Test Points ............................................................................................... 7-28

Table 7-3, Vertical Speed Table .............................................................................................. 7-29

Table 7-4, Required GRS/GMU Calibrations ........................................................................... 7-34



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1. INTRODUCTION

1.1 Content, Scope, Purpose

This document provides Instructions for Continued Airworthiness (ICA) for the NXi configuration of the Garmin G1000 Integrated Flight Deck including the GFC700 Automatic Flight Control

System (AFCS) as installed in the Textron Aviation G36 and G58 aircraft, under STC

SA01830WI. This document satisfies the requirements for continued airworthiness as defined by 14 CFR Part 23.1529 and 14 CFR Part 23 Appendix G. Information in this document is required to maintain the continued airworthiness of the G1000 and GFC700.

Throughout this document, the GFC 700 autopilot system is included in the G1000NXi system description and is identified separately only when needed.

This manual covers both the G36 Bonanza and G58 Baron. All references in the manual cover both aircraft unless specifically noted.

This document is a supplement to the existing G36 or G58 Aircraft Maintenance Manual, the

G1000 58/G58 System Maintenance Manual (Garmin p/n 190-00451-03), and the G1000

System Maintenance Manual for the G36 for STC SA1595WI-D (Garmin p/n 190-01259-00) or the G1000 System Maintenance Manual for the G58 for STC SA01584WI-D (Garmin p/n 190-

01180-02). Except where noted, refer to the applicable Aircraft Maintenance Manual or the applicable System Maintenance Manual for servicing instructions.

Applicability

This document applies to all Textron Aviation G36/G58 aircraft equipped with the G1000NXi system. All G1000NXi G36/G58 airplanes are configured per General Arrangement drawing

005-00620-41 Rev 1 or subsequent.

Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft operator to include the maintenance information provided by this document in the operator’s

Aircraft Maintenance Manual.

Identifying an STC Configuration

The General Arrangement drawing lists the G1000 System Software Version numbers approved for this STC.

IMPORTANT!

If the technician is unsure of an aircraft’s STC configuration, perform the following:

After acknowledgement of the splash screen, use the FMS knob to go to the

Aux – System

Status

page on the MFD. In the AIRFRAME section (upper right corner,) the display shows the current G1000NXi airframe configuration and system software version number. The airframe configuration is shown in the Airframe field and the system software version number is shown in the following format: ‘SYS SOFTWARE VERSION XXXX.XX’. It correlates to the software image used to load the software to the system:

EXAMPLE:

System Software Version

’2780.00’

= Software Image P/N

006-B

2780-00



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1.2 Organization

The following outline briefly describes the organization of this manual:

Section 2: System Description

Provides a description of the type design change associated with installing the G1000 update in the Textron Aviation G36/G58 aircraft.

Section 3: Software and Configuration

Provides software and configuration loading instructions for a complete system software load.

Section 4: Instructions for Continued Airworthiness

Provides maintenance instructions for continued airworthiness of the G1000 system.

Section 5: Troubleshooting

Provides troubleshooting information to aid in diagnosing and resolving potential problems with the G1000 system.

Section 6: Equipment Removal & Replacement

Gives instructions for the removal and replacement of G1000 equipment.

Section 7: Garmin G1000 LRU Replacement/Configuration & Testing

Gives instructions for loading software, configuring, and testing of G1000 equipment.

Section 8: Subsystem Functional Checks

Gives instructions for testing G1000 subsystems.

Section 9: G1000 System Return to Service Procedure

Specifies return-to-service procedures to be performed upon completion of maintenance of the

G1000 system.



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1.3 Definitions/Abbreviations

ADC: Air Data Computer

ADF: Automatic Direction Finder

ADS-B: Automatic Dependent Surveillance – Broadcast

ADTS: Air Data Test Set

AFCS: Automatic Flight Control System

AFM: Airplane Flight Manual

AFMS: Airplane Flight Manual Supplement

AHRS: Attitude Heading Reference System

AML: Approved Model List

CDU: Control Display Unit

CFR: Code of Federal Regulations

DME: Distance Measuring Equipment

EIS: Engine Indication System

FIS-B: Flight Information Services – Broadcast

FS: Flight Stream

TM

GPS: Global Positioning System

HSDB: High-Speed Data Bus (Ethernet)

LRU: Line Replaceable Unit

OAT: Outside Air Temperature

PFD: Primary Flight Display

STC: Supplemental Type Certificate

TAWS: Terrain Awareness & Warning System

TIS-B: Traffic Information Services – Broadcast

VHF: Very High Frequency



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1.4 Units of Measure

Unless otherwise stated, all units of measure are English units.

1.5 Publications

The following documents are required by this maintenance manual to perform maintenance. It is the responsibility of the owner / operator to ensure latest versions of these documents are used during operation, servicing or maintenance of the airplane.

Table 1-1, Required Documents

Part Number Garmin Document

005-00620-21

005-00620-41

005-00620-43

005-00620-44

005-00620-45

005-00620-46

Master Drawing List, G1000 Avionics Updates, Part 23 AML STC

General Arrangement, G1000 Update, Textron G36/G58

Forward Avionics Install, G1000 Update, G36/G58

Aft Avionics Install, G1000 Update, G36/G58

GRS 79 AHRS Shelf, G1000 Update, Textron G36/G58

Wiring Diagram, G1000 Update, Textron G36/G58

005-00620-BD Avionics Install, GSR56, Textron G36/G58

005-00620-BE

005-00620-BF

005-00620-BG

Aft Avionics Install, GSR56, Textron G36/G58

Radar Install, GWX75, Textron G58

Wiring Diagram, E-AFCS Beechcraft G36/G58

005-00620-BH

005-00620-BJ

005-00620-BS

Wiring Diagram, GMA1360 Audio Panel, Textron G36/G58

Wiring Diagram, GWX75 Radar, Textron G58

Wiring Diagram, GSR56 Iridium Data Link, Textron G36/G58

Part Number Textron Aviation Documents

55-590000-13

58-590001-1

58-590001-3

58-590001-5

36-590001-9

36-590001-11

36-590001-13

36-590001-15

58-590001-11

Maintenance Manual, Baron Models 55/58

Maintenance Manual Supplement – G58

Wiring Manual – G58

Avionics Wiring Manual – G58

Maintenance Manual, Bonanza 35/33/36 Series

Maintenance Manual Supplement – G36

Wiring Manual – G36

Avionics Wiring Manual – G36

Beechcraft Bonanza Series and Baron 55 and 58 Series Structural Inspection and Repair

Manual



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The following publications are recommended to be on hand during the performance of maintenance activities.

Table 1-2, Reference Publications

Part Number Garmin Document

190-02128-03

190-02180-00

190-02182-00

190-00355-04

190-01259-00

190-01180-02

190-00451-03

190-00422-06

Airplane Flight Manual Supplement, G1000 NXi Integrated Avionics System and GFC 700

AFCS In Textron G36/G58 Series of aircraft

G1000 Cockpit Reference Guide for Beechcraft G36

G1000 Cockpit Reference Guide for Beechcraft G58

GDL 69 Series SiriusXM Satellite Radio Activation Instructions

G1000 System Maintenance Manual Hawker Beechcraft G36 (contains Instructions for

Continued Airworthiness for STC SA1595WI-D)

G1000 System Maintenance Manual Hawker Beechcraft G58 (contains Instructions for

Continued Airworthiness for STC SA01584WI-D)

G1000 System Maintenance Manual Beechcraft 58/G58

G1000 System Maintenance Manual Bonanza A36/G6 Including TAWS

Generic installation manuals for individual Garmin LRUs are also available through the ‘Dealer

Resource Center’ section of the Garmin web site; refer to Section 1.6 for details.

1.6 Revision and Distribution

This document is required for maintaining the continued airworthiness of the aircraft. When this document is revised, every page will be revised to indicate current revision level.

Garmin Dealers may obtain the latest revision of this document on the Garmin Dealer Resource

Center website.

Owner/operators may obtain the latest revision of this document from the https://fly.garmin.com/

Support page, or by contacting a Garmin dealer, contacting Garmin Product Support at 913-

397-8200, toll free 866-739-5687, or using around the world contact information on https://fly.garmin.com/.

A Garmin Service Bulletin describing the revision to this document will be sent to Garmin dealers if the revision is determined to be significant.



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2. SYSTEM DESCRIPTION

For description of equipment and functions not listed here, refer to the following documents, as applicable to the airframe:



G1000 System Maintenance Manual, Beechcraft 58/G58, Garmin part number 190-

00451-03



G1000 System Maintenance Manual Hawker Beechcraft G58, Contains Instructions for

Continued Airworthiness for STC SA01584WI-D, Garmin part number 190-01180-02



G1000 System Maintenance Manual, Bonanza A36 including TAWS, Garmin part number 190-00422-06.



G1000 System Maintenance Manual, Hawker Beechcraft G36, Contains Instructions for

Continued Airworthiness for STC SA1595WI-D, Garmin part number 190-01259-00

GDU 1050 PFD AND GDU 1055 MFD

A Garmin GDU 1050 PFD and a GDU 1055 MFD are installed in the instrument panel.

The GDU 1050 and GDU 1055 displays are 10.4 inch LCD displays with 1024 x 768 resolution.

The GDU 1050 and GDU 1055 units communicate with each other and the GIA 63W units through a high-speed data bus (HSDB) Ethernet connection.

The PFD receives electrical power from the Left Avionics Bus The MFD receives electrical power from the Right Avionics Bus. The PFD will power-up immediately with external or aircraft power or battery operation.

All displays are installed in the panel using ¼-turn fasteners.

Flight Stream 510

The Flight Stream™ 510 (FS 510) is a Wi-Fi/Bluetooth capable multi-media card (MMC) installed the bottom SD slot of the MFD. It sends position, velocity, time, attitude, heading, FIS-

B, TIS-B traffic, Sirius XM audio control, Sirius XM weather data, and flight plan transfer to mobile devices via Bluetooth. The FS 510 can also interface with a mobile device via Wi-Fi pairing for the purposes of updating databases used by the GDU(s). Bluetooth and Wi-Fi are mutually exclusive with only one interface functional at a time. Connecting via Wi-Fi requires a pilot-configurable Wi-Fi Protected Access WPA2 security password. By updating databases wirelessly, new databases may be transferred to the G1000 system without taking the data card out of the aircraft.

Figure 2-1 Flight Stream 510



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Transponder

The Garmin GTX 345R or GTX 335R transponders communicate with the GIA 63Ws through

RS-232 digital interface.

The GTX 345R also communicates with the G1000 Avionics through an HSDB interface connected to the PFD. When installed, the GTX 345R communicates and controls the GTS

Processor through the HSDB interface for all TAS operations. The GTX 345R mixes and coordinates the TAS targets with TIS-B targets to provide one coordinated traffic display to the crew.

The transponder unit is mounted behind the PFD in the instrument panel of the aircraft.

Power is provided to the GTX from the Left Avionics Bus. The GTX transponder interfaces with a transponder antenna mounted to the bottom of the fuselage.

Figure 2-2, GTX 345R/GTX 335R Transponder

GRS 79 AHRS

The GRS 79 AHRS (Attitude and Heading Reference System) is a device that provides flight attitude and heading data for flight instrumentation. The unit is mounted in the tail avionics area. It contains advanced tilt sensors, accelerometers, and rate sensors. The GRS 79 receives GPS data from the GIA 63Ws, and magnetic heading from the GMU 44 Magnetometer.

The GRS receives electrical power from the Left Avionics Bus. The GRS 79 provides electrical power to the GMU 44 Magnetometer.

The GRS 79 provides the following information via ARINC 429 busses to both GIAs, the PFD and the MFD.



Aircraft heading, pitch and roll



Aircraft yaw, pitch and roll rates



Aircraft body-axis accelerations



Rates of change of heading, pitch and roll



Aircraft accelerations expressed in a local level frame of reference

Figure 2-3 GRS 79 AHRS with Mounting Tray



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GDC 72 Air Data Computer

The GDC 72 ADC (Air Data Computer) is a device that provides air data for flight instrumentation. The unit is mounted in the G1000 system rack forward of the PFD. It contains static pressure sensors and pitot pressure sensors.

The GDC 72 receives electrical power from the Left Avionics Bus. The GDC 72 provides electrical power to the GTP 59 OAT probe.

The GDC 72 connects to the existing pitot/static ports.

The GDC 72 provides the following information via ARINC 429 busses to both GIAs, the PFD and the MFD.



Aircraft altitude and airspeed



Aircraft vertical speed, Mach and outside air temperature

Figure 2-4 GDC 72 ADC with Mounting Tray

GDL 69A SXM Datalink

The GDL 69A SXM provides SiriusXM Radio weather and music entertainment through means of a dedicated satellite data link. The GDL 69A SXM is mounted behind the instrument panel.

Power to the GDL 69A SXM is received from the Right Avionics bus. The GDL 69A SXM sends weather data through the HSDB bus to the MFD, where the data link interface is controlled.

Audio is sent directly to the GMA Audio Panel.

Figure 2-5, GDL 69A SXM Datalink



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GTS 800 Traffic System

The GTS 8X0 is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode C transponders to provide Traffic Advisories to the pilot.

Traffic is displayed on the MFD via Ethernet High Speed Data Bus (HSDB). An aural alert is also provided to inform the crew a traffic advisory (TA) will be displayed.

The installation includes a top GA58 directional antenna and a bottom GA 58 directional antenna. The GTS 800 is located in the tail avionics compartment. The GTS 800 traffic system is powered from the Right Avionics bus.

Figure 2-6 GTS 800 Traffic System Processor

GSA 81 Servo Actuator and GSM 86 Servo Gearbox

The Garmin GSA 81 Servo Actuators are electromechanical units that provides the autopilot control for pitch, pitch trim, roll and yaw. The GSM 86 Servo Gearboxes are attached to a mount bracket and are responsible for transferring the output torque of the GSA 81 servo actuators to the mechanical flight control surface linkage.

Figure 2-7, GSA 81 Servo Actuator, GSM 86 Servo Gearbox

The installation of these units supports Electronic Stability Protection (ESP) and Under Speed

Protection (USP) features. ESP works to assist the pilot in maintaining the aircraft in a stable flight condition. When autopilot is not engaged, ESP helps avoid inadvertent flight attitudes and provide airspeed protection while the pilot is hand-flying the aircraft. The USP feature will correct for slow airspeeds while the autopilot is engaged. USP will lower the nose of the aircraft to maintain an airspeed that prevents the aircraft from stalling.



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GMA 1360 Audio Panel

The GMA 1360 audio panel integrates NAV/COM digital audio, intercom system and marker beacon controls. Manual display reversion mode (red DISPLAY BACKUP button) for the PFD and MFD is controlled by the GMA.

Figure 2-8, GMA 1360 Audio Panel

GIA 64W Integrated Avionics Unit

The GIA 64W functions as the main communication hub to the G1000 system linking LRUs with the PFD and MFD displays. The GIA 64 contains the GPS/WAAS receiver, VHF COM/NAV receivers, and system integration microprocessors.

Figure 2-

9

, GIA 64W Integrated Avionics Unit



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GEA 71B Engine Airframe Unit

The GEA 71B Engine/Airframe unit receives and processes signals from engine sensors.

Communication interface is to the GIA via RS-485.

Figure 2-10, GEA 71B Engine Airframe Unit

GSR 56 Satellite Transceiver

The GSR 56 provides airborne low speed data link and voice communication capability. The

GSR 56 contains a transceiver that operates on the Iridium Satellite network. The GSR 56 interfaces directly to the GIA.

Figure 2-11, GSR 56 Satellite Transceiver

GWX 75 Weather Radar

The GWX 75 Airborne Weather Radar provides weather radar data output to the PFD and MFD.

The GWX is mounted forward of the forward bulkhead under the nose cone.

Figure 2-12, GWX 75 Weather Radar



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2.2 G1000 Optional Interfaces

There are no new optional interfaces approved as part of this STC. Refer to the existing G36 or

G58 Avionics Manuals listed in section 1.1 for optional interfaces.

2.3 Electrical Power Distribution

The electrical power distribution has not changed as a result of this STC. Refer to the G36 or

G58 Wiring Manuals listed in section 1.1 for power distribution.

The layout of the pitot/static system has not changed as a result of this STC.

2.5 GDU 1050 and GDU 1055 Displays

The location and function of the controls on the GDU 1050 (PFD) and GDU 1055 (MFD) displays are unchanged from those described for the GDU 1040 and GDU 1043 in the G36 and

G58 Avionics Manuals listed in section 1.1.

2.6 Softkeys

Some pages have commands or selections that are activated by the GDU 1050 or GDU 1055 softkeys. If a softkey is associated with a command, that command will be displayed directly above the key. A grayed-out softkey shows a command that is unavailable. A softkey that is highlighted (green bar) shows the current active selection.

Figure 2-13, G1000 Softkeys

The FMS knob is the primary control for the G1000 system.

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 again, deactivating the cursor. The

CLR

key may also be used to cancel a selection or deactivate the cursor.



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2.8 G1000 Normal Mode

To start the G1000 system in Normal Mode:

1. With a ground power unit connected to the external power receptacle, turn ON the L

BAT MASTER and R BAT MASTER switches. The following G1000 equipment is powered on:



PFD



GRS 79 AHRS



GDC 72 ADC



GIA #1 (NAV and COM)



GEA Engine/Airframe Unit (G36 Only)



GEA #1 Engine/Airframe Unit (G58 Only)



GEA #2 Engine/Airframe Unit (G58 Only)



GTX

2. Turn ON the AVIONICS Master switch. The following G1000 equipment is powered on:



MFD



GTS 800 Traffic System (if installed)



GIA #2 (NAV and COM)



GMA Audio Panel



GSA Servos



Radar Only)



GDL 69A (if installed)



GSR 56 (if installed)



GWX 75 (if installed)

The G1000 system is now powered in the normal mode. In the normal operating mode, data fields that are invalid have large red X’s through them. A valid field does not display a red X.

Allow the displays to initialize for approximately one minute for the red X’s to be removed.

The PFD and MFD will function as specified in the G1000 Cockpit Reference Guide when the system has been correctly installed and configured.

Figure 2-14, Normal Mode



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Reversionary mode allows for display of information related to safe flight in the event of a display communication or hardware failure. The PFD automatically goes into reversionary mode when communication to the MFD is lost. Manual reversionary mode allows the operator to force the PFD and MFD into reversionary mode by pressing the large red button labeled

‘DISPLAY BACKUP’ on the GMA audio panel.

NOTE

When the ‘DISPLAY BACKUP’ button is pushed to exit reversionary mode, there is a 5-second delay until the display returns to normal mode. If the ‘DISPLAY

BACKUP’ button is pushed again during this 5-second delay, the display will reset the five second delay timer.

Figure 2-15, Automatic Reversion with MFD failure



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3. Software and Configuration

3.1 Configuration Mode Overview

Throughout this document, references are made to the PFD and/or MFD being in configuration mode. The configuration mode exists to provide the avionics technician with a means of configuring, checking, and calibrating various G1000 sub-systems. Troubleshooting and diagnostics information can also be viewed in this mode.

To start the G1000 system in configuration mode, follow these steps:

1. Apply power to the G1000 system by applying aircraft EXT power, selecting the L BAT

MASTER, R BAT MASTER, and AVIONICS MASTER switches to ON.

2. Pull the MFD and PFD circuit breakers.

3. Press and hold the ENT key on the MFD while applying power using the MFD circuit breaker.

4. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the MFD.

5. Press and hold the ENT key on the PFD while applying power using the PFD circuit breaker.

6. Release the ENT key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the PFD.

CAUTION:

Configuration Mode contains certain pages and settings that are critical to aircraft operation and safety. These pages are protected and cannot be modified, unless the technician is properly authorized and equipped. However, most protected pages are viewable to allow system awareness for troubleshooting.

NOTES

If the specific procedure requires an SD card to be in the top slot of the PFD/MFD, this card must be inserted prior to applying power to the PFD/MFD. Any time a card is inserted, the power to the PFD/MFD must be cycled.

For a complete description and breakdown of each Configuration Mode page, refer to the G1000 System Maintenance Manual listed in Table 1-2.

Throughout the configuration mode pages, there are SET and ACTIVE columns for input/output settings and other parameters.

SET:

Refers to a setting or group of settings that reside in PFD Internal Memory and/or the

Master Configuration Module.

ACTIVE:

Refers to an ‘active’ setting or parameter currently being used by the LRU. LRUs store the ‘active’ settings within internal memory.

Data can be manually copied from one column to the other (and consequently from PFD memory to the LRU memory and vice-versa) by using the following two softkeys, when available:



SET>ACTV (read ‘Set to Active’) softkey: Allows the installer to send the information in the SET column (data stored in the master config module) to the ACTV column (data used by LRU).



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

ACTV>SET (read ‘Active to Set’) softkey: Causes the LRUs current settings to be copied to the master configuration module as SET items.

CAUTION:

The ACTV>SET softkey must be used with caution! If an improperly configured unit is installed, this softkey causes the wrong configuration to replace the correct aircraft configuration.

In the first example shown in Figure 3-1 the SET columns do not match the ACTIVE columns. The inequality between SET and ACTIVE indicates a configuration mismatch.

By pressing the SET>ACTV softkey, this copies the SET column to the LRU unit’s configuration memory. The settings then become the ACTIVE settings for the LRU being configured.

Figure 3-1, SET>ACTV Diagram

When troubleshooting the system, technicians can look for inequalities between SET and

ACTIVE columns. Certain problems can be resolved simply by pressing the SET>ACTV softkey, which reloads settings to the specific LRU from the PFD. (Note that this can also be accomplished by reloading the configuration files for the LRU. Section 7 describes this process for each LRU).



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A blank active column, as shown in Figure 3-2, represents loss of communication between the display and the particular unit. See Section 5 for more details on troubleshooting.

Figure 3-2, Loss of Communication

When configuration settings are changed, the technician receives on-screen prompts and/or confirmations such as those shown in Figure 3-3.

Figure 3-3, Configuration Status

Data Transmission Indicators

Several configuration screens utilize an indicator light system to show discrete (ON/OFF) data and/or hardware component status. Unless otherwise noted, the following applies to all such status indicators:



Green Checkmark: Expected data is successfully received and is ON. A green check could also indicate that the parameter/component is working correctly.



Red X: Expected data is not received. A red X could also indicate that a parameter/component is invalid.



White N/A: Expected data is OFF, or no data is expected.

Figure 3-4, Data Transmission Indicators



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Configuration Mode Navigation

Using the FMS knob as described in Section 2.7, a user can navigate through different pages and page groups in the Configuration Mode. For complete description and breakdown of each page, refer to the G1000 System Maintenance Manual listed in Table 1-2. Pages below will be shown only for the units/options installed on the aircraft.

System Page Group

1. System Status

2. Time Configuration

3. Lighting Configuration

4. System Audio

5. System Upload

6. LRU Replacement

7. Transaction Log

8. Aircraft Configuration

9. Diagnostics Terminal

10. OEM Diagnostics

11. System Configuration

12. System Data Path

Configuration

13. System Setup

14. Manifest Configuration

15. Log Utilities

16. Configuration Manager

GDU Page Group

1. Serial Configuration

2. CDU Status Page

3. Key Test

6. Diagnostics

7. Ethernet Test

8. Video Test

11. Airframe Configuration

12. TAWS Configuration

13. SurfaceWatch

Configuration

14. Connext Connections 4. FS 510 Test

5. CDU Calibration

9. Alert Configuration

10. DAT Configuration

GIA Page Group

(for GIA 63W only)

1. Serial Configuration 3. GIA I/O Configuration

2. GIA RS-485 Configuration 4. GIA COM Setup Page

GIA 64x Page Group

(for GIA 64W only)

1. ARINC Configuration 5. GFC Status

2. CAN Configuration

3. COM Calibration

6. COM Status

7. GFC Configuration

5. GIA Status Page

6. GIA CAN Configuration

9. IO Configuration

10. NAV Status

11. Serial Configuration

GEA Page Group

(for GEA 71 only)

1. Engine Configuration 2. GEA Status Page

GEA 71x Page Group

(for GEA 71B only)

1. Engine Configuration 4. Digital In

2. Analog In

3. Annunciate Out

5. Discrete In

6. Excitation

GTX Page Group

(for GTX 33 only)

1. Serial Configuration 2. Transponder Configuration

GTX 3X5 Page Group

(for GTX 335R, GTX 345R only)

1. Transponder Airframe Config 2. Transponder Diagnostics

GRS Page Group

1. Inputs Configuration

2. GRS / GMU Calibration

ADC Page Group

1. ADC Configuration

3. GRS Flight Data Log



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7. GEA Status

8. XVDT In

9. XVDT Out

3. Transponder Wiring Config

4. GRS 79 Flight Log Download

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GFC Page Group

1. GFC Configuration 2. GFC Status

GMA Page Group

(for GMA 1347 only)

1. GMA Configuration

GMA x36x Page Group

(for GMA 1360 only)

1. GMA Discrete In 5. GMA Misc

2. GMA Discrete Out 6. GMA Noise

3. GMA Fast Volume

Configuration

4. GMA Marker

7. GMA Options

GDL Page Group

1. GDL 69 Configuration

8. GMA Squelch

2. GSR 56 Configuration

GWX Page Group

1. GWX Configuration

GTS Page Group

1. GTS Configuration

OTHER Page Group

1. Stormscope

CAL Page Group

1. Fuel Tank Calibration

2. Flaps & Trim Calibration

3. HSCM Calibration

4. DAT Calibration

9. GMA Status

10. GMA Volume



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G1000 System Software Information

NOTE

The following sections provide a detailed description of loading all G1000 software and configuration files, which may be excessive for individual LRU removal and replacement. If removing and replacing individual LRUs, refer to Section 6 of this manual for the necessary steps.

