Garmin G1000: Beechcraft Baron G58 User manual

190-01180-02 April 2012 Revision 3

G1000

System Maintenance Manual

Hawker Beechcraft G58

Contains Instructions

For Continued Airworthiness

For STC SA01584WI-D

This page intentionally left blank.

G1000 System Maintenance Manual - Hawker Beechcraft G58 Page A

Revision 3 190-01180-02

Garmin Ltd. or its subsidiaries

Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,

disseminated, downloaded or stored in any storage medium, for any purpose without the express prior

written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual

and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and

to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of

this manual or revision must contain the complete text of this copyright notice and provided further that

any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited.

Garmin International, Inc.

1200 E. 151

st

Street

Olathe, KS 66062 USA

Telephone: 913-397-8200

www.garmin.com

Garmin (Europe) Ltd.

Liberty House

Bulls Copse Road

Hounsdown Business Park

Southampton, SO40 9RB, UK

Phone: +44 (0) 23 8052 4000

Fax: +44 (0) 23 8052 4004

RECORD OF REVISIONS

Revision Revision Date Description ECO #

1 5/13/10 Initial release ------

2 5/25/10 Corrected errors in Table 4.1 72258

3 11/28/11 Revised to add -20 GIA and .09 image 89665

DOCUMENT PAGINATION

Section Pagination

Table of Contents i – iv

Section 1 1-1 – 1-4

Section 2 2-1 – 2-6

Section 3 3-1 – 3-24

Section 4 4-1 – 4-6

Section 5 5-1 – 5-6

Section 6 6-1 – 6-6

Section 7 7-1 – 7-4

Section 8 8-1 – 8-11

Page B G1000 System Maintenance Manual - Hawker Beechcraft G58

Revision 3 190-01180-02

INFORMATION SUBJECT TO EXPORT CONTROL LAWS

This document may contain information which is subject to the Export Administration Regulations (“EAR”)

issued by the United States Department of Commerce (15 CFR, Chapter VII Subchapter C) and which

may not be exported, released or disclosed to foreign nationals inside or outside the United States

without first obtaining an export license. The preceding statement is required to be included on any and

all reproductions in whole or in part of this manual.

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

cause cancer, birth defects, or reproductive harm. This Notice is being provided in accordance with

California's Proposition 65. If you have any questions or would like additional information, please refer to

our web site at www.garmin.com/prop65.

The GDU 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.

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.

CAUTION

WARNING

IMPORTANT

G1000 System Maintenance Manual - Hawker Beechcraft G58 Page i

190-01180-02 Revision 3

TABLE OF CONTENTS

PARAGRAPH PAGE

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

1.1 C

ONTENT, SCOPE, PURPOSE .......................................................................................... 1-1

1.2 O

RGANIZATION ............................................................................................................... 1-1

1.3 D

EFINITIONS/ABBREVIATIONS .......................................................................................... 1-2

1.4 P

UBLICATIONS ................................................................................................................ 1-3

1.5 D

ISTRIBUTION ................................................................................................................. 1-4

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

2.1 E

QUIPMENT DESCRIPTIONS ............................................................................................. 2-1

2.2 O

PTIONAL FEATURES ...................................................................................................... 2-6

3 G1000 CONTROL & OPERATION ..................................................................................... 3-1

3.2 G1000

NORMAL MODE ................................................................................................... 3-1

3.3 R

EVERSIONARY MODE .................................................................................................... 3-2

