Garmin G1000 NXi Owner's manual

190-02765-05 May2021 Revision 2
Supplemental Maintenance
Manual
Textron Aviation
G36/G58
Includes Instructions for Continued Airworthiness
for STC SA01945WI

G1000 System Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page i
© Copyright 2020-2021
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted,
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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: [phone]
www.garmin.com
Garmin (Europe) Ltd.
Liberty House, Bulls Copse Road
Hounsdown Business Park
Southampton, SO40 9RB, UK
Phone: [phone]
Fax: [phone]
Garmin AT, Inc.
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Salem, OR 97302 USA
Telephone: [phone]
RECORD OF REVISIONS
Revision
Date
Description
1
6/10/20
Initial Release
2
5/14/21
Rework manual for G1000 NXi field retrofit.
DOCUMENT PAGINATION
Section
Pagination
Table of Contents
i –v
Section 1
1-1 –1-5
Section 2
2-1 –2-5
Section 3
3-1 –3-37
Section 4
4-1–4-7
Section 5
5-1 –5-20
Section 6
6-1 –6-7
Section 7
7-1–7-9
Section 8
8-1 –8-3
Section 9
9-1 - 9-8

G1000 System Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
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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 190-02765-05
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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 ......................................................................................... 2-3
2.3 Electrical Power Distribution....................................................................................... 2-3
2.4 Pitot/Static System..................................................................................................... 2-3
2.5 GDU 1050 and GDU 1055 Displays........................................................................... 2-3
2.6 Softkeys..................................................................................................................... 2-3
2.7 FMS Knob.................................................................................................................. 2-3
2.8 G1000 Normal Mode.................................................................................................. 2-4
2.9 Reversionary Mode.................................................................................................... 2-5
3. SOFTWARE AND CONFIGURATION ............................................................................. 3-1
3.1 Configuration Mode Overview.................................................................................... 3-1
3.2 G1000 System Software Information.......................................................................... 3-5
3.3 Configuration Mode.................................................................................................. 3-12
3.4 G1000 Hardware/Software Compatibility Check....................................................... 3-13
3.5 Equipment Verification (Third Party/Optional Equipment Documentation)................ 3-14
3.6 G1000 Software/Configuration Procedure................................................................ 3-15
3.7 System Software and Configuration Load ................................................................ 3-16
3.8 Feature Enablement................................................................................................. 3-28
3.9 Aircraft Registration Number Entry and Flight ID Configuration................................ 3-31
3.10 Configuration Manager............................................................................................. 3-32
3.11 Splash Screen Loading............................................................................................ 3-32
3.12 Database Loading.................................................................................................... 3-33
3.13 Clearing Default User Settings................................................................................. 3-35
3.14 Interface Confirmation.............................................................................................. 3-36
3.15 Flight Stream 510 Firmware Review......................................................................... 3-37
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............................................................................................... 4-4
4.5 G1000 Redundant Connection Check........................................................................ 4-6
5. TROUBLESHOOTING..................................................................................................... 5-1
5.1 System Annunciations................................................................................................ 5-2
5.2 G1000 Alerting System .............................................................................................. 5-6
5.3 Synthetic Vision and Pathways Troubleshooting........................................................ 5-7
5.4 Backup Communications Path Checks....................................................................... 5-8
5.5 GDU 105X Troubleshooting ....................................................................................... 5-9
5.6 GDU 105X Alerts...................................................................................................... 5-11
5.7 GTX Troubleshooting............................................................................................... 5-14
5.8 GDL69A SXM Troubleshooting (if installed)............................................................. 5-15
5.9 Software/Configuration Troubleshooting................................................................... 5-17
5.10 Backshell/Backplate Connectors.............................................................................. 5-19