G1000 Software Image

All software and configuration files were certified by Garmin and are considered part of FAAapproved Type Design data. Approved software and hardware definitions for each STC

Configuration are defined on the appropriate General Arrangement drawing listed in Table 1-1.

G1000 software and configuration files are controlled via the approved software image part number listed on the General Arrangement drawing listed in Table 1-1. This software image is loaded into the G1000 using a software loader card. The installer shall create this software loader card by downloading the approved software image in accordance with Section 3.1.6.

NOTE

Only SanDisk brand SD cards are recommended for use with the G1000 system.

Other brand cards have not been tested by Garmin.

NOTE

Installers may obtain the software image already on a loader card by ordering

Garmin part number 010-02126-XX directly from Garmin. Reference the General

Arrangement drawing 005-00620-41 for loader card part number information.

IMPORTANT!

To satisfy the G1000/GFC700 STC requirements for the G36/G58 aircraft, it is critical that the technician install correct software image part number when servicing the G1000 system.

Approved software image part numbers are defined on the appropriate

General Arrangement drawing (see Table 1-1).

CAUTION:

Be cautious when using software loader cards during maintenance. The G1000 system immediately initializes the card upon power-up. On-screen prompts must be given careful attention in order to avoid potential loss of data. Always read through procedures given in this manual before attempting to use the software loader cards.



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Loader Card Creation

The software image is an executable self-extracting file which builds the correct file structure onto an SD card for use loading software to the G1000 System. To obtain the current file follow the procedures outlined below.

NOTE

In order to create a Textron G36/G58 system loader card, the installer completing these procedures must be an authorized Garmin Service

Center to gain access to the necessary data via the Garmin website.

1. Go to and click on the Dealer Resource Center link in the lower portion of the home page. Enter your Garmin Dealer username and password.

2. Select button then select

Software Downloads

.



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3. In the tab, type Beechcraft in the

Product Name or Part Number

box, then select the appropriate system and then press the

Search

button.

4. A screen similar to the one shown below will appear. The numbers shown are for example only.

5.

Click

on the

Select Action

button for the appropriate software image part number as shown on the Garmin General Arrangement drawing 005-00620-41 and choose

Download

to save the software file to the local hard drive.

6. After the file is downloaded, close the web browser.

7. Insert a blank (empty) SD card in the card reader. The loader card program will delete all files on the SD card before loading G1000 system software files on it if the card is not blank.

8.

Double-click

the .exe file that was downloaded onto the local hard drive. The following window will pop-up on the screen. Click

Yes

to continue.



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9. Follow the on screen prompts to continue.



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10. Check the “I accept the terms of the License Agreement” checkbox.

11. Select the SD card reader drive and click Next>.



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12. Follow the on screen prompts to continue.

13. The program will make the SD loader card and prompt you when it’s done.



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14. Once successfully completed, the following window will display. Click Finish to close the program. The SD card can then be removed from the computer and is ready for use in the aircraft.



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Software files are defined by part number and version number on the General Arrangement drawing. Each G1000 system LRU reports the software version it currently contains to the user in two places.



Normal System Mode: The

Aux – System Status

page lists each LRU and the reported software version.



Configuration Mode: The

System Status

page (System page group) reports more detailed LRU information, including software version, part number, and LRU status.

Software files are loaded to LRUs from the PFD System Upload page in configuration mode.

Configuration File Descriptions

There are configuration files for baseline settings and various options. Configuration files contain preset selections for input/output channels, aircraft-specific settings, and LRU-specific settings.

IMPORTANT!

Certain software and configuration files are REQUIRED to be re-loaded during maintenance that involves removal and replacement of G1000 equipment.

Refer to Section 7 for re-configuration requirements for each individual

G1000 LRU. Pay special attention to the selection of option files for the units to assure a complete load.



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Configuration File Storage

The storage of G1000 system configuration files is unchanged from that depicted in the applicable Maintenance Manual, except as noted in Figure 3-5 for the GRS 79 and the GDC 72.

The GDC 72 ADC air data configuration file is loaded directly to GDC 72 internal memory. A copy of the file is stored in the GDC 72 configuration module. The GRS 79 stores AHRS calibration data acquired during the post installation checkout, which is characteristic to the specific installation. A copy of this calibration data is stored in the GRS configuration module.

While performing maintenance on this unit, re-calibration may be required. See Section 7.11 for more information on re-calibration criteria.

GRS 79 Config Module

(located in GRS connector backshell)

GDC 72 Config Module

(located in GDC connector backshell)

Stores a copy of the AHRS/ magnetometer calibration that are recorded upon completion of postinstallation calibration procedures.

Stores a copy of the Air Data configurationfile.

GRS 79 AHRS

The GRS stores calibration and configuration file internally.

The GRS 79 also stores factory calibration internally.

Should internal memory or the configuration module fail, AHRS output data is flagged as invalid .

GDC 72 ADC

The GRS stores calibration and configuration file internally.

The GDC 72 also stores factory calibration internally.

Should internal memory or the configuration module fail, loss of some or all air data outputs will result .

GRS 79 Internal Memory

Contains internal sensor calibration data that is not installation-specific .

Data is stored from factory calibrations .

GDC 72 Internal Memory

Contains internal sensor calibration data that is not installation-specific .

Data is stored from factory calibrations .

Figure 3-5, GRS and GDC Configuration Settings Storage



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Throughout this document, references are made to the PFD and/or MFD being in configuration mode. To start the G1000 system in configuration mode, follow these steps:

1. With the G1000 system off, open the MFD and PFD circuit breakers.

2. Connect external power to the aircraft and energize the aircraft and avionics electrical busses.

3. Press and hold the

ENT

key on the MFD and close the MFD circuit breaker.

4. Release the key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the MFD.


ENT

key on the PFD and close the PFD circuit breaker.

6. Release the key after ‘INITIALIZING SYSTEM’ appears in the upper left corner of the PFD.

3.3 G1000 Hardware/Software Compatibility Check

Before installing software, the technician must first ensure that hardware part numbers are compatible with the G1000 system software image that is to be used. The General

Arrangement drawing shows all available combinations of hardware and software part numbers.

A G1000 system loader card is required to install software and configuration settings to a newly installed G1000 system. The part number of the software image used to create the loader card is directly associated with the combination of software file part numbers and version levels that are defined on the General Arrangement drawing. Should software part numbers or versions change, a new software image part number is issued.

IMPORTANT

After verifying hardware/loader card compatibility, record the software image part number and all LRU hardware part numbers in the appropriate aircraft records before proceeding.

NOTE

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.

3.4 Equipment Verification (Third Party/Optional Equipment Documentation)

It is extremely important to know exactly what equipment the aircraft is equipped with before loading any files. Loading the incorrect files could lead to longer down time and unplanned removal of equipment.



Garmin optional equipment (i.e. GDC 74 ADC, GRS 77 AHRS, GRS 79 AHRS, or GDC

72 ADC, GTX 33 or GTX 3X5R, GSR 56, etc.). Section 3.4.1 helps find which units are installed without a physical inspection.



Third party avionics equipment interfaced to G1000 (DME, non-Garmin traffic systems,

WX-500, etc.). To determine if the third party equipment is installed, check the circuit



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breaker panel for circuit breakers for the units, and check for G1000 controls for the third party devices.

Determining Installed Garmin Units

Use the table in Appendix A to determine what the unit part number is based on the unit’s serial number reported on the MFD Aux - System Status page in Normal mode or PFD System Status page in Config mode. The table lists the units that have different loader card option files so the installer can choose the correct file without requiring the unit to be physically inspected.

Figure 3-6, Garmin Unit S/N Location



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3.5 G1000 Software/Configuration Procedure

This section summarizes the procedures required to load software and configuration files to the

G1000. It is intended to work as a central guide for technicians to use while performing maintenance on the aircraft. In sections of this manual where software is required to be reloaded, these sections will make reference back to this section for instructions. The technician should use proper judgment regarding the context of maintenance required while following this section.

The following diagram depicts an overview of the software/configuration sequence for the

G1000 system. This applies mostly to a new G1000 system software installation by Service

Bulletin and is for informative purposes only.

Figure 3-7, Software/Configuration Overview



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3.6 System Software and Configuration Load

System Power Up

Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.

DO NOT RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A

BATTERY CHARGER AS AN EXTERNAL POWER SOURCE DUE TO ELECTRICAL

NOISE IT MAY INJECT IN THE G1000 SYSTEM.

Power loss during a software upgrade may cause a LRU to become corrupted and unresponsive requiring replacement. Remove power only when told to do so in the procedure.

MFD & PFD Software Load

1. Open the MFD and PFD circuit breakers.

2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of PFD and MFD if present.

3. Insert the software loader card into the PFD top card slot.

4. Turn on Avionics/electrical busses.


ENT

key on the PFD.

6. Close the PFD circuit breaker.

7. When the “DO YOU WANT TO UPDATE SYSTEM FILES?” prompt appears, release the

ENT

key, then press the

YES

softkey.

8. After the new GDU software is loaded to the PFD, a “DO YOU WANT TO UPDATE THE

SPLASH SCREEN?” prompt may appear. If it does, press the

NO

softkey. The splash screen will be loaded later in this procedure.

9. When complete, the PFD starts in configuration mode displaying the “System Status” page.

10. Start the MFD in configuration mode by pressing and holding the

ENT

key when closing the circuit breaker. Release the key when the words “INITIALIZING SYSTEM” appear on the screen.



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Baseline Software and Configuration Load

IMPORTANT

If the aircraft being modified has incorporated any modifications beyond factory configuration that effect engine or airspeed limitations, your configuration may not be supported at this time. It is the responsibility of the installer to ensure compatibility with existing modifications.

Do not allow power to be removed from the system when loading software.

Remove power only when instructed by the following procedures.

Unless instructed otherwise, all displays should be in the same mode

(configuration or normal).

Follow the order of software and configuration loading, do not skip or rearrange steps.

Do not operate or turn off MFD while loading software and configuration files unless specifically instructed to do so. A failed or cancelled load may result.

If an incorrect configuration file is loaded at any time during this procedure,

STOP and start the configuration load over.

1. Ensure all avionics circuit breakers are closed and the G1000 system is fully powered.

2. On the PFD, go to the SYSTEM UPLOAD page using the small FMS knob.

3. Push in the PFD FMS knob to activate the cursor in the Group field. Rotate the small

FMS knob to activate the drop-down menu. Rotate the small FMS knob to highlight the applicable airframe. Select Beechcraft Gxx (G36 if using the G36 loader card, G58 if using the G58 loader card). Press the

ENT

key to select it.

4. If an airframe type was selected that does not match the previously configured airframe type, a popup similar to the one shown in Figure 3-8 will appear. Select “NO” by pressing the “NO” softkey at the bottom of the screen. Return to the previous step and select the correct airframe type in the Airframe Group selection.

Figure 3-8, Airframe Change Confirmation



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5. Once the appropriate airframe option is selected, the cursor moves to the ITEM window.

Rotate the small FMS knob to activate the drop-down menu. Highlight

“Beechcraft G58

– Baseline Configuration” or “Beechcraft G36 – Baseline Configuration ”

(as applicable to the airframe and press the

ENT

key to select it. The PRODUCT field will then populate.

NOTES

The PRODUCT window displays information regarding each G1000 LRU. The

LRU column depicts the reported software version of the LRU (may be blank if

PFD cannot communicate with the unit yet until after config files are loaded).

The CARD VERS column shows the LRU software version stored on the Loader

Card.

The SOFTWARE column may or may not have all boxes checked automatically.

For the initial software load in the system all software boxes should be checked to load all files. This is done by pressing the CHK ALL softkey when instructed below.

The CONFIGURATION column defaults to having all unit configuration boxes checked.

The hardware serial number is used to determine appropriate software for the

GIA COM, GIA NAV, GMU 44, and GSA 8X units. Until the system configuration loads sufficiently to access and read these units, they may show a

“INV” invalid status under the LRU VERS and CARD VERS columns with up to two line items per item (representing different hardware configurations). After the configuration files are loaded, the units will update and remove the “INV” status and will load automatically.

6. Press the softkey.


8. Monitor the loading progress and verify the software load completes without errors as indicated by the following:



Green “PASS” or White “N/A” in all Configuration and Software columns.



“Upload Complete………….COMPLETE” in the summary box.

9. Press the key to acknowledge the prompt that appears in the pop-up box..



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GRS 79 and GDC 72 Software/Configuration Loading (if installed)

Follow this procedure to configure the GRS 79 AHRS and GDC 72 ADC. Do not follow the procedures in this section if a GRS 79 is not installed.

Move the cursor to the Item window and rotate FMS inner knob to display drop down menu. Highlight

“Baseline Option – GRS79 and GDC 72 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.

Monitor the loading progress and verify the software load completes without errors as indicated by the following:



Green “PASS” or White “N/A” in all Configuration and Software columns.




Press the key to acknowledge the prompt that appears in the pop-up box.

GTX 335 Transponder Software/Configuration Loading (if installed)

Follow this procedure to configure the GTX 335 transponder in the aircraft. Do not follow the procedures in this section if a GTX 335 is not installed in the aircraft.


“Baseline Option – GTX 335 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.




Green “PASS” in the Configuration and Software columns for each item loaded.







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GTX 345 without GTS 8XX Transponder Software/Configuration Loading (if installed)

Follow this procedure to configure the GTX 345 transponder in the aircraft. Do not follow the procedures in this section if a GTX 345 is not installed in the aircraft or if a GTS 8XX Traffic

Sensor is installed.


“Baseline Option – GTX 345 without GTS 8XX Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









GTX 345 with GTS 8XX Transponder Software/Configuration Loading (if installed)

Follow this procedure to configure the GTX 345 transponder in the aircraft. Do not follow the procedures in this section if a GTX 345 is not installed in the aircraft or if a GTS 8XX Traffic

Sensor is not installed.


“Baseline Option – GTX 345 with GTS 8XX Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GDL 69A SXM Software/Configuration Loading (if installed)

Follow this procedure to configure the GDL 69A SXM Receiver. Do not follow the procedures in this section if a GDL69A SXM unit is not installed.

Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select

“Baseline

Option – GDL69A SXM Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









GTS 800 without GTX 345 Software/Configuration Loading (if installed)

Follow this procedure to configure the GTS 800 Traffic System in aircraft that do not have a

GTX 345 Transponder installed. Do not follow the procedures in this section if the aircraft is not equipped with GTS 800 or if the aircraft has a GTX 345 Transponder installed.

NOTE

Configuration of the GTS Processor will require entering the aircraft registration number into the unit using Section 3.8 “Aircraft Registration

Number Entry”.


“Option – GTS

800 without GTX 345 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GTS 800 with GTX 345 Software/Configuration Loading (if installed)

Follow this procedure to configure the GTS 800 Traffic System in aircraft that also have a GTX

345 Transponder. Do not follow the procedures in this section if the aircraft is not equipped with

GTS 800 or if it does not have a GTX 345 Transponder

NOTE


Number Entry”.


“Option – GTS

800 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









KN63 DME Configuration Loading (if installed)

Follow this procedure to configure the system to use the KN 63 DME. Do not follow the procedures in this section if the aircraft is not equipped with a KN 63.


“Option – KN63

DME Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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WX500 Configuration Loading (if installed)

Follow this procedure to configure the system to utilize the WX 500. Do not follow the procedures in this section if the aircraft is not equipped with WX500.


“Option –

WX500 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









SKY497 Skywatch Configuration Loading (if installed)

Follow this procedure to configure the system to use the SKY497 Skywatch. Do not follow the procedures in this section if the aircraft is not equipped with a SKY497.


“Option –

SKY497 Skywatch Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GRS 77 Software/Configuration Loading (if installed)

Follow this procedure to configure the system for GRS 77 AHRS. Do not follow the procedures in this section if the aircraft is not equipped with the GRS 77.


“Baseline

Option – Legacy – GRS77 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









GDC 74 Software/Configuration Loading (if installed)

Follow this procedure to configure the system for GDC 74 ADC. Do not follow the procedures in this section if the aircraft is not equipped with the GDC 74.


“Baseline

Option – Legacy – GDC74 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GTX 33 ES Software/Configuration Loading (if installed)

Follow this procedure to configure the system to use a GTX 33 ES Transponder. Do not follow the procedures in this section if the aircraft is not equipped with a GTX 33 ES.


“Baseline

Option – Legacy – GTX 33ES Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









GDL 69 Software/Configuration Loading (if installed)

Follow this procedure to configure the GDL 69 Receiver. Do not follow the procedures in this section if a GDL69 unit is not installed.


“Baseline

Option – Legacy – GDL 69 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GTS 820 without GTX 345 Software/Configuration Loading (if installed)

Follow this procedure to configure the GTS 820 Traffic System in the aircraft in those aircraft that have a GTS 820 without a GTX 345 installed. Do not follow the procedures in this section if the aircraft is not equipped with GTS 820 or if the aircraft has a GTS 820 and a GTX 345.

NOTE


Number Entry”.


“Baseline

Option – Legacy – GTS 820 without GTX 345 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GTS 820 with GTX 345 Software/Configuration Loading (if installed)

Follow this procedure to configure the GTS 820 Traffic System in the aircraft in those aircraft that have a GTS 820 with a GTX 345 installed. Do not follow the procedures in this section if the aircraft is not equipped with GTS 820 or if the aircraft has a GTS 820 and does not have a

GTX 345.

NOTE


Number Entry”.


“Baseline

Option – Legacy – GTS 820 with GTX 345 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.









GMA 1360 Software/Configuration Loading

Follow this procedure to configure the GMA 1360 Audio panel.


“Baseline

Option – GMA 1360 Installation”

and press the

ENT

key to select it.

Press the softkey.

Press the softkey.











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GWX 75 Weather Radar Software/Configuration Loading

Follow this procedure to configure the GWX 75 Weather Radar.

1. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select

“Baseline Option –

GWX 75 Installation”

and press the

ENT

key to select it.










1. Press the key to acknowledge the prompt that appears in the pop-up box.

GFC 700 Software/Configuration Loading (if installed)

Follow this procedure to configure the GFC 700 Autopilot with GIA 64.


“Baseline

Option – GFC 700 with GIA 64 Installation”

and press the

ENT

key to select it.










5. Press the ENT key to acknowledge the prompt that appears in the pop-up box.

Enhanced GFC 700 Software/Configuration Loading (if installed)

Follow this procedure to configure the GFC 700 Enhanced Autopilot with GIA 64. Do not follow the procedures in this section if the aircraft is not equipped with GFC 700.

1. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “

Baseline

Option – GFC 700 with GIA 64 E-AFCS Installation

” and press the

ENT

key to select it.













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Flight Stream 510 Configuration Loading (if installed)

Follow this procedure to configure the system to use the FS 510 WiFi/Bluetooth datalink. Do not follow the procedures in this section if the aircraft is not equipped with a FS 510.

1. Rotate the large FMS knob until the Item field is highlighted, rotate the small FMS knob to activate the drop down menu. Rotate the small FMS knob and select “

Option –

Enable FS510

” and press the

ENT

key to select it.






Green “PASS” in the Configuration column for each item loaded.





GSR 56 loading (if installed)

Follow this procedure to load the GSR 56 satellite phone/text/weather datalink transceiver. Do not follow the procedures in this section if the aircraft is not equipped with a GSR 56.


“Option – GSR

56 Installation”

and press the

ENT

key to select it.













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This section describes how to unlock or enable optional features. The installer will only load the sections for the features they require. For installing all feature enablement cards, the PFD and the MFD must be in configuration mode.

The G1000 has various features that require the use of unlock/enable cards to activate the feature. Throughout this document these cards are generically referred to as ‘enablement cards’. In some cases, the actual label on the physical card may say ‘unlock’.

If uncertain what SD Card to use, the technician must verify the card part number on the

General Arrangement drawing prior to use to assure the correct feature is unlocked.

Follow this procedure to activate Jeppesen ChartView. Enabling this feature, allows the pilot to switch between Garmin FliteCharts and Jeppesen ChartView products.

NOTES

The required ChartView databases are subscription-based and need to be procured by the installing agency from the Garmin or Jeppesen website. The

ChartView database is not present in a new display.

Insert the ChartView Enablement card in the top slot of the PFD and power on the PFD in configuration mode.

If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10

On the PFD, select the

“System Upload”

page using the small FMS knob.

Push in the FMS knob to activate the cursor in the Group field. Rotate the small FMS knob to highlight “

Configuration Files

” and press the

ENT

key to select it.

In the ITEM window, rotate the small FMS knob to highlight “

Enable ChartView

” and press the

ENT

key to select it.

Press the softkey.

Monitor load progress. Verify software load completes without errors as indicated by the following:








Open the PFD circuit breakers and remove the ChartView enablement card.



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Synthetic Vision System Enablement

Follow this procedure to enable the Synthetic Vision feature.

Insert the SVS Enablement card in the top slot of the PFD and power on the PFD in configuration mode.

If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.10.






” and press the

ENT

key to select it.


Enable SVS Single PFD

” and press the

ENT

key to select it.

Press the softkey.









Open the PFD circuit breakers and remove SVS enablement card.

Follow this procedure to enable the SurfaceWatch feature.

Insert the SurfaceWatch Enablement card in the top slot of the PFD and power on the

PFD in configuration mode.


On PFD, select the




Enable_SurfaceWatch

” and press the

ENT

key to select it.


SurfaceWatch Feature

Enable

” and press the

ENT

key to select it.

Press the softkey.









Open PFD circuit breaker and remove the SurfaceWatch enablement card.



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Follow this procedure to enable the TAWS-B feature.

Insert the TAWS-B Enablement card in the top slot of the PFD, power on the PFD in configuration mode.







” and press the

ENT

key to select it.


Enable TAWS

” and press the

ENT

key to select it.

Press the softkey.









Open the PFD circuit breaker and remove TAWS-B enablement card.

Enhanced AFCS Enablement

Follow this procedure to enable the Enhanced AFCS feature.

1. Insert the Enhanced AFCS Enablement card in the top slot of the PFD, power on PFD in configuration mode.

2. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.7.

3. On the PFD, select the



4. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS knob to highlight “

Enhanced AFCS

” and press the

ENT

key to select it.

5. In the ITEM window, rotate the small FMS knob to highlight “

Enable Enhanced AFCS

” and press the

ENT

key to select it.


7. Monitor load progress. Verify software load completes without errors as indicated by the following:








9. Open the PFD circuit breaker and remove the Enhanced AFCS enablement card.



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GWX 75 Ground Clutter Suppression and Turbulence Detection Enablement

Follow this procedure to enable the Ground Clutter Suppression and Turbulence Detection feature.

1. Insert the Enhanced AFCS Enablement card in the top slot of the PFD, power on PFD in configuration mode.

2. If a message appears on the PFD stating an “arfrm_imgs.zip” file is not present, follow the on screen instructions to continue. This file will be loaded in Section 3.7.

3. On the PFD, select the



4. Push in the FMS knob to activate the curser in the Group field. Rotate the small FMS knob to highlight “

Enable_TD_GCS

” and press the

ENT

key to select it.

5. In the ITEM window, rotate the small FMS knob to highlight “

Doppler, TD, GCS

Enablement

” and press the

ENT

key to select it.










9. Open the PFD circuit breaker and remove the Enhanced AFCS enablement card.



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3.8 Aircraft Registration Number Entry and Flight ID Configuration

NOTE

Steps to complete the aircraft registration entry and Flight ID configuration are dependent on transponder equipment installed. Choose the appropriate procedure from Section 3.8.1 or 0 to complete the aircraft registration entry.

Aircraft Equipped with GTX 33

Aircraft Registration Number Entry

Place the PFD in configuration mode, if not already there. Select the

AIRCRAFT

CONFIGURATION

page on the PFD.

Activate the cursor to select the”

AIRCRAFT REGISTRATION

” field and enter the aircraft’s tail number.

If the ICAO Address field does not auto-fill, rotate the large FMS knob to select the

“ICAO ADDRESS”

and enter the aircraft’s 24 bit ICAO address.

If applicable, rotate the large FMS knob to select the

“ICAO REGION”

field and select the appropriate ICAO region.


“DOMAIN IDENTIFIER

” field and enter the number. Press the ENT key to save. Otherwise, leave blank.

Rotate the large FMS knob to select the “

VFR CODE

” field and enter the desired code that will become active when the VFR key on the GDU is pressed.

Press the softkey and acknowledge the PFD prompt by pressing the

ENT

key.

Press the softkey (if present) and acknowledge the PFD prompt by pressing the

ENT

key.

After completing transponder configuration, deactivate the cursor.

Flight ID Configuration

1. Select the Group and the

TRANSPONDER CONFIGURATION

page on the PFD.

2. Activate the cursor and select the

“FLIGHT ID TYPE”

field.

3. Rotate the small FMS knob to activate the drop-down menu.

4. Select and press the

ENT

key.

5. After completing transponder configuration, deactivate the cursor.



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Aircraft Equipped with GTX 335 or GTX 345

Aircraft Registration Number Entry

Insert the software loader card into the top slot of the PFD.

Place the PFD in configuration mode.

Press the softkey (number 11 softkey) to acknowledge the following prompt.