3.4 C

ONFIGURATION MODE OVERVIEW ................................................................................. 3-3

3.5 C

ONFIGURATION MODE NAVIGATION ............................................................................... 3-3

3.6 G1000

SOFTWARE INFORMATION .................................................................................... 3-5

3.7 G1000

SOFTWARE/CONFIGURATION PROCEDURE ......................................................... 3-11

3.8 SOFTWARE LOAD CONFIRMATION .................................................................................. 3-17

3.9 AVIATION DATABASE LOADING PROCEDURES ................................................................ 3-19

3.10 SVS / PATHWAYS ACTIVATION (OPTION)..................................................................... 3-20

3.11 CHARTVIEW ENABLE PROCEDURE .............................................................................. 3-22

3.12 TAWS-B ENABLE PROCEDURE .................................................................................... 3-23

3.13 AIRCRAFT REGISTRATION NUMBER ENTRY ................................................................. 3-24

3.14 CLEARING DEFAULT USER SETTINGS ......................................................................... 3-24

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

4.1 A

IRWORTHINESS LIMITATIONS ......................................................................................... 4-1

4.2 S

ERVICING INFORMATION ................................................................................................ 4-1

4.3 M

AINTENANCE INTERVALS ........................................................................................... 4-3

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

5.1 SVS/P

ATHWAYS TROUBLESHOOTING .............................................................................. 5-1

5.2 GTS

820 TROUBLESHOOTING ......................................................................................... 5-2

5.3 S

OFTWARE/CONFIGURATION TROUBLESHOOTING ............................................................ 5-3

5.4 GRT

10 / GRC 10 XM REMOTE CONTROL TROUBLESHOOTING ........................................ 5-4

5.5 S

YSTEM COMMUNICATION HIERARCHY ............................................................................ 5-4

5.6 B

ACKSHELL/BACKPLATE CONNECTORS ........................................................................... 5-5

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

6.1 GTS

820 TAS PROCESSOR ............................................................................................ 6-1

6.2 GPA

65 LNA/PA ............................................................................................................ 6-2

6.3 TAS ANTENNAS .............................................................................................................. 6-2

6.4 GRT 10 XM REMOTE CONTROL TRANSCEIVER................................................................. 6-3

6.5 GDU

REMOVAL & REPLACEMENT .................................................................................... 6-4

6.6 GMU

44 REMOVAL & REPLACEMENT .............................................................................. 6-5

6.7 GTX

33ES TRANSPONDER REMOVAL & REPLACEMENT ................................................... 6-6

6.8 GIA

63W REMOVAL & REPLACEMENT ............................................................................. 6-7

7 G1000 EQUIPMENT CONFIGURATION & TESTING ........................................................ 7-1

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Revision 3 190-01180-02

7.1 TRANSPONDER TESTING ................................................................................................. 7-1

7.2 GTS

TRAFFIC SYSTEM .................................................................................................... 7-1

8 SYSTEM RETURN TO SERVICE PROCEDURE ............................................................... 8-1

8.1 D

ISPLAY TESTING ........................................................................................................... 8-1

8.2 GIA

63W INTEGRATED AVIONICS UNIT ............................................................................ 8-6

8.3 GFC

700 AUTOPILOT GROUND CHECKS .................................................................. 8-8

8.4 MAINTENANCE RECORDS .............................................................................................. 8-13

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LIST OF ILLUSTRATIONS

FIGURE PAGE

Figure 2.1. Display Unit .............................................................................................................. 2-1

Figure 2.2. Transponder ............................................................................................................ 2-2

Figure 2.3. Magnetometer .......................................................................................................... 2-2

Figure 2.4. GTS Receiver .......................................................................................................... 2-3

Figure 2.5 GPA 65 PA/LNA Module .......................................................................................... 2-3

Figure 2.6 G58 Traffic Antenna ................................................................................................. 2-4

Figure 2.7 GRT 10 Transceiver ................................................................................................ 2-4

Figure 2.8 GRC 10 Remote Control .......................................................................................... 2-5

Figure 2-9 GIA unit .................................................................................................................. 2-5

Figure 3.1 - G1000 Softkeys ...................................................................................................... 3-1

Figure 3.2 - Normal Mode (with SVS enabled) .......................................................................... 3-2

Figure 3.3 - Normal Mode (without SVS enabled) ..................................................................... 3-2

Figure 3.4 - Display Reversionary Mode .................................................................................... 3-2

Figure 3.5, Configuration Status ............................................................................................... 3-4