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6. EQUIPMENT REMOVAL & INSTALLATION................................................................... 6-1
6.1 GDU 1050/1055......................................................................................................... 6-2
6.2 GTX 335R/GTX 345R Transponder (if installed) ........................................................ 6-2
6.3 GDL 69A SXM (if installed) ........................................................................................ 6-3
6.4 Configuration Modules ............................................................................................... 6-3
6.5 FS 510 Wifi/Bluetooth Data Link (if installed).............................................................. 6-7
7. GARMIN G1000 LRU REPLACEMENT/CONFIGURATION & TESTING......................... 7-1
7.1 GDU 1050 PFD & GDU 1055 MFD ............................................................................ 7-1
7.2 GTX 335R or GTX 345R Transponder....................................................................... 7-4
7.3 GDL 69A SXM Data Link (if installed)......................................................................... 7-8
8. SUBSYSTEM FUNCTIONAL CHECKS ........................................................................... 8-1
8.1 TAWS Functional Check............................................................................................ 8-1
8.2 FliteCharts Functional Check ..................................................................................... 8-1
8.3 ChartView Functional Check...................................................................................... 8-2
8.4 SafeTaxi Functional Check ........................................................................................ 8-2
9. G1000 SYSTEM RETURN TO SERVICE PROCEDURE ................................................. 9-1
9.1 Display Test ............................................................................................................... 9-1
9.2 Display Failure Test ................................................................................................... 9-4
9.3 Reversion Mode Check.............................................................................................. 9-5
9.4 GPS Signal Acquisition .............................................................................................. 9-6
9.5 GPS Failure Test........................................................................................................ 9-7
9.6 G1000 Backup Path Test........................................................................................... 9-8
9.7Maintenance Records ................................................................................................ 9-8
APPENDIX A..........................................................................................................................A-1
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, GDL 69A SXM Datalink......................................................................................... 2-2
Figure 2-4, G1000 Softkeys .................................................................................................... 2-3
Figure 2-5, Normal Mode........................................................................................................ 2-4
Figure 2-6, Automatic Reversion with MFD failure ................................................................. 2-5
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, Garmin Unit S/N Location ................................................................................... 3-14
Figure 3-6, Software/Configuration Overview........................................................................ 3-15
Figure 3-7, Airframe Change Confirmation............................................................................ 3-17
Figure 3-9, MFD Aux - Database Page DB Transfer ............................................................. 3-34
Figure 3-9, Stormscope Configuration Page ......................................................................... 3-36
Figure 3-10, Stormscope Configuration................................................................................. 3-36
Figure 5-1, Aux –System Status Page ................................................................................... 5-1
Figure 5-2, System Annunciations........................................................................................... 5-2
Figure 5-3, Alerts & Annunciations.......................................................................................... 5-6
Figure 5-4, Alerts Softkey Annunciation .................................................................................. 5-6
Figure 5-5, GTX 335R/345R Looking at Front of Connector (P3251).................................... 5-19
Figure 5-6, GTX 345R (Only) Looking at Front of Connector (P3252)................................... 5-19
Figure 5-7, GDU 1054B/1050 Backshell Connector (P10401)............................................... 5-20
Figure 5-8, GDL 69A SXM Backplate Connector (P69A1)..................................................... 5-20
Figure 6-1, Configuration Module Installation.......................................................................... 6-4

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Figure 6-2, Configuration Module Installation.......................................................................... 6-6
Figure 7-1, G1000 Normal Mode Check................................................................................. 7-3
Figure 7-2, GTX Ground Test Mode Softkey.......................................................................... 7-6
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 5-1, SVS Troubleshooting............................................................................................. 5-7
Table 5-2, SVS-Related Alert Messages................................................................................ 5-8
Table 6-1, Configuration Module Kit –011-00979-00............................................................. 6-5
Table 6-2, Configuration Module Kit –011-00979-03............................................................. 6-5

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
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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
SA01945WI.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 as modified by this STC. All airplanes modified by this STC are configured per General
Arrangement drawing 005-01474-02, Rev 2 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 ’4014.00’= Software Image P/N 006-B4014-00

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page 1-2
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 & Installation
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.

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page 1-3
1.3 Definitions/Abbreviations
ADC: Air Data Computer
ADS-B: Automatic Dependent Surveillance –Broadcast
AFCS: Automatic Flight Control System
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
FIS-B: Flight Information Services –Broadcast
FS: Flight StreamTM
GPS: Global Positioning System
HSDB: High-Speed Data Bus (Ethernet)
ICS: Inter-Com System
LRU: Line Replaceable Unit
MFD: Multi-Function Display
MMC: Multi-Media Card
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

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page 1-4
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
005-01474-00
Master Drawing List, G1000 Avionics Updates, Part 23 AML STC
005-01474-02
General Arrangement, G1000 Update, Textron G36/G58
005-01474-12
Forward Avionics Install, G1000 NXi, G36/G58
005-01474-20
Wire Harness Install/Routing Textron G36/G58
005-W0047-00
Wiring Diagram, G1000 NXi Update, Textron G36/G58
Part Number
Textron Aviation Documents
55-590000-13
Maintenance Manual, Baron Models 55/58
58-590001-1
Maintenance Manual Supplement –G58
58-590001-3
Wiring Manual –G58
58-590001-5
Avionics Wiring Manual –G58
36-590001-9
Maintenance Manual, Bonanza 35/33/36 Series
36-590001-11
Maintenance Manual Supplement –G36
36-590001-13
Wiring Manual –G36
36-590001-15
Avionics Wiring Manual –G36
58-590001-11
Beechcraft Bonanza Series and Baron 55 and 58 Series Structural Inspection and Repair
Manual