Rotate the small FMS knob, select the

AIRCRAFT CONFIGURATION

page on PFD.

Activate the cursor to select the

“AIRCRAFT REGISTRATION

” field and enter the aircraft’s tail number.

If the ICAO Address field does not auto-fill, rotate the large FMS knob to select the

“ICAO ADDRESS”

and enter the aircraft’s 24 bit ICAO address.


“ICAO REGION”

field and select the appropriate ICAO region.


“DOMAIN IDENTIFIER

” field and enter the number. Press the ENT key to save. Otherwise, leave blank

Rotate the large FMS knob to select the “

VFR CODE

” field and enter the desired code that will become active when the VFR key on the GDU is pressed.

Press the

SET GTS

softkey (if present) and acknowledge the prompt by pressing the

ENT

key.

Deactivate the cursor.

Rotate large FMS knob to select

“GTX 3X5.”

Rotate the small FMS knob to select “

Transponder Airframe Configuration

” page.

Verify the GTX1 box at the top of the page is green and the tail number, ICAO address,

IATA Airline Designator, and VFR code that were entered previously are correct.

Flight ID Configuration

1. Select the Group and the

Transponder Airframe Config

page on the PFD.

2. Activate the cursor and select the

“Allow Flight ID Entry”

field.

3. Rotate the small FMS knob to activate the drop-down menu.

4. Select and press the

ENT

key.

5. Scroll Down to highlight

“SET > ACTIVE”

and press the

ENT

key.




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NOTE

All items listed in the Configuration Manager will display “Valid” in the

Status column, with the exception of the GSR 56 (if installed). The GSR

56 will display “Status not supported” in the Status column.

Rotate the large FMS knob to select “

SYSTEM

”.

Rotate the small FMS knob to select Configuration Manager page on PFD.

Press the softkey labelled CNFM CFG on PFD.

Press the key on PFD to select OK when prompted to confirm configuration as expected configuration.

Verify the fleet, aircraft expected and actual configuration IDs match.

If they do not match, repeat steps 2-4. If they match, continue to next step.

Open MFD and PFD circuit breakers.

3.10 Splash Screen Loading

When all software and configuration has been loaded, the splash screens must be loaded to the display units (PFD and MFD).

Insert the software loader card in the upper slot of the MFD.

Cloe MFD circuit breaker.

When prompted to update system files, press the

NO

softkey.

When prompted to update splash screen files, press the

YES

softkey.

When the SYSTEM STATUS configuration page appears, Open the MFD circuit breaker.

Remove the loader card from the MFD and insert it into the upper slot of the PFD.

Close PFD circuit breaker.

When prompted to update system files, press the

NO

softkey.

When prompted to update splash screen files, press the

YES

softkey.

When the SYSTEM STAUTS configuration page appears, Open PFD circuit breaker.



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3.11 Database Loading

Follow this procedure to load the databases.

Obtain the following databases from fly.garmin.com and install on a blank 16GB or larger card or by obtaining Garmin SD Card p/n 010-00474-50. Databases with an asterisk are not included on the p/n 010-00474-50 SD card. When obtaining the databases from fly.garmin.com and using SD cards smaller than 16GB, you may need to use multiple cards (or reuse one) to load all the databases into the G1000 system. a. Terrain (Worldwide, 4.9 Arc Second, TBD2 format) b. Obstacle (US/Canada/Europe, OBD2 format) c. AOPA Airport Directory (US) d. AC-U-KWIK Airport Directory* e. SafeTaxi (US, North America*, Canada*, Europe*, Full Coverage*) g. Garmin FliteCharts (US, Canada*, Europe*) h. Jeppesen ChartView* i. IFR/VFR Charts (US) j. Navigation*

With the displays off, insert the SD card into the MFD bottom slot.

Apply power to the PFD and the MFD.

On the MFD, database verification messages may appear. If so, follow the on-screen instructions to continue.

Go to the MFD Aux - Databases page to monitor the automatic database update progress. The new databases will show “Syncing” to the Standby column. After the databases are synchronized, the system will verify them for use by showing “Verifying” in the Standby column. After the databases are verified, a cyan double arrow symbol will appear between the Standby and Active columns to show which databases will be transferred to Active use on the next power cycle or restart.



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Figure 3-9, MFD Aux - Database Page DB Transfer

When all database updates are complete, the Database Update field at the top of the screen will say, “Restart avionics to activate selected standby databases.” If the engine is not running, a

Restart

softkey appears at the bottom of the MFD. Press

Restart

to cycle power on the displays. If the Restart softkey is not present, turn

OFF

PFD and

MFD.

Remove the database update card from the top slot of the MFD.

Turn the displays.

The displays may state they are verifying databases at power-up. If so, follow the onscreen instructions to continue.

Go to the MFD Aux - Databases page and verify the uploaded databases transferred from the Standby column to the Active column. If any did not transfer, follow these steps to initiate a manual transfer - a. Push the FMS knob on the MFD controller to turn on the cursor. b. Turn the FMS knob to highlight the database to transfer to the Active column. the key on the MFD and a cyan double arrow will appear between the

Standby and Active columns. d. Restart the displays. e. Go to the MFD Aux - Databases page and confirm the databases transferred.



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3.12 Configuration of Navigation Map for Traffic System

With the MFD in normal mode, use the FMS knob to select the Navigation Map page then press the Map Opt softkey, the press the Traffic Softkey and ensure that the bar under the Traffic softkey turns green.

Press the MENU button on the MFD, then select “Map Settings” with the FMS knob, then press ENT.

Verify the flashing cursor highlights the GROUP field.

Turn the small FMS knob to select Traffic and press

ENT

on the MFD.

If not already selected, use the MFD FMS knob to make the following selections:



Traffic – On



Traffic Mode – All Traffic



Traffic Symbols – 250NM



Traffic Labels – On 250NM

Return to the Map Page by pressing the FMS knob.

3.13 Clearing Default User Settings

Open MFD and PFD circuit breakers.

While holding the

CLR

button on the PFD, close the PFD circuit breaker.

When prompted to clear user settings, select the

YES

softkey.

When user settings have been cleared appears on the screen, Open the PFD circuit breaker.

Wait ten seconds, then while holding the

CLR

button on the MFD, close the MFD circuit breaker.

When prompted to clear user settings, select the

YES

softkey.

When user settings have been cleared appears on the screen, open MFD circuit breaker.



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3.14 Interface Confirmation

Lightning Detection System Configuration Load Confirmation

Coordinate the StormScope configuration with Section 8.1 “Stormscope Functional Check”.

1. With PFD in configuration mode, use the PFD large FMS knob to select OTHER and the

Stormscope configuration page.

Figure 3-10, Stormscope Configuration Page

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

Figure 3-11, Stormscope Configuration



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3. Verify that the DATA window shows the following:

Hdg: None: J3-1 Open

Hdg Valid Flag

Flag Sense

Hdg Value

Inhibit Line

N/A

Off

Antenna Mount Bottom

N/A

N/A

4. Deactivate the cursor.

NOTE

The DATA window is only updated once every five seconds.



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G1000 LRU maintenance is ‘on condition’ only. No component-level overhaul is required for this type design change.

On Condition Servicing

‘On Condition’ replacement and/or servicing should occur when an item exhibits conditions, symptoms, and/or abnormalities defined in Section 5 of this manual. Replacement and/or servicing should be made only after the technician troubleshoots the system to the extent determined necessary by using the guidance in this manual along with common avionics maintenance practices.

IMPORTANT!

It is impossible to provide guidance for every conceivable failure scenario within the scope of this manual. Every effort has been made to provide comprehensive guidance for possible failures. The information in this document should always be combined with sound aviation maintenance practices and a thorough knowledge of the system. Use sound avionics maintenance practices when working around or on G1000 equipment.

The remainder of this document is organized in the following fashion:



Section 4.3 lists maintenance requirements related to the G1000 system.



Section 6 gives instructions regarding the removal and replacement of physical G1000 equipment and parts.



Section 7 gives configuration and testing instructions to be accomplished if G1000 equipment or parts are removed or replaced.



Section 9 specifies system return-to-service procedures.

The beginning of Section 6 provides instructions to check the software part number and version of each LRU before removing a unit. Procedures in Section 7 require the same check after

LRU replacement and software loading.

IMPORTANT

!

All structural repairs associated with this installation are to be addressed in accordance with the Beechcraft Structural Inspection and Repair Manual listed in Table 1-1.

NOTE

After replacing or servicing electrical components near the GMU 44 magnetometers, the Magnetometer Interference Test (reference Section 5) and

Magnetometer Calibration Procedure (reference Section 7) must be performed.



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The following tools are needed to perform maintenance tasks on G1000 equipment:



Calibrated Milliohm meter, OR o

Agilent 34410A Ammeter or equivalent o

Fluke 187 Voltmeter or equivalent o

Variable DC Power Supply capable of providing 1 amp current



#2 Non-Magnetic Phillips Screwdriver



3/32” Hex tool



Calibrated digital level (Required for AHRS ‘Procedure A’ Calibration)



Calibrated VHF NAV/COM/ILS ramp tester or equivalent



Calibrated transponder ramp tester or equivalent



Calibrated pitot/static ramp tester



Outdoor line-of-site to GPS satellite signals or GPS indoor repeater



Headset/microphone



Ground Power Unit (Capable of supplying 28 VDC)



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Table 4-1 shows systems and items, installed by this STC, which must undergo tests or checks at specific intervals. If the interval is shown in flight time as well as calendar months, the first interval reached should be used as the limit.

IMPORTANT

!

The tolerance for inspection times is the same as that stated in 5-10-00 of the Beechcraft/Textron Aviation Maintenance Manual applicable to the airframe.

The intention of Garmin is to align this maintenance program as best possible with the existing

Textron Aviation G36/G58 inspection program. For a complete description of the G36/G58 inspection program, refer to the Beechcraft Maintenance Manuals listed in Table 1-1.

For equipment not listed here, refer to the applicable G1000 Maintenance Manual(s) listed in

Table 1-1.

Table 4-1, Maintenance Intervals

Manual

Section No.

Interval

G1000/GFC 700 Equipment

GDU 1050 PFD and

GDU 1055 MFD

Removal & Replacement 6.1 On Condition

GTX 335R or GTX

345R Transponder

GRS 79 AHRS

GDC 72 ADC

Removal & Replacement

Special Inspection - Perform GTX 335R,

GTX 345R test.


Magnetic variation database update.


Special Inspection – Perform Air Data Test.



6.2

7.5.4

6.3

4.5

6.4

7.8.3

6.5

6.8

On Condition

24 Calendar Months

On Condition

On Condition

On Condition

24 Calendar Months

On Condition

On Condition

GDL 69A SXM

GMA 1360 Audio

Panel

GEA 71B

Engine/Airframe Unit

GSR 56 Satellite

Transceiver

Iridium Antenna

GSA 81 Servo

Actuators

GSM 86 Servo

Gearboxes






6.12

6.10

6.11

6.12

6.15

On Condition

On Condition

On Condition

On Condition

On Condition



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Manual

Section No.

Interval

GSM 86 Servo

Gearbox Spring

Cartridge Torque

Check

GWX 75 Weather

Radar

G1000 Redundant

Connection Check

Verify that the pitch, pitch trim, roll, and yaw

GSM 86 spring cartridge torque values are within acceptable limits


Verify ARINC connection between GRS

79/GDC 72 and PFD/MFD.

4.7

6.16

4.6

1000 flt-hrs or 1 year

(annual inspection) whichever occurs first

On Condition

24 Calendar Months

G1000 Accessories

Configuration Module

Replacement

Removal & Replacement. 6.7 On Condition

Electrical Bonding

Test

G1000 Lightning Protection

Perform the electrical bonding resistance check of G1000 equipment.

4.4.3 24 Calendar Months

4.4 Electrical Bonding Test

The following bonding tests are provided for G1000-equipped G36/G58 aircraft as a requirement beyond what is given in the G36 or G58 Maintenance Manual.

Requirements

All G1000 equipment must be installed. Gain access for the procedure listed below in Section

4.4.3 as required and in accordance with the Beechcraft G36/G58 Maintenance Manuals.



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A milliohm meter and Kelvin probes are recommended for this test. However, an alternate method may be used to provide equivalent results by using the following procedure and a standard voltmeter, power supply with adjustable current limit, and ammeter. The test set up for this alternate method is described below.

All test equipment used for the bond checks must be calibrated.

1. Connect the positive lead of the power supply to airframe ground. Connect/touch the positive lead of the voltmeter to the same point.

NOTE

Ensure that the voltmeter and power supply probes do not touch, so as not to induce contact resistance.

2. Touch negative lead of power supply to each of the test points listed while performing

Step 3. At each required point, configure the power supply to produce 1 amp before measuring voltage. (Use an ammeter to ensure current is within

minimum

of 1 amp

±100 milliamp at each point). Do not allow the reference current to exceed 1.5 amps for safety.

3. With the current set to 1A, the voltage reading will be the value of the bonding resistance. Set the voltmeter to measure millivolts and null the reading. Measure the voltage from airframe ground (step 1) to each required test points and record the voltage. (Perform Step 2 at each required point and ensure that

minimum

of 1 amp

±100 milliamp is present when measuring the voltage.)

TIP: When a 1A current is used all the millivolt readings are the same as milliohms, and required no further calculation of bond resistance. If 1 amp reference current cannot be maintained and is higher divide the measured voltage by current to get the resistance value. Alternatively, calculate the percentage increase in current and then reduce the measured voltage reading by the same percentage. Example: If the measured current is

1.2 amps, (20% high from the desired 1 amp current) and the measured voltage is 3.0 millivolts, then the value recorded will be 3 millivolts reduced by 20% which is 2.4 millivolts which is the same as 2.4 milliohms.



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Electrical Bonding Procedure

Using one of the two measurement methods in Section 4.4.2, record the bonding measurement for the following equipment. Some equipment in the list is optional and may not be installed.

Ensure that the PFD unit, and MFD unit test points, no more than 40 m Ω is present. Ensure that at other unit test points, no more than 5 m Ω is present.

Pilot Compartment



Metal case of PFD: __________ m Ω



Metal case of MFD: __________ m Ω



GDC 72 body: __________ m Ω



GDL 69A body: __________ m Ω



GTX 335R or GTX 345R body: __________ m Ω



GEA 71B body: __________ m Ω



GEA 71B #2 body: __________ m Ω (G58 only)



GIA 64W #1 top: __________ m Ω



GIA 64W #2 top: __________ m Ω



GMA 1360 body: __________ m Ω

Fuselage and Empennage



GRS 79 body: __________ m Ω



GTS 800 body: __________ m Ω



GSR 56 metal base: __________ m Ω



GWX 75 body: __________ m Ω (G58 only)



GSA 81 body (pitch): __________ m Ω



GSA 81 body (trim): __________ m Ω



GSA 81 body (roll): __________ m Ω



GSA 81 body (yaw): __________ m Ω

4.5 GRS 79 Earth Magnetic Field Updates

The GRS 79, utilizes an Earth magnetic field model which is updated once every five years.

The update is expected to be available from Garmin every five years as long as the GRS 79 remains a Garmin-supported product.

The G1000 system alerts the operator that the magnetic field database is out of date by issuing the message “AHRS SERVICE – AHRS Magnetic-field model needs update”. Garmin will distribute updates as part of the navigation database cycle. If the IGRF model in the update is newer than the model installed, a prompt will appear for the GRS (Select “OK” to update the

IGRF Magnetic Field Model). Use the FM Knob and ENT key to select “OK”.



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4.6 G1000 Redundant Connection Check

Perform the following steps to verify the following:

The GRS 79 and GDC 72 (if installed) data paths to the PFD and MFD.

Note: This section is not required if a GRS 79 and GDC 72 is not installed. Refer to the applicable System Maintenance Manuals (ref Section 1.1) for procedures if a GDC 74A and GRS 77 are installed.

AHRS and ADC data path check (when GRS 79 and GDC 72 installed)

1. Verify there are no AHRS loss of data messages, such as:



AHRS not receiving any GPS information



AHRS not receiving backup GPS information



AHRS using backup GPS source

2. Place the G1000 system in configuration mode.

3. In the GIA page group, go to the GIA RS-232/ARINC 429 CONFIG page.

4. With GIA1 selected in the SELECT UNIT window, verify the following indicators are green checks:



RS232 Channel 1 (GDC72 #1)



RS232 Channel 6 (GRS79 #1)



ARINC 429 IN 5 (GDC72 #1)



ARINC 429 IN 6 (GRS79 #1)

(Ref. Section 5.1.1.2.)

5. With GIA2 selected in the SELECT UNIT window, verify the following indicators are green checks:



RS232 Channel 6 (GRS79 #1)



ARINC 429 IN 5 (GDC72 #1)



ARINC 429 IN 6 (GRS79 #1)


6. In the GDU page group, go to the GIA RS-232/ARINC 429 CONFIG page.

7. With PFD1 selected in the SELECT UNIT window, verify the following indicators are green checks:



ARINC 429 IN1 (GRS79 #1)



ARINC 429 IN2 (GDC72 #1)


8. With MFD selected in the SELECT UNIT window, verify the following indicators are green checks:



ARINC 429 IN1 (GRS79 #1)



ARINC 429 IN2 (GDC72 #1)


9. Restart the G1000 in normal mode.



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4.7 GSM 86 Spring Cartridge Torque Check

Perform the test per Sections 4.71 or 4.7.2.

Automated Torque Check Procedure

1. Start the G1000 system in Configuration Mode and go to the GFC Page Group and select the GFC STATUS page using the FMS knob.

Figure 4-1, GFC Status Page

IMPORTANT!

It is highly recommended that the following test be performed at temperatures between 50° F and 120° F.

2. Use GIA 1 in the SELECT GIA UNIT field for these tests. Use the FMS knob to select the desired servo (Pitch, Pitch Trim, Roll, or Yaw) in the SELECT SERVO AXIS field.

3. Verify that the Monitor Board and Control Board PFT status fields show PASSED.

4. Verify that the aircraft control surface to be checked is free to travel throughout its range of motion.

5. Press the Test SVO softkey on the PFD. Follow prompts to begin the test.

IMPORTANT!

Once the test starts the servo will begin to move the aircraft controls. If the test must be stopped, firmly grasp the aircraft control being moved and press the red AP DISC switch on the aircraft control wheel. If an abnormal disconnect of a servo occurs, reset the AFCS SERVO circuit breaker and repeat the test.

6. The test begins and the selected servo drives the control surface to the control stop.



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7. Upon reaching the control stop, the test initializes and begins a 50 second data collection period, where the servo is commanded to drive at ~2.5 rpm while the servo load cell measures clutch torque.

8. Monitor the CURRENT field and verify the current displayed is greater than zero.

9. After the data is collected and processed, the test displays the results of the first direction on the PFD.

10. The servo immediately begins to drive in the opposite direction toward the opposite control stop.

11. Upon reaching the stop, the test repeats the data collection process and displays the results on the PFD.

12. Firmly grasp the aircraft control under test and push the red AP DISC button to relieve any control tension. Push the ENT key to acknowledge the COMPLETE prompt on the

PFD.

13. Record the torque values in Table 4-2 or in the appropriate aircraft maintenance records.

14. Repeat this procedure for each servo axis.

15. Verify the minimum and maximum torque values measured are within the Minimum and

Maximum torque values allowed for the given axis, listed in Table 4-2.

16. If the values are outside of the torque values allowed, repeat the test twice in the failed axis. If the tests do not pass, the servo gearbox must be removed from the aircraft and tested per Section 4.7.2.

Table 4-2, GSM 86 Allowable Torque Values (Automated Test)

Axis Direction

Min

Measured

Torque

(in-lb)

Max

Measured

Torque

(in-lb)

Min

Allowed

Torque

(in-lb)

Max

Allowed

Torque

(in-lb) Model

Left

Roll

Right

Left

Yaw

Right

Up

Pitch

Down

Up

Pitch

Trim

Down



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Fixture Torque Check Procedure

This test is an alternative to the automated torque check procedure.

The GSM 86 servo gearbox does not have an adjustable slip clutch; however, the torque value can be measured using this procedure.

IMPORTANT!

This adjustment requires the use of the Garmin fixture, P/N T10-00110-01. For detailed operating instructions for the fixture, refer to GSA8X / GSM85(A) Installation Manual.

It is highly recommended that the following test be performed at temperatures between 50° F and 120° F.

1. Remove the GSM 86 servo gearbox as per Section 6.13.

2. Place the GSM 86 servo gearbox on the adjustment fixture and secure with the toggle clamps. Install the fixture cable between the capstan under test and the fixture capstan.

Remove the slack in the cable using the tension adjustment knob. Tighten the two wingnuts on bottom of fixture while holding the top thumbscrews.

3. Attach a socket to a calibrated torque wrench of appropriate range and place on top of the fixture capstan. Adjust the wrench support fixture so that it contacts the handle in the appropriate location.

4. Connect a 2 Amp, 24 V, DC power supply to the fixture.

5. Place the solenoid switch to "on" and move the direction switch to the clockwise or counter-clockwise position. Allow the spring clutch to rotate at least one revolution in each direction (note: the capstan itself is fixed.)

6. Observe the torque reading for at least two full revolutions in each direction. Ensure the minimum and maximum torque readings are within the tolerance specified.

7. If the minimum and maximum torque values are within the specified range in Table 4-3, the GSM 86 spring cartridge is acceptable. Reinstall the GSM 86 servo gearbox per

Section 6.13.

8. If the minimum and maximum torque values are not within the specified range in Table

4-3, the GSM 86 slip clutch cartridge must be replaced.

Table 4-3, GSM 86 Allowable Torque Values (Fixture Test)

G36/G58 43 to 79 in-lb 43 to 79 in-lb 22 to 42 in-lb 32 to 59 in-lb



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5. TROUBLESHOOTING

This section provides instructions and guidance for G1000 system troubleshooting as installed in the Textron Aviation G36/G58 aircraft.

IMPORTANT!

Sections 6, 7 and 9 provide detailed instructions on equipment removal, replacement, configuration, and return-to-service testing. Anytime a G1000 component or LRU is removed, swapped, or replaced, the technician must follow the procedures given in Sections 6, 7 and 9 to ensure proper operation of the system.

Troubleshoot the G1000 system by first identifying, then isolating the specific failure to the responsible LRU. There are several indications that the G1000 presents to the pilot or technician, showing overall system condition. A course of action should be determined based on the information presented on the display. This section shows possible scenarios likely to be encountered during normal operation and gives troubleshooting guidance to the technician to resolve problems.

Figure 5-1, Aux – System Status Page



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The

Aux – System Status

page displays the following information for each LRU and subfunction:



Status: A green check is displayed for properly operating LRUs. A red ‘x’ appears when an internal LRU fault is detected and it has taken itself offline, or if the MFD cannot communicate with the LRU.



Serial Number: Each LRU serial number is displayed (functions such as COM and GS are contained within an LRU; therefore, serial numbers are not shown for these).



Current SW Version Loaded.

When troubleshooting, first check to ensure that each LRU status is ‘green’ and that the correct software is loaded in each unit. Additional airframe and database information is also displayed on this page.

5.1 System Annunciations

If data fields become invalid due to an LRU failure, the PFD/MFD typically annunciates the failure with a large red X, as shown in Figure 5-2.

Figure 5-2, System Annunciations



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Failed Path Messages

The following message indicates there is a data path connected to the GDU (PFD or MFD) or the GIA (1 or 2) that has failed.

FAILED PATH – A data path has failed.

The

FAILED PATH

message is triggered by a timeout of any one digital channel.

IMPORTANT!

Once the FAILED PATH message has been triggered, it will remain on the list of messages until the next power cycle. This latching was implemented so that for intermittent failures, the message would remain at the end of the flight (to alert maintenance crew). Also, this keeps the crew from having to acknowledge message repeatedly in the case of intermittent failures.

To determine which path is causing the

FAILED PATH

message, start the PFD and MFD in configuration mode. Using the FMS knobs, scroll to the pages listed below.

The channels that are checked are listed on these pages in config mode:

1) GDU RS-232 / ARINC 429 CONFIG (PFD and MFD)

2) GIA RS-232 / ARINC 429 CONFIG (GIA1 and GIA2)

3) GIA CAN / RS-485 CONFIGURATION (GIA1 and GIA2)

The box next to each channel indicates the current status of the channel per the below:



Red X = data path is known to be failed



Amber question mark (?) = data path status is unknown



Green checkmark (



)= data path is known to be good

The applicable data paths can be verified by viewing the following configuration mode pages.

NOTE

For paths not listed here, refer to the applicable G1000 Line/System Maintenance

Manuals listed in Section 1.1.



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GDU ARINC 429 CONFIG Page

PFD and MFD ARINC 429

IN 1

IN 2

GRS 79 #1

(if GRS 79 installed)

GDC 72 #1

(if GDC 72 installed)

Green PFD/GRS 79 data path is functioning correctly.

Red

PFD/GRS 79 data path is not functioning correctly.



Verify GRS 79 status is “OK” using the

Aux – System

Status

page on the MFD. If it is not, correct condition before proceeding, reference GRS troubleshooting sections.



Load PFD configuration file.



Swap PFD and MFD to confirm if the problem is in the original PFD. o

Replace original PFD if box turns green after swapping displays.



Check the PFD/GRS 79 interconnect wiring for faults. o

Replace the GRS 79 if problem persists.

Amber

PFD/GRS 79 data path functionally is unknown. Reload

PFD configuration file.