Figure 3.6, Data Transmission Indicators ................................................................................. 3-5

Figure 3.8, Software/Configuration Overview ......................................................................... 3-11

Figure 3.9 - Configuration/Software Load Page ....................................................................... 3-14

Figure 3.10 - Option Selection ................................................................................................. 3-15

Figure 5.1 - GTS 820 Mating Connector .................................................................................... 5-5

Figure 5.2 - GTS 820 Mating Connector .................................................................................... 5-5

Figure 5.3 - GPA 65 Connector ................................................................................................. 5-6

Figure 5.4 - GRT 10 Mating Connector ..................................................................................... 5-6

Figure 6.1 - Battery Compartment ............................................................................................. 6-3

Figure 8.1 – MFD Initial Power Up page (format reference) ...................................................... 8-1

Figure 8.2 – PFD Power Up System Annunciations .................................................................. 8-2

Figure 8.3 – Normal Display (without SVS enabled) .................................................................. 8-2

Figure 8.4 – Normal Display (with SVS enabled) ....................................................................... 8-3

Figure 8.5 – PFD Display without SVS enabled ........................................................................ 8-4

Figure 8.6 – PFD with SVS enabled .......................................................................................... 8-5

Figure 8-7 AUX – GPS STATUS Page (MFD) ........................................................................ 8-6

Figure 8.8 - GFC 700 Pre-Flight Test ........................................................................................ 8-9

LIST OF TABLES

TABLE PAGE

Table 1.1 - Required Documents .............................................................................................. 1-3

Table 1.2 - Reference Publications ............................................................................................ 1-3

Table 3.1 - Required Loader Cards ........................................................................................... 3-5

Table 3.2 – SVS Enable Card .................................................................................................. 3-20

Table 4.1 - Maintenance Intervals .............................................................................................. 4-3

Table 5.1 – SVS Troubleshooting .............................................................................................. 5-1

Table 5.2 – SVS Alert Messages ............................................................................................... 5-2

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G1000 System Maintenance Manual - Hawker Beechcraft G58 Page 1-1

190-01180-02 Revision 3

1 INTRODUCTION

1.1 CONTENT, SCOPE, PURPOSE

This document provides Instructions for Continued Airworthiness (ICA) for the Garmin G1000

integrated avionics as installed in the Hawker Beechcraft G58 as modified under STC

SA01584WI-D. This document satisfies the requirements for continued airworthiness as

defined by 14 CFR Part 23.1529 and Appendix G. Information in this document is required to

maintain the continued airworthiness of the G1000. This document is intended to be used in

conjunction with the existing Hawker Beechcraft Baron 55 and 58 Maintenance Manual and the

Hawker Beechcraft Baron (Model G58) Maintenance Manual Supplement listed in Table

1.1.

1.1.1 APPLICABILITY

This document applies to all G58 aircraft that have been modified in accordance with STC

SA01584WI-D. The data defining this modification is contained in the Master Drawing List 005-

00606-01.

Modification of an aircraft by this Supplemental Type Certificate (STC) obligates the aircraft

operator to include the maintenance information provided by this document in the operator’s

Aircraft Maintenance Manual and the operator’s Aircraft Scheduled Maintenance Program.

1.2 ORGANIZATION

The following outline briefly describes the organization of this manual:

Section 2: System Description

Provides a complete description of the type design change associated with updating the G1000

system in the Hawker Beechcraft G58 .

Section 3: G1000 Control & Operation

Presents basic control and operation information specifically tailored to maintenance practices.

Basic G1000 Configuration Mode operation is also described.

Section 4: Instructions for Continued Airworthiness

Provides maintenance instructions for continued airworthiness of the G1000 systems.

Section 5: Troubleshooting

Provides troubleshooting information to aid in diagnosing and resolving potential problems with

the G1000.

Section 6: G1000 Equipment Removal & Replacement

Gives instructions for the removal and replacement of G1000 equipment associated with this

modification.