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
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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
190-02765-01
G1000 NXi System Post Installation Checkout Procedure, Textron G36/G58
190-02765-03
Airplane Flight Manual Supplement, G1000 NXi Integrated Avionics System and GFC 700
AFCS In Textron G36/G58 Series of aircraft
190-02826-00
CRG, G1000 NXi Beechcraft G36, SSV 4014.00 or later
190-02828-00
CRG, G1000 NXi Beechcraft G58, SSV 4014.00 or later
190-00355-04
GDL 69 Series SiriusXM Satellite Radio Activation Instructions
190-02765-05
G1000 NXi Supplemental Maintenance Manual, Textron Aviation G36/G58, includes
Instructions for Continued Airworthiness for STC SA01945WI
190-01259-00
G1000 System Maintenance Manual Hawker Beechcraft G36 (contains Instructions for
Continued Airworthiness for STC SA1595WI-D)
190-01180-02
G1000 System Maintenance Manual Hawker Beechcraft G58 (contains Instructions for
Continued Airworthiness for STC SA01584WI-D)
190-00451-03
G1000 System Maintenance Manual Beechcraft 58/G58
190-00422-06
G1000 System Maintenance Manual Bonanza A36/G36 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.

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page 2-1
2. SYSTEM DESCRIPTION
2.1 Equipment Descriptions
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 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 a data card.
Figure 2-1 Flight Stream 510

G1000 NXi Supplemental Maintenance Manual 190-02765-05
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Page 2-2
GTX 345R / GTX 335R Transponder
The Garmin GTX 345R or GTX 335R transponders communicate with the GIAs 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 and ADS-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
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 2-3, GDL 69A SXM Datalink

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Page 2-3
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.
2.4 Pitot/Static System
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 2-4, G1000 Softkeys
2.7 FMS Knob
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.

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page 2-4
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 display
•GRS 77 AHRS
•GDC 74 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 Transponder
2. Turn ON the AVIONICS Master switch. The following G1000 equipment is powered on:
•MFD
•GTS 820 Traffic System (if installed)
•GIA #2 (NAV and COM)
•GMA Audio Panel
•GSA Servos
•Radar (G58 Only)
•GDL 69A (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 2-5, Normal Mode

G1000 NXi Supplemental Maintenance Manual 190-02765-05
Textron Aviation G36/G58 Revision 2
Page 2-5
2.9 Reversionary Mode
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 2-6, Automatic Reversion with MFD failure

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Textron Aviation G36/G58 Revision 2
Page 3-1
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 completedescription and breakdown of each Configuration Mode page, refer
to the G1000 System Maintenance Manual listed in Table 1-2.
SET>ACTV Configuration
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
Configuration Prompts
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

G1000 NXi Supplemental Maintenance Manual 190-02765-05
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Page 3-4
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
7. Transaction Log
13. System Setup
2. Time Configuration
8. Aircraft Configuration
14. Manifest Configuration
3. Lighting Configuration
9. Diagnostics Terminal
15. Maintenance Log
4. System Audio
10. OEM Diagnostics
16. Configuration Manager
5. System Upload
11. System Configuration
6. LRU Replacement
12. System Data Path
Configuration
GDU Page Group
1. Serial Configuration
6. Diagnostics
11. Airframe Configuration
2. CDU Status Page
7. Ethernet Test
12. TAWS Configuration
3. Key Test
8. Video Test
13. SurfaceWatch
Configuration
4. FS 510 Test
9. Alert Configuration
5. CDU Calibration
10. DAT Configuration
GIA Page Group (for GIA 63W only)
1. Serial Configuration
3. GIA I/O Configuration
5. GIA Status Page
2. GIA RS-485 Configuration
4. GIA COM Setup Page
6. GIA CAN Configuration
GEA Page Group (for GEA 71 only)
1. Engine Configuration
2. GEA Status Page
3. GEA Configuration
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 Wiring Config
3. Transponder Diagnostics
Note: This configuration page is not shown unless software loader card is installed in upper slot of
PFD1.
GRS Page Group
1. Inputs Configuration
3. GRS Flight Data Log
2. GRS / GMU Calibration
ADC Page Group
1. ADC Configuration
GFC Page Group
1. GFC Configuration
2. GFC Status
GMA Page Group (for GMA 1347 only)
1. GMA Configuration
GDL Page Group
1. GDL 69 Configuration
GWX Page Group