Green PFD/GDC 72 data path is functioning correctly

Red

PFD/GDC 72 data path is not functioning correctly.



Verify GDC status is “OK” using the

Aux – System

Status

page on the MFD. If it is not, correct condition before proceeding, reference GDC troubleshooting sections.



Load PFD and GDC configuration files.



Swap PFD and MFD to confirm if the problem is in the original PFD. o

Replace original PFD if box turns green after swapping displays.



Check the PFD/GDC 72 interconnect wiring for faults. o

Replace GDC 72 if problem remains.

Amber

PFD/GDC 72 data path functionality is unknown. Reload

PFD configuration file.



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GIA RS-232 / ARINC 429 CONFIG Page

GIA1 RS-232

CHNL 1

CHNL 5

GDC 72 #1

(if GDC 72 is installed)

GTX 3x5 #1

(if GTX 335 or GTX 345 installed)

Green GIA1/GDC 72 data path is functioning correctly.

Red

Amber

GIA1/GDC 72 data path is not functioning correctly.



Load GIA1 and GDC 72 configuration files.



Swap GIA1 and GIA2, reconfigure both GIA’s to their new locations to confirm if the problem is in the original

GIA1. o

Replace original GIA1 if box turns green after swapping units.



Check the GIA1/GDC 72 interconnect wiring for faults. o

Replace GDC 72 if problem remains.

GIA1/GDC 72 data path functionality is unknown. Reload

GIA1 configuration files.

Green

GIA1/GTX 3X5 data path is functioning correctly.

Red

Amber

GIA1/GTX 3X5 data path is not functioning correctly.



Load GIA1 and GTX 335 or GTX 345 (as applicable) configuration files.




GIA1. o




Check the GIA1/GTX 3X5 interconnect wiring for faults. o

Replace GTX 335 or GTX 345 (as applicable) if problem remains.

GIA1/GTX 3X5 data path functionality is unknown. Reload




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GIA1 RS-232 (continued)

CHNL 6

GRS 79 #1

(if GRS 79 installed)

Green GIA1/GRS 79 data path is functioning correctly.

Red

Amber

GIA1/GRS 79 data path is not functioning correctly.



Load GIA1 configuration files.




GIA1. o




Check the GIA1/GRS 79 interconnect wiring for faults. o

Replace GRS 79 if the problem persists.

GIA1/GRS 79 data path functionality is unknown. Reload




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GIA1 ARINC 429

IN 5

IN 6

GDC 72 #1

(if GDC 72 is installed

GRS 79 #1

(if GRS 79 is installed)


Red

Amber








GIA1. o





Replace GDC 72 if problem persists.




Red








GIA1. o





Replace GRS 79 if problem persists.

Amber





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GIA2 RS-232

CHNL 5

GTX 3x5

#1 (if GTX

335 or

GTX 345 is installed)

CHNL 6

GRS 79 #1


Green GIA2/GTX 3X5 data path is functioning correctly.

Red

GIA2/GTX 3X5 data path is not functioning correctly.



Load GIA2 and GTX 335 or GTX 345 (as applicable) configuration files.




GIA1. o




Check the GIA2/GTX 3X5 interconnect wiring for faults. o

Replace GTX 335 or GTX 345 (as applicable) if problem remains.

Amber

GIA2/GTX 3X5 data path functionality is unknown. Reload



Red

Amber




Load GIA2 and GRS configuration files.




GIA1. o





Replace GRS 79 if problem remains.





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GIA2 ARINC 429

IN 5

IN 6

GDC 72 #1

(if GDC 72 is installed

GRS 79 #1



Red

Amber








GIA2. o





Replace GDC 72 if problem persists.




Red

Amber




Load GIA2 and GSR 79 configuration files.




GIA2. o





Replace GRS 79 if problem remains.

GIA2/GSR 79 data path functionality is unknown. Reload




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System Failure Troubleshooting

The following table provides basic troubleshooting guidance for LRU failures. Refer to G1000

Wiring Diagram, listed in Table 1-1, as needed to verify interconnects.

NOTE:

For troubleshooting of data fields and units not listed here, refer to the applicable Line/System

Maintenance Manual (ref section 1.1).

Invalid Data Field

Associated

LRU(s)

Solution

XPDR FAIL

GTX 335R,

GTX 345R

(if installed)



Check GTX 335R/345R configuration settings for GIA1 and

GIA2.



Check GTX 335R/345R and GIA1 interconnect.



Check GTX 335R/345R and GIA2 interconnect.



Perform a SET>ACTV configuration reset on the GTX Config page, and verify the aircraft registration is present.



Replace GTX 335R/345R.

 If problem persists, replace GIA.

TAS FAIL

AIRSPEED FAIL

ALTITUDE FAIL

VERT SPEED FAIL

GDC 72 (if installed)



Inspect GDC 72 pitot/static plumbing integrity.



Inspect pitot/static ports and associated equipment for faults.



For TAS failure, also check GTP 59 probe.



Check GDC 72 configuration settings for the PFD, MFD,

GIA1, and GIA2.

 If problem persists, replace the GDC 72.



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ATTITUDE FAIL

Associate d LRU(s)

GRS 79

(if installed)

Solution



Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin.



Cycle GRS 79 power to restart initialization.



Ensure GRS 79 connecter is secure and proper wire harness strain relief is provided.



Ensure the GRS 79 is fastened down tightly in its mounting rack and that the mounting rack is not loose (CAUTION - do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re-leveled and the

PITCH/ROLL OFFSET procedure performed).



Ensure GPS has acquired at least four satellites, has a 3D navigation solution, and a DOP of less than 5.0. This is particularly important for an ATTITUDE FAIL that appears during ground operation only.



Perform an Engine Run-Up Test to check if engine vibration is causing the GRS 79 to go offline.



Load configuration files to the PFD, MFD, GIA1, and GIA2.



Calibrate the GRS 79 (Pitch/Roll Offset and Magnetometer

Calibration).



Replace 79.

 If problem persists replace GRS 79 configuration module.



Contact Garmin Aviation Product Support if condition continues after replacing the GRS 79 and config module for additional assistance

.



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HDG FAIL

Associate d LRU(s)

Solution

GRS 79

(if installed)

&

GMU 44



Ensure metal objects (tool boxes, power carts, etc.) are not interfering with the magnetometer and aircraft is not in hangar, near other buildings, parked over metal drainage culverts or on hard surfaces that may contain steel reinforcements






Cycle power after moving aircraft away from metal objects to determine if metal objects were the source of the interference. Allow up to five minutes for the heading to reinitialize.



Perform a Magnetometer Interference Test to check for interference from onboard electrical system components

(e.g. NAV lights). Pay particular attention to any new electrical devices that have been installed since the aircraft was new. Correct any discrepancies that do not allow this test to pass before continuing.



Ensure GRS 79 and GMU 44 connectors are secure.



Check the wiring and any inline connectors between the

GRS and GMU for faults.



Recalibrate the GMU 44



Load configuration files to the PFD, GIA1, and GIA2

 If problem persists replace the GMU 44.



If problem persists, replace the GRS 79.

GRS 79

(if installed)

&

GMU 44



If this message persists longer than five minutes, perform

AHRS calibration procedures as described in Section 7.11.



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5.2 G1000 Alerting System

Figure 5-3, Alerts & Annunciations

The G1000 Alert System conveys alerts to the pilot using combinations of the following features:

Alert Window:

The Alert window displays alert text messages. Pressing the Alerts softkey displays the Alerts window. Pressing the ALERTS softkey again removes the Alerts window from the display.

Softkey Annunciation:

When the G1000 Alerting System issues an alert, the Alerts softkey is used as a flashing annunciation to accompany the alert. During the alert, the Alerts softkey label flashes between white letters on black to black letters on a white. The flashing continues until the alert is acknowledged by a press of the Alerts softkey. The alerts softkey remains black letters on white until the condition causing the alert is corrected, or a new alert triggers the flashing.

Figure 5-4, Alerts Softkey Annunciation

System Failure Annunciations:

Typically, a large red X appears in windows when a failure is detected in the LRU providing the information to the window.



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5.3 Synthetic Vision and Pathways Troubleshooting

The SVS/Pathways software feature requires the following G1000 sensors/data to be valid:



AHRS



Heading



GPS



9 Arc-Second (or less) Terrain Data

In the event that one the above items fails or is unavailable, the SVS/Pathways feature is automatically removed from the PFD. The following table describes possible symptoms associated with the SVS/Pathways feature, and provides corresponding actions for troubleshooting:

Table 5-1, SVS Troubleshooting

“SVT” softkey does not appear on

PFD softkey tier.

Follow the steps in Section 3.7.2 to reactivate the SVS/Pathways feature.

3D terrain presentation does not appear on PFD.

Verify that terrain database is current on the

Aux – Databases

page on the

MFD.

Verify that the alert messages shown in Table 5-2 are not displayed on the

PFD Alerts Window. If so, follow the solutions described in Table 5-2.

Verify that the G1000 AHRS and heading data are valid on the PFD. Verify that a valid GPS 3D position solution is being received. Troubleshoot these systems in accordance with Section 5.14 and the Applicable G1000

Line/System Maintenance Manuals (refer to Section 1.1)

If a terrain database update has just been performed, allow the system time to initialize and verify the data. When the databases have been verified, the current database cycle and version are reported on the MFD

Aux – System

Status

and

Aux – Databases

page.

The following table provides SVS/Pathways specific alert messages which may appear in the

Alerts Window on the PFD (press the ALERTS softkey on the PFD to view the Alerts Window):



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Failure Message

Table 5-2, SVS-Related Alert Messages

SVS – SVS DISABLED: Out of available terrain region.

Cause

SVS is disabled because the aircraft exceeded the boundaries of the loaded terrain database.

Solution

Geographical operation limitations are defined in the AFMS listed in Table 1-1.

Ensure that operations are within this geographic area.

5.4 Backup Communications Path Checks

Overview

The G1000 system architecture is designed with redundant communication ports for several

LRUs so that critical information can continue to be displayed in the event of an equipment or wiring failure. Of most importance is flight attitude, heading, and air data information. The GRS

79 and GDC 72 (if installed) have separate ARINC 429 data lines which are all capable of sending data to the displays. The GTX 335R or GTX 345R (if installed) have two redundant serial communication paths for the same purpose. See the Applicable Line/System

Maintenance Manuals (refer to Section 1.1) for a basic G1000 block diagram depicting general system architecture. The GRS 79 and GDC 72 replace references to the GRS 77 and GDC 74 in that manual, and the GTX 335R or GTX 345R replace references to the GTX 33 in that manual. Several other diagrams are shown later in this section for illustrative purposes. When troubleshooting, refer to the G1000 Wiring Diagram listed in Table 1-1.

NOTE

Refer to Section 9.8 for procedures on checking the status of each configured

G1000 / GFC 700 backup data path.



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Data Path Failures

Failure Message

FAILED PATH – A data path has failed.

Cause

A communications data path status is not being received by the

G1000.

Solutions

Determine which data path has failed:

See Section 5.1.1.

Check wiring continuity for the failed path.

Swap or replace the affected LRU.

Display is blank

Display resets

Display flickers

SD card is stuck in GDU



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




Cycle

 If GDU recovers, observe display for yellow text containing error information at the top of the screen. If message indicates software need to be re-loaded, then re-load software. Otherwise, replace the GDU.



Use a bright light to verify LCD is active.

 Adjust avionics dimmer control full clockwise.

 Manually turn up backlight on the PFD and load configuration files to the

GDU.



Ensure slide lock is fully engaged with the locking tabs on the back of the unit.

 If slide lock is not fully engaged, remove connector and verify the locking tabs on the GDU are perpendicular to the connector. If necessary, straighten them before reseating connector.



Ensure GDU is receiving power. If a circuit breaker is tripped, determine source of short before resetting breaker.



Ensure circuit breakers have not failed and power wire connections are secure.



Swap PFD and MFD



If problem follows unit, replace the display. Please note the position it failed in (PFD or MFD).

 If problem does not follow unit, troubleshoot aircraft wiring for fault.



DO NOT insert a screwdriver of any length into the card slot.



DO NOT pry against the overlay.



DO NOT force the SD Card out.



Use a small screwdriver in the groove on the side of the exposed end of the card to help pull out the card.



Push the card in further to release the card locking mechanism.



Check SD Card for having more than one label. Two or more labels on the card will cause sticking.

 Remove all but one label.



Ensure the SD card is from SanDisk. Use of other SD Cards is not recommended.



If card was inserted with the label facing to the right, do not attempt to remove.

Return the unit to an authorized repair facility.

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A button/knob/joystick does not appear to function

Terrain/Obstacle/SafeTaxi does not display

Display will not track dimmer bus



Go to the GDU TEST page in configuration mode and verify button, knob, or joystick operates correctly by observing a change in color from red to green in the button/knob/joystick icon when the button/knob/joystick is pressed. If a button is stuck, the button icon will be green without pressing the button as soon as you turn to the GDU TEST page.

 If problem is verified, replace GDU.



Allow the system to verify the data in internal memory for approximately five minutes after power-up.



If a database does not activate, reload the problem database.



Reload GDU configuration files.



Swap PFD and MFD to see if problem remains with display.



Replace display if condition remains with the same unit.

 If condition remains in original position after swapping displays, check GDU dimmer input to verify voltage is present.



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Failure Message

SW MISMATCH – GDU software version mismatch. Xtalk is off.

MANIFEST – PFD 1 software mismatch. Communication

Halted.

MANIFEST – MFD1 software mismatch. Communication

Halted.

Cause

The system has found the PFD and MFD software versions do not match.

Solution

The system has detected an incorrect software version loaded in the specified display.



Load correct software version.

See Section 3.6.2 for GDU

1050/1055 Software Loading procedure.

CNFG MODULE – PFD 1 configuration module is inoperative.

The PFD master configuration module has failed.



Check master configuration module connector and wiring for damage inside the GDU connector backshell.

 Replace master configuration module wiring and pins.

 If problem persists, replace master configuration module.

NOTE

New Terrain/Obstacle databases,

Jeppesen Aviation Database and other optional features (i.e. TAWS unlock card) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old Terrain and other databases will no longer work as they will remain locked to the old System ID number.



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Failure Message

MFD1 CONFIG – MFD1 configuration error. Config service req’d.

PFD 1 CONFIG – PFD 1 configuration error. Config service req’d.

Cause

A configuration mismatch has occurred between the display and the Master Configuration Module.

Solution



Reload the display configuration files from SD Loader Card.



Reload system configuration files by pressing the UPDT CFG softkey on the Configuration

Upload Page in the PFD System

Page Group to load configuration files into the configuration module.

 If message persists, check

PFD config module wiring for faults and replace if necessary.

 If issue continues, replace

PFD master configuration module.

 If problem persists, replace the display.

NOTE





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Failure Message

MFD “key” KEYSTK – key is stuck.

Cause

The SYSTEM has determined a key is stuck on MFD.

PFD “key” KEYSTK – key is stuck.

The system has determined a key is stuck on the PFD.

Solution



Go to the GDU TEST page in configuration mode and verify key is stuck (if key is stuck the corresponding indicator will be green).



Exercise suspected stuck key and reset GDU TEST page to see if indicator remains green without pressing the key.

 If problem persists replace the display.

Failure Message

DATA LOST – Pilot stored data lost. Recheck settings.

Cause

XTALK ERROR – A flight display cross talk error has occurred.

A communication error has occurred between the MFD and

PFD.

Pilot stored data has been lost.

Solution



Ensure a database error has not occurred (identified in the ALERTS window on the PFD).

 If a database error has occurred, correct error before proceeding.



Check Ethernet interconnect wiring.



Replace PFD with a known good unit, to verify location of problem:

 If problem persists, reinstall original PFD and replace MFD.



If the CLR key was held during a power cycle, disregard message.



Cycle power to PFD:



Ensure CLR key is not stuck on the GDU TEST page.

 If problem persists, replace

PFD.



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Failure Message

MFD SERVICE – needs service.

Return unit for repair.

PFD SERVICE – needs service.

Return unit for repair.

PFD VOLTAGE – PFD has low voltage. Reducing power usage.

MFD VOLTAGE – MFD has low voltage. Reducing power usage.

Cause

The G1000 has determined MFD needs service.

Solution



Ensure the MFD connector is fully seated and locked.



Replace the MFD.



Return faulty unit to an Authorized

Repair Facility.

The G1000 has determined the

PFD needs service.

The MFD supply voltage is low.



Ensure the PFD connector is fully seated and locked.



Replace the PFD.




Repair Facility.

The specified PFD supply voltage is low.



Check input voltage to PFD.



If input voltage is ok, replace PFD.



Check input voltage to MFD.



If input voltage is ok, replace MFD.



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Failure Message

MANIFEST – GTX software mismatch. Communication halted.

Cause

The system has detected an incorrect software version loaded in the GTX unit.

Solutions



Reload software.

XPDR CONFIG – XPDR configuration error. Config service req’d.

XPDR SRVC – XPDR needs service. Return unit for repair.

XPDR FAIL – XPDR is inoperative.

XPDR ADS-B FAIL – XPDR unable to transmit ADS-B message.

The system has detected a configuration mismatch for the

GTX unit.

The G1000 has detected a failure in the GTX

The GTX is not responding.

The GTX transponder is not able to transmit ADS-B data.



Perform a SET>ACTV configuration reset on the GTX

Config page and verify the aircraft registration is present.



If error is still present, reload config files from a loader card.

 If problem persists, replace master configuration module, check config module harness for faults and replace if necessary.

NOTE





Replace GTX unit.




Repair Facility.



Check wiring between GIA’s and

GTX.



Replace GTX unit.




Repair Facility.




GPS antenna.




GTX.



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5.8 GDL69A SXM Troubleshooting (if installed)

For GDL69A SXM Troubleshooting, refer to the GDL 69A section in the appropriate

Line/System Maintenance Manual (see Section 1.1).

5.9 GEA 71B Troubleshooting (if installed)

For GEA 71B Troubleshooting, refer to the GEA 71 section in the appropriate Line/System

Maintenance Manual (see Section 1.1).

5.10 GIA 64W Troubleshooting (if installed)

For GIA 64W Troubleshooting, refer to the GIA 63W section in the appropriate Line/System


5.11 GMA 1360 Troubleshooting (if installed)

For GMA 1360 Troubleshooting, refer to the GMA 1347 section in the appropriate Line/System


5.12 GWX 75 Troubleshooting (if installed)

For GWX 75 Troubleshooting, refer to the GWX 68 section in the appropriate Line/System


5.13 GSR 56 Troubleshooting

No communication with GSR 56

No or low-quality Iridium signal

No audio output

Unable to make a phone call



Check power wiring and pin out of GSR 56 unit.



Ensure GSR 56 configuration option has been loaded.



Ensure the Iridium antenna has an unobstructed view of satellite constellation.



Check the Iridium antenna cable and connectors.



Verify antenna ground plane is adequate.



Check wiring from GSR 56 to GIA #1.



Verify subscription with Garmin Connext (reference Section 7.15.1).



Verify signal quality is adequate



Verify communication between GSR 56 and the display/control device



Verify subscription with Garmin Connext (reference Section 7.15.1).



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5.14 GRS 79 and GMU 44 Troubleshooting

For GRS 77 Troubleshooting, refer to the appropriate Line/System Maintenance Manual (see

Section 1.1).

AHRS does not complete initialization

Attitude appears unstable






Ensure GPS has acquired at least four satellites, has a 3D navigation solution, and a DOP of less than 5.0. This is particularly important if this issue appears during ground operation only.



Calibrate the GRS 79.



Check GRS 79 configuration module wiring for damage.



Check GRS 79 connector for bent pins.

 If no damage can be found, replace GRS 79 configuration module.

 If problem persists, replace the GRS 79.



Ensure that a cell phone or a device using cell phone technology is not turned on (even in a monitoring state) in the cabin. (Wi-Fi and Bluetooth may be operational)



Ensure the two mounting jack screws are tight. Finger tight is not sufficient, a screwdriver must be used to verify.



Ensure mounting rack and airframe shelf are secure and all hardware and brackets are present (CAUTION - do not loosen the mounting rack hardware to the airframe shelf or the aircraft will need to be re-leveled and the PITCH/ROLL

OFFSET procedure performed).



Ensure the GRS 79 connector is securely fastened and proper strain relief is provided.



Remove the GRS 79 connector and verify there are no bent pins.



Replace the GRS 79.



Contact Garmin for further troubleshooting if required.



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Failure Message

MANIFEST – GRS software mismatch. Communication halted.

AHRS SERVICE – AHRS magnetic-field model needs update.

GEO LIMITS – AHRS too far north/south, no magnetic compass.

AHRS GPS – AHRS not receiving backup GPS information.

MAG VAR WARN – Large magnetic variance. Verify all course angles.

Cause

The system has detected an incorrect software version loaded in the specified GRS unit.

The AHRS magnetic field model should be updated for the specified unit. Appears on ground only.

No magnetic compass information available due to being too far north or south.

The GRS 79 is not receiving backup GPS information from GIA

63 #2.

AHRS GPS – AHRS using backup

GPS source.

The GRS 79 is using the backup

GPS data path.

Magnetic variance value from

GMU 44 is not accurate.

Solutions



Load correct software version.



Load updated AHRS magnetic field file. See Section 4.5.



Operate the aircraft only within the limits as specified in the G1000

AFMS, listed in Table 1-2






Check GPS status for GIA 1 and 2 on MFD

Aux – GPS Status

page. If one or both GPS receivers cannot acquire a position lock, see GPS troubleshooting section



Troubleshoot GIA1/2 –GRS wiring for faults (ref. Failed Path troubleshooting section).



Replace the GRS 79.



If flying near large radio towers or other sources of possible electromagnetic interference, the condition should correct itself as the aircraft leaves the area.



If problem persists, run magnetic interference check in Section 5.14.4 to check for magnetic interference in the aircraft.

Failure Message

MANIFEST – GMU software mismatch. Communication halted.

Cause

The system has detected an incorrect software version loaded in the GMU 44.

Solutions

Load the correct software version.

HDG FAULT – AHRS magnetometer fault has occurred

A fault has occurred in the magnetometer; heading will be flagged invalid.



Check GMU 44/GRS 79 interconnect for faults.

 Replace 44.

 If problem persists, replace

GRS 79.



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Calibration Procedure E: Magnetometer Interference Test

A magnetometer interference test is available for troubleshooting and/or verifying a magnetically

‘clean’ installation of the GMU 44. This test exercises various devices on the aircraft that could potentially affect the magnetic field as measured by the GMU 44.

NOTE

This test is used to validate that no electronic device or magnetized components produce a magnetic field sufficient to interfere with the operation of the GMU 44 magnetometer. It is highly recommended that this test be performed after installation or maintenance of electrical components on the aircraft and/or for troubleshooting the GMU 44.

Figure 5-5, Magnetometer Interference Test

1. Initiate the AHRS magnetometer interference test procedure by performing the following steps:

2. On the PFD, enter Configuration Mode and go to GRS/GMU Calibration page as shown in Figure 5-5.

3. This page is protected and requires a keystroke password to perform this test. Press the following softkeys in sequence: (as counted from left to right on lower bezel of MFD)



softkey



softkey



softkey



softkey

4. Select MAG INTERFERENCE TEST and press the PFD ENT key.

5. Follow the checklist items displayed on the PFD, and press the ENT key as each one is completed or confirmed.



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NOTE

The 3 rd item on the checklist instructs the operator to “prepare a detailed test sequence with precise start and stop times for exercising all electronic devices”.

The list of relevant electronic devices is given in Table 5-3. Begin test with flaps retracted, flight controls in a neutral position, all lights selected OFF.

Elapsed Time since Start of Test

(min:secs)

Action

0:10

0:20

0:30

0:40

0:50

1:00

Navigation lights on

Navigation lights off

Landing lights on

Landing lights off

Taxi lights on

Taxi lights off

1:50

2:00

2:10

2:20

2:30

2:40

2:50

3:00

3:10

3:20

3:50

4:00

4:10

4:20

4:30

6:20

6:30

6:40



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Ice Light on

Ice Light off

Pitot Heat on

Pitot Heat off

Fuel Vent Heat on

Fuel Vent Heat off

Stall Warn Heat on

Stall Warn Heat off

Prop Heat on

Prop Heat off

L/R Fuel Boost Pump Hi on

L/R Fuel Boost Pump Lo on

L/R Fuel Boost Pump off

Aileron full right

Aileron full left

Rudder full left

Rudder full right

Elevator full nose UP

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Elapsed Time since Start of Test

(min:secs)

6:50

Action

7:00

7:10

7:20

7:30

7:40

Elevator full nose DN

Elevator trim full nose UP

(manual)

Elevator trim full nose DN

(manual)

Air Conditioner On (if equipped)

Air Conditioner Off (if equipped)

End of test

Table 5-3, Magnetometer Interference Test Sequence

6. When the CALIBRATE field is blinking, press the ENT key to begin the procedure, and have a stopwatch ready to begin recording the elapsed time.

NOTE

It is important that the “time equals zero” moment corresponds with the moment the PFD first displays the blinking TEST COMPLETE? Message.

7. The operator should carry out the actions called for in the prepared test sequence.

NOTE

It is important that all actions are carried out in the order and at the precise elapsed time as specified in the prepared test sequence.

8. When the operator has completed the actions specified in the test sequence, press the

ENTER button to indicate that the process is complete. When this is done, the TEST

COMPLETE field stops blinking.