Section 7: G1000 Equipment Configuration & Testing

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

Section 8: System Return to Service Procedure

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

G1000 system.

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1.3 DEFINITIONS/ABBREVIATIONS

AFCS: Automatic Flight Control System

CFR: Code of Federal Regulations

DME: Distance Measuring Equipment

VHF: Very High Frequency

AC: Advisory Circular

AFMS: Airplane Flight Manual Supplement

FPGA: Field Programmable Gate Array

FPM: Flight Path Marker

HSDB: High Speed Data Bus

GDU: Garmin Display Unit

GDC: Garmin Air Data Computer

GTS: Garmin Traffic System

GRT: Garmin Remote Transceiver

GTX: Garmin Transponder

GDL: Garmin Datalink

GMU: Garmin Magnetometer

GA: Garmin Antenna

GIA: Garmin Integrated Avionics

GMA: Garmin Audio Panel

GPS: Global Position System

GRS: Garmin AHRS

HSI: Horizontal Situation Indicator

LCD: Liquid Crystal Display

LRU: Line Replaceable Unit

MDL: Master Drawing List

MFD: Multi-Functional Display

PFD: Primary Flight Display

STC: Supplemental Type Certificate

SVS: Synthetic Vision System

TCAS: Traffic Collision Avoidance System

TAWS: Terrain Awareness and Warning System

WAAS: Wide Area Augmentation System

1.3.1 UNITS OF MEASURE

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

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1.4 PUBLICATIONS

The following documents are required by this maintenance manual to perform maintenance. It

is the responsibility of the owner / operator to ensure latest versions of these documents are

used during operation, servicing or maintenance of the airplane.

Table 1.1 - Required Documents

P/N Description

005-00606-12 General Arrangement, G1000 Update with Options, G58

005-W0029-00 Wiring Diagram, Optional GRT 10, Hawker Beechcraft G58 Update

005-W0030-00 Wiring Diagram, Optional GTS 820, Hawker Beechcraft G58 Update

005-00606-14 GRT 10 Equipment Install, Hawker Beechcraft G58

005-00606-15 GTS 820 Equipment Install, Hawker Beechcraft G58

005-00606-20 GTS 820 Wire Harness Installation, Hawker Beechcraft G58

005-00606-22 GRT 10 Wire Harness Installation, Hawker Beechcraft G58

320-00587-XX Harness and Coax Fabrication, GTS 820 Option, Hawker Beechcraft G58

320-00596-XX Harness Fabrication, GRT 10 Option, Hawker Beechcraft G58

58-590001-1C *

(or subsequent

revision)

Hawker Beechcraft Baron (Model G58) Maintenance Manual Supplement

for Airplanes with Garmin G1000 Equipment Installed

58-590001-5B *

(or subsequent

revision)

Hawker Beechcraft Baron G58 Avionics Wiring Diagram Manual

55-590000-13F *

(or subsequent

revision)

Hawker Beechcraft Baron 55 and 58 Maintenance Manual

* Hawker Beechcraft document

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

maintenance activities.

Table 1.2 - Reference Publications

P/N Description

190-01180-01

FAA Approved Airplane Flight Manual Supplement, G1000 Integrated

Avionics Update with Options Including Synthetic Vision/Pathways on

Hawker Beechcraft G58

190-00526-02 Cockpit Reference Guide for the Hawker Beechcraft G58

190-01180-00 Post Installation Checkout Procedures Hawker Beechcraft G58

190-00355-04 GDL 69/69A XM Satellite Radio Activation Instructions

190-00907-00 G1000 System Maintenance Manual

190-00587-00 GTS 8XX/GPA 65 Installation Manual

Page 1-4 G1000 System Maintenance Manual - Hawker Beechcraft G58

Revision 3 190-01180-02

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

Only’ section of the Garmin web site.

1.5 ICA 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

2.1 EQUIPMENT DESCRIPTIONS

The following subparagraphs provide a brief description and picture of each Garmin LRU installed

or replaced by this STC. For all other G1000/GFC 700 LRUs, refer to the Hawker Beechcraft

Baron (Model G58) Maintenance Manual Supplement for Airplanes with Garmin G1000 Equipment

Installed listed in Table 1.1.