9. The PFD informs the operator if the installation has passed or failed the magnetometer interference test. If the test passes, no further action is required for this test.

If the test fails, the installation should be considered unreliable until the source of magnetic interference is identified and remedied. When the magnetometer interference test fails, record the three magnetometer maximum deviation values and their corresponding timestamps. Reference the installation manual for the GRS 79 (190-

01852-00) for acceptable magnetic interference limits. Compare the corresponding timestamps with the prepared test sequence to identify which action produced the problem. Contact Garmin for assistance in resolving the problem.

NOTE

Two common reasons for a failed magnetometer interference test are: 1) new equipment is installed in close proximity to the GMU 44 magnetometer, and 2) an existing or new electronic device has become grounded through the aircraft structure instead of via the proper ground wire in a twisted shielded pair.

10. Press the ENT key on the PFD to conclude this procedure.



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5.15 GDC 72 Troubleshooting

For GDC 72 Troubleshooting, refer to the GDC 74 A section of the appropriate Line/System

Maintenance Manual (refer to Section 1.1).

5.16 Software/Configuration Troubleshooting

Problem Solutions

MFD or PFD displays do not power up:

Software file load fails:

Configuration file load fails:

GIA1 and/or GIA2 to ‘LRU’ data path not working

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

After being in configuration mode, the PFD displays a red AFCS annunciation and cycling of the transponder field between valid and invalid states.



Ensure that the criteria listed in Section 5.16.1 are fulfilled for the applicable situation.



Ensure power is present at display backshell connector.



Troubleshoot per the “Blank Display” GDU section.



Ensure that criteria listed in Section 5.16.1 are fulfilled for the applicable situation.



Ensure that LRU is reporting data on

Aux –

System Status

page (LRU is ‘ONLINE’). Check data path wiring as needed.



Retry software file load or try using a different card.

Ensure that the MFD is not touched during the loading process.



Ensure that LRU part number is compatible with software version and Card Loader. Refer to

Section 3.1.7.



Replace






Ensure that LRU is reporting data on the

Aux –

System Status

page (LRU is ‘ONLINE’). Check data path wiring as needed.



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



Ensure that LRU part number is compatible with

Card Loader. Refer to Section 3.1.7.



Replace






Ensure GIA1 and GIA2 are configured correctly.



Check wiring, connectors & pins as needed.



Ensure that proper software file part number and version were loaded to LRU. Refer to Section

5.16.1.



Check and ensure that correct Card Loader was used during load process. Refer to the General

Arrangement Drawing.



Reload software to LRU.



With the G1000 system powered on, open the MFD and PFD circuit breakers for approximately 30 seconds, then close the circuit breakers.



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The following criteria must be satisfied to be able to perform the desired operation:

Desired Operation

Load Software to MFD or PFD Displays

Load AIRFRAME, SYSTEM, MFD, PFD and

MANIFEST configuration files to MFD and PFD

Load Software/Configuration files to GIA 63Ws

Load Software/Configuration files to:

- GMA 1347/GMA 1360

- GRS 79 (if installed)

- GDC 72 (if installed)

- GDC 74 (if installed)

- GEA 71/71B (#1 and #2 on G58, single unit on G36)

- GRS 77 (software only) (if installed)

- GMU 44 (software only)

- GTX 33 (if installed)

- GTX 335R or GTX 345R (if installed)

Criteria for Success



SW Loader Card must be inserted in top slot for each display to be loaded.



ENT keys must be held during power up of display.



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



SW Loader Card must be inserted in top slot of

PFD.



PFD and MFD must be powered on.



PFD and MFD must have correct software.



SW Loader Card must be inserted in top slot of

PFD.



G1000 system must be powered on.



PFD and MFD must have correct software.



PFD and MFD must be successfully configured with AIRFRAME, SYSTEM, MANIFEST, MFD and

PFD configuration files.



SW Loader Card must be inserted into PFD top slot.



G1000 must be powered on.



PFD and MFD must have correct software and configuration settings.



GIAs must have correct software.



GIAs must be successfully configured with GIA1 and GIA2 configuration files.



Data path from GIA1 to each LRU must be operational.



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5.17 Backshell/Backplate Connectors

The following figures depict the backplate connectors as viewed with the LRU removed. For units not shown here, refer to the applicable Maintenance Manual.

Figure 5-6, GTX 335R/345R Looking at Front of Connector (P3251)

Figure 5-7, GTX 345R (Only) Looking at Front of Connector (P3252)



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Figure 5-8, GDU 1054B/1050 Backshell Connector (P10401)

Figure 5-9, GRS 79 Connector View from Front (P791)

Figure 5-10, GDC 72 Connector View from Front (P721)

Figure 5-11, GDL 69A SXM Backplate Connector (P69A1)



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COM BOARD CONNECTOR (P601)

COM ANTENNA CONNECTOR

COOLING PORT

1 2 3

16 17

4 5 6 7 8 9 10 11 12 13 14 15

18 19 20 21 2223 24 25 26 2728 2930

31 32 3334 35 3637 3839 40 41 42 43 44

MAIN DISCRETE CONNECTOR (P604)

MAIN SERIAL CONNECTOR (P603)

GPS ANTENNA CONNECTO

I/O CONNECTOR #2 (P606)

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

I/O CONNECTOR #1 (P605)

1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

G/S ANTENNA CONNECTOR

NAV ANTENNA CONNECTOR

VOR/ILS CONNECTOR (P602

Figure 5-12, GIA 64W Backplate Connectors

1 2 3 4 5 6 7

8 9 10 11 12 13 14 15 16 17 18 19 20

21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38

40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59

60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78

Figure 5-13, GEA 71B Backplate Connectors



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Figure 5-14, GMA 1360 Backplate Connectors

15 14 13 12 11 10 9 8 7 6 5 4 3 2 1

30 29

44

43

28 27

42 41

26 25 24

40

39 38

23 22

37 36

21 20

35 34

19 18

33 32

17 16

31

Figure 5-15, GSR 56 Mating Connector

Figure 5-16, GWX 75 Mating Connector



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6. Equipment Removal & Installation

This section describes how to remove and replace equipment in the Textron Aviation G36/G58 aircraft associated with this STC. After removal and replacement, LRUs must be configured and tested as described in Section 7.

CAUTION:

When removing and/or replacing any G1000 component, always ensure that aircraft power is off. Unplug any auxiliary power supplies. Before performing maintenance, it is required that the technician verify the LRU software part number and version number matches the software configuration listed in the General Arrangement drawing, listed in Table 1-1.

NOTE

After installation or maintenance of electrical components near the GMU 44 magnetometers, perform the Calibration Procedure E: Magnetometer Interference

Test (reference Section 5) and Procedure B: GRS 79 and GMU 44 magnetic calibration (reference Section 7).

To check an LRU software part number and/or version, follow the procedure defined in Section

3.1.7.

If a faulty LRU is not reporting its software version and part number, check aircraft maintenance logs for last software version loaded and verify against the General Arrangement drawing. The

Software Manifest page may also be used to check part numbers and versions.

The General Arrangement drawing allows alternate part number units to be installed with certain hardware/software combination restrictions. Refer to the applicable “Garmin

Equipment/Software List” contained in the General Arrangement drawing for details.



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Removal:

1. Using a 3/32” hex tool, rotate all four ¼-turn fasteners counter-clockwise until they reach their stops.

2. Carefully remove the display from the panel.

3. While supporting the display, disconnect the connector.

Reinstallation:

1. Visually inspect the connector and pins for signs of damage. Repair any damage.

2. While supporting the display, connect the connector to the rear of the unit. Verify the connector is fully locked by rocking the connector up and down to verify the connector stays attached to the unit.

3. Carefully insert the display into the panel cutout, ensuring that all 4 ¼-turn fasteners align with the corresponding holes.

4. Seat the display in the panel cutout. Do not use excessive force while inserting the display.

5. Once seated, rotate all four ¼-turn fasteners clockwise to lock the display to the panel.

6. Configure and test the MFD and/or PFD according to Section 7.1.

6.2 GTX 335R/GTRX 345R Transponder (if installed)

GTX 335R/GTX 345R Removal:

1.

Remove the PFD (reference Section 6.1).

2.

Insert a 3/32” hex drive tool into the access hole in the front of the unit.

3.

Turn hex drive tool counterclockwise until the hex drive tool stops.

4.

Pull the unit from the rack using the spring-loaded tab on the front of the unit.

GTX 335R/GTX 345R Reinstallation:

1.

Visually inspect the connectors in the back of the rack to ensure there are no bent or damaged pins. Repair any damage if found.

2.


3.

Turn hex drive tool counterclockwise until the hex drive tool stops.

4.

Slide the unit in the rack until it stops. The unit will appear to stick out of the rack approximately 3/8”.

5.


6.

Push on the left side of the unit and turn hex drive tool clockwise until it stops. Do not apply more than 8 in-lbs of torque on the hex tool to seat the unit.

7.

Configure and test the GTX 335R or GTX 345R according to Section 7.5.



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6.3 GRS 79 AHRS (if installed)

GRS 79 Removal:

1. Gain access to the aft avionics compartment in the tail of the aircraft.

2. Disconnect the AHRS connector.

3. Turn each retention screw counterclockwise until they disconnect from the remote rack.

4. Gently slide the unit from the remote rack. Do NOT loosen the remote rack hardware fastening it to the avionics shelf or the GRS 79 must be re-calibrated per Section 7.11)

GRS 79 Installation:

1. Visually inspect the connector to ensure there are no bent or damaged pins. Also inspect the pitot and static fittings for damage. Repair any damage.

2. Place the GRS 79 unit on the remote rack and slide the unit back until the feet are fully engaged with the remote rack.

3. Push down and turn each retention screw clockwise. Torque each retention screw to

15-20 in-lbs.

4. Connect the AHRS connector to the unit.

5. Calibrate and test the GRS 79 per Section 7.11.

6.4 GDC 72 ADC (if installed)

GDC 72 Removal:

1. Remove the PFD (Reference Section 6.1)

2. Disconnect the ADC connector.

3. Disconnect the pitot and static lines.

4. Turn the retention screw counterclockwise until it disconnects from the remote rack.

5. Gently slide the unit from the remote rack.

6. Remove the 2 screws holding the endplate mount to the unit and retain for reinstallation.

GDC 72 Installation:

1. Visually inspect the connector to ensure there are no bent or damaged pins. Also inspect the pitot and static fittings for damage. Repair any damage.

2. Attach the GDC 72 Endplate Mount to the unit using 2 #6-32 screws.

3. Place the GDC 72 unit on the remote rack and slide the unit back until the feet are fully engaged with the remote rack.

4. Push down and turn the retention screw clockwise. Torque the retention screw to 15-20 in-lbs.

5. Connect the pitot and static lines.

6. Connect the connector to the unit.

7. Test the GDC 72 per Section 7.7.



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6.5 GDL 69A SXM (if installed)

Removal:

1.

Remove the PFD (reference Section 6.1)

2.

Unlock the GDL 69A SXM handle by loosening the Phillips screw on the handle.

3.

Pull the handle upward to unlock the GDL 69A. Gently remove the unit from the rack.

Reinstallation:

1.

Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage.

2.

Lift the handle and gently insert the GDL 69A SXM into its rack. The handle should engage the dogleg track.

3.

Press down on the GDL 69A SXM handle to lock the unit into the rack.

4.

5.

Lock the handle to the GDL 69A SXM body using the Philips screw. Torque the handle screw to 10-14 in-lbs.

Configure and test the GDL 69A SXM according to Section 7.12.

6.6 GTS 800 Traffic System (if installed)

For removal and reinstallation of the GTS 800 traffic system, refer to the instructions for removing the GTS 820 Traffic System in the applicable maintenance manual listed in Table 1-1.

Configuration Module Removal & Replacement

Configuration modules (Reference Figure 6-1 and Table 6-1, Item 1 shown below) are located in the following LRU harness connector backshells: GDU 1050 PFD. Additionally, the GRS 79 and GDC 72 have different style configuration modules that are located in the connector backshells. Refer to Section 6.7.2 for the GRS 79 and GDC 72 configuration module removal and replacement instructions. Refer to the Master Drawing List, listed in Table 1-1, for specific installation drawings.



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Figure 6-1, Configuration Module Installation

Table 6-1, Configuration Module Kit – 011-00979-00

Garmin Part

Needed

Number

1

2

3

4

Configuration Module PCB Board Assembly w/EEPROM & Temp

Sensor

Spacer, Config Module

Cable, 4-Conductor Harness

Pins, #22 AWG (HD)

1

1

1

5

012-00605-00 or -02

213-00043-00

325-00122-00

336-00021-00

Removal:

1. Disconnect connector from LRU.

2. Remove 2 screws (8) from cover (7) and remove cover.

3. Unplug connector from configuration module (1).

4. Remove configuration module.

Installation:

1. Inspect connector for damaged pins (4).

2. Place configuration module (1) in position.

3. Insert connector into configuration module (1).

4. Assembly of the connector is the reverse of disassembly.

5. Checkout per Section 6.7.3.



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GRS 79 and GDC 72 Configuration Module Removal & Replacement

C O N FIG U R A TIO N M O D U LE

Figure 6-2, GRS 79 and GDC 72 Configuration Module Installation

Table 6-2, GRS 79 and GDC 72 Configuration Module Kit – 011-00979-20

Needed

Number

1

2

3

4

Sub-Assy,Potted,Config Mdl,w/EEPROM,Jackscrew

Cable, 4-Conductor Harness

Pins, #22 AWG (HD)

Pan Head Screw

Removal:

1. Disconnect connector from LRU.

2. Remove 2 screws from cover and remove cover.

3. Unplug the connector from the configuration module.

4. Remove 1 screw from configuration module.

5. Remove the configuration module.

Installation:

1. Inspect connector for damaged pins.

2. Insert the connector into the configuration module.

3. Place configuration module in position.

4. Install 1 screw attaching the configuration module to the backshell.

5. Assembly of the connector is the reverse of the disassembly.

6. Checkout per Section 6.7.3.

1 011-02179-00

1

4

1

325-00122-00

336-00021-00

211-60232-07



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Configuration Module Checkout

If a GRS 79 Configuration Module is replaced:

Configuration settings must be reloaded to the GRS 79 per Section 7.6, then proceed to Section

7.8.3.

Additionally, GRS 79 and GMU 44 calibration procedures must be performed. Proceed to

Section 7.11.

If a GDC 72 Configuration Module is replaced:

Configuration settings must be reloaded to the GDC 72 per Section 7.7, then proceed to Section

7.8.3.

If only the Master (PFD) Configuration Module is replaced:

NOTE

New Terrain/Obstacle databases, Jeppesen Aviation Database and other optional features (i.e. unlock/enablement cards) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old databases and feature enable cards will no longer work as they will remain locked to the old

System ID number.

1. Start the G1000 system in configuration mode.

2. Go to the Configuration Upload Page on the PFD.

3. Press the UPDT CFG softkey and press ENT.

If both the PFD and Master Configuration Module are replaced:

NOTE

New Terrain/Obstacle databases, Jeppesen Aviation Database and other optional features (i.e. unlock/enablement cards) will need to be replaced if the master configuration module is changed. The G1000 System ID number will change to a new number when installing a new master config module. The old databases and feature enable cards will no longer work as they will remain locked to the old

System ID number.

1. The entire G1000 system must be re-configured. Insert the correct G1000 software loader card into the PFD.

2. Start the G1000 in configuration mode. Go to the System Upload Page on the PFD.

3. See Section 3.6 for instructions on how to use the System Upload page. Check all configuration files and reload them.

4. After reloading configuration files, examine the G1000 installation for any installed configuration options. Options are listed in Section 3.6. Load optional files as necessary.

5. Recalibrate the fuel system in accordance with the G58 Maintenance Manual

Supplement or G36 Maintenance Manual Supplement (reference Table 1-1), Chapter

77-40-07.

6. Continue to Section 9 and conduct the return to service checkout.



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6.8 GMA 1360 Audio Panel (if installed)

Removal:

1. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the GMA is unlocked from the rack in the instrument panel.

2. Carefully remove the GMA from its rack.

Reinstallation:

1. Visually inspect the connectors to ensure there are no bent or damaged pins. Repair any damage.

2. Using a 3/32” hex tool, turn the hex nut counter-clockwise until the lock tab stops.

3. Gently insert the GMA into the rack until the locking tab engages the rack.

4. Tighten the hex nut until resistance is felt and the unit stops sliding into the rack. Do not over-tighten the nut.

5. Configure and test the GMA according to Section 7.2.

6.9 GIA 64W Integrated Avionics Unit (if installed)

Removal:

1. Gain access to the tail of the aircraft.

2. Unlock the GIA handle by loosening the Phillips screw on the handle.

3. Pull the handle upward to unlock the GIA. Gently remove the unit from the rack.

Reinstallation:


2. Lift the handle and gently insert the GIA into its rack. The handle should engage the dogleg track.

3. Press down on the GIA handle to lock the unit into the rack.

4. Lock the handle to the GIA body using the Philips screw. Torque the handle screw to

10-14 in-lbs.

6.

Configure and test the GIA(s) according to Section 7.3.



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6.10 GSR 56 Satellite Transceiver (if installed)

Removal:

1. Gain access to the tail of the aircraft.

2. Unlock the unit from the rack by pulling out on the ratcheting latch mechanism and turning counter-clockwise until the latch mechanism clears the tab on the unit.

3. Slide the unit out of the rack.

Reinstallation:


2. Insert the unit into the installation rack.

CAUTION:

Do not use excessive force when inserting the GSR 56 into the rack. This may cause damage to occur to the connectors, unit, and/or unit rack. If heavy resistance is felt during installation, stop! Remove the GSR 56 and identify the source of resistance.

3. Lock the unit into the rack by using the ratcheting latch mechanism.

4. Register with Garmin Connext per Section 7.15.1.

5. No software or configuration loading is required for the GSR 56. Test the GSR 56 according to Section 7.15.2.

6.11 Iridium Antenna (if installed)

Removal:

1. Gain access to the antenna coaxial cable connector in the tail.

2. Disconnect the antenna coaxial cable.

3. Remove the antenna mounting screws.

4. Remove antenna.

Reinstallation:

1. Install antenna using retained mounting screws.

2. Connect the antenna coaxial cable.

3. Fillet seal around antenna.

4. Proceed to Section 7.15.2 for testing of the GSR 56.



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6.12 GEA 71B Engine/Airframe Unit (if installed)

Removal:

1. Gain access to #1 GEA by removing the MFD (see Section 6.1).

2. Gain access to #2 GEA by removing the retaining bracket. Unit is mounted vertically behind the glove box on the copilot side. Access to the unit is from underneath the instrument panel.

3. Unlock the GEA handle by unscrewing the Phillips screw.

4. Firmly grasp the GEA handle and pull it. This unlocks the unit from the rack.

5. Gently remove the GEA from its rack.

Reinstallation:


2. Lift the handle and gently insert the GEA into the rack. The handle should engage the dogleg track.

3. Press on the handle to lock the unit into place.

4. Lock the handle to the GEA body using the Philips screw. Torque the handle screw to

10-14 in-lbs.

5. Reinstall the MFD for #1 GEA.

6. Reinstall the retaining bracket for #2 GEA.

7. Configure and test the GEA according to Section 7.4.

6.13 FS 510 Wifi/Bluetooth Data Link (if installed)

Removal:

1.

2.

FS 510 card is installed in the bottom slot of the MFD.

Press the edge of the card and release to remove card.

Reinstallation:

1.

Insert FS510 card in the bottom slot of the MFD.



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6.14 GSA 81 Servo Actuator (if installed)

Removal:

1. Gain access to the desired servo(s).

2. Disconnect the servo harness connector.

3. Use a socket or open-wrench to loosen and remove the servo attachment bolts.

4. Carefully remove the servo and place a protective cover on the output gear.

5. Place a protective cover over the GSM 86 servo gearbox.

Reinstallation:

1. Inspect the servo output gear for abnormal wear.

2. Using a lint-free cloth, remove excess grease build-up from the servo output gear (see

Figure 6-1.)

IMPORTANT!

It is not necessary to remove all of the grease from the output gear, only the excess grease. DO NOT USE SOLVENTS TO CLEAN THE OUTPUT GEAR!

3. Using a brush or other applicator, apply a thin coat of Aeroshell 33MS (Lithium-complex based) grease to the servo output gear.

Figure 6-3, Servo Gear

4. Carefully place the servo into the servo gearbox, ensuring proper orientation and alignment.

5. Fasten the servo to the servo gearbox using the existing hardware. Follow the installation instructions provided in the respective servo installation drawing(s) listed in

Table 1-1.

6. Inspect the harness connectors and check that no pins are bent or otherwise damaged.

Connect the harness and secure it appropriately.

7. Configure and test the GSA according to Section 7.13.



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6.15 GSM 86 Servo Gearbox (if installed)

Removal:

1. Remove the desired servo(s) per Section 6.12.

2. Disconnect the servo cables from the flight control system.

3. Use a socket or open-wrench to loosen and remove the servo gearbox attachment bolts.

4. Carefully remove the servo gearbox(es).

5. Remove the cable retention pins and top ring and then remove the servo cable from the capstan.

Reinstallation:

1. Follow the installation instructions provided in the respective servo installation drawing(s) listed in Table 1-1 to reinstall the servo cable and servo gearbox.

2. If no other maintenance is to be performed, reinstall the servo(s) per Section 7.13.

6.16 GWX 75 Weather Radar (if installed)

Removal:

1. Gain access to the GWX by removing nose cone.

2. Disconnect backshell assembly from GWX unit.

3. Use a 3/16” hex drive tool to remove each of the four mounting screws.

Reinstallation:

1. Inspect connector for damaged pins.

2. Hold the GWX unit flush with the radar mount.

3. Use a 3/16” hex drive tool to tighten each of the four mounting screws.

4. Connect backshell assembly to the GWX unit.

Configure and test the GWX according to Section 7.16.



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7. Garmin G1000 LRU Replacement/Configuration & Testing

This section provides procedures to be followed after a piece of G1000 equipment is replaced.

At the beginning of each LRU section, instructions are given to guide the technician for various removal/replacement scenarios. These instructions define necessary procedures to be followed for situations where original equipment was reinstalled as well as for situations where new equipment (new serial number) is installed.

NOTE

Only SanDisk brand SD cards are recommended for use with the G1000 system.

Other brand cards have not been tested for use with the G1000 system.

CAUTION

Connect a ground power unit to the aircraft for software loading. DO NOT

RELY ON THE AIRCRAFT BATTERY TO LOAD SOFTWARE. DO NOT USE A

BATTERY CHARGER AS AN EXTERNAL POWER SOURCE DUE TO

ELECTRICAL NOISE IT MAY INJECT IN THE G1000 SYSTEM. DO NOT

ALLOW POWER TO BE REMOVED FROM THE SYSTEM WHEN LOADING

SOFTWARE! Remove power only when told to do so by the following procedure.

Power loss during a software upgrade may cause a LRU to become corrupted and unresponsive requiring replacement. Remove power only when told to do so in the procedure.

All displays should be in the same mode (configuration or normal), unless instructed differently.

If an incorrect configuration file is loaded at any time in this section, STOP and start the configuration load over using Section 3.6.

7.1 GDU 1050 PFD & GDU 1055 MFD

Original Display Reinstalled

If the removed display(s) are re-installed in their original positions, no software or configuration loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the PFD/MFD

Test procedure, Section 7.1.5.

Original Displays Installed in Opposite Locations for Troubleshooting

If the PFD and MFD are installed in opposite positions, no software or configuration loading is required. Continue to the PFD/MFD Test procedure, Section 7.1.5. Units must be returned to their original positions after troubleshooting is complete.

New Repair or Exchange Display(s) Installed

If a new, repaired or exchanged GDU is installed, the correct software and configuration files must be loaded to the unit.



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LRU Replacement Procedure PFD


2. Remove SD cards from top and bottom slots of the MFD and PFD if present.

3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft and avionics electrical busses.

4. Turn on Avionics/electrical busses.

5. Power on the MFD and PFD in configuration mode.

6. Using the MFD, scroll to the LRU replacement page.

7. Activate the cursor and select PFD in the LRU dropdown box.


9. Press the softkey

.

10. Press

ENT

to acknowledge the process was complete.


12. Scroll to the Configuration Manager page.

13. Press the

CNFM CFG

softkey.

14. Select ok when prompted to “Confirm configuration as expected configuration”

15. Power cycle the system verify there are no red-Xs or system alerts.

16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 3.6.

17. If there are no red-Xs or system alerts, continue to Section 7.1.5.

Legacy Replacement Procedure PFD (Alternate Method)

A full system configuration re-load is required when a new, repaired, or exchanged display is installed using this method. This includes all options and feature enablements.

To complete this procedure, continue to Section 3.6.

LRU Replacement Procedure MFD

NOTE

Anytime the MFD is replaced, all databases must be reloaded.


2. Remove SD cards from top and bottom slots of the MFD and PFD if present.


4. Turn on Avionics electrical busses.


6. Using the PFD, scroll to the LRU replacement page.

7. Activate the cursor and select MFD in the LRU dropdown box.



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.

10. Press

ENT




13. Press the

CNFM CFG

softkey.



16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 3.8.

17. Install databases as directed in Section 3.14.

18. After databases are re-loaded, continue to Section 7.1.5.

Legacy Replacement Procedure MFD (Alternate Method)

A full system configuration re-load is required when a new, repaired, or exchanged display is installed using this method. This includes all options and feature enablements. To complete this procedure, perform Section 3.6.