2.1.1 GDU 1040 PFD & GDU 1045 MFD

One Garmin GDU 1040 display and one GDU 1045 display is installed in the Baron instrument

panel. The GDU 104X units, 10.4 inch LCD displays with 1024x768 resolution, are configured as

PFD and an MFD. Both displays provide control and display of nearly all functions of the G1000

integrated cockpit system. The PFD is located on the left side of the MFD.

The GDU 1045 communicates with the GDU 1040, the GDL 69A, and the GWX 68 through a high-

speed data bus (HSDB) Ethernet connection. The GDU 1045 also communicates with the GDL 59

and the GTS 820 through the HSDB via the GDL 69A. The GRS 77 and GDC 74A send

information to the GDU 1045 via ARINC 429 data bus. The display units communicate with each

other and the GIA 63W units through a high-speed data bus (HSDB) Ethernet connection.

This STC installation approves alternate part numbers for these displays that accept external video

input and have an additional HSDB Ethernet connection. There are no mechanical or electrical

interface changes needed for these new part number displays. Refer to the General Arrangement

Drawing 005-00606-12 listed in Table 1.1 for part number information.

NOTE

While the alternate part numbers of displays authorized by this STC include an

external video input and HDSB Ethernet connection, this STC does not approve any

interfaces to these ports. Any interfaces to these ports will require additional

airworthiness approvals.

Figure 2.1. Display Unit

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2.1.2 GTX 33 TRANSPONDER

The Garmin GTX 33 transponder communicates with the on-side GIA 63W through RS-232 digital

interface. This STC provides for the optional installation of a GTX 33ES transponder that provides

extended squitter functionality. The unit is mounted on the back side of the instrument panel.

There are no mechanical or electrical interface changes needed GTX 33ES option and is installed

in place of the existing GTX 33 if selected. Refer to the General Arrangement Drawing 005-

00606-12 listed in Table 1.1 for part number information.

Figure 2.2. Transponder

2.1.3 GMU 44 MAGNETOMETER

The GMU 44 provides horizontal and vertical magnetic field information to the GRS 77 AHRS.

This allows heading to be calculated and provides assistance during AHRS alignment. The

GMU 44 unit is mounted in L/H wing tip. This STC approved an alternate part number of the

GMU 44. There are no mechanical or electrical interface changes needed for the new

magnetometer and it is installed in place of the existing part if selected. Refer to the General

Arrangement Drawing 005-00606-12 listed in Table 1.1 for part number information.

Figure 2.3. Magnetometer

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2.1.4 GTS 820 TRAFFIC SYSTEM

The optional GTS 820 system is designed to use active interrogations of Mode S and Mode C

transponders to provide Traffic Advisories (TA) to the pilot. Passive surveillance is available only

when installed with a GTX 33 with extended squitter. Traffic is displayed on the MFD via Ethernet

High Speed Data Bus routed through the existing GDL 69A. The GTS receiver is installed at FS

190. It is powered from the 5 amp Traffic Alert circuit breaker fed from the 28 Vdc Avionics bus.

The GPA 65 is a power amplifier / low noise amplifier (PA/LNA) module installed between the top

antenna and the GTS receiver just forward of FS 140 behind the headliner.. A top GA 58 antenna

is installed on the top of the aircraft just forward of FS 106.25. A lower GA 58 antenna is installed

on the bottom of the aircraft between FS 131.00 and FS 151.00 (standard location) or just forward

of FS 131.00 (optional location)

Figure 2.4. GTS Receiver

Figure 2.5 GPA 65 PA/LNA Module

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Figure 2.6 G58 Traffic Antenna

2.1.5 XM REMOTE CONTROL SYSTEM

The optional XM remote control system consists of the GRT 10 transceiver and the GRC Remote

Control. This system allows for remote control of the XM satellite radio function provided by the

existing GDL 69A. The GRT 10 is installed behind the instrument panel on the top of the MFD

system rack. It is powered from the existing 3 amp Datalink circuit breaker off the 28 Vdc Avionics

Bus.