1. Allow displays to initialize for ~1 minute.

2. Check that all COM/NAV display fields are valid in the top corners of both PFDs.

3. Check that attitude, heading, altitude, airspeed, vertical speed and OAT fields are valid within 2 minutes of power up on both PFDs.

4. Check that the engine instrument fields are valid on the MFD.

Figure 7-1, G1000 Normal Mode Check

5. Push the red DISPLAY BACKUP button on the GMA. Verify that the PFD and MFD displays enter reversion mode. MFD should have valid altitude, airspeed, vertical speed,

COMM1, COMM2, NAV1, NAV2 and engine instruments.

6. De-activate pilot-side reversion mode by pushing the DISPLAY BACKUP button. Verify the PFD and MFD return to normal display modes.



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7. Select the page on the MFD.

8. Verify that the title at the top of the page reads “Map – TAWS-B”. If TAWS has not been enabled, the title will read “

Map – Terrain Proximity

” or “

Map – Terrain

”.

9. Press the MENU button and select “Test TAWS” from the pop-up menu.

10. After the TAWS test has completed, verify that “TAWS System Test Okay” is heard over the cockpit speaker.

11. If no other service is to be performed, perform final return-to-service test as specified in

Section 9.

7.2 GMA 1347 or GMA 1360 Audio Panel

Original GMA 1347 or GMA 1360 Reinstalled

No software/configuration loading or testing is required if the removed GMA is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the final return-to-service checks in

Section 9.

New, Repaired or Exchange GMA 1347 or GMA 1360 Installed

If a new, repaired or exchanged GMA is installed, the correct software and configuration files must be loaded to the unit. See Section 7.2.1.

LRU Replacement Procedure GMA


2. Remove Garmin SD/MMC/FS 510 cards from bottom slots of the MFD and PFD if present.





7. Activate the cursor and select GMA1 in the LRU dropdown box



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.



16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.2.2.



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Legacy Replacement Procedure GMA (Alternate Method)

To load the GMA complete the following subsections in order as they apply to the aircraft.

Baseline Configuration

1. Insert the software loader card in the top slot of the PFD.


3. Select no when “Do you want to update system files” is displayed on the screen of the

PFD.

4. Select the “

SYSTEM UPLOAD

” page using the small FMS knob on PFD.

5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the small FMS knob to highlight “

Beechcraft G58” or “Beechcraft G36”

(as applicable) and press

ENT

key on the PFD.

6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight

“Beechcraft A36/G36 – Baseline Configuration” or “Beechcraft B58/G58

– Baseline Configuration”

(as applicable).

Press

ENT

key on the PFD.


8. Use the large FMS knob to scroll to GMA.

9. Highlight the software box and press the

ENT

key.

10. Highlight the Configuration box and press the

ENT

key.

11. Press “

Load

” softkey.


13. Green “PASS” in the Configuration and Software columns for each item loaded.

14. “Upload Complete………….”COMPLETE” in the summary box.

15. Acknowledge the prompt by pushing the

ENT

key.

Option – KN63 DME Installation (For GMA replacement and aircraft equipped with a DME only)

1. Scroll the cursor to the ITEM window highlight

“Option – KN63 DME Installation”

and press the

ENT

key on the PFD.


3. Scroll the cursor to GMA and press the

ENT

key to check the box.

4. Press softkey.







“Upload Complete………….”COMPLETE” in the summary box.


ENT

key.



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Configuration Manager Update

1. With the system still in configuration mode, scroll to the Configuration Manager page on the PFD.




5. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 .


GMA 1347 or GMA 1360 Test

Except for marker beacon operation, an in-aircraft checkout may be performed in the aircraft with a known good microphone, headset, and speaker.

Intercom System (ICS) Check

1. Ensure that the MAN SQ key is off (no light).

2. Ensure that PILOT and COPLT ICS ISOLATION are off (no light).

3. Adjust GMA ICS volume to a comfortable level.

4. Plug in a headset at each COCKPIT position. One at a time, plug a headset into each left and right CABIN ICS jack location (if installed) (one headset on right, one headset on left).

5. Verify that there is two-way communications between all jack positions.

6. On GMA select COM1 MIC and AUDIO.

7. Verify an active (green) COM1 frequency is displayed on the PFD.

8. On the GMA, select PA and verify the PA select annunciator is illuminated on GMA.

Verify COM1 active frequency is displayed white.

9. Initiate passenger address using pilot’s headset boom mic by keying the pilot’s PTT.

Verify the following:



Clear PA audio can be heard over cabin speaker and headsets



PA selected annunciator on GMA flashes ~ once per second during PA address.

10. Repeat Step 8 using hand mic.

11. Initiate passenger address using copilot’s headset boom mic by keying the copilot’s PTT.

Verify the following:



Clear PA audio can be heard over cabin speaker and headsets



PA selected annunciator on GMA flashes ~ once per second during PA address.



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Transceiver Operational Check

Perform a ramp test radio check by exercising the installed transceivers, microphone, microphone key and audio over the headphones and speaker. Verify that communications are clear and PTT operation is correct for each pilot position.

1. On the pilot’s audio panel, select the audio source corresponding to each installed avionics unit (i.e. NAV1, NAV2, COM1, COM2, ADF and DME) and check for audio over the pilot’s headset.

2. Press the SPKR key on pilot’s audio panel and verify that the selected audio is heard over the pilot’s speaker.

Failsafe Operation Check – GMA

1. Turn the GMA off by pulling the AUDIO/MKR circuit breaker. This directs all COM 1 phone audio, MIC audio and MIC key to the pilot’s position.

2. Check the failsafe operation by exercising the COM 1 boom mic, hand mic, microphone key and audio over the headphones. All volume control for the COM audio should be through the PFD volume control. Verify proper operation of COM 1 using the failsafe operation.

3. Close the AUDIO/MKRcircuit breaker to continue testing.

1. Using a ramp tester, simulate the outer marker, middle marker, and inner marker signals by following the test equipment manufacturer’s instructions. Verify that each marker audio signal is present over the pilot and co-pilot headphones and speaker.

2. Verify that the outer, middle, and inner annunciations appear on PFD when the corresponding signal is applied. Marker beacon annunciations ( , , and ) appear at the upper left corner of the altitude indicator on the PFD. Operate the MKR MUTE key on the GMA and ensure that the audio signal is muted.

3. If no other service is to be performed, continue to the return-to-service checks in Section

9.



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7.3 GIA 63W or GIA64W Integrated Avionics Unit

Original GIA 63W or GIA 64W Reinstalled

No software or configuration loading is required if the removed GIA is re-installed in its original position (GIA1 and GIA2 in their original racks). This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process.

Continue to the return-to-service checks in Section 9.

Original GIA 63W or GIA 64W Swapped for Troubleshooting

No software loading is required if the originally installed GIA units are re-installed in opposite positions (GIA1 and GIA2 in opposite unit racks). However, configuration loading is required.

See Section 7.3.1.

New, Repaired or Exchange GIA 63W or GIA 64W Installed

If a new, repaired or exchange GIA is installed, the correct software and configuration files must be loaded to the unit. See Section 7.3.1.

LRU Replacement Procedure GIA1 or GIA2



3. Apply power to the G1000 system by connecting external power to the aircraft to energize the aircraft.




7. Activate the cursor and select GIA1 or GIA2, whichever was replaced in the LRU dropdown box.



.

10. Press

ENT


11. Select Com1 or 2 (as applicable) in the LRU dropdown box.

12. Press the

CHK All

softkey.

13. Press the

Load

softkey

.

14. Press

ENT


15. Select GPS1 or 2 (as applicable) in the LRU dropdown box.

16. Press the

CHK All

softkey.

17. Press the

Load

softkey

.

18. Press

ENT


19. Select Nav1 or 2 (as applicable) in the LRU dropdown box.

20. Press the

CHK All

softkey.

21. Press the

Load

softkey

.

22. Press

ENT




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25. Press the

CNFM CFG

softkey.




29. If there are no red-Xs or system alerts, continue to Section 9.

Legacy Replacement Procedure GIA1 or GIA2 (Alternate Method)

To load the GIA complete the following subsections in order as they apply to the aircraft.

Baseline Configuration (For GIA 1 or GIA 2 replacement)



3. Select no when “Do you want to update system files” is displayed on the screen of PFD.

4. Select the “

SYSTEM UPLOAD

” page using the small FMS knob on the PFD.

5. Activate the cursor and rotate the small FMS knob to display the drop down menu.

Rotate the large FMS knob to highlight

“Beechcraft G36” or “Beechcraft G58”


ENT

key on the PFD.



– Baseline Configurations”

(as applicable).

Press

ENT

key on the PFD.


8. Use the large FMS knob to scroll to GIA 1 or GIA 2, whichever was replaced.


ENT



ENT


11. Use the large FMS knob to scroll to GIA 1 – Region Config or GIA 2 – Region Config, whichever was replaced.


ENT


13. Use the large FMS knob to scroll to NAV 1 or NAV 2, whichever was replaced.


ENT


15. Use the large FMS knob to scroll to COM 1 or COM 2, whichever was replaced.


ENT


17. Highlight the configuration box and press the

ENT


18. Use the large FMS knob to scroll to GPS 1 or GPS 2, whichever was replaced.


ENT

key to check the box

20. Use the large FMS knob to scroll to GIA 1 Audio or GIA 2 Audio, whichever was replaced.



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ENT


22. Scroll to GIA Audio Config.


ENT


24. Scroll to GIA Gains.

25. Highlight the Software box and press the

ENT


26. Press “

Load

” softkey.









ENT

key.

GDC and GRS GIA Configuration (For GIA 1 or GIA 2 replacement)

NOTE

The aircraft will be equipped with a either a GRS 79 AHRS and a GDC 72 ADC or a GRS 77 AHRS and a GDC 74A ADC.

Only load the files applicable to the aircraft.

1. Scroll the cursor to the Group window and select

“G36 Options” or “G58 Options”

(as applicable)

.

2. Press the key.

3. In the ITEM window highlight one of the following:

“Baseline Option – GRS 79

Installation” or “Baseline Option – GDC 72 Option” or “Baseline Option – Legacy –

GRS 77 Installation” or “Baseline Option – Legacy – GDC74 Installation”

(as applicable) and press the

ENT

key on the PFD.


5. Scroll the cursor to GIA1 or GIA 2 configuration box, whichever was replaced, and press the

ENT


6. Press softkey.









ENT

key.

9. Repeat steps 3 through 8 for the second sensor.



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Transponder GIA Configuration (For GIA 1 or GIA 2 replacement)

1. In the ITEM window highlight either

“Baseline Option – GTX 335 Installation” or

“Baseline Option – GTX 345 without GTS 800 Installation” or “Baseline Option –

GTX 345 with GTS 800 Installation” or “Baseline Option – Legacy – GTX 33 ES

Installation”


ENT

key on the PFD.


3. Scroll the cursor to GIA1 or GIA 2 configuration box, whichever was replaced, and press the

ENT


4. Press softkey.









ENT

key.

DME GIA Configuration (For GIA 2 replacement and aircraft equipped with a

DME only)


“Option – KN63 DME Installation”

and press the

ENT

key on the PFD.


3. Scroll the cursor to GIA 2 configuration box, and press the

ENT


4. Press softkey.









ENT

key.



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Traffic System GIA Configuration (For GIA 1 or GIA 2 replacement and aircraft equipped with a Traffic system only)

1. Scroll the cursor to the ITEM window and highlight

“Option – GTS 800 without GTX

345 Installation” OR “Option – GTS 800 with GTX 345 Installation” OR “Option –

SKY497 Skywatch Installation” or “Baseline Option – Legacy – GTS 820 without

GTX 345 Installation” OR “ Baseline Option – Legacy – GTS 820 with GTX 345

Installation”


ENT

key on PFD.


3. Scroll the cursor to GIA 1 or GIA 2 configuration box, whichever was replaced, and press the

ENT


4. Press softkey.









ENT

key.

Stormscope GIA Configuration (For GIA 2 replacement and aircraft equipped with a WX500 system only)


“Option – WX500 Installation”

and press the

ENT

key on the PFD.


3. Press softkey.









ENT

key.




3. Select ok when prompted to “Confirm configuration as expected configuration”.



6. If there are no red-Xs or system alerts, continue to Section 9.



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GPS Signal Acquisition

Figure 7-2, Aux – GPS Status Page (MFD)

The GIA units should normally acquire a GPS navigation solution within 5 to 10 minutes of startup, provided the aircraft is outside (or indoors with a GPS repeater). Select the

Aux – GPS

Status

page on the MFD. Two softkeys on the bottom of the display allow the user to toggle between GPS 1 and GPS 2. Verify that both receivers show 3D DIFF NAV on the MFD.

NOTE

It may be necessary to temporarily disable or move away from GPS repeaters while testing, as repeaters may adversely affect GPS receiver performance.

VHF COM Interference Test

This test must be conducted outside. Use of a GPS repeater inside a hangar may result in a failed test. This procedure assumes that the system is currently set to 25 kHz COM channel spacing. Once the signal acquisition test has been completed successfully, perform the following steps:

1. On the MFD, monitor GPS signal strength bars on the


page.

2. On the PFD, ensure that the CDI is set to GPS. If it is not, press the ‘CDI’ softkey until

GPS ENR is displayed.

3. Verify that the GPS “INTEG” flag is out of view.

4. Select 121.150 MHz on the No. 1 COM transceiver.

5. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels.

6. During the transmit period, verify that the GPS “INTEG” flag does not come into view on the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD.



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7. Repeat steps 5 and 6 and re-transmit while monitoring GPS 2 signal levels on the MFD.

8. Repeat steps 4 through 7 for each of the following frequencies:



121.175



121.200



131.250



131.275



131.300

9. Repeat steps 4 through 8 for the No. 2 COM transceiver (GIA2).

10. On the MFD, select the

Aux – System Setup

page.

11. Under the COM CONFIG field, change the COM channel spacing from 25 kHz to 8.33 kHz.

12. Go back to the


page.

13. Select 121.185 MHz on the No. 1 COM transceiver.

14. Transmit for a period of 35 seconds while monitoring GPS 1 signal strength levels.

15. During the transmit period, verify that the GPS “INTEG” flag does not come into view on the PFD and verify that GPS 1 does not lose a 3-D navigation solution on the MFD.

16. Repeat steps 14 and 15 and re-transmit while monitoring GPS 2 signal levels on the

MFD.

17. Repeat steps 14 through 16 for each of the following frequencies:



121.190



130.285



131.290

18. Repeat steps 14 through 17 for the No. 2 COM transceiver (GIA2).

19. On the MFD, select the

Aux – System Setup

page and change the COM channel spacing back to 25 kHz.

Check the VOR, ILS, and Glideslope functions with ramp test equipment. Operate the equipment according to the test equipment manufacturer’s instructions. Adjust the RF signal to a level adequate to perform the test. Select the appropriate HSI source by using the CDI softkey.

NOTE

The PFD HSI does not show a course deviation bar unless a valid VHF NAV frequency is tuned.



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GFC 700 VOR/LOC/GS Test (if GFC 700 is installed)

1. Simulate a VOR signal on a radial equivalent to the aircraft heading. Tune the NAV 1 and NAV 2 receivers to the simulation frequency.

2. Set the HSI on the PFD to VOR1 by pressing the CDI softkey until VOR1 is selected.

Rotate CRS knob to set VOR1 course pointer to aircraft heading.

3. Verify full scale deflection of VOR1 CDI by varying CRS1 selected course at least 10° left and right. Reset course pointer to aircraft heading.

4. Engage the autopilot and press the NAV key on the AFCS mode controller. Using the

CRS knob alter course by 10° to the right. Verify the flight director and aircraft controls respond by flying to the VOR course. Repeat to the left.

5. Set CRS course pointer to aircraft heading.

6. Simulate a Localizer/Glideslope signal. Tune this signal on NAV 1 and NAV 2 receiver.

Set the PFD HSI to LOC1 by pressing CDI softkey until LOC1 is selected. Use the test equipment to center the deviation bars (localizer and glideslope) on the PFD.

7. Press the APR key on the AFCS mode controller. Verify that the LOC and PIT annunciations are green and ALTS and GS are white on the PFD. Apply right/left and up/down localizer/glideslope signals using the test equipment. Verify that the Flight

Director and flight controls respond appropriately.


9.



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7.4 GEA 71 or GEA 71B Engine/Airframe Unit

Original GEA 71 or GIA 71B Reinstalled

No software or configuration loading is required if the removed GEA is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the return-to-service checks in Section 9.

Original GEA 71 or GEA 71B Swapped for Troubleshooting (applicable to G58 only)

No software loading is required if the originally installed GEA units are re-installed in opposite positions (GEA1 and GEA2 in opposite unit racks). However, configuration loading is required.

See Section 7.4.1.

New, Repaired or Exchange GEA 71 or GEA 71B Installed

If a new, repaired or exchange GEA is installed, the correct software and configuration files must be loaded to the unit. See Section 7.4.1.

LRU Replacement Procedure GEA







7. Activate the cursor and select GEA1 or GEA2 as applicable in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.



16. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5 or reload the system using the legacy method in Section 7.4.2




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Legacy Replacement Procedure GEA (Alternate Method)

To load the GEA complete the following subsections in order as they apply to the aircraft.

GEA Configuration (For GEA replacement)




4. Select the “

SYSTEM UPLOAD


5. Activate the cursor and rotate the small FMS knob to display the drop down menu.

Rotate the large FMS knob to highlight



ENT

key on the PFD.



– Baseline Configuration”

(as applicable) and Press

ENT

key on the PFD.


8. Use the large FMS knob to scroll to GEA 1 or GEA 2 as applicable.


ENT



ENT


11. Press “

Load

” softkey.









ENT

key.







6. If there are no red-Xs or system alerts, test the GEA per Section 7.4.3.



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On the MFD (normal mode), check the indication for each of the sensor or monitor inputs with the aircraft engines off.

In general, verify all engine and system instruments show valid static normal values and markings, with no red Xs or erratic indications. Reference Figure 7-3 for normal engine instrument markings (figure may not reflect actual aircraft installation). If individual engine readings do not appear normal or have a red-X over them, refer to the appropriate G1000

Line/System Maintenance Manual (refer to Section 1.1).

Figure 7-3, Normal Engine Instrument Markings (MFD) (G58 Shown, G36 similar)

If no other service is to be performed and individual GEA input testing is not required, continue to the return-to-service checks in Section 9.



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7.5 GTX 335R, GTX 345R, or GTX 33 Transponder

Original GTX is Reinstalled

No software or configuration loading is required if the removed GTX 335R, GTX 345R, or GTX

33 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to GTX 335R, GTX

345R, or GTX 33 Test Section 7.5.4.

New, Repaired or Exchange GTX is Installed

If a new, repaired or exchange GTX 335R, GTX 345R, or GTX 33 is installed, the correct software and configuration files must be loaded to the unit. See Section 7.5.1.

LRU Replacement Procedure GTX1







7. Activate the cursor and select GTX1 in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.





Legacy Replacement Procedure GTX (Alternate Method)




PFD.

4. Select the “

SYSTEM UPLOAD




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5. Activate cursor and rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight



ENT

key on the PFD.


“Baseline Option – GTX 335 Installation” OR “Baseline Option – GTX

345 without GTS 800 Installation” or “Baseline Option – GTX 345 with GTS 800

Installation” or “Baseline Option – Legacy – GTX 33 ES Installation”

(as applicable).

Press

ENT

key on the PFD.


8. Use the large FMS knob to scroll to GTX.

9. Highlight the software box(es) and press the

ENT



ENT


11. Press “

Load

” softkey.









ENT

key.



16. Press the

CNFM CFG

softkey.



19. If red-Xs or system alerts are present, troubleshoot as necessary using Section 5.


1. If not applied, apply power to the G1000 system and put all displays into config mode.

2. On the PFD, select the AIRCRAFT CONFIGURATION page.

3. For GTX 33 unit replacement only, press the Set GTX #1 softkey and acknowledge the

PFD prompt by pressing the ENT key. GTX 335R and 345R units automatically save the registration number, no action is needed for these units.




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Figure 7-4, Aircraft Registration

GTX 335R, GTX 345R, or GTX 33 Test

Operation of the GTX 335R, GTX 345R, or GTX 33 Mode-S transponder is accomplished using the PFD or the MFD. Refer to the G36 or G58 G1000 Cockpit Reference Guide (as applicable), listed in Table 1-1, for basic operation.

The integrated transponder/altitude reporting system must be verified in accordance with Title

14 of the Code of Federal Regulations (14 CFR) §§ 91.411 and 91.413,

every 24 calendar months

, or any time the transponder is removed. This test requires the use of a Mode S ramp generator. Specific instructions for operating the ramp tester are contained in the applicable operator's manual. Refer to 14 CFR Part 43 Appendices E and F for testing criteria.

If no other service is to be performed, continue to the return-to-service checks in Section 9.



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Original GRS unit is Reinstalled

No software or configuration loading is required if the removed GRS 79 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to Section 9.

New, Repaired or Exchange GRS unit is Installed

If a new, repaired or exchange GRS unit is installed, the correct software and configuration files must be loaded to the unit.

New GRS 79 Configuration Module is Installed

The correct configuration files must be loaded if the GRS 79 configuration module has been replaced.

LRU Replacement Procedure GRS







7. Activate the cursor and select GRS1 in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.




17. If there are no red-Xs or system alerts, continue to Section 7.11.5 for GRS testing.



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Legacy Replacement Procedure GRS (Alternate Method) (if installed)




4. Select the “

SYSTEM UPLOAD





ENT

key on PFD.


“Baseline Option – GRS79 Installation”

.

Press

ENT

key on PFD.


8. Use the large FMS knob to scroll to GRS 1.


ENT



ENT


11. Press “

Load

” softkey.









ENT

key.



16. Press the

CNFM CFG

softkey.




20. If there are no red-Xs or system alerts, continue to Section 7.11.5 for GRS testing.



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7.7 GDC 72 ADC (if installed)

Original GDC unit is Reinstalled

No software or configuration loading is required if the removed GDC 72 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Perform a pitot - static system leak check and continue to Section 9.

New, Repaired or Exchange GDC unit is Installed

If a new, repaired or exchange GDC unit is installed, the correct software and configuration files must be loaded to the unit.

New GDC 72 Configuration Module is Installed

The correct configuration files must be loaded if the GDC 72 configuration module has been replaced.

LRU Replacement Procedure GDC







7. Activate the cursor and select GDC1 in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.




17. If there are no red-Xs or system alerts, continue to Section 7.8.3 for testing.



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Legacy Replacement Procedure GDC (Alternate Method) (if installed)




4. Select the “

SYSTEM UPLOAD





ENT

key on PFD.


“Baseline Option – GDC72 Installation”

.

Press

ENT

key on PFD.


8. Use the large FMS knob to scroll to GDC 1.


ENT



ENT


11. Press “

Load

” softkey.









ENT

key.



16. Press the

CNFM CFG

softkey.




20. If there are no red-Xs or system alerts, continue to Section 7.8.3 for the air data checks.

7.8 GDC 74A Air Data

Original GDC unit is Reinstalled

No software or configuration loading is required if the removed GDC 74 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Perform a pitot - static system leak check and continue to Section 9 if no other service is performed.

New, Repaired or Exchange GDC unit is Installed

If a new, repaired or exchange GDC unit is installed, the correct software and configuration files must be loaded to the unit.



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New GDC 74A Configuration Module is Installed

The correct configuration files must be loaded if the GDC 74A configuration module has been replaced.

LRU Replacement Procedure GDC 74A (if installed)







7. Activate the cursor and select GDC1 in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.







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Legacy Replacement Procedure GDC 74A (Alternate Method) (if installed)




PFD.

4. Select the “

SYSTEM UPLOAD





ENT

key on the PFD.


“Baseline Option – Legacy –GDC 74 Installation”

.

Press

ENT

key on the

PFD.


8. Use the large FMS knob to scroll to GDC.


ENT



ENT


11. Press “

Load

” softkey.









ENT

key.



16. Press the

CNFM CFG

softkey.





Air Data Test (GDC 72 or GDC 74A)

The G1000 system must be maintained in accordance with the G1000 System Maintenance

Manual listed in Table 1-2 and appropriate regulations. When the GDC unit is tested in accordance with 14 CFR Part 43, Appendix E, note the following exceptions:



Do not perform paragraph (b)(1)(iv) Friction



Do not perform paragraph (b)(1)(vi) Barometric Scale Error

The following Air Data Test is to be performed in addition to or in conjunction with any other regulated tests. This test must be performed with a calibrated Air Data Test Set (ADTS) with a combined accuracy/repeatability specification of less than ±20 feet for the test altitude range.



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1. Perform pitot static system leak check as described in Chapter 34 of the appropriate

Beechcraft Maintenance Manual (refer to Table 1-1 for Manual details)

2. Connect the pitot/static tester to the aircraft pitot and static ports.

3. Verify that the PFD altimeter baro setting is set to 29.92 in Hg (1013.25 mb).

4. Start the PFD in configuration mode and navigate to the GRS page. The values for altitude and airspeed are shown on the AHRS/AIR DATA INPUT table as B ALT and IAS for AIR DATA 1.