Figure 2.7 GRT 10 Transceiver

G1000 System Maintenance Manual - Hawker Beechcraft G58 Page 2-5

190-01180-02 Revision 3

Figure 2.8 GRC 10 Remote Control

2.1.6 GIA 63W INTEGRATED AVIONICS UNIT (2)

Two Garmin GIA 63W Integrated Avionics Units (IAUs) contain the VHF COM/NAV receivers,

WAAS GPS receiver, Flight Director, and system integration microprocessors. The GIAs also

serve as a communication interface to all other G1000 LRUs in the system. Each GIA 63W

communicates directly with the on-side GDU display using a HSDB Ethernet connection. Both

GIAs are mounted in the systems rack behind the MFD.

GIA 1 is powered through Bus 2 and immediately powers up when the battery 1 or Battery 2

master switch is turned on. GIA #2 receives power through the Avionics Bus and powers up when

the avionics master switch is turned on.

Figure 2-9 GIA unit

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2.2 OPTIONAL FEATURES

The following optional features are included with this STC. These features are enabled via

individual Enable cards that are to be retained with the aircraft.

• Synthetic Vision and Pathways

• TAWS-B

• Chartview

These features will need to be re-enabled after replacement of a display unit.

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3 G1000 CONTROL & OPERATION

All control and operation of G1000 equipment as normally used in flight occurs through the PFD,

MFD, and GMA audio panel.

3.1.1 SOFTKEYS

Some pages have commands or selections that are activated by the GDU 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 shows

the current active selection.

Figure 3.1 - G1000 Softkeys

3.1.2 FMS KNOB

The FMS knob is the primary control for the G1000 system. Operation is similar to the Garmin

400/500 Series units.

To cycle through different configuration screens:

To change page groups:

Rotate the large FMS knob.

To change pages in a group:

Rotate the small FMS knob.

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

regular button.

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

To change the contents of a highlighted data field, rotate the small FMS knob. This action

either brings up an options menu for the particular field, or in some cases allows the operator to

enter data for the field.

To confirm a selection, press the ENT key.

To cancel a selection, press the small FMS knob in again, deactivating the cursor. The CLR

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

3.2 G1000 NORMAL MODE

To start the G1000 system in Normal Mode:

1. With a ground power unit connected to the external power receptacle, set the L and R BAT

switch to ‘ON’.

2. Set the AVIONICS MASTER switch to ‘ON’.

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. The PFD and MFD will function as

specified in the Cockpit Reference Guide for the Hawker Beechcraft G58 when the system has

been correctly installed and configured.

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Revision 3 190-01180-02

Figure 3.2 - Normal Mode (with SVS enabled)

Figure 3.3 - Normal Mode (without SVS enabled)

3.3 REVERSIONARY MODE

Reversionary mode allows for display of information related to safe flight in the event of a

display communication or hardware failure. As installed in the G58, both manual and automatic

reversionary modes are possible. Manual reversionary mode allows the operator to force the

PFD or MFD into reversionary mode by pressing the large red button labeled ‘DISPLAY

BACKUP’ on the GMA audio panel. In addition to the manual mode, the system will detect

when a display failure has occurred and will put the still functioning display into reversionary

mode automatically.

NOTE

When the ‘DISPLAY BACKUP’ button is pushed to exit reversionary mode, there

is a 5-second debounce (or the GDU waits for 5 consecutive seconds) and then

returns to normal mode if no other input is received. If the ‘DISPLAY BACKUP’

button is pushed again during this 5-second interval, the timer will repeat the

count.

Figure 3.4 - Display Reversionary Mode

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Garmin G1000: Beechcraft Baron G58, G1000, G1000 - Beechcraft Baron G58, Software Version 0857.09 User manual

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