5. Simulate the altitudes shown in Table 7-1. Wait for ADTS to report that target values have been achieved.

6. On Table 7-1, record the altitude (B ALT) displayed on the PFD for AIR DATA 1 for each altitude.

7. Simulate the airspeeds shown in Table 7-1

8. On Table 7-2, record the airspeed (IAS) displayed on the PFD for AIR DATA 1 for each airspeed.

9. Verify that the indicated altitudes and airspeeds are within allowable tolerances.

10. File the results with the aircraft maintenance records.

If either the pilot or copilot air data system does not meet the tolerances specified, have maintenance checks performed on the air data system or the pitot/static system.

Table 7-1, Altitude Test Points

Test Set Altitude

PFD Altitude Reading

(from B ALT field)

Allowed Tolerance

Table 7-2, Airspeed Test Points

Test Set Airspeed

PFD Airspeed Reading

(from IAS field)

Allowed Tolerance



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Static Port Vertical Speed (Rate of Climb) Test

1. Command ADTS to change the altitude at the rates shown in the table below.

2. Wait for ADTS to report that target rates have been achieved.

3. Verify that the Rate of Climb reported by the Vertical Speed field on the PFD are within the tolerances specified in Table 7-3.

Table 7-3, Vertical Speed Table

Vertical Speed, feet/minute Allowed tolerance, ±feet/minute

2000 100

1000 50

500 45

200 45

0 N/A (No VS Display)

-200 45

-500 45

-1000 50

-2000 100

OAT Probe Check

1. Ensure the outside air temperature (OAT) probes and a calibrated thermometer stabilize at ambient temperature.

2. Verify that the OAT measurement shown on the PFD, in degrees Celsius, indicate within

2 °C of the ambient temperature as measured by the calibrated thermometer.




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Original GRS is Reinstalled

If the original GRS is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process.

If the GRS rack was not removed or loosened, continue to the GRS/GMU Test Section 7.11.5.

If the GRS rack was removed or loosened, continue to the GRS/GMU Calibration Procedures

Section 7.11.

New, Repaired or Exchange GRS is Installed

If a new, repaired or exchange GRS is installed, then software must be loaded.

New GRS Configuration Module is Installed

If the GRS configuration module is replaced, no software loading is required. Continue to the

GRS/GMU Calibration Procedures Section 7.11.

LRU Replacement Procedure GRS 77 (if installed)







7. Activate the cursor and select GRS1 in the LRU dropdown box.

8. Verify all boxes are checked. If they are not checked, press the

CHK All

softkey.


.

10. Press

ENT




13. Press the

CNFM CFG

softkey.




17. If there are no red-Xs or system alerts and the GRS rack(s) were not removed or loosened, continue to the GRS/GMU Test Section 7.11.5.

18. If there are no red-Xs or system alerts and the GRS rack(s) was removed or loosened, continue to the GRS/GMU Calibration Procedures Section 7.11.



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Legacy Replacement Procedure GRS 77 (Alternate Method) (if installed)




PFD.

4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD.



(as applicable) and press ENT key on the PFD.


“Baseline Option – Legacy – GRS77 Installation”

. Press ENT key on the

PFD.


8. Use the large FMS knob to scroll to GRS 1.

9. Highlight the software box and press

ENT

.

10. Press “

Load

” softkey.








12. Acknowledge the prompt by pushing the ENT key.



15. Press the CNFM CFG softkey.




17. If there are no red-Xs or system alerts and the GRS rack(s) were not removed or loosened, continue to the GRS/GMU Test Section 7.11.5.

18. If there are no red-Xs or system alerts and the GRS rack(s) was removed or loosened, continue to the GRS/GMU Calibration Procedures Section 7.11.



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7.10 GMU 44 Magnetometer

Original GMU 44 is Reinstalled

If the original GMU 44 is reinstalled, then no software loading is required. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GRS/GMU Test Section 7.11.5.

New, Repaired or Exchange GMU 44 is Installed

If a new, repaired or exchange GMU 44 is installed, then software must be loaded.

LRU Replacement Procedure GMU







7. Activate the cursor and select GMU1 in the LRU dropdown box.

8. Verify all boxes are checked. If they are not checked, press the

CHK All

softkey.


.

10. Press

ENT




13. Press the

CNFM CFG

softkey.




17. If there are no red-Xs or system alerts, continue to Section 7.11.

Legacy Replacement Procedure GMU (Alternate Method)




PFD.

4. Select the “SYSTEM UPLOAD” page using the small FMS knob on the PFD.



(as applicable) and press ENT key on the PFD.



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6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob to highlight either

“Baseline Option – GRS79 Installation” or “Baseline Option –

Legacy – GRS77 Installation”

as applicable. Press ENT key on the PFD.

7. Press the CLR ALL softkey.

8. Scroll to GMU.

9. Highlight the Software box.

10. Press the

ENT

key.

11. Press “

Load

” softkey.








13. Acknowledge the prompt by pushing the ENT key.



16. Press the CNFM CFG softkey.




20. If there are no red-Xs or system alerts, continue to Section 7.11.

7.11 GRS/GMU Calibration Procedures

GRS/GMU Recalibration Criteria

The following calibration procedures are provided for the GRS and GMU 44:



Pitch/Roll Offset: (Procedure A1, PROVIDED IN SECTION 7.11.1)



Magnetometer Calibration: (Procedure B, PROVIDED IN SECTION 7.11.3)



Engine Run-Up Vibration Test: (Procedure D, PROVIDED IN SECTION 7.11.4)



Magnetometer Interference Test: (Procedure E, PROVIDED IN SECTION 5.14.4)

Follow the steps given for each procedure on-screen at the GRS/GMU CALIBRATION page.

Note that the CALIBRATE command cannot be selected and activated until the installer acknowledges all required steps have been carried out by pressing the ENT key on each step.



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Table 7-4, Required GRS/GMU Calibrations

Condition

GMU 44 was removed and reinstalled. (no change in serial number)

GMU 44 was replaced with new unit.

(New serial number)

GRS AHRS was removed and/or replaced.

The mounting tray was NOT removed and the mounting tray bolts were NOT loosened.

GRS AHRS was removed and/or replaced.

The mounting tray WAS removed and/or mounting tray bolts WERE loosened.

GRS AHRS Configuration Module was replaced.

Calibrations Required

Procedure A1:

Procedure B: Procedure D:

GRS 79 or GRS 77

GRS/GMU

Magnetic

Engine Run-up

Vibration

Pitch/Roll

Calibration

Offset

None Required.

Continue to GRS/GMU Test Section.

Test

X

X

None Required.

Continue to GRS/GMU Test Section.

X X

X X X

Procedure A1: GRS 79 or GRS 77 Pitch/Roll Offset Calibration

This first procedure must be carried out with the engine off.

1. Level the aircraft to within



0.25° of zero pitch and zero roll. (Follow instructions in the appropriate Beechcraft Maintenance Manual, listed in Table 1-1, for leveling)

2. Start the PFD in Configuration mode.

3. Go to the GRS Page Group and select the GRS/GMU Calibration page at the PFD. This page is protected and the following softkey password must be entered at the PFD to continue:



9



10



11



12 (Far Right softkey)



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Figure 7-5, GRS/GMU Calibration, Pitch/Roll Offset

4. Ensure that the GRS 1 is selected in the SELECT GRS UNIT window on the PFD.

5. Activate the cursor and highlight the SELECT PROCEDURE window and select PITCH /

ROLL OFFSET.

6. Press the ENT key.

7. Use the cursor to highlight Step 1 in the BEFORE CALIBRATION window.

8. Follow the checklist items displayed on the PFD and press the ENT key as each step is completed or confirmed.

9. When the CALIBRATE field is blinking, press the ENT button to begin the procedure.

10. After several seconds, a new checklist appears in the lower half of the PFD. Press the

ENT key as each step is confirmed. When the CONFIRM AIRCRAFT IS LEVEL field is blinking, press the ENT key to continue.

11. The result of the pitch/roll offset compensation is displayed on the PFD. If successful, the AHRS records the required pitch and roll offsets, informs the operator of a successful conclusion and returns to normal operation.

12. Press the ENT key on the PFD to conclude this procedure for GRS 1.



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Compass Rose Evaluation of Magnetic Disturbances for Magnetometer

Calibration Procedure (Optional)

NOTE

The Magnetometer Calibration Procedure that follows in Section 7.11.3

(Calibration Procedure B) must be carried out at a site that is determined to be free of magnetic disturbances. If it is unsure whether the site is ‘clean’, the technician should verify that the site is ‘clean’ by following the guidance provided in Section 7.11.2. The technician may skip Section 7.11.2 if the site condition is acceptable.

Typically, a compass rose is an acceptable location to perform the magnetometer calibration procedure. However, because not all compass roses are well maintained, even an existing compass rose should be regularly evaluated using the method described here to determine if it is free of magnetic disturbances. If evaluation of an existing compass rose indicates that magnetic disturbances are present, then an alternative location must be found to perform the

Magnetometer Calibration Procedure.

A G1000-equipped airplane that has completed the pitch/roll offset compensation procedure

(Procedure A-1, Section 7.11.1) can be used to evaluate a candidate site for magnetic disturbances and determine whether it is a suitable location to perform the magnetometer calibration procedure. The magnetometer calibration procedure itself contains the logic to simultaneously survey the location for magnetic cleanliness while it is computing the magnetometer calibration parameters.

In order to evaluate a candidate site, the Magnetometer Calibration Procedure must be performed twice: once turning clockwise around the site, and once turning counter-clockwise.

Both times, the procedure should be conducted as described in Section 7.11.3 of this document, with the exception of the direction of turns around the site.

NOTE

Although Section 7.11.3 indicates that the Magnetometer Calibration

Procedure should be performed by making a series of clockwise turns around the site, the procedure can also be performed by making counter-clockwise turns for the purpose of evaluating the site for magnetic disturbances.

If the PFD displays the “CALIBRATION SUCCESSFUL / SITE IS CLEAN” message upon completion of the Magnetometer Calibration Procedure in each clockwise and counterclockwise direction, then the candidate site is sufficiently free of magnetic disturbances and is acceptable for performing the Magnetometer Calibration Procedure. It is important to obtain successful result in both the clockwise and counter-clockwise directions to ensure that the magnetometer sweeps over a large enough area at the candidate site.

If the PFD displays either the “MAG FIELD AT SITE NOT UNIFORM” or “MAG FIELD AT SITE

DIFFERS FROM IGRF MODEL” message upon completion of the Magnetometer Calibration

Procedure in either of the two directions, then the site contains magnetic disturbances that are too large.



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Procedure B: GRS 79 or GRS 77 and GMU 44 Magnetic Calibration

NOTES

Procedure A-1 (Section 7.11.1) must first be successfully accomplished before performing Procedure B, only for situations where the GRS was replaced with a new unit.

On the calibration pages, “GRS” refers to whichever GRS unit is installed.

1. Start the aircraft engine following the procedures referenced in the appropriate

Beechcraft AFM as listed in Table 1-1.

2. After aircraft engine startup, taxi the aircraft to a properly calibrated compass rose.

3. At the compass rose, align the aircraft to a heading of magnetic north (



5°).

CAUTION

Calibration Procedure B must be carried out on a compass rose in order to guarantee measurements free of environmental magnetic disturbances.

Attempting to carry out this maneuver on a typical ramp area may not yield a successful calibration. The accuracy of the AHRS cannot be guaranteed if this calibration is not performed on a magnetically clean compass rose or equivalent. If the compass rose condition is not known, it is recommended that the technician follow the guidance in Section 7.11.2.

4. Restart the PFD in configuration mode.

5. Go to the GRS Page Group on the PFD.

6. Select the GRS/GMU Calibration page and enter the following softkey password:



9



10



11



12 (far right softkey)

7. Use the FMS small knob to highlight GRS for calibration and press the ENT key.

8. Using the FMS small knob, select MAGNETOMETER. Press the ENT button.

9. Use the cursor to highlight the first step in the BEFORE CALIBRATION window.

10. Follow the checklist items displayed on the PFD and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure.

11. The PFD display advises the operator when to turn the aircraft, when to stop, and when to turn again.

12. Upon instruction to turn, taxi the aircraft in a right turn. After approximately 25° to 30° of turn from the last heading, the PFD display advises the operator to stop the aircraft.

NOTE

Due to the difficulties in executing smooth, accurate turns the PFD may incorrectly interpret a station and instruct to “HOLD POSITION” prior to full completion of a 30



turn. If this scenario is encountered, it is best for the



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operator to ignore the “HOLD POSITION” command and instead use outside references to complete the approximate 30



turn. Instead of using the PFD instruction to turn as a real-time indication of when to turn, simply judge the 30°

(±5°) turn increments of the aircraft by using the compass rose radials.

Dwelling at these 30



increments for the time recommended by the PFD should result in successful calibration.

13. The PFD guides the operator to dwell at multiple headings around a complete circle.

NOTE

Due to high winds or excessive airframe vibration, the operator may encounter a condition where the PFD restarts the 18-second countdown without full completion of the previous countdown. If this is encountered more than once for a given station, the operator should begin turning to the next station

(approximately 30



). A minimum of 2 successful stations per quadrant is required, where a successful station is a full 18-second countdown followed by instruction to move. Ensure that at least 2 stations per quadrant are completed.

Thus, it may sometimes be required to dwell at a station after a countdown restart. A maximum of 30 stations is allowed for the entire calibration procedure. If too many countdown restarts are encountered, the calibration will fail with the message, “TOO MANY STATIONS.”

14. Repeat the turn-and-stop process until the PFD advises that a successful calibration is complete. The GRS AHRS then enters its normal operational mode. Press the ENT button on the PFD to conclude this procedure.



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Procedure D: Engine Run-Up Vibration Procedure

NOTES

On the calibration pages, “GRS” refers to whatever GRS unit is installed.

Calibration Procedure D is performed in order to guarantee that the AHRS mounting is sufficiently rigid and insensitive to vibration. This procedure must be performed for both GRS units installed in the aircraft. Calibration

Procedures A1 and B (Sections 7.11.1 and 7.11.3 respectively) are not required prior to this procedure.

Figure 7-6, GRS/GMU Calibration, Engine Run-Up

1. Restart the PFD in configuration mode.

2. Use the FMS small knob to highlight GRS 1 for calibration and press the ENT key. The

SELECT PROCEDURE field is not blinking.

3. Initiate the AHRS engine run-up vibration test procedure by performing the following steps: a) Select the ENGINE RUN-UP TEST procedure and press the ENT key. b) Follow the checklist items displayed on the PFD, and press the ENT key as each one is completed or confirmed. When the CALIBRATE field is blinking, press the ENT key to begin the procedure.

4. The PFD display instructs the operator to gradually increase power from idle to full throttle and back to idle over a period of 1-2 minutes.

5. When the operator has completed the engine run-up and the engine is back to an idle setting, press the ENT key to indicate that the process is complete. When this is done, the TEST COMPLETE field stops blinking.



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6. The PFD informs the operator if the installation has passed or failed the vibration test. If the test fails, the specific measurements causing the failure are identified and associated numeric values are displayed on the PFD.

NOTE

Should a failure occur, the technician may perform the Engine Run-up test up to 3 times successively before corrective action must be taken. If the test does not pass after three attempts, then the installation should not be considered reliable until the source of the vibration problem is identified and remedied. In the event of repeated failure of the engine run-up test, record the values that are reported to be out of range for future reference.

Performing this test on a windy day may cause a failure of the test. It may be required to retest when the wind is not as strong or to reposition the aircraft such that it isn’t affected by the wind.

The following are potential causes for failure of the engine run-up test: a) Vibration motion of GRS and/or GMU44 caused by neighboring equipment and/or supports. b) Mounting screws and other hardware for GRS and/or GMU44 not firmly attached. c) GRS connector not firmly attached to unit. d) Cabling leading to GRS or GMU44 not firmly secured to supporting structure. e) An engine / propeller that is significantly out of balance.

7. Press the ENT key on the PFD to conclude this procedure, then the aircraft can be taxied back and the engine can be shut down for final testing. Continue to Section 7.11.5.



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Start the displays in normal mode. The AHRS attitude and heading information displayed should become valid within 1 minute of power-up as shown in Figure 7-7 if at least one GPS receiver has a valid position. If GPS is unavailable, the AHRS initialization may take up to 2 minutes.

Figure 7-7, Normal Mode AHRS Check




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7.12 GDL 69A or GDL 69A SXM Data Link (if installed)

Original GDL 69A/69A SXM is Reinstalled

No software or configuration loading is required if the removed GDL 69A is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GDL 69A/69A SXM Test Section

7.12.3.

New, Repaired or Exchange GDL 69A/69A SXM is Installed

If a new, repaired or exchange GDL 69A/69A SXM is installed, the correct software and configuration files must be loaded to the unit, then the SiriusXM Satellite Radio subscription must be reactivated. See the SiriusXM Activation Instructions listed in Table 1-2.

LRU Replacement Procedure







7. Activate the cursor and select GDL69 in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.





Legacy Replacement Procedure GDL69 (Alternate Method)




PFD.

4. Select the “

SYSTEM UPLOAD




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ENT

key on the PFD.


“Baseline Option – GDL 69A SXM Installation” or “Baseline Option –

Legacy – GDL 69 Installation”

as applicable. Press

ENT

key on the PFD.


8. Using the large FMS knob scroll down to the GDL software box and press

ENT.

9. Scroll down to the GDL configuration box and press

ENT.

10. Press the

Load

softkey.








NOTE

If the software load fails, cycle power to the GDL 69A only and confirm that the software part number and version are updated in the DATA window on the MFD. Then, press ENT button on the PFD to check the

GDL 69A SXM SOFTWARE and CONFIGURATION check boxes and press LOAD softkey again to resume the software update.

12. Press

ENT

key on the PFD to acknowledge upload complete.

13. Deactivate cursor.


15. Press the

CNFM CFG

softkey.





GDL 69A Test

If a SiriusXM Satellite Radio subscription has already been activated for the GDL 69A/69A

SXM, then power up the G1000 and go to the

Aux – Information

page and verify that the GDL

69A/69A SXM is working properly. Refer to the Cockpit Reference Guide, listed in Table 1-2, for details on Sirius XM Radio weather and music operation.

If the GDL 69A/69A SXM is replaced (new unit), the owner must re-activate the subscription, using the new GDL 69A/69A SXM’s Radio ID number(s). Refer to the GDL 69A/69A SXM

Satellite Radio Activation Instructions, listed in Table 1-2, for details on the activation process.

As a final operations check, make sure there are no MANIFEST errors shown on the PFD for the GDL 69A/69A SXM.




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7.13 GSA 81 Servos (if installed)

Original Servo(s) Reinstalled

No software loading is required if the removed servo(s) is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the return-to-service checks in Section 9.

New, Repaired or Exchange Servo(s) Installed

If a new, repaired or exchange servo is installed, the correct software files and certification gains must be loaded to the unit.

LRU Replacement Procedure GSA81 Servos







7. Activate the cursor and select the installed GSA CTRL in the LRU dropdown box.



.

10. Press

ENT


11. Select the installed GSA MON in the LRU dropdown box.

12. Press the

CHK All

softkey.

13. Press the

Load

softkey

.

14. Press

ENT




17. Press the

CNFM CFG

softkey.




21. If there are no red-Xs or system alerts, continue to return to service checks in Section 9.



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Legacy Replacement Procedure GSA81 Servos (Alternate Method)




PFD.

4. Select the “

SYSTEM UPLOAD





ENT

key on the PFD.

6. Rotate the small FMS knob to display the drop down menu. Rotate the large FMS knob highlight

“Beechcraft A36/G36 – Baseline Configuration” or “Beechcraft B58/G58 –

Baseline Configuration”

. Press

ENT

key on the PFD.

7. Press the key.

8. Scroll to highlight the installed servo.


ENT



ENT

key to check the bx.

11. Scroll to highlight the installed servo gains line.


ENT


13. Press the

Load

softkey.








15. Press

ENT

key on the PFD to acknowledge upload complete.



18. Press the

CNFM CFG

softkey.




22. If there are no red-Xs or system alerts, continue to return to service checks in Section 9.



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7.14 Garmin Traffic Systems (GTS 800 or GTS 820) (if installed)

Original GTS Reinstalled

No software or configuration loading is required if the removed GTS is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GTS Test Section 7.14.3.

New, Repaired or Exchange GTS Installed

If a new, repaired or exchange GTS is installed, the correct software and configuration files must be loaded to the unit. See Section 7.14.1 and then continue to the GTS Test Section

7.14.3.

LRU Replacement Procedure GTS







7. Activate the cursor and select GTS in the LRU dropdown box.



.

10. Press

ENT




13. Press the

CNFM CFG

softkey.





Legacy Replacement Procedure GTS (Alternate Method)




PFD.

4. Select the “

SYSTEM UPLOAD




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ENT

key on the PFD.


“Option – GTS 800 Installation without GTX 345” or “Option – GTS 800

Installation with GTX 345” or “Baseline Option – Legacy – GTS 820 without GTX

345 Installation” or “Baseline Option – Legacy – GTS 820 with GTX 345

Installation”

(as applicable). Press

ENT

key on the PFD.


8. Using the large FMS knob scroll down to the GTS software box and press

ENT.

9. Scroll down to the GTS configuration box and press

ENT.

10. Press the

Load

softkey.








12. Press

ENT

key on PFD to acknowledge upload complete.



15. Press the

CNFM CFG

softkey.





GTS Antenna Functional Check

The following test assures the GA 58 traffic antennas and coaxial cables are properly connected.

1. On the MAP-TRAFFIC MAP page of the MFD, press the

OPERATE

softkey. A self-test of the antenna circuit is initialized. If the MFD displays FAILURE at the upper left corner of the traffic display area, it will be necessary to recheck the coaxial connections. If MFD displays OPERATING without indicating a fault, proceed to the next step of antenna verification.

2. Ensure that the transmitter or receiver (RX/TX) that you are testing is significantly closer to the ramp tester than another operating RX/TX, or erroneous and inaccurate results may occur. All four quadrants (0, 90, 180 and 270 degrees) will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the MAP-TRAFFIC MAP page of the MFD.



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3. Set up a stationary intruder by selecting the following on the ramp tester:



Intruder type: ATCRBS.



Intruder Start Distance: 2 nm



Intruder Start Altitude: 600 feet above field elevation



Vertical Speed: 0 fpm



Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario.)

4. Position ramp tester at 0 degrees.

5. Initiate the intruder scenario and verify a target is annunciated on the MAP-TRAFFIC

MAP page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co-altitude (read as +06 above a filled diamond indicating proximate traffic).

6. On the ramp tester, toggle intruder traffic to standby or off.

7. Reposition ramp tester and reengage the same intruder scenario for 90, 180 and 270 degrees.

8. Verify a target is annunciated on the MAP-TRAFFIC MAP page of the MFD at the same bearing as the ramp tester.

9. If the bearing is not as anticipated or multiple targets are displayed during tests, verify the following:



Coax cable connectors are properly secured at the bulkhead adapter fittings, GA

58 antennas, and GTS unit



Connections are made to the proper channels and color-coded heat shrink is the same color on both ends of coax cables



Connectors are correctly installed on coax cables.

Note: These tests are conducted at field elevation. Additional local traffic targets may appear and are not an indication of improper system operation.

Note: When an IFR6000 ramp tester is used with a GTS 800, the IFR6000 must be configured for a distance that is 4 times the actual distance. For example, if the ramp tester is located 10 ft away from an aircraft, the IFR6000 should be configured as if it were 40 ft away from the aircraft.

This will adjust the MTL setting of the IFR6000 such that it will see the GTS 800 low power interrogations and reply to the interrogations.



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GTS Ramp Functional Check

The following test provides a scenario that will converge and intercept the GTS to assure proper operational and surveillance functions.

1. On the MAP-TRAFFIC MAP page of the MFD, press the

OPERATE

softkey.


3. Select the following on the ramp tester:









Intruder Start Altitude : 600 feet above field elevation






Velocity:600

4. Initiate the intruder scenario and observe the following:



Traffic should be acquired at approximately 10 NM at 90 degree bearing and coaltitude. Observe intruder closes on own aircraft at a rate of 0.1 NM/sec. Verify that only a single target is displayed in the expected quadrant.



The intruder should transition from Other Traffic (displayed as an open diamond with +06 displayed above), to proximate traffic (displayed as a filled white diamond with +06 displayed above), to a Traffic Advisory (TA) alarm (yellow filled circle with +06 displayed above.)

NOTE

The aural TA annunciations are muted if the height above terrain is below

400 feet.

Note: When an IFR6000 ramp tester is used with a GTS 800, the

IFR6000 must be configured for a distance that is 4 times the actual distance. For example, if the ramp tester is located 10 ft away from an aircraft, the IFR6000 should be configured as if it were 40 ft away from the aircraft. This will adjust the MTL setting of the IFR6000 such that it will see the GTS 800 low power interrogations and reply to the interrogations.



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Original GSR 56 Reinstalled

No software or configuration loading is required if the removed GSR 56 is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GSR 56 Functional Check Section

7.15.2.

New, Repaired or Exchange GSR 56 Installed

If a new, repaired or exchange GSR 56 is installed, the correct software and configuration files must be loaded to the unit. See Section 3.7 and then continue to Section 7.15.1.

Activation of Garmin Connext

In order to activate the optional GSR 56 for Garmin Connext, contact Garmin Product Support at one of the following numbers (M-F, 7:00 a.m. to 7:00 p.m. Central Standard Time, - Central

USA) or the following website:



1.866.739.5687 (toll free in USA)



+1.913.440.1135 (worldwide)



https://fly.garmin.com/fly-garmin/connext/satellite-services/

Have the following information ready prior to calling or visiting the activation website:



If activating services for a GSR 56 installation o

Aircraft tail number, serial number, manufacturer, and model o

GSR 56 serial number o

G1000 NXi system ID number o

Name of aircraft owner and contact information o

Credit card information

Garmin Product Support will provide additional information for activation of data services.

NOTE

The standard activation time for data services is one business day.

To obtain the G1000 NXi system ID number and unit serial numbers, accomplish the following:

Turn the large FMS knob on the MFD to select the AUX page group.

Turn the small FMS knob to select the AUX System Status page. Record the System ID number shown in the Airframe field. This number is unique for each G1000 NXi system.

Press the softkey to activate the cursor in the LRU INFO field. Use the large FMS knob to scroll the cursor to GSR1 (if GSR 56 is installed). Record the GSR 56 serial number shown in the LRU INFO field.

Continue to the GSR 56 Functional Check Section 7.15.2.



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GSR 56 Satellite Receiver Functional Check

Power up the PFD in configuration mode.

On the PFD, select GDL page group using the large FMS knob.

Using the small FMS knob select the GSR56 Configuration page. Verify the page can be displayed and information is available.

Restart the G1000 NXi System in Normal Mode.

Using the large FMS knob, select the AUX page group on the MFD. Using the small

FMS knob, select the Aux-Telephone page.

Ensure the system is showing Iridium signal strength (best if aircraft is outside).

Press button on the GMA.

Press the softkey on the MFD.

Enter a test phone number (chosen by the installer) in the Enter Phone Number field using the MFD FMS knob.

Press the

ENT

key on the MFD keypad to accept the phone number.

Press the

ENT

key on the MFD keypad to initiate the dialing sequence.

After call is answered on the test phone end of the connection, verify that 2-way phone communication is achieved.

When call is complete, press the

Hangup

softkey on the Aux – Telephone page on the

MFD to end the call.

7.16 GWX 75 Weather Radar

Original GWX Reinstalled

No software or configuration loading is required if the removed GWX is re-installed. This does not include units that were returned for repair as their software and configuration files are deleted during the repair testing process. Continue to the GWX Functional Check Section

7.16.1.

New, Repaired or Exchange GWX Installed

If a new, repaired or exchange GWX is installed, the correct software and configuration files must be loaded to the unit. See Section 3.7 and then continue to the Section 7.16.1.

GWX Functional Check

Operation of the GWX Weather Radar is accomplished using the MFD.

NOTE

Before energizing the equipment, be sure microwave radiation safety precautions including both fuel and personnel safety considerations have been observed. These include clearing all personnel to an area beyond the maximum permissible exposure level (MPEL) boundary, approximately 10 feet.

1. On the GCU, turn the large FMS knob to select the Map Page Group then turn the small

FMS knob to select the

Map – Weather Radar

page.



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2. Select the Mode softkey.

3. Select the Standby softkey to initiate the one minute warm-up period. Verify the radar enters the standby mode after the warm-up is complete.


5. Select the Weather softkey. After reading the CAUTION statement, turn the large FMS knob to select YES. Press the ENT key.

6. Select the STAB softkey to activate or deactivate antenna stabilization. Verify the current stabilization condition is shown in the upper right of the weather radar display.

7. Select the Back softkey.

8. Select the Vertical softkey.

9. Select the Tilt softkey to activate the cursor in the Tilt field.

10. Turn the small FMS knob to select the desired antenna tilt angle. Press the GCU ENT key. Press the GCU FMS knob to remove the cursor.

11. Select the Gain softkey to activate the cursor in the Gain field.

12. On the GCU, turn the small FMS knob to adjust the gain for the desirable level. Verify the gain setting is visible in the gain field as a movable horizontal bar in a flashing box and the line pointer is a reference depicting the calibrated position. Press the FMS knob to remove the cursor.

13. On the GCU, select the Gain softkey again to recalibrate the gain. Verify ‘Calibrated’ is displayed in the Gain field.


15. Select the Off softkey.



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8. Subsystem Functional Checks

8.1 Stormscope Functional Check (if installed)

Refer to the applicable Line/System Maintenance Manual for Stormscope Functional Checks

(refer to Section 1.1).


8.2 TAWS Functional Check

Functional Check for TAWS-B (if enabled/installed)

Refer to the applicable Line/System Maintenance Manual for TAWS-B Functional Checks (refer to Section 1.1).

8.3 FliteCharts Functional Check

FliteCharts is enabled by default.

1. If Dual Charts are installed, ensure FlightCharts are set as the preferred charts.

2. With the G1000 in Normal Mode, use the MFD FMS knob to select

Aux – System

Status

page, then select MFD1 DB softkey.

3. Use the small FMS knob to scroll to CHART.

4. Verify “FliteCharts” is displayed in blue text adjacent to “CHART”.

5. Verify the FliteCharts database cycle number is displayed in blue text and the

FliteCharts database is current.

6. Deactivate the cursor and use the MFD large FMS knob to select the

Map - Navigation

Map

page then press the Charts softkey.

7. Verify the airport chart is displayed and the following softkeys are displayed (some softkeys may be grayed out):



CHRT



Show



INFO-1



DP



STAR



APR



WX



NOTAM



Go Back

8. Press the CHRT OPT softkey and verify the following softkeys are displayed (some softkeys may be grayed out):



All



Header



Plan



Profile



Minimums



Fit



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

Full



Back


9.

ChartView must be enabled using a ChartView Enable Card. Reference Section 3.7.1 for enabling procedures.

NOTE

The required ChartView databases are subscription-based and are to be procured by the aircraft owner directly from Jeppesen.

1. Ensure ChartView is set as the preferred charts.

2. With the G1000 in Normal Mode, use the MFD FMS knob to select ‘

Aux – System

Status

’ page, then select MFD1 DB softkey.

3. Use the small FMS knob to scroll to CHART.

4. Verify “ChartView” is displayed in blue text adjacent to CHART.

5. Verify the ChartView database cycle number is displayed in blue text and the ChartView database is current.

6. Deactivate the cursor and use the large MFD FMS knob to select the Navigation Map

Page then press the Charts softkey.

7. Verify the airport chart is displayed and the following softkeys are displayed(some softkeys may be grayed out):



CHRT



Show



INFO-1



DP



STAR



APR



WX



NOTAM



Go Back

8. Press CHRT OPT softkey and verify the following softkeys are displayed (some softkeys may be grayed out):



All



Header



Plan



Profile



Minimums



Fit



Full



Back


9.



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8.5 SafeTaxi Functional Check

The maximum map ranges for enhanced detail are configurable by the flight crew. When zoomed in close enough to show the airport detail, the map reveals runways with numbers, taxiways with identifying letters/numbers, and airport landmarks including ramps, buildings, control towers, and other prominent features. Resolution is greater at lower map ranges. When the aircraft location is within the screen boundary, including within SafeTaxi ranges, an airplane symbol is shown on any of the navigation map views for enhanced position awareness.

Any map page that displays the navigation view can also show the SafeTaxi airport layout, within the maximum configured range. The following is a list of pages where the SafeTaxi feature can be seen:



Navigation Map Page



Inset



HSI



Weather Datalink Page



Airport Information Page



Intersection Page



NDB Information Page



VOR Information Page



User Waypoint Information Page



Trip Planning Page



Nearest

1. Use the FMS knob on the MFD to select

Map - Navigation Map

page.

2. On the MFD, press MENU. With Map Settings highlighted, press ENT on the MFD.

Rotate the small MFD FMS knob to select the Aviation group and press the ENT key on

MFD.

3. Turn the MFD large FMS Knob to scroll through the Aviation Group options to ‘SafeTaxi’.

4. Turn the MFD small FMS Knob to display the range of distances.

5. Turn the MFD FMS Knob to select 1.5nm as the distance for maximum SafeTaxi display range, and then press the MFD ENT key to complete the selection.

6. Using the MFD range knob, select a range of 1.5nm or less. Verify SafeTaxi display represents the current aircraft location and the airport layout.


9.



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8.6 DME Functional Check

Refer to the applicable Line/System Maintenance Manual for DME Functional Check (refer to

Section 1.1).

8.7 GTS Traffic System Functional Check

This section is applicable to the GTS 800 (TAS) traffic systems. Perform the following tests to verify GTS 800 operational and surveillance functions. Use a ramp tester such as a TIC TR220 or equivalent to perform the tests.

These tests are conducted at field elevation. Note that additional local traffic targets may appear and are not an indication of improper system operation.

Note: Due to running the test at field altitude, additional traffic targets may be present, and are not an indication of improper system operation.

Note: When an IFR6000 ramp tester is used with a GTS 800, the IFR6000 must be configured for a distance that is 4 times the actual distance. For example, if the ramp tester is located 10 ft away from an aircraft, the IFR6000 should be configured as if it were 40 ft away from the aircraft.

This will adjust the MTL setting of the IFR6000 such that it will see the GTS 800 low power interrogations and reply to the interrogations.

NOTE

The aural TA annunciations are muted if the height above terrain is below 400 feet.

Figure 8-1, Traffic Map



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The following test assures the antennas and coaxial cables are properly connected. The GTS

800 must be in Ground Test mode.

1. On the page of the MFD, press the

TAS OPER

softkey. A self-test of the antenna circuit is initialized. If the MFD displays FAILURE at the upper left corner of the traffic display area, it will be necessary to recheck the coaxial connections. If MFD displays OPERATE without indicating a fault, proceed to the next step of antenna verification.

2. Ensure that the transmitter or receiver (TX/RX) that you are testing is significantly closer to the ramp tester than another operating RX/TX, or erroneous and inaccurate results may occur. All four quadrants (0, 90, 180 and 270 degrees) will be similarly tested to verify bearing of simulated intruder supplied via the ramp tester are correctly displayed on the

Map – Traffic Map

page of the MFD.

3. Set up a stationary intruder by selecting the following on the ramp tester:









Intruder Start Altitude: 600 feet above field elevation






Velocity: 0 kts (on some ramp testers, a velocity greater than 0 kts is required and a stationary intruder is created by not starting the scenario.)


5. Initiate the intruder scenario and verify a target is annunciated on the


page of the MFD at the correct bearing of approximately 0 degree azimuth at 2 NM and co-altitude (read as +06 above a filled diamond indicating proximate traffic).

6. On the ramp tester, toggle intruder traffic to standby or off.

7. Reposition ramp tester and reengage the same intruder scenario for 90, 180 and 270 degrees.

8. Verify a target is annunciated on the


page of the MFD at the same bearing as the ramp tester.

9. If the bearing is not as anticipated or multiple targets are displayed during tests, verify the following:



Coax cable connectors are properly secured at the GA58 antennas and GTS unit.



Connections are made to the proper channels and color-coded heat shrink is the same color on both ends of coax cables



Connectors are correctly installed on coax cables


9.



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The following test provides a scenario that will converge and intercept the GTS 800 to assure proper operational and surveillance functions.

1. On the page of the MFD, press the

TAS OPER

softkey.


3. Select the following on the ramp tester:









Intruder Start Altitude: 600 ft above Field Elevation






Velocity: 600 kts

4. Initiate the intruder scenario and observe the following:



Traffic should be acquired at approximately 10 NM at 90 degree bearing and coaltitude. Observe intruder closes on own aircraft at a rate of 0.1 NM/sec. Verify that only a single target is displayed in the expected quadrant.



The intruder should transition from Other Traffic (displayed as an open diamond with +03 displayed above), to proximate traffic (displayed as a filled white diamond with +03 displayed above), to a Traffic Advisory (TA) alarm (yellow filled circle with +03 displayed above.)

NOTE

The aural TA annunciations are muted if the height above terrain is below 400 feet.




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9. G1000 System Return to Service Procedure

If a G1000 LRU was replaced, verify the correct LRU software part numbers and versions against the numbers listed on the General Arrangement drawing listed in Table 1-1.

Perform the following subsection tests to confirm the G1000 system is operating correctly.

Apply aircraft power. On the MFD power-up screen in the upper right corner, find the

‘Beechcraft Gxx’ number. The first line will indicate the airframe type. The number in the second line is the G1000 System Loader Image version number that was used to install the software to the system. (G58 image shown for reference, G36 is similar)

Figure 9-1, MFD Power Up Page

Verify that the System Software Version is the same as listed in Table 1 of the 005-

00620-41 General Arrangement Drawing.

Press the MFD

ENT

key to acknowledge the ‘DEFAULT PROFILE’ Crew Profile option on the MFD (NOTE: The rightmost softkey may also be used).



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Figure 9-2, PFD Power-up System Annunciations

Allow the displays to initialize for approximately one minute. During normal operation, this causes the airspeed, altitude, vertical speed, and OAT fields to be invalid during the first ~40-60 seconds of PFD power-up. After two minutes, verify no Red-X’s are present on the PFD and the MFD. Examples of potential Red-Xs are shown in Figure 9-2. If any

Red-X’s are present, stop and troubleshoot per Section 5. Examples of a PFD with no

Red-X failure indications are shown in Figure 9-3.



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(Without SVS enabled)

(With SVS enabled)

Figure 9-3, PFD Normal Operation



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NOTE

Outputs from the GRS 77 or GRS 79 and GMU 44 are not valid until the units have been calibrated.

Check that all COM/NAV fields are valid in the top corners of the PFD.

Check that altitude, airspeed, vertical speed, GS, TAS, and OAT fields are valid on PFD.

Press the PFD Opt softkey on each PFD.

Check that engine instrument fields are valid on the MFD.

Verify that no MANIFEST alert messages appear in the lower right corner (press the flashing

ALERTS

softkey to view alert messages). If any MANIFEST errors appear, the correct software to the related LRU must be loaded before proceeding.

9.2 Display Failure Test

MFD Failure Condition:

1. Open MFD CB.

3. Close MFD CB.

PFD Display Failure Condition:

1. Open PFD circuit breaker.

3. Close PFD circuit breaker.

For an MFD failure condition, the following shall occur:



MFD goes blank.



All PFD primary flight information is retained.



The COM 1 and NAV 1 tuning fields remain valid and can be tuned by rotating the tuning knobs on PFD.



XPDR fields remain valid and XPDR can adjusted via

PFD softkeys.

For a PFD failure condition, the following shall occur:



PFD goes blank.



MFD switches automatically to reversionary mode



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9.3 Reversion Mode Check

Push the red

DISPLAY BACKUP

button on the GMA. Verify that the PFD and MFD displays enter reversion mode (See Figure 9-4). MFD should have valid altitude, airspeed, vertical speed, COM1, COM2, NAV1, NAV2 and engine instruments.

Figure 9-4, GDU Reversionary Mode

De-activate reversion mode by pushing the

DISPLAY BACKUP

button. Verify PFD and

MFD return to normal display modes.



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9.4 GPS Signal Acquisition

This test requires the aircraft to be outside to see the GPS satellites or indoors with a GPS repeater.

Figure 9-5, AUX-GPS Status Page

Select the AUX - GPS Status page on the MFD. After the G1000 system has been on for a minimum of two minutes, toggle between GPS 1 and GPS 2 using the two softkeys on the bottom of the display. Verify that both receivers show a 3D GPS Solution in the GPS Status field.



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9.5 GPS Failure Test

Before starting this test, create a simple Direct-To flight plan to an airport or other waypoint that is greater than 31 NM from the present aircraft position. Verify that the phase of flight displayed on the GPS CDI is ENR.

Step

Single GPS Failure Condition:

1. Ensure GPS satellites are acquired.

2. Place a shroud over the GPS antenna for GIA 1 to prevent signal reception. Verify loss of signal on MFD


page.

3. Check for desired results.

4. Remove shroud from the GIA 1 GPS antenna and allow system to re-acquire satellites.

5. Place a shroud over the GPS antenna for GIA 2 to prevent signal reception. Verify loss of signal on MFD


page.


7.

Remove shroud from the GIA 2 GPS antenna.

Dual GPS Failure Condition:


2. Cover both GPS antennas. Verify loss of signal on


page.


4. Remove shrouds from GPS antennas.

5. Allow both receivers to re-acquire satellite signals before continuing.

Desired Result

For each of the single GPS failure conditions, the following shall remain valid on the PFD throughout the procedure:



Attitude and Heading from AHRS.



Airspeed, Altitude, Vertical Speed, and OAT from Air

Data Computer.



GPS Course Deviation Indicator

For a dual GPS failure condition, the following shall occur:



GPS CDI flags LOI on the PFD.



Attitude and Heading remain valid from both AHRS on the PFD.



Airspeed, Altitude, Vertical Speed and OAT remain valid from both Air Data Computers on the PFD.



LOI appears on MFD Map.



TAWS N/A aural alert & annunciation given.

When GPS satellites are re-acquired, verify that the INTEG

OK annunciation is given on the HSI in white for a brief period of time then disappears.

After ~10 seconds of stable GPS position reacquisition, verify the TAWS AVAILABLE aural alert is given.

Verify that the system returns to normal navigation mode

(GPS CDI restored, LOI annunciation removed, & GPS data magenta).



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9.6 GIA Failure Test

GIA 1 Failure Condition:


2. Open INTEG AVION 1 CB.

4. Close INTEG AVION 1 CB. Allow system to reacquire satellites and return to normal display modes.

For a GIA 1 failure condition, the following shall occur:



NAV 1 and COMM1 tuning fields on PFD are invalid

(red X).



Engine data remains valid



AHRS is using backup GPS source.



AHRS and ADC data remain valid on PFD.

GIA 2 Failure Condition:

1. Open INTEG AVION 2 CB.

3. Close INTEG AVION 2 CB. Allow system to reacquire satellites and return to normal display modes.

For a GIA 2 failure condition, the following shall occur:



NAV2 and COMM2 tuning fields on PFD are invalid

(red X).



Engine data remains valid.



AHRS not receiving backup GPS Information.



AHRS and ADC data remain valid on PFD.

Dual GIA Failure Condition:

1. Open INTEG AVION 1 and INTEG AVION 2

CBs.


3. Restore power to both GIA units.

For a dual GIA failure, the following shall occur:



COM1/NAV1 & COM2/NAV2 fields flag invalid.



GPS CDI flags LOI on PFD



NAV1 & NAV2 CDI loses deviation bar.



XPDR field flags invalid on PFD.



Engine Instrument field flags invalid on MFD.



All AHRS & ADC fields remain valid.



Red AFCS status annunciation given.



TAWS FAIL annunciation given.



ADF/DME windows flag invalid.*

*If equipped.



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9.7 GEA Functional Check

Verify the MFD engine instruments are displayed and indicate valid readings. Reference figure below for normal EIS Display. Note: G58 model EIS strip is shown. G36 is similar.

On GMA, select

DISPLAY BACKUP

button. Observe MFD in reversion mode and verify all engine instruments are displayed and indicate valid readings.



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Normal EIS Display

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9.8 G1000 Backup Path Test

With both displays in normal mode and the entire avionics system turned on, verify on PFD there is not a system alert message stating “Failed Data Path". If this message is present, troubleshoot per Section 5.1.1 and resolve the issue before continuing.

9.9 GFC 700 Autopilot Clutch Overpower Check

The basic operation and checkout of the GFC 700 AFCS is not changed by this STC. Refer to the G36 or G58 Aircraft Maintenance Manual for specific procedures for the GFC 700 AFCS.

Refer to Section 4.7 for the GSM 86 servo gearbox spring cartridge torque check.

NOTE

The GFC 700 uses electronic torque limiting as well as mechanical clutches to limit the maximum servo effort. When the system is on the ground, the electronic torque limiting is removed, allowing manual checks of the clutch settings.

1. Move the flight controls through their full range motions. Check for any signs of binding or resistance.

2. Engage the Autopilot by pressing the AP key.

3. Manually overpower the autopilot clutches in pitch, yaw, and roll.

4. Actuate and hold PITCH TRIM switch in either the NOSE UP or NOSE DOWN direction to disconnect the autopilot. While the trim is running, restrain the aircraft pitch trim wheel and verify that the trim clutch can be overpowered.

5. Verify that the trim wheel moves smoothly in both directions throughout the entire trim range during manual electric trim operation. If the trim wheel hesitates, this may indicate that the pitch trim servo gearbox clutch is slipping. Verify GSM 86 servo gearbox torque and cable tension.

6. If the autopilot servo cannot be overpowered during any of the preceding steps, check the GSM 86 servo gearbox torque per Section 4.7.

9.10 Maintenance Records

Record the following information:



Part number of the G1000 software loader card used to perform software loading or software updates.



Record part and serial numbers of any LRU which was replaced.



Record any database updates which were performed during maintenance.



Any other applicable information related to the maintenance work performed on the aircraft.



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APPENDIX A Garmin Unit Part and Serial Number Cross Reference

This table allows shows the unit part number and serial number prefix combinations.

GIA 63W (LEGACY)

GIA 64W

GDU 1055 (MFD)

GDU 1050 (PFD)

GMA 1347 (LEGACY)

GMA 1360

GEA 71 (LEGACY)

GEA 71B

GDC 74 (LEGACY)

GRS 77 (LEGACY)

GMU 44

GRS 79 (OPTIONAL)

GDC 72 (OPTIONAL)

GTX 33 ES (LEGACY)

GTX 335R (OPTIONAL)

GTX 345R (OPTIONAL)

GDL 69A (LEGACY)

GDL 69 SXM (OPTIONAL)

GSA 81 PITCH SERVO (LEGACY)

GSA 81 ROLL SERVO (LEGACY)

GSA 81 PITCH TRIM SERVO (LEGACY)

GSA 81 YAW SERVO (LEGACY)

GSA 81 PITCH SERVO

GSA 81 ROLL SERVO

GSA 81 PITCH TRIM SERVO

GSA 81 YAW SERVO

GTS 800 TAS (OPTIONAL)

GTS 820 TAS (OPTIONAL)

FLIGHT STREAM 510 (OPTIONAL)

GSR 56

SERIAL NUMBER FIRST

THREE DIGITS

011-03301-00

011-03303-00

011-00987-00

011-03177-10

011-00878-00

011-00878-00

011-00878-00

011-00878-00

011-00878-20

011-00878-20

011-00878-20

011-00878-20

011-01356-00

011-01446-00

011-03595-00

011-02286-01

011-01105-20

011-03711-00

011-03470-80

011-03470-00

011-00809-00

011-03568-00

011-00831-00

011-03682-00

1HQ

4SK

494

494

471

4FQ

467

497

011-00882-00 478

011-00882-10 206

011-00868-10 420

011-00870-00 475

011-00870-10 1CM

011-03732-00 45T

011-03734-00

011-00779-30

45S

891 or 848

3EF

3EH

477

3NV

664

664

664

664

1A1

1A1

1A1

1A1

15L

1EA

402

2HU



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Garmin G1000 NXi: Beechcraft Baron G58 G1000 NXi Maintenance Manual for Textron G36/G58, includes Instructions for Continued Airworthiness for STC SA01830WI

Supplemental Maintenance

Manual

Textron Aviation

G36/G58

Includes Instructions for Continued Airworthiness for STC SA01830WI

1. INTRODUCTION

’2780.00’

2780-00

2. SYSTEM DESCRIPTION

3. Software and Configuration

NOTE

IMPORTANT

NOTE

IMPORTANT

NOTE

NOTE

NOTE

NOTE

NOTES

NOTE

NOTE

IMPORTANT

NOTE

IMPORTANT

G1000/GFC 700 Equipment

G1000 Accessories

NOTE

5. TROUBLESHOOTING

NOTE

6. Equipment Removal & Installation

7. Garmin G1000 LRU Replacement/Configuration & Testing

NOTE

CAUTION

8. Subsystem Functional Checks

9. G1000 System Return to Service Procedure

NOTE

APPENDIX A Garmin Unit Part and Serial Number Cross Reference

Related manuals

Table of contents

Garmin G1000 NXi: Beechcraft Baron G58 G1000 NXi Maintenance Manual for Textron G36/G58, includes Instructions for Continued Airworthiness for STC SA01830WI

Supplemental Maintenance

Manual

Textron Aviation

G36/G58

Includes Instructions for Continued Airworthiness for STC SA01830WI

1. INTRODUCTION

’2780.00’

2780-00

2. SYSTEM DESCRIPTION

3. Software and Configuration

NOTE

IMPORTANT

NOTE

IMPORTANT

NOTE

NOTE

NOTE

NOTE

NOTES

NOTE

NOTE

IMPORTANT

NOTE

IMPORTANT

G1000/GFC 700 Equipment

G1000 Accessories

NOTE

5. TROUBLESHOOTING

NOTE

6. Equipment Removal & Installation

7. Garmin G1000 LRU Replacement/Configuration & Testing

NOTE

CAUTION

8. Subsystem Functional Checks

9. G1000 System Return to Service Procedure

NOTE

APPENDIX A Garmin Unit Part and Serial Number Cross Reference

Related manuals

Garmin

G1000 NXi: Beechcraft Baron G58

Garmin

G1000 NXi - Beechcraft Bonanza A36/G36

Garmin

G1000: Beechcraft Baron G58

Garmin

G1000: Beechcraft Bonanza A36/G36

Garmin

G1000: Beechcraft Baron G58

Garmin

G1000: Beechcraft Baron G58

Garmin

G1000: Beechcraft Bonanza A36/G36

Garmin

G1000 NXi: Cessna 206H/T206H Nav III

Garmin

G1000: Beechcraft King Air 200/B200

Garmin

G1000: Beechcraft King Air 200/B200

Table of